STAAD.Pro V8i Verification Manual - Bentley Communities · PDF fileFigure1-1:Spacetruss...

STAAD.ProV8i (SELECTseries 5)

Verification ManualLast Updated: Monday, January 06, 2014

STAAD Verification ProblemsRelease STAAD.Pro 20.07.10.41

Date last updated: 13 December 2013

Quality Assurance ProgramSTAAD.Pro V8i (SELECTseries 5) is a suite of proprietary computer programs of BentleySystems, Inc.. Although every effort has been made to ensure the correctness of these programs,Bentley Systems, Inc. will not accept responsibility for any mistake, error, or misrepresentationin or as a result of the usage of these programs.

Notes on ComparisonsIn each verification problem, a table is used to summarize the numerical outputs fromSTAAD.Pro with a reference or hand calculations. A difference column presents the percentdeviation from the reference, when a significant difference exists.

The deviation is taken as the reference value minus the value determined by STAAD.Pro, dividedby the reference value to express in percent of the reference.

In this context, "significant" is take as larger than a 1% (one percent) difference. When adifference between 0.5% and 1% exists, then the difference is simply listed as "<1%". Otherwise,the difference is listed as "none".

This level of significance is intended to reflect that small differences in rounding or calculationmethods do not present a realistic difference in the calculated result.

Verification Manual — 2

Table of Contents1 Static Trusses 1Static Truss 1 1

Static Truss 2 4

Static Truss 3 8

Static Truss 4 12

Static Truss 5 16

Static Truss 6 19

Static Truss 7 31

2 Static Beams 35Static Beam 1 35

Static Beam 2 39

Static Beam 3 43

Static Beam 4 47

Static Beam 5 53

Static Beam 6 56

Static Beam 7 59

Static Beam 8 62

Static Beam 9 65

Static Beam 11 72

Static Beam 12 75

Static Beam 13 78

Static Beam 15 87

3 Static Frames 91Static Frame 1 91

Static Frame 2 95

Static Frame 3 99

Static Frame 4 102

Static Frame 5 108

Static Frame 10 123

Static Frame 11 127

Static Frame 12 131

4 Static Plate/Shell Elements 139


Static Element 1 139

















5 Solid Elements 249Static Solid 1 249

Static Solid 2 253

6 Nonlinear Static Analysis 263Static Nonlinear 1 263

7 Dynamic Analysis 269Dynamic Truss 1 269

Dynamic Beam 1 272

Dynamic Beam 2 276

Dynamic Beam 3 278

Dynamic Beam 4 281

Dynamic Beam 7 287

8 Concrete Design - ACI 318 291Concrete Design per ACI 318 1 291

Concrete Design per ACI 318 3 296



4 — STAAD.Pro

9 Steel Design - AISC 360-10 307Steel Design per AISC 360-10 - Example E-2 307

Steel Design per AISC 360-10 - Example G-6 313

Steel Design per AISC 360-10 - Example D-2 319

Steel Design per AISC 360-10 - Example F.2-2 326

Steel Design per AISC 360-10 - Example H.1B 332

Steel Design per AISC 360-10 - Example E.5 339

Steel Design per AISC 360-10 - Example F.1-3B 345

10 Steel Design per AISC ASD 353Steel Design per AISC ASD 1 353

Steel Design per AISC ASD 2 357

















11 Steel Design per AISC LRFD 413Steel Design per AISC LRFD 1 414

Steel Design per AISC LRFD 2 416


























12 Steel Design per AS 4100-1998 497Steel Design per AS 4100-1998 1 497

Steel Design per AS 4100-1998 2 502



13 Steel Design per BS 5950-1:2000 515Steel Design per BS 5950-1:2000 1 515

Steel Design per BS 5950-1:2000 2 521






6 — STAAD.Pro

Copyright InformationTrademark NoticeBentley, the "B" Bentley logo, STAAD.Pro are registered or nonregistered trademarks of BentleySystems, Inc. or Bentley Software, Inc. All other marks are the property of their respectiveowners.

Copyright Notice© 2013, Bentley Systems, Incorporated. All Rights Reserved.

Including software, file formats, and audiovisual displays; may only be used pursuant toapplicable software license agreement; contains confidential and proprietary information ofBentley Systems, Incorporated and/or third parties which is protected by copyright and tradesecret law and may not be provided or otherwise made available without proper authorization.

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ANSYS is a registered trademark of ANSYS, Inc.

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Restricted Rights LegendsIf this software is acquired for or on behalf of the United States of America, its agencies and/orinstrumentalities ("U.S. Government"), it is provided with restricted rights. This software andaccompanying documentation are "commercial computer software" and "commercial computersoftware documentation," respectively, pursuant to 48 C.F.R. 12.212 and 227.7202, and "restrictedcomputer software" pursuant to 48 C.F.R. 52.227-19(a), as applicable. Use, modification,reproduction, release, performance, display or disclosure of this software and accompanyingdocumentation by the U.S. Government are subject to restrictions as set forth in this Agreementand pursuant to 48 C.F.R. 12.212, 52.227-19, 227.7202, and 1852.227-86, as applicable.Contractor/Manufacturer is Bentley Systems, Incorporated, 685 Stockton Drive, Exton, PA 19341-0678.

Unpublished - rights reserved under the Copyright Laws of the United States and Internationaltreaties.

End User License AgreementTo view the End User License Agreement for this product, review: eula_en.pdf.


http://www.bentley.com/bentleywebsite/files/legal/eula_en.pdf

8 — STAAD.Pro

Notes

1Static Trusses

Static Truss 1 1

Static Truss 2 4

Static Truss 3 8

Static Truss 4 12

Static Truss 5 16

Static Truss 6 19

Static Truss 7 31

Static Truss 1ObjectiveTo find member stress due to a joint load in a space truss using static analysis.

ReferenceBeer, F.P., and Johnston, Jr., E.R., Vector Mechanics for Engineers, Statics and Dynamics, McGraw -Hill, Inc., New York, 1962, p.47, Problem 2.70.

ProblemA 50 lb load is supported by three bars which are pinned to a ceiling as shown. Determine thestress, σ, in each bar.

