Executive Summarybull Team FLARE of the University of Texas at Austin has been tasked with confirming the flyby anomaly
notably experienced first by Galileo in 1990 followed by NEAR Cassini Messenger and Rosetta
bull The anomaly takes the form of an unaccounted for change in energyvelocity which takes place around periapse of a hyperbolic planetary flyby during which their is a change in declination The velocity anomalies vary by as much as 135 mms from precisely modeled values
bull A phenomenological formula which relates the velocity discrepancy to a change in declination excess velocity and a constant scaling factor serves to guide a flyby trajectory corollary to the anomaly
bull Many causes have been conjectured accounted for or otherwise proved innocent (from atmospheric drag to modifications to inertia) A thorough investigation of the navigation software and mathematical models used for navigation by JPL uncovered two potential culprits (high order gravity terms and anisotropy of the speed of light)
bull Team FLARErsquos proposed design is an affordable CubeSat mission whose goal is to gather more data points on the anomaly to corroborate its existence
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Executive Summarybull Team FLARE of the University of Texas at Austin has been tasked with confirming the flyby anomaly
notably experienced first by Galileo in 1990 followed by NEAR Cassini Messenger and Rosetta
bull The anomaly takes the form of an unaccounted for change in energyvelocity which takes place around periapse of a hyperbolic planetary flyby during which their is a change in declination The velocity anomalies vary by as much as 135 mms from precisely modeled values
bull A phenomenological formula which relates the velocity discrepancy to a change in declination excess velocity and a constant scaling factor serves to guide a flyby trajectory corollary to the anomaly
bull Many causes have been conjectured accounted for or otherwise proved innocent (from atmospheric drag to modifications to inertia) A thorough investigation of the navigation software and mathematical models used for navigation by JPL uncovered two potential culprits (high order gravity terms and anisotropy of the speed of light)
bull Team FLARErsquos proposed design is an affordable CubeSat mission whose goal is to gather more data points on the anomaly to corroborate its existence
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Executive Summarybull Team FLARE of the University of Texas at Austin has been tasked with confirming the flyby anomaly
notably experienced first by Galileo in 1990 followed by NEAR Cassini Messenger and Rosetta
bull The anomaly takes the form of an unaccounted for change in energyvelocity which takes place around periapse of a hyperbolic planetary flyby during which their is a change in declination The velocity anomalies vary by as much as 135 mms from precisely modeled values
bull A phenomenological formula which relates the velocity discrepancy to a change in declination excess velocity and a constant scaling factor serves to guide a flyby trajectory corollary to the anomaly
bull Many causes have been conjectured accounted for or otherwise proved innocent (from atmospheric drag to modifications to inertia) A thorough investigation of the navigation software and mathematical models used for navigation by JPL uncovered two potential culprits (high order gravity terms and anisotropy of the speed of light)
bull Team FLARErsquos proposed design is an affordable CubeSat mission whose goal is to gather more data points on the anomaly to corroborate its existence
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
The primary benefit from this mission is filling in the gap of closest approach left by most heritage missions and in the process prove whether the anomaly truly exists Furthermore the data gained from FLARE would allow further evaluation of the two most probable explanations of the anomaly
This endeavor will lead to more accurate trajectory propagation methods by further characterizing this anomalous perturbation By those standards objects like Earth rendezvousing asteroids will be predictable to a higher degree
