Lection #3 LAUNCH VEHICLES : The Principles Parameters

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Lection #3 LAUNCH VEHICLES : LAUNCH VEHICLES : The Principles Parameters. Methods of Estimation

Transcript of Lection #3 LAUNCH VEHICLES : The Principles Parameters

Lection #3LAUNCH VEHICLES : LAUNCH VEHICLES :

The Principles Parameters. Methods of Estimation

The First Space Velocity

HOrb

RE

First Space Velocity of Earth

2

Rocket Flight dynamic scheme

X, Y Coordinate system from Center Gravity, X‐local horizont

Xc, Yc Start coordinate system

 

 

Xc, Yc Start coordinate system

XA,YA Air‐dynamic force projections

V Rocket velocityV Rocket velocity

H Rocket flight altitude

P Rocket engine thrustP Rocket engine thrust

L Distance from start point

R Radius of EarthR Radius of Earth

mg Weight of rocket 

φ Pitch angle ‐ between rocket axisφ Pitch angle  between rocket axis and local horizont

α Angle of attack

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θ Trajectory angle ‐ between velocity vector and local horizont 

Payload mass m pl kg

The principal parameters of Launch Vehicle: m pl, kg

Initial launch mass m 0, kgPropellant type Liquid Solid

High - boiling or Low-boilingOxydizer + Fuel:

Amil +Heptyl Oxigen+HydrogenOxigen+Kerosyne

Cellulose Nitrate or Mixtured

g y

Engine thrust P, Nuton

Specific Impulse Is = P / propellant consumption m/secIs = P / propellant consumption, m/sec

2900….3300 m/s 4000…4500 m/s

2700…2900 m/sec

Number of stages NNumber of stagesUsually: N = 2…..3

Initial thrust / weight ratio n0 = P /m 0 g0Pitch angle as function of ( )Pitch angle as function of time φ = φ (t)Relative mass characteristics (statistics) Propellant Section mass characteristics a ps

Rocket engine relative mass eng

Name LV, stage Propellant P Is m eng Rocket

The typical examples of rocket engines

Thrust in vacuum, N

Specific impulse in vacuum, m/s

mass, kg engine relative mass

eng, gr/NStatistic Amil + Heptyl 3 000-3 300 0,8-1,2RD-253 Proton, I stage Amil + Heptyl 1 635 000 3 040 1 280 0,8RD-0212 Proton, III stage Amil+ Heptyl 482 000 3 210 550 1,1

RD 261 C l 2 3 4 A il + H t l 2 800 000 2 990RD‐261 Cyclone-2 , 3, 4 Amil + Heptyl 2 800 000 2 990

Statistic O2 + kerosyne 3 020-3 500 1,05-1,2

RD-107 Soyuz, I stage O2 + kerosyne 1 000 000 3 020 1 160 1,16

RD-170 Energia, I stage O2 + kerosyne 8 000 000 3 310 10 700 1,34

RD 191 A I t O2 k 2 080 000 3 300 2 200 1 06RD-191 Angara, I stage O2 + kerosyne 2 080 000 3 300 2 200 1,06

Statistic H2 + O2 4 460-4 500 1,5-1,8

RD-0120 Energia, II stage H2 + O2 2 000 000 4 460 3 450 1,7

Rocket engine mass characteristics:

eng =meng / P = f (P) Rocket engine relative mass [ gr/N ]eng =meng / P = f (P) Rocket engine relative mass [ gr/N ]

Asdaslkjlk

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RD 261

Engine for the first RD 855gstage of Cyclone LV Steering engine

for the first stage of Cycloneof Cyclone

PropellantsPropellants AmilAmil + + HeptylHeptyl PropellantsPropellants AmilAmil + + HeptylHeptylPropellantsPropellants AmilAmil + + HeptylHeptylVacuum thrustVacuum thrust , , N N 2 800 000 N 2 800 000 N Vacuum specific impulse, Vacuum specific impulse, m/sm/s 29902990Total burn duration, sTotal burn duration, s 115115

PropellantsPropellants AmilAmil HeptylHeptylVacuum thrustVacuum thrust , , N N 350 000 N 350 000 N Vacuum specific impulse, Vacuum specific impulse, m/sm/s 29202920Total burn duration, s 12Total burn duration, s 1277

FIRST STAGE VIEW

PROPELLANT SECTION DESIGNPROPELLANT SECTION DESIGN

Propellant Section mass characteristics: a m m ll t ti / ll t aps = m ps / m pr propellant section mass / propellant

mass

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Thrust / Weight Ratio: n0

LV Name N m0 P0 nNNumber of stages

m0

Stage initial mass ,t

P0

Engine Thrust in vacuum, kN

n0

Initial Thrust/Weight ratio

P t 3 m o I= 716 0 9 520 1 33Proton 3 m o I= 716,0m o II= 260,0m o III= 94,0

9 5202 330

613

1,330,900,65

Zenit-2 2 m o I= 460,0 7 257 1,58Zenit 2m o II= 103,0 912 0,89

Soyuz 3 m o I= 306,0m o II= 96,0

III 32 0

4 065941304

1,330,980 95m o III= 32,0 304 0,95

Cosmos-3M 2 m o I= 109,0m o II= 22,5

1 480158

1,360,72

Rockot (SS-19) 2 m o I= 107,0 1 880 1,78Rockot (SS 19) 2 ,m o II= 19,7 255

,1,29

Dnepr (SS-18) 3 m o I= 211,0m o II= 53,7

III 6 3

4 610775

8

2,181,350 12m o III= 6,3 8 0,12

Average for statistics

I stageII stage

III stage

1,25…2.00,7…0.90,3…0,6

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g , ,