Area of each bar = 1 in2, E = 30 (10)6 psi


Figure 1-1: Space truss

Comparison

Result Type Theory STAAD.Pro Difference

σAD 31.2 31.2 none

σBD 10.4 10.4 none

σCD 22.9 22.9 none

Table 1-1: Comparison of member stress, in psi, for static truss no. 1

STAAD InputSTAAD TRUSS :A SPACE TRUSS* FILE TRUSS01.STD** REF: "VECTOR MECHANICS FOR ENGINEERS, STATICS & DYNAMICS",* MCGRAW HILL BOOK CO., INC., NEW YORK, 1962* PROBLEM 2.70, PAGE 47.*UNIT FT POUNDJOINT COORDINATES1 0. 0. 0.2 8. 0. 0.3 0. 6. 0.4 4. 2. 6.MEMBER INCIDENCES1 1 42 2 43 3 4UNIT INCHMEMBER PROPERTIES1 TO 3 PRIS AX 1.CONSTANTSE 30E6 ALLSUPPORTS1 TO 3 PINNEDLOAD 1 WEIGHTJOINT LOAD4 FZ 50.PERFORM ANALYSISPRINT MEMBER STRESSESFINISH

2 — STAAD.Pro

1 Static Trusses

Static Truss 1

STAAD OutputPAGE NO. 1

***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:30: 8 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD TRUSS :A SPACE TRUSSINPUT FILE: TRUSS01.STD

2. * FILE TRUSS01.STD3. *4. * REF: "VECTOR MECHANICS FOR ENGINEERS, STATICS &AMP; DYNAMICS",5. * MCGRAW HILL BOOK CO., INC., NEW YORK, 19626. * PROBLEM 2.70, PAGE 47.7. *8. UNIT FT POUND9. JOINT COORDINATES10. 1 0. 0. 0.11. 2 8. 0. 0.12. 3 0. 6. 0.13. 4 4. 2. 6.14. MEMBER INCIDENCES15. 1 1 416. 2 2 417. 3 3 418. UNIT INCH19. MEMBER PROPERTIES20. 1 TO 3 PRIS AX 1.21. CONSTANTS22. E 30E6 ALL23. SUPPORTS24. 1 TO 3 PINNED25. LOAD 1 WEIGHT26. JOINT LOAD27. 4 FZ 50.28. PERFORM ANALYSIS

**WARNING** THE POISSON'S RATIO HAS NOT BEEN SPECIFIED FOR ONE OR MOREMEMBERS/ELEMENTS/SOLIDS. THE DEFAULT VALUE HAS BEEN SET FOR THE SAME.

:A SPACE TRUSS -- PAGE NO. 2* FILE TRUSS01.STD

P R O B L E M S T A T I S T I C S-----------------------------------

NUMBER OF JOINTS 4 NUMBER OF MEMBERS 3NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 3

SOLVER USED IS THE IN-CORE ADVANCED SOLVER

TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 3

29. PRINT MEMBER STRESSESMEMBER STRESSES

:A SPACE TRUSS -- PAGE NO. 3

1 Static Trusses


* FILE TRUSS01.STD

MEMBER STRESSES---------------ALL UNITS ARE POUN/SQ INCHMEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z

1 1 .0 10.4 T 0.0 0.0 10.4 0.0 0.01.0 10.4 T 0.0 0.0 10.4 0.0 0.0

2 1 .0 31.2 T 0.0 0.0 31.2 0.0 0.01.0 31.2 T 0.0 0.0 31.2 0.0 0.0

3 1 .0 22.9 T 0.0 0.0 22.9 0.0 0.01.0 22.9 T 0.0 0.0 22.9 0.0 0.0

************** END OF LATEST ANALYSIS RESULT **************30. FINISH

*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:30:11 ****

:A SPACE TRUSS -- PAGE NO. 4* FILE TRUSS01.STD

************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Static Truss 2ObjectiveTo find member force due to a member load in a plane articulate structure.

ReferenceKinney, J. S.,Indeterminate Structural Analysis, Addison - Wesley Publishing Co., 1957, p.275,Problem 6 - 19.(Original data is in US Customary Units)

ProblemFind the tensile stress in the cable. The cross - sectional area of the cable is 967.74 mm2 withan E of 137.895 GPa. The timber beam 1-3 is 304.8 mm x 304.8 mm in section, with E = 11.03161GPa. Each member of the steel cantilever truss has a cross - sectional area of 2,580.64 mm2,and E of 206.8427 GPa.

4 — STAAD.Pro

1 Static Trusses

Static Truss 2

Figure 1-2: Plane articulate truss

Comparison


Cable, 3-4 22.7 22.58 0.6% (negligible)

Table 1-2: Comparison of member force, in kN, for static truss no. 2

STAAD InputSTAAD PLANE :A PLANE ARTICULATE STRUCTURE* FILE TRUSS02.STD** REFERENCE: INDETERMINATE STRURAL ANALYSIS, KINNEY, 1957,* ADISON-WESLEY PUBLISHING COMPANY, PAGE 275, PROBLEM 6-19.**UNIT NEWTON METERJOINT COORDINATES1 0 0 02 3.0480 0 03 4.5720 0 04 4.5720 2.4384 05 6.4008 4.8768 06 6.4008 2.4384 07 8.2296 4.8768 08 8.2296 2.4384 09 10.0586 4.8768 010 10.0586 2.4384 0*MEMBER INCIDENCES1 1 2 3 1 14 4 65 6 86 8 107 4 58 6 59 6 710 8 711 8 912 5 713 7 9MEMBER PROPERTIES1 2 PRI YD .3048 ZD .30483 PRI AX 9.6774E-4 IZ 41.62314E-84 TO 13 PRI AX 25.8064E-4 IZ 41.62314E-8CONSTANTSE 11.03161E9 MEMB 1 2

1 Static Trusses


E 137.89500E9 MEMB 3E 206.84270E9 MEMB 4 TO 13MEMBER RELEASES3 TO 13 START MZ*SUPPORT1 9 10 FIXED*LOADING 1JOINT LOADS2 FY -44.4822E3*PERFORM ANALYSISUNITS KNSPRINT MEMBER FORCES LIST 3FINISH

STAADOutputPAGE NO. 1

***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:30:11 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD PLANE :A PLANE ARTICULATE STRUCTUREINPUT FILE: TRUSS02.STD