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Dominate Anomaly Sources (JUNO) High Order Gravity Terms and Anisotropy of the Speed of Light
bull HOGT Truncation in Earthrsquos geopotential model is actually a perturbation capable of producing something detectable in real time comparable to the predicted flyby anomaly [36]
bull ASL The flyby anomalies result from the assumption that the speed of light is isotropic in all frames but the speed of light is not invariant and isotropic only with respect to a dynamical 3-space [44]
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Primary Requirementsbull [A] The system shall be capable of gathering the velocity profile during the inbound
and outbound legs of a hyperbolic flyby trajectory of Earth
bull [B] This project will provide at least 4 velocity profiles associated with the flyby phenomenon in its projected lifetime
bull [C] The system shall be capable of tracking the velocity the satellite experiencing the hyperbolic flyby anomaly during closest approach on the order of 01 mms accuracy
bull [D] The mission design shall perform velocity data collection on ldquopairedrdquo flybys (with minimal separation) at the above mentioned accuracy (~01 mms) including coverage throughout closest approach
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Secondary Requirementsbull A The trajectory of the satellites during closest approach shall be monitored with GPS including
backside lobe GNSS tracking the use of tens of ground stations and post processing for added accuracy
bull B Confirmation of an anomalous DV shall be achieved via (Doppler effects) X-band radio broadcasting during the flyby phases
bull C The error of Doppler velocity measurements shall be at maximum 05 mms
bull D The satellites will be constrained to a standard 3u6u format
bull E The satellites will perform flybys with sufficient hyperbolic excess velocity and change in declination to produce an anomaly of at least plusmn3 mms
bull F The altitude of periapse upon each flyby shall be between 500 and 2000 km the best fit range of the phenomenological formula
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
bull CSD [4]bull 34 kg in massbull X and Y dimensions 2634 cm and 1575 cmbull Ejection plate force on payload from launch vibration 0-191 Nbull Ejection plate force on payload from spring ejection 156-467 Nbull Survival temperature extrema -50 to 100 degCbull Operational temperature extrema -45 to 90 degCbull Life 50 door closures
bull Payload [27]bull 12 kg maxbull Tab lengths X = 2392 cm Z = 365 cmbull Force from deployment switches Z-axis 5 Nbull Friction from 4 sides contacting walls 2 N
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
6From mid 2015 to mid 2018 further project development will take place Further pre-phase A and conceptualization will take place during 2015 to mid 2016 Fabrication testing and assembly will take place from mid 2016 to early 2018
ConOps B Mother ship deployment moon assist
Speaker Amritpreet Kang
1 Launch as secondary payload to a GTO orbit
2 SHERPA delivers CubeSats to moon sphere of influence
3 Powered flyby of the moon
4 SHERPA provides hyperbolic excess velocity CubeSats deployed into tandem hyperbolic flyby trajectories Inbound excess velocity calculated (DSN monitored radio Doppler)
5 Flyby GPS data from spacecraft to ground station DSN measured Doppler shift SLR tracking possibility
6 Hyperbolic excess velocity calculated on outbound leg via radio Doppler
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Day in the Life CubeSat Orientationbull Heliocentric
ndash Solar panels point toward sun intermittentlyndash Stable spin (Z-axis)tumble to distribute heat passivelyndash MCM maneuver and reaction wheel desaturationndash Small course correction in weeks leading to and days following flyby
bull Inout bound flybyndash X-band patch antennas (plusmn Z faces) face towards DSN station of interestndash A slow spin about the Z-axis wouldnrsquot distort data (preprocessed signal)ndash Trajectory profile gathered in intervals