2. * FILE TRUSS02.STD3. *4. * REFERENCE: INDETERMINATE STRURAL ANALYSIS, KINNEY, 1957,5. * ADISON-WESLEY PUBLISHING COMPANY, PAGE 275, PROBLEM 6-19.6. *7. *8. UNIT NEWTON METER9. JOINT COORDINATES10. 1 0 0 011. 2 3.0480 0 012. 3 4.5720 0 013. 4 4.5720 2.4384 014. 5 6.4008 4.8768 015. 6 6.4008 2.4384 016. 7 8.2296 4.8768 017. 8 8.2296 2.4384 018. 9 10.0586 4.8768 019. 10 10.0586 2.4384 020. *21. MEMBER INCIDENCES22. 1 1 2 3 1 123. 4 4 624. 5 6 825. 6 8 1026. 7 4 527. 8 6 528. 9 6 729. 10 8 730. 11 8 931. 12 5 732. 13 7 9

6 — STAAD.Pro

1 Static Trusses

Static Truss 2

33. MEMBER PROPERTIES34. 1 2 PRI YD .3048 ZD .304835. 3 PRI AX 9.6774E-4 IZ 41.62314E-836. 4 TO 13 PRI AX 25.8064E-4 IZ 41.62314E-837. CONSTANTS38. E 11.03161E9 MEMB 1 2:A PLANE ARTICULATE STRUCTURE -- PAGE NO. 2

* FILE TRUSS02.STD39. E 137.89500E9 MEMB 340. E 206.84270E9 MEMB 4 TO 1341. MEMBER RELEASES42. 3 TO 13 START MZ43. *44. SUPPORT45. 1 9 10 FIXED46. *47. LOADING 148. JOINT LOADS49. 2 FY -44.4822E350. *51. PERFORM ANALYSIS






52. UNITS KNS53. PRINT MEMBER FORCES LIST 3

MEMBER FORCES LIST 3:A PLANE ARTICULATE STRUCTURE -- PAGE NO. 3

* FILE TRUSS02.STD

MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- KNS METE (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

3 1 3 -22.58 0.00 0.00 0.00 0.00 0.004 22.58 0.00 0.00 0.00 0.00 0.00



:A PLANE ARTICULATE STRUCTURE -- PAGE NO. 4* FILE TRUSS02.STD


1 Static Trusses


Static Truss 3ObjectiveTo find member forces due to joint loads in a plane truss.

ReferenceNorris C.H., Wilbur J. B., Elementary Structural Analysis, 2nd Edition, McGraw – Hill, Inc., Page159, Problem 4.3. (Original data is in US Customary Units)

ProblemCompute the bar forces in the bars a, b, c, d, e of the truss due to the loads shown.

Figure 1-3: Plane truss

Comparison


a -202.13 -202.13 none

b -185.76 -190.28 2.4% (negligible)

c -22.42 -23.42 4.5%

d 266.23 269.52 1.2% (negligible)

e 119.61 117.08 2.1% (negligible)

Table 1-3: Comparison of member force, in kN, for static truss no. 3

8 — STAAD.Pro

1 Static Trusses

Static Truss 3

STAAD InputSTAAD PLANE :A PLANE TRUSS* FILE TRUSS03.STD** REFERENCE: ELEMENTARY STRUCTURAL ANALYSIS, NORIS AND WILBUR,* 2ND EDITION, MCGRAW-HILL BOOK COMPANY, PAGE 159,* PROBLEM 4.3 (ORIGINAL DATA IN US CUSTOMAY UNITS)*UNIT NEWTON METERJOINT COORDINATES1 0 02 7.62 03 7.62 9.1444 15.24 05 15.24 4.5726 15.24 9.1447 22.86 08 22.86 12.1929 30.48 010 30.48 4.57211 30.48 9.14412 38.10 013 38.10 9.14414 45.72 0*MEMBER INCIDENCES1 1 2; 5 2 48 4 7; 11 7 914 9 12; 17 12 142 1 5; 3 1 34 2 3; 6 5 37 3 6; 9 7 521 4 5; 22 5 610 6 8;23 7 812 7 10; 13 11 824 9 10; 25 10 1115 10 13; 16 11 1318 14 10; 19 12 1320 14 13MEMBER PROPERTIES1 TO 25 PRI AX 12.9032E-4CONSTANTE 206.84271E9 ALLMEMBER TRUSS1 TO 25*SUPPORTS1 PINNED14 FIXED BUT FX*LOADING 1 VERTICAL JOINT LOADSJOINT LOADS2 9 FY -4.448222E44 7 FY -8.896444E412 FY -2.224111E4*PERFORM ANALYSISUNITS KNSPRINT MEMBER FORCES LIST 2 5 6 10 12FINISH


1 Static Trusses



1. STAAD PLANE :A PLANE TRUSSINPUT FILE: TRUSS03.STD

2. * FILE TRUSS03.STD3. *4. * REFERENCE: ELEMENTARY STRUCTURAL ANALYSIS, NORIS AND WILBUR,5. * 2ND EDITION, MCGRAW-HILL BOOK COMPANY, PAGE 159,6. * PROBLEM 4.3 (ORIGINAL DATA IN US CUSTOMAY UNITS)7. *8. UNIT NEWTON METER9. JOINT COORDINATES10. 1 0 011. 2 7.62 012. 3 7.62 9.14413. 4 15.24 014. 5 15.24 4.57215. 6 15.24 9.14416. 7 22.86 017. 8 22.86 12.19218. 9 30.48 019. 10 30.48 4.57220. 11 30.48 9.14421. 12 38.10 022. 13 38.10 9.14423. 14 45.72 024. *25. MEMBER INCIDENCES26. 1 1 2; 5 2 427. 8 4 7; 11 7 928. 14 9 12; 17 12 1429. 2 1 5; 3 1 330. 4 2 3; 6 5 331. 7 3 6; 9 7 532. 21 4 5; 22 5 633. 10 6 8;23 7 834. 12 7 10; 13 11 835. 24 9 10; 25 10 1136. 15 10 13; 16 11 1337. 18 14 10; 19 12 1338. 20 14 13:A PLANE TRUSS -- PAGE NO. 2

* FILE TRUSS03.STD39. MEMBER PROPERTIES40. 1 TO 25 PRI AX 12.9032E-441. CONSTANT42. E 206.84271E9 ALL43. MEMBER TRUSS44. 1 TO 2545. *46. SUPPORTS47. 1 PINNED48. 14 FIXED BUT FX49. *50. LOADING 1 VERTICAL JOINT LOADS

10 — STAAD.Pro

1 Static Trusses

Static Truss 3

51. JOINT LOADS52. 2 9 FY -4.448222E453. 4 7 FY -8.896444E454. 12 FY -2.224111E455. *56. PERFORM ANALYSIS






*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 1 EQN.NO. 1LOADS APPLIED OR DISTRIBUTED HERE FROM ELEMENTS WILL BE IGNORED.THIS MAY BE DUE TO ALL MEMBERS AT THIS JOINT BEING RELEASED OREFFECTIVELY RELEASED IN THIS DIRECTION.

*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 2 EQN.NO. 4*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 3 EQN.NO. 7*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 4 EQN.NO. 10*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 5 EQN.NO. 13*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 6 EQN.NO. 16*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 7 EQN.NO. 19*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 8 EQN.NO. 22*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 9 EQN.NO. 25*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 10 EQN.NO. 28*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 11 EQN.NO. 31

:A PLANE TRUSS -- PAGE NO. 3* FILE TRUSS03.STD

*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 12 EQN.NO. 34**WARNING - THERE WERE MORE THAN 12 DOF WITH ZERO STIFFNESS.

THE FIRST 12 ARE LISTED ABOVE.TOTAL # TRANSLATIONAL= 0 TOTAL # ROTATIONAL= 13

57. UNITS KNS58. PRINT MEMBER FORCES LIST 2 5 6 10 12

MEMBER FORCES LIST 2:A PLANE TRUSS -- PAGE NO. 4

* FILE TRUSS03.STD

MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- KNS METE (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

2 1 1 190.28 0.00 0.00 0.00 0.00 0.005 -190.28 0.00 0.00 0.00 0.00 0.00

5 1 2 -269.52 0.00 0.00 0.00 0.00 0.004 269.52 0.00 0.00 0.00 0.00 0.00

6 1 5 -117.08 0.00 0.00 0.00 0.00 0.003 117.08 0.00 0.00 0.00 0.00 0.00

10 1 6 202.12 0.00 0.00 0.00 0.00 0.008 -202.12 0.00 0.00 0.00 0.00 0.00

12 1 7 23.42 0.00 0.00 0.00 0.00 0.0010 -23.42 0.00 0.00 0.00 0.00 0.00



1 Static Trusses




Static Truss 4ObjectiveTo find support reactions and member forces due to a joint load in a space truss.

ReferenceBeer F. P., and Johnston, E. R., Vector Mechanics for Engineers - Statics, 4th Edition, McGraw –Hill, Inc., p.216, Problem 6.20.

ProblemThe space truss is supported by the six reactions shown. If a horizontal 2,700 N load is appliedat A, determine the reactions and the force in each member.

12 — STAAD.Pro

1 Static Trusses

Static Truss 4


Comparison


Bv 0 0 none

Bz 2,700 2,700 none

Cx 1,800 1,800 none

Cv 3,375 3,375 none

Dx 1,800 1,800 none

Dv 3,375 3,375 none

Table 1-4: Comparison of support reactions, in N, for static truss no. 4


AB 0 0 none

AC 4,275 4,275 none

Table 1-5: Comparison of member forces, in N, for static truss no. 4

1 Static Trusses



AD 4,275 4,275 none

BC 4,270 4,269 negligible

CD 0 0 none

BD 4,270 4,269 negligible

STAAD InputSTAAD SPACE :A SPACE TRUSS* FILE: TRUSS04.STD** REFERENCE: VECTOR MECHANICS FOR ENGINEERS - STATICS, BEER AND* JOHNSTON, 4TH EDITION, MCGRAW-HILL BOOK CO.,* PAGE 216, PROBLEM 6.20.*UNITS NEWTON METERJOINT COORDINATES1 1.0 0.0 0.62 1.0 0.0 -0.63 -0.8 0.0 0.04 0.0 1.5 0.0*MEMBER INCIDENCES1 1 42 2 43 3 44 1 2 56 3 1MEMBER PROPERTIES1 TO 6 PRI AX 0.001CONSTANTSE 200.0E9 ALLMEMBER TRUSS1 TO 6*SUPPORTS1 FIXED BUT FZ2 FIXED BUT FZ3 FIXED BUT FX*LOADING 1 HORIZONTAL LOADJOINT LOAD4 FZ 2700.0PERFORM ANALYSISPRINT SUPPORT REACTIONSPRINT MEMBER FORCESFINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:30:18 *

14 — STAAD.Pro

1 Static Trusses

Static Truss 4

* ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE :A SPACE TRUSSINPUT FILE: TRUSS04.STD

2. * FILE: TRUSS04.STD3. *4. * REFERENCE: VECTOR MECHANICS FOR ENGINEERS - STATICS, BEER AND5. * JOHNSTON, 4TH EDITION, MCGRAW-HILL BOOK CO.,6. * PAGE 216, PROBLEM 6.20.7. *8. UNITS NEWTON METER9. JOINT COORDINATES10. 1 1.0 0.0 0.611. 2 1.0 0.0 -0.612. 3 -0.8 0.0 0.013. 4 0.0 1.5 0.014. *15. MEMBER INCIDENCES16. 1 1 417. 2 2 418. 3 3 419. 4 1 2 520. 6 3 121. MEMBER PROPERTIES22. 1 TO 6 PRI AX 0.00123. CONSTANTS24. E 200.0E9 ALL25. MEMBER TRUSS26. 1 TO 627. *28. SUPPORTS29. 1 FIXED BUT FZ30. 2 FIXED BUT FZ31. 3 FIXED BUT FX32. *33. LOADING 1 HORIZONTAL LOAD34. JOINT LOAD35. 4 FZ 2700.036. PERFORM ANALYSIS:A SPACE TRUSS -- PAGE NO. 2

* FILE: TRUSS04.STD







*WARNING- ZERO STIFFNESS IN DIRECTION 5 AT JOINT 4 EQN.NO. 8*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 4 EQN.NO. 9