bull Closest approach flybyndash SLR reflector (plusmn Z faces) would be pointed towards the relevant stationndash GPS signals received stored and then relayed when appropriatendash (optional) Radio tracking via relevant station (DSN or ESA based on position and slew rate)ndash No spin about the Z-axis is preferred due to the slewing necessity at this phase
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Design resource for Ling Budget and comms system characteristics [34]bull 1 U with 05U goalbull ~1 Kgbull 8 W active with ~3 W goalbull ~gt1 m ranging accuracybull Goal of ~$100k unit cost
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 9189 g
11 Propulsion (WET)
MPS-120XLtrade CubeSat High-Impulse Adaptable13 3200 g 320 g 3520 g12 ADCS
BCT XACT10 850 g 85 g 935 g13 Communication
Iris Navigation and Telecomm Transponder 400 g 40 g 440 g14 CampDH
Andrews Model 160 High Performance Flight Computer9 70 g 7 g 77 g
15 Power12
FleXible EPS 6 x 12W BCR 139 g 139 g 1529 gCubeSat Power Distribution Module 61 g 61 g 671 gCubeSat Standalone Battery 256 g 256 g 2816 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g6U CubeSat SIDE Solar Panel 290 g 29 g 319 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g3U CubeSat Side Solar Panel 135 g 135 g 1485 g
16 Structure
6-Unit CubeSat Structure9 1100 g 110 g 1210 g17 Sensors
FOTON GPS Receiver 400 g 40 g 440 g18 Wiring
15 Of components not including structure 1027 g 102729 g 1130 g20 Margin (15 of 10) 1378 g
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 18073 W
11 ADACSBCT XACT 283 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 64 W 064 W 704 W
13 GPSFOTON GPS Receiver 1 W 01 W 11 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 5 W 05 W 55 W
15 EPSFleXible EPS 6 x 12W BCR 01 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 01 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 1 W 01 W 11 W
20 Margin (15 of 10 271095 W30 Total Nominal Power Usage 20784 W
Level 2
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element CBE Contingency (10) Allocated Level 110 Spacecraft Bus 29623 W
11 ADACSBCT XACT 3 W 0283 W 3113 W
12 RadioIris Navigation and Telecomm Transponder 6 W 064 W 704 W
13 GPSFOTON GPS Receiver 5 W 045 W 495 W
14 Flight ComputerAndrews Model 160 High Performance Flight Computer 9 W 09 W 99 W
15 EPSFleXible EPS 6 x 12W BCR 0 W 001 W 011 W
16 BatteriesCubeSat Standalone Battery 0 W 001 W 011 W
17 PropulsionMPS-120XLtrade CubeSat High-Impulse Adaptable 4 W 04 W 44 W
20 Margin (15 of 10 444345 W30 Total Maximum Power Usage 340665 W
Level 2
Power Equipment List (PEL) Maximum Power Usage
Element12 Power Output6U CubeSat SIDE Solar Panel 1878 W6U CubeSat SIDE Solar Panel 1878 W3U CubeSat Side Solar Panel 73 W3U CubeSat Side Solar Panel 73 W
Total Power Output 5216 W40 Total Power Output70 Total Power Output
2086 W3651 W
Power Equipment List (PEL) Desaturation Power Usage
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Type Product Cost SourceStructure 6-Unit CubeSat Structure $8242 Directly from cubesatshopcomADACS BCT XACT $139995 Directly from pumpkininccomRadio Iris Navigation and Telecomm Transponder $10000 Estimated from cubesatshopcomGPS FOTON GPS Receiver $50000 Directly from Brumbaugh ThesisFlight Computer Andrews Model 160 High Performance Flight Computer $53261 Directly from cubesatshopcomEPS FleXible EPS 6 x 12W BCR $10550 Directly from clyde-spacecomPower Dist CubeSat Power Distribution Module $8450 Directly from clyde-spacecomBatteries CubeSat Standalone Battery $1800 Directly from clyde-spacecomSolar Panels 6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom
6U CubeSat SIDE Solar Panel $14300 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom3U CubeSat Side Solar Panel $6050 Directly from clyde-spacecom
Propulsion MPS-120XLtrade CubeSat High-Impulse Adaptable $125000 Estimated from tudelftnlWiring 15 Of components not including structure $4479980 10 of Other Product Costs
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Element Product Minimum MaximumStructure 6-Unit CubeSat Structure -40degC 80degCFlight Computer Andrews Model 160 High Performance Flight Computer -30C 65degCPower Dist CubeSat Power Distribution Module -40degC 85degCBatteries CubeSat Standalone Battery -10degC 50degCPropulsion MPS-120XLtrade CubeSat High-Impulse Adaptable 5degC 50degC