37. PRINT SUPPORT REACTIONSSUPPORT REACTION

1 Static Trusses


:A SPACE TRUSS -- PAGE NO. 3* FILE: TRUSS04.STD

SUPPORT REACTIONS -UNIT NEWT METE STRUCTURE TYPE = SPACE-----------------

JOINT LOAD FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z

1 1 1800.00 3375.00 0.00 0.00 0.00 0.002 1 -1800.00 -3375.00 0.00 0.00 0.00 0.003 1 0.00 0.00 -2700.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************38. PRINT MEMBER FORCES

MEMBER FORCES:A SPACE TRUSS -- PAGE NO. 4

* FILE: TRUSS04.STD

MEMBER END FORCES STRUCTURE TYPE = SPACE-----------------ALL UNITS ARE -- NEWT METE (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 4275.00 0.00 0.00 0.00 0.00 0.004 -4275.00 0.00 0.00 0.00 0.00 0.00

2 1 2 -4275.00 0.00 0.00 0.00 0.00 0.004 4275.00 0.00 0.00 0.00 0.00 0.00

3 1 3 0.00 0.00 0.00 0.00 0.00 0.004 0.00 0.00 0.00 0.00 0.00 0.00

4 1 1 0.00 0.00 0.00 0.00 0.00 0.002 0.00 0.00 0.00 0.00 0.00 0.00

5 1 2 4269.07 0.00 0.00 0.00 0.00 0.003 -4269.07 0.00 0.00 0.00 0.00 0.00

6 1 3 -4269.07 0.00 0.00 0.00 0.00 0.001 4269.07 0.00 0.00 0.00 0.00 0.00



:A SPACE TRUSS -- PAGE NO. 5* FILE: TRUSS04.STD


Static Truss 5ObjectiveTo find support reactions due to joint loads in a plane truss.

ReferenceMcCormack, J.C. Structural Analysis, Intext Educational Publishers, 3rd Edition, 1975.

16 — STAAD.Pro

1 Static Trusses

Static Truss 5

ProblemFind the vertical support reactions of the truss.

E = 30,000.0 ksi

A = 100 in2

Loads as shown.


Comparison


R1 -76.7 -76.67 none

R4 346.7 346.67 none

R9 30 30 none


STAAD InputSTAAD TRUSS :A PLANE TRUSS* FILE: TRUSS05.STD** REFERENCE: MCCORMAC, J.C.,"STRUCTURAL ANALYSIS", INTEXT* EDUCATIONAL PUBLISHERS, NEW YORK, 3RD EDITION, 1975.*INPUT WIDTH 72UNIT FEET KIPJOINT COORDINATES1 0. 0. 0.; 2 30. 0. 0.; 3 60. 0. 0.; 4 90. 0. 0.; 5 120. 0. 0.6 150. 0. 0.; 7 180. 0. 0.; 8 210. 0. 0.; 9 240. 0. 0.; 10 0. 20. 0.11 30. 20. 0.; 12 60. 20. 0.; 13 90. 20. 0.; 14 120. 20. 0.15 150. 20. 0.; 16 180. 20. 0.; 17 210. 20. 0.; 18 240. 20. 0.MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8; 8 8 9; 9 10 1110 11 12; 11 12 13; 12 13 14; 13 14 15; 14 16 17; 15 17 18; 16 1 1017 10 2; 18 2 11; 19 11 3; 20 3 12; 21 12 4; 22 4 13; 23 13 5; 24 5 1425 14 6; 26 6 15; 27 15 7; 28 7 16; 29 16 8; 30 8 17; 31 17 9; 32 9 18UNIT INCHES KIPMEMBER PROPERTY AMERICAN1 TO 32 PRI AX 100.* MEMBER TRUSS* 1 TO 32CONSTANTSE 30000. ALL

1 Static Trusses


SUPPORTS1 PINNED4 9 FIXED BUT FX MZLOAD 1 POINT LOADS AT SPECIFIC JOINTSJOINT LOAD6 TO 8 FY -60.3 FY -80.2 FY -40.PERFORM ANALYSISPRINT SUPPORT REACTIONSFINISH



1. STAAD TRUSS :A PLANE TRUSSINPUT FILE: TRUSS05.STD

2. * FILE: TRUSS05.STD3. *4. * REFERENCE: MCCORMAC, J.C.,"STRUCTURAL ANALYSIS", INTEXT5. * EDUCATIONAL PUBLISHERS, NEW YORK, 3RD EDITION, 1975.6. *7. INPUT WIDTH 728. UNIT FEET KIP9. JOINT COORDINATES10. 1 0. 0. 0.; 2 30. 0. 0.; 3 60. 0. 0.; 4 90. 0. 0.; 5 120. 0. 0.11. 6 150. 0. 0.; 7 180. 0. 0.; 8 210. 0. 0.; 9 240. 0. 0.; 10 0. 20. 0.12. 11 30. 20. 0.; 12 60. 20. 0.; 13 90. 20. 0.; 14 120. 20. 0.13. 15 150. 20. 0.; 16 180. 20. 0.; 17 210. 20. 0.; 18 240. 20. 0.14. MEMBER INCIDENCES15. 1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8; 8 8 9; 9 10 1116. 10 11 12; 11 12 13; 12 13 14; 13 14 15; 14 16 17; 15 17 18; 16 1 1017. 17 10 2; 18 2 11; 19 11 3; 20 3 12; 21 12 4; 22 4 13; 23 13 5; 24 5 1418. 25 14 6; 26 6 15; 27 15 7; 28 7 16; 29 16 8; 30 8 17; 31 17 9; 32 9 1819. UNIT INCHES KIP20. MEMBER PROPERTY AMERICAN21. 1 TO 32 PRI AX 100.22. * MEMBER TRUSS23. * 1 TO 3224. CONSTANTS25. E 30000. ALL26. SUPPORTS27. 1 PINNED28. 4 9 FIXED BUT FX MZ29. LOAD 1 POINT LOADS AT SPECIFIC JOINTS30. JOINT LOAD31. 6 TO 8 FY -60.32. 3 FY -80.33. 2 FY -40.34. PERFORM ANALYSIS

:A PLANE TRUSS -- PAGE NO. 2* FILE: TRUSS05.STD

18 — STAAD.Pro

1 Static Trusses

Static Truss 5








SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = TRUSS-----------------


1 1 0.00 -76.67 0.00 0.00 0.00 0.004 1 0.00 346.67 0.00 0.00 0.00 0.009 1 0.00 30.00 0.00 0.00 0.00 0.00





Static Truss 6ObjectiveTo find support reactions due to joint loads in a plane truss.