Overall Thermal Limits 5degC 50degC
Operating Temperature
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Questions and Comments
Project ManagerAmritpreet Kang
Systems EngineerGraeme Ramsey
Chief EngineerJeffrey Alfaro
Associate EngineersKyle ChaffinAnthony Huet Graphic courtesy of NASA
= 3099 x
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Referencesbull [1] Michael M Nieto and John D Anderson ldquoEarth flyby anomaliesrdquo Physics Today Oct 2009bull [2] Anderson John D Campbell James K ldquoAnomalous Orbital Energy Changes Observed during Spacecraft Flybys of Earthrdquo JPL
March 2008 Web lthttpjournalsapsorgprlpdf101103PhysRevLett100091102gtbull [3] Jason Andrews ldquoSpaceflight Secondary Payload System (SSPS) and SHERPA Tug - A New Business Model for Secondary and Hosted
Payloadsrdquo Spaceflight Inc 26th Annual AIAAUSU Conference on Small Satellitesbull [4] ldquoCANISTERIZED SATELLITE DISPENSER (CSD) DATA SHEETrdquo Planetary Systems Corporation 21 Jul 2014bull [5] ldquoSpace Launch Report RokotStrelardquo httpwwwspacelaunchreportcomrokothtmlconfig 19 Dec 2014bull [6] Antreasian P Guinn J ldquoInvestigations Into the Unexpected Delta-V Increases During the Earth Gravity Assists of Galileo and NEARrdquo
JPL Web bull [7] Operational considerations for CubeSats Beyond Low Earth Orbit
bull [8] Orbital Mechanics ed Robert A Braeunig httpwwwbraeunigusspaceorbmechhtm [accessed 02162015]bull [9] ISIS ldquoCubeSatShopcomrdquolthttpwwwcubesatshopcomgtbull [10] Blue Canyon Technologies ldquoProductsrdquohttpbluecanyontechcomproductsbull [11] SkyFox Labs ldquopiNAV-L1FMrdquohttpwwwskyfoxlabscomproductsdetail1bull [12] Clyde Space ldquoCubeSat Labrdquohttpwwwclyde-spacecomcubesat_shopbull [13] Aerojet Rocketdyne ldquoCubeSat Modular Propulsion Systems (MPS)rdquolthttpswwwrocketcomcubesatgtbull [14] Surrey Satellite Technology US LLC ldquoSGR-05U ndash Space GPS Receiverrdquo lthttpwwwsst-uscomshopsatellite-subsystemsgpssgr-
05u- space-gps-receivergtbull [15] Bill Schreiner Doug Hunt Chris Rocken Sergey Sokolovskiy ldquoApproach and Quality Assessment of Precise GPS Data Processing at
the UCAR CDAACrdquo University Corporation for Atmospheric Research (UCAR)COSMIC Project OfficeBoulder CO
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Referencesbull [16] E Kahr1 O Montenbruck K OrsquoKeefe1 S Skone J Urbanek L Bradbury P Fenton ldquoGPS TRACKING ON A NANOSATELLITE ndash THE CANX-2 FLIGHT
EXPERIENCErdquo 8th International ESA Conference on Guidance Navigation amp Control Systems Czech Republic 5-10 June 2011
bull [17] Jessica Arlas Sara Spangelo ldquoGPS Results for the Radio Aurora Explorer II CubeSat Missionrdquo American Institute of Aeronautics and Astronautics
bull [18] Oliver Montenbruck Remco Kroes ldquoIn-flight performance analysisof the CHAMP BlackJackGPS Receiverrdquo GPS Solutions 2003bull [19] Jonathan Sauder ldquoUltra-Compact Ka-Band Parabolic DeployableAntenna (KaPDA) for Cubesatsrdquo JPL Icube Sat Workshop Pasadena CA May
2014bull [20] S W Asmar and J W Armstrong ldquoSpacecraft Doppler tracking Noise budget and accuracyachievable in precision radio science observationsrdquo Jet
Propulsion Laboratory California Institute of Technology Pasadena California USA RADIO SCIENCE VOL 40 RS2001 doi1010292004RS003101 2005
bull [21] NASA National Space Science Data Center lthttpnssdcgsfcnasagovnmcSpacecraftQueryjspgtbull [22] JPL ldquoBasics of Space Flightrdquo Section II Chapter 13 Spacecraft Navigation httpwww2jplnasagovbasicsbsf13-1phpbull [23] Srinivisan Dipak K and Fielhauer Karl B ldquoThe Radio Frequency Subsystem and Radio Science on the MESSENGER Missionrdquo August 2007
lthttpwww- geodynmitedusrinivasanmercuryrsssr07pdfgtbull [24] Taylor Jim et al ldquoGalileo Telecommunicationsrdquo DECANSO Design and Performance Summary Series Article 5 JPL July 2002
lthttpdescansojplnasagovDPSummaryDescanso5--Galileo_newpdfgtbull [25] Spaceflight Inc Secondary Payload Users Guide 3415 S 116th St Suite 123Tukwila WA 98168 SF-2100-PUG-00001 Rev D 2013-03-05bull [26] Mukai Ryan et al Juno Telecommunications DECANSO Design and Performance Summary Series Article 16 JPL October 2012bull [27] 2002367B Payload Spec for 3U 6U 12U 27U Planetary Systems Corporation 21 July 2014bull [28] Adler Stephen L ldquoModeling the Flyby Anomalies with Dark Matter Scatteringrdquo Princeton Institute for Advance Study 17 Feb 2012 Web
lthttparxivorgpdf11125426pdfgt bull [29] Robertson R Shoemaker Michael ldquoHighly Physical Penumbra Solar Radiation Pressure Modeling and the Earth Flyby Anomalyrdquo SpaceOps
Conferences 5-9 May 2014 Web lthttparcaiaaorgdoipdf10251462014-1881gt bull [30] McCulloch ME ldquoCan the Flyby Anomalies Be Explained by a Modification of Inertiardquo Journal of British Interplanetary Society 18 Dec 2007 Web
lthttparxivorgpdf07123022v1pdfgt
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
References
bull [31] Mbelek Jean P ldquoSpecial Relativity May Account for the Spacecraft Flyby Anomaliesrdquo Service DrsquoAstrophysique 15 Mar 2009 Web lthttparxivorgftparxivpapers080908091888pdfgt
bull [32] Atchison et al ldquoLorentz Accelerations in the Earth Flyby Anomalyrdquo Journal of Guidance Control and Dynamics 2012 Web lthttparcaiaaorgdoipdf102514147413gt
bull [33] Duncan Courtney ldquoIris CubeSat Compatible DSN Compatible Transponder for Lunar Communication and Navigation hellip and Beyond ldquo Jet Propulsion Laboratory California Institute of Technology Lunar Cubes 3 Nov 15 2013
bull [34] Duncan Courtney ldquoMicrowaves Communications and Navigation in Deep Space hellip even in nano-SpaceCraftrdquo San Bernardino Microwave Society Corona California Oct 2 2014
bull [35] Courtney Duncan and Amy Smith ldquoIris Deep Space CubeSat Transponderrdquo Jet Propulsion Laboratory California Institute of Technology CubeSat Workshop 11 Cal Poly San Luis Obispo April 23 2014
bull [36] Thompson et al ldquoReconstruction of Earth Flyby by the JUNO Spacecraftrdquo California Institute of Technology 2014 Webbull [37] NovAtel ldquoOEM628 Triple-Frequency + L-Band GNSS Receiverrdquohttpwwwnovatelcomprodecutsgnss-receiversoem-receiver-
boardsoem6-receiversbull [38] European Space Agency ldquoSAC-C (Satelite de Aplicaciones Cientificas-C)rdquohttpsdirectoryeoportalorgwebeoportalsatellite-missionsssac-cbull [39] Orfeu Bertolami Frederico Francisco Paulo J S Gil Jorge Paramos ldquoTesting the Flyby Anomaly with the GNSS Constellationrdquo WSPCInstruction
file arSiv12010163v1 [physicsspace-ph] Universidade Tacuteecnica deLisboa Lisboa Portugal Jan 4 2012bull [40] General Dynamics ldquoSmall Deep-Space Transponder (SDST)rdquo lthttpwwwgd-aiscomDocumentsSpace20ElectronicsSDST20-20DS5-813-
12pdfgtbull [41] Tyvak Intrepid System Board lthttptyvakcomintrepidsystemboardgtbull [42] Antenna Development Corporation ldquoMicrostrip patch Antennasrdquo lthttpwwwantdevcocomADC-050925110720R620Patch20data
20sheet_non- ITARpdfgt
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
References
bull [43] Sara Spangelo Matthew Bennett Daneil Meinzer Andrew Klesh Jessica Arlas James Cutler ldquoDesign and Implementation of the GPS Subsystem for the Radio Aurora Explorerrdquo University of Michigan 1320 Beal Ave Ann Arbor MI 48109 Jan 7 2013
bull [44] Cahill RT ldquoResolving Spacecraft Earth-Flyby Anomalies with Measured Light Speed Anisotropyrdquo School of Chemistry Physics and Earth Sciences Flinders University Adelaide 5001 Australia July 2008
bull [45] Duncan Courtney ldquoIris for INSPIRE CubeSat Compatible DSN Compatible Transponder Flight Communications Systems Section 337 Jet Propulsion Laboratory California Institute of Technology July 31 2013[46] SLR ldquoSatellite Laser Rangingrdquo NASA May 4 2015 httpescgsfcnasagovspace-communicationsNENslrhtml
bull [47] ldquoSatellite Laser Ranging and Earth Sciencerdquo NASA Space Geodesy Program May 4 2015 httpilrsgsfcnasagovdocsslroverpdf
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Trade Studies Doppler and GPS Heritagebull Data Acquisition Projected Accuracy