ReferenceMcCormack, J.C., Structural Analysis, Intext Educational Publishers, 3rd Edition, 1975.

ProblemFind the vertical and horizontal reactions at the supports of the truss.

E = 30,000.0 ksi. A = 100 in2. Loads as shown.

1 Static Trusses



Comparison


Horizontal, R1 34.3 34.29 none

Vertical, R1 11.5 11.49 none

Horizontal, R2 36.0 36.0 none

Vertical, R2 -31.7 -31.67 none


STAAD InputSTAAD TRUSS :A PLANE TRUSS* FILE TRUSS06.STD** REFERENCE: MCCORMAC, J.C.,"STRUCTURAL ANALYSIS", INTEXT* EDUCATIONAL PUBLISHERS, NEW YORK, 3RD EDITION, 1975.*INPUT WIDTH 72UNIT FEET KIPJOINT COORDINATES1 0. 0. 0.; 2 0. 60. 0.; 3 12.5 60. 0.; 4 0. 15. 0.; 5 0. 30. 0.6 0. 45. 0.; 7 9.375 45. 0.; 8 6.25 30. 0.; 9 3.125 15. 0.10 50. 90. 0.; 11 100. 90. 0.; 12 50. 75. 0.; 13 25. 75. 0.14 66.667 90. 0.; 15 83.333 90. 0.; 16 83.333 85. 0.; 17 66.667 80. 0.18 31.25 67.5 0.; 19 200. 0. 0.; 20 200. 60. 0.; 21 187.5 60. 0.22 200. 15. 0.; 23 200. 30. 0.; 24 200. 45. 0.; 25 190.625 45. 0.26 193.75 30. 0.; 27 196.875 15. 0.; 28 150. 90. 0.; 29 150. 75. 0.30 175. 75. 0.; 31 133.333 90. 0.; 32 116.667 90. 0.; 33 116.667 85. 0.34 133.333 80. 0.; 35 168.75 67.5 0.

20 — STAAD.Pro

1 Static Trusses

Static Truss 6

MEMBER INCIDENCES1 1 4; 2 2 3; 3 3 7; 4 4 5; 5 5 6; 6 6 2; 7 7 8; 8 8 9; 9 9 1; 10 4 911 9 5; 12 5 8; 13 8 6; 14 6 7; 15 7 2; 16 2 13; 17 10 14; 18 11 1619 12 18; 20 13 10; 21 14 15; 22 15 11; 23 16 17; 24 17 12; 25 18 326 3 13; 27 13 18; 28 13 12; 29 12 10; 30 10 17; 31 17 14; 32 14 1633 16 15; 34 19 22; 35 20 21; 36 21 25; 37 22 23; 38 23 24; 39 24 2040 25 26; 41 26 27; 42 27 19; 43 22 27; 44 27 23; 45 23 26; 46 26 2447 24 25; 48 25 20; 49 20 30; 50 28 31; 51 11 33; 52 29 35; 53 30 2854 31 32; 55 32 11; 56 33 34; 57 34 29; 58 35 21; 59 21 30; 60 30 3561 30 29; 62 29 28; 63 28 34; 64 34 31; 65 31 33; 66 33 32UNIT INCHES KIPMEMBER PROPERTY AMERICAN1 TO 66 PRI AX 100.CONSTANTSE 30000. ALLSUPPORTS1 19 PINNEDUNIT FEET KIPLOAD 1 JOINT LOADS AT SPECIFIC NODESJOINT LOAD11 14 15 31 32 FY -10.10 28 FY -5.4 TO 6 FX 4.2 FX 2.02 10 FX 1.543513 FX 3.08702 10 FY -2.572513 FY -5.145PERFORM ANALYSISPRINT SUPPORT REACTIONSFINISH




2. * FILE TRUSS06.STD3. *4. * REFERENCE: MCCORMAC, J.C.,"STRUCTURAL ANALYSIS", INTEXT5. * EDUCATIONAL PUBLISHERS, NEW YORK, 3RD EDITION, 1975.6. *7. INPUT WIDTH 728. UNIT FEET KIP9. JOINT COORDINATES10. 1 0. 0. 0.; 2 0. 60. 0.; 3 12.5 60. 0.; 4 0. 15. 0.; 5 0. 30. 0.11. 6 0. 45. 0.; 7 9.375 45. 0.; 8 6.25 30. 0.; 9 3.125 15. 0.12. 10 50. 90. 0.; 11 100. 90. 0.; 12 50. 75. 0.; 13 25. 75. 0.13. 14 66.667 90. 0.; 15 83.333 90. 0.; 16 83.333 85. 0.; 17 66.667 80. 0.14. 18 31.25 67.5 0.; 19 200. 0. 0.; 20 200. 60. 0.; 21 187.5 60. 0.15. 22 200. 15. 0.; 23 200. 30. 0.; 24 200. 45. 0.; 25 190.625 45. 0.16. 26 193.75 30. 0.; 27 196.875 15. 0.; 28 150. 90. 0.; 29 150. 75. 0.17. 30 175. 75. 0.; 31 133.333 90. 0.; 32 116.667 90. 0.; 33 116.667 85. 0.

1 Static Trusses


18. 34 133.333 80. 0.; 35 168.75 67.5 0.19. MEMBER INCIDENCES20. 1 1 4; 2 2 3; 3 3 7; 4 4 5; 5 5 6; 6 6 2; 7 7 8; 8 8 9; 9 9 1; 10 4 921. 11 9 5; 12 5 8; 13 8 6; 14 6 7; 15 7 2; 16 2 13; 17 10 14; 18 11 1622. 19 12 18; 20 13 10; 21 14 15; 22 15 11; 23 16 17; 24 17 12; 25 18 323. 26 3 13; 27 13 18; 28 13 12; 29 12 10; 30 10 17; 31 17 14; 32 14 1624. 33 16 15; 34 19 22; 35 20 21; 36 21 25; 37 22 23; 38 23 24; 39 24 2025. 40 25 26; 41 26 27; 42 27 19; 43 22 27; 44 27 23; 45 23 26; 46 26 2426. 47 24 25; 48 25 20; 49 20 30; 50 28 31; 51 11 33; 52 29 35; 53 30 2827. 54 31 32; 55 32 11; 56 33 34; 57 34 29; 58 35 21; 59 21 30; 60 30 3528. 61 30 29; 62 29 28; 63 28 34; 64 34 31; 65 31 33; 66 33 3229. UNIT INCHES KIP30. MEMBER PROPERTY AMERICAN31. 1 TO 66 PRI AX 100.32. CONSTANTS33. E 30000. ALL34. SUPPORTS35. 1 19 PINNED36. UNIT FEET KIP37. LOAD 1 JOINT LOADS AT SPECIFIC NODES38. JOINT LOAD:A PLANE TRUSS -- PAGE NO. 2

* FILE TRUSS06.STD39. 11 14 15 31 32 FY -10.40. 10 28 FY -5.41. 4 TO 6 FX 4.42. 2 FX 2.043. 2 10 FX 1.543544. 13 FX 3.087045. 2 10 FY -2.572546. 13 FY -5.14547. PERFORM ANALYSIS








SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = TRUSS-----------------


1 1 11.49 34.29 0.00 0.00 0.00 0.0019 1 -31.67 36.00 0.00 0.00 0.00 0.00




************************************************************* For technical assistance on STAAD.Pro, please visit *

22 — STAAD.Pro

1 Static Trusses

Static Truss 6

* http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Plane Truss: Support Reactions Due to a Joint LoadObjectiveTo find the support reactions due to a joint load in a plane truss.

ReferenceTimoshenko, S., Strength of Materials, Part 1, D. Van Nostrand Co., Inc., 3rd edition, 1956, p.346,problem 3.

ProblemDetermine the horizontal reaction at support 4 of the system.


Comparison

Result Type Theory STAADBasic Solver

STAADAdvanced Solver

R4 8.77 8.77 8.77

Table 1-8: Comparison of Support Reaction, in kips, for verification problemno. 1

1 Static Trusses


STAAD InputSTAAD TRUSS VERIFICATION PROBLEM NO. 1** REFERENCE `STRENGTH OF MATERIALS' PART-1 BY S. TIMOSHENKO* PAGE 346 PROBLEM NO. 3. THE ANSWER IS REACTION = 0.877P.* THEREFORE IF P=10, REACTION = 8.77*UNITS INCH KIPJOINT COORD1 0. 0. ; 2 150. 100. ; 3 150. 50. ; 4 300. 0.MEMBER INCI1 1 2 ; 2 1 3 ; 3 2 3 ; 4 2 4 ; 5 3 4MEMB PROP1 4 PRIS AX 5.0 ; 2 5 PRIS AX 3.0 ; 3 PRIS AX 2CONSTANTE 30000. ALLPOISSON STEEL ALLSUPPORT ; 1 4 PINNEDLOADING 1JOINT LOAD ; 2 FY -10.PERFORM ANALYSISPRINT REACTIONFINISH



1. STAAD TRUSS VERIFICATION PROBLEM NO. 1INPUT FILE: VER01.STD

2. *3. * REFERENCE `STRENGTH OF MATERIALS' PART-1 BY S. TIMOSHENKO4. * PAGE 346 PROBLEM NO. 3. THE ANSWER IS REACTION = 0.877P.5. * THEREFORE IF P=10, REACTION = 8.776. *7. UNITS INCH KIP8. JOINT COORD9. 1 0. 0. ; 2 150. 100. ; 3 150. 50. ; 4 300. 0.10. MEMBER INCI11. 1 1 2 ; 2 1 3 ; 3 2 3 ; 4 2 4 ; 5 3 412. MEMB PROP13. 1 4 PRIS AX 5.0 ; 2 5 PRIS AX 3.0 ; 3 PRIS AX 214. CONSTANT15. E 30000. ALL16. POISSON STEEL ALL17. SUPPORT ; 1 4 PINNED18. LOADING 119. JOINT LOAD ; 2 FY -10.20. PERFORM ANALYSIS


24 — STAAD.Pro

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Static Truss 6




VERIFICATION PROBLEM NO. 1 -- PAGE NO. 2*21. PRINT REACTION

REACTIONVERIFICATION PROBLEM NO. 1 -- PAGE NO. 3

*

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = TRUSS-----------------


1 1 8.77 5.00 0.00 0.00 0.00 0.004 1 -8.77 5.00 0.00 0.00 0.00 0.00



VERIFICATION PROBLEM NO. 1 -- PAGE NO. 4*


Plane Truss Joint DeflectionObjectiveTo find the joint deflection due to joint loads in a plane truss.

ReferenceMcCormack, J. C., “Structural Analysis,” Intext Educational Publishers, 3rd edition, 1975, page 271,example 18 - 2.

ProblemDetermine the vertical deflection at point 5 of plane truss structure shown in the figure.

1 Static Trusses


Figure 1-8: Plane truss model

Given

P = 20 kip

Truss width = 4 spaces at 15 ft = 60 ft

Truss height = 15 ft

AX 1-4 = 1 in2, AX 5-6 = 2 in2, AX 7-8 =1.5 in

2,

AX 9-11B = 3 in2P, AX 12-13 = 4 in

2

E = 30E3 ksi

Comparison



δ5 (in.) 2.63 2.63 2.63

Table 1-9: Comparison of deflection (δ) for verification problem no. 7

STAAD InputSTAAD TRUSS VERIFICATION PROBLEM NO. 7** REFERENCE 'STRUCTURAL ANALYSIS' BY JACK McCORMACK, PAGE* 271 EXAMPLE 18-2. ANSWER - Y-DISP AT JOINT 5 = 2.63 INCH*UNIT FT KIPJOINT COORD1 0 0 0 5 60 0 06 15. 7.5 ; 7 30. 15. ; 8 45. 7.5MEMB INCI1 2 6 ; 2 3 4 ; 3 4 8 ; 4 4 5 ; 5 1 26 2 3 ; 7 3 6 ; 8 3 8 ; 9 3 710 1 6 ; 11 5 8 ; 12 6 7 13UNIT INCHMEMB PROP1 TO 4 PRI AX 1.0