ndash Dopplerbull Ionosphere (and solar wind) refractive index is proportional to λ^2 (wavelength squared) [20]bull Prospective Europa Orbiter Mission estimated X band Doppler shift of 01 mms [67e-13 Allen Deviations in 2 way X-band
Doppler at 60 seconds integration which is equivalent to 4e-13 over 1000s integration] [20]bull Iris and XX LMRST projected to attain 01 mms accuracy estimate courtesy of JPL
ndash GPS real time processingbull CanX-2 mission OEM4-G2L receiver 10-100 m position error 01-05 ms velocity error [limited by employed antenna]
[16]bull Radio Aurora Explorer II mission RAX-2 receiver 29 m 34 ms average position and velocity error [17]
ndash GPS post processingbull CHAMP mission JPL developed BlackJack GPS Bernese 43 and 50 software packages respectively (post processing)
produced 05 mms and 01 mms error [18]bull Multi-GNSS real time tracking offers ~20 mms in accuracy in HEO With weak signal and offline processing 10 mms
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Table of steady-state navigation errors [21] for analysis of expected accuracies Two perigee passes were necessary to achieve this level of steady-state accuracy
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
SME-SMAD WBS Element Input CER ($K FY 10) CER ($K FY15) Cost Driver(s) Input Range Standard Error (absolute)
11a Spacecraft Bus (alternate) 101756 kg $172586 K $185776 K Spacecraft Bus Dry Weight 20-400 kg $369600 K11b Spacecraft Bus $886204 K $953937 K Sum of Spacecraft Bus Elements ($)111 Structure 242 kg $44828 K $48254 K Structure Weight (kg) 5-100 kg $109700 K112a Thermal Control 10 kg $90500 K $97417 K Min Thermal Control Weight (kg) 5-12 kg $11900 K112b Thermal Control 24 kg $361820 K $389474 K Max Thermal Control Weight (kg) 5-12 kg $11900 K113 ADCS 187 kg $189091 K $203544 K ADCS Weight (kg) 1-25 kg $111300 K114 EPS 03058 kg $149067 K $160460 K EPS Weight (kg) 7-70 kg $91000 K115 Propulsion (Reaction Control) 101756 kg $14493 K $15601 K Bus Dry Weight (kg) 20-400 kg $31000 K116a TTampC 176 kg $60505 K $65130 K TTampC Weight (kg) 3-30 kg $62900 K116b CampDH 0154 kg $66400 K $71475 K CampDH Wight (kg) 3-30 kg $85400 K
12 Payload $886204 K $354482 K $381575 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
13 IAampT $886204 K $123182 K $132597 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
40 Program Level $886204 K $202941 K $218452 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
50 LOOS $886204 K $54058 K $58190 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)
60 GSE $886204 K $58489 K $62960 K Spacecraft Bus Total Cost ($K) 2600-69000 ($K FY 10)Total Cost $1807710598
11 Spacecraft
60 Aerospace Ground Equipment
50 Flight Support
40 Program Level
13 Spacecraft Integration Assembly and Test
12 Payload
Small Spacecraft Cost Model (SSCM) not accurate shows current cost model inadequacies
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
Power Equipment List (PEL) Desaturation Power Usage
Power Equipment List (PEL) Flyby Power Usage
Iris Comms Link Budget
Slide 58
Cost Analysis Components of One 6U CubeSat
Cost Analysis Two 6U CubeSats and Operations
Risk
Mandatory Considerations External Issues
Critical Issues
Questions and Comments
References
References (2)
References (3)
References (4)
Image References
Trade Studies Doppler and GPS Heritage
Slide 71
Small Spacecraft Cost Model (SSCM) not accurate shows curren
Trade Study Velocity Data Accuracy Comparison
Trade Study Velocity Data Accuracy Comparisonbull Data Acquisition Position and Velocity
ndash GNSSGPSbull Multitude of Ground Stations (NEN)bull L1L2 (dual band or more)bull Will serve primarily as complimentary data and near periapse coveragebull Cross link ranging option
ndash Radio Doppler Monitoringbull DSNbull Dual frequencybull Slew rate of DSN limits coverage near periapse
ndash Deployable dish vs patch antennabull Earth SOI is at about 006 AUbull Noise considerations for data acquisition
ndash X- vs S- vs Ka-bandbull Noise mitigationbull Velocity accuracy over our range (~006 AU)
ndash Relative position systembull Requires inordinate power and pointing precision
ndash SLRbull Closest approach coveragebull No onboard power requirementbull Coverage provided by eight particular ground stations