26 — STAAD.Pro

1 Static Trusses

Static Truss 6

5 6 PRIS AX 2.7 8 PRI AX 1.59 10 11 PRI AX 3.12 13 PRI AX 4.CONSTANTE 30E3 ALLPOISSON STEEL ALLSUPPORT1 PINNED ; 3 FIXED BUT FX MZLOAD 1 VERTICAL LOADJOINT LOAD2 4 5 FY -20.0PERFORM ANALYSISPRINT DISPLACEMENTSFINISH



1. STAAD TRUSS VERIFICATION PROBLEM NO. 7INPUT FILE: VER07.STD

2. *3. * REFERENCE 'STRUCTURAL ANALYSIS' BY JACK MCCORMACK, PAGE4. * 271 EXAMPLE 18-2. ANSWER - Y-DISP AT JOINT 5 = 2.63 INCH5. *6. UNIT FT KIP7. JOINT COORD8. 1 0 0 0 5 60 0 09. 6 15. 7.5 ; 7 30. 15. ; 8 45. 7.510. MEMB INCI11. 1 2 6 ; 2 3 4 ; 3 4 8 ; 4 4 5 ; 5 1 212. 6 2 3 ; 7 3 6 ; 8 3 8 ; 9 3 713. 10 1 6 ; 11 5 8 ; 12 6 7 1314. UNIT INCH15. MEMB PROP16. 1 TO 4 PRI AX 1.017. 5 6 PRIS AX 2.18. 7 8 PRI AX 1.519. 9 10 11 PRI AX 3.20. 12 13 PRI AX 4.21. CONSTANT22. E 30E3 ALL23. POISSON STEEL ALL24. SUPPORT25. 1 PINNED ; 3 FIXED BUT FX MZ26. LOAD 1 VERTICAL LOAD27. JOINT LOAD28. 2 4 5 FY -20.029. PERFORM ANALYSISVERIFICATION PROBLEM NO. 7 -- PAGE NO. 2

*

P R O B L E M S T A T I S T I C S

1 Static Trusses


-----------------------------------NUMBER OF JOINTS 8 NUMBER OF MEMBERS 13NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2



30. PRINT DISPLACEMENTSDISPLACE


JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = TRUSS------------------

JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN

1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.000002 1 -0.12000 0.18000 0.00000 0.00000 0.00000 0.000003 1 -0.24000 0.00000 0.00000 0.00000 0.00000 0.000004 1 -0.48000 -0.89516 0.00000 0.00000 0.00000 0.000005 1 -0.72000 -2.63033 0.00000 0.00000 0.00000 0.000006 1 -0.00820 0.24000 0.00000 0.00000 0.00000 0.000007 1 0.29758 -0.12000 0.00000 0.00000 0.00000 0.000008 1 0.06578 -0.83516 0.00000 0.00000 0.00000 0.00000





Deflection and stress of a truss systemObjectiveTo find the joint deflection and member stress due to a joint load in a plane truss.

ReferenceTimoshenko, S., Strength of Materials, Part 1, D. Van Nostrand Co., Inc., 3rd edition, 1956, page 10,problem 2.

ProblemDetermine the vertical deflection at point A and the member stresses

AX = 0.5 in2

E = 30E6 psi

P = 5000 lbf

28 — STAAD.Pro

1 Static Trusses

Static Truss 6

L = 180 in.

angle = 30°

Figure 1-9: Model of two member truss

Comparison



σA (psi) 10,000. 10,000. 10,000.

δA (in) 0.12 0.12 0.12

Table 1-10: Comparison of stress (σ) and Deflection (δ) for verificationproblem 12

STAAD InputSTAAD TRUSS VERIFICATION PROBLEM NO 12** THIS EXAMPLE IS TAKEN FROM 'STRENGTH OF MATERIALS'* (PART 1) BY TIMOSHENKO, PAGE 10 PROB 2.* THE ANSWER IN THE BOOK , DEFLECTION = 0.12 INCH* AND STRESS =10000 PSI*UNIT INCH POUNDJOINT COORD1 0. 0. ; 2 155.88457 -90. ; 3 311.76914 0.MEMB INCI ; 1 1 2 2MEMB PROP1 2 PRIS AX 0.5CONSTANTE 30E6POISSON 0.15 ALLSUPPORT ; 1 3 PINNEDLOAD 1 VERT LOADJOINT LOAD ; 2 FY -5000.PERFORM ANALYSISPRINT DISPLACEMENTSPRINT STRESSESFINISH

1 Static Trusses




1. STAAD TRUSS VERIFICATION PROBLEM NO 12INPUT FILE: VER12.STD

2. *3. * THIS EXAMPLE IS TAKEN FROM 'STRENGTH OF MATERIALS'4. * (PART 1) BY TIMOSHENKO, PAGE 10 PROB 2.5. * THE ANSWER IN THE BOOK , DEFLECTION = 0.12 INCH6. * AND STRESS =10000 PSI7. *8. UNIT INCH POUND9. JOINT COORD10. 1 0. 0. ; 2 155.88457 -90. ; 3 311.76914 0.11. MEMB INCI ; 1 1 2 212. MEMB PROP13. 1 2 PRIS AX 0.514. CONSTANT15. E 30E616. POISSON 0.15 ALL17. SUPPORT ; 1 3 PINNED18. LOAD 1 VERT LOAD19. JOINT LOAD ; 2 FY -5000.20. PERFORM ANALYSIS





VERIFICATION PROBLEM NO 12 -- PAGE NO. 2*21. PRINT DISPLACEMENTS

DISPLACEVERIFICATION PROBLEM NO 12 -- PAGE NO. 3

*



1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.000002 1 0.00000 -0.12000 0.00000 0.00000 0.00000 0.000003 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

************** END OF LATEST ANALYSIS RESULT **************22. PRINT STRESSES

STRESSES

30 — STAAD.Pro

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Static Truss 6

VERIFICATION PROBLEM NO 12 -- PAGE NO. 4*


1 1 .0 10000.0 T 0.0 0.0 10000.0 0.0 0.01.0 10000.0 T 0.0 0.0 10000.0 0.0 0.0

2 1 .0 10000.0 T 0.0 0.0 10000.0 0.0 0.01.0 10000.0 T 0.0 0.0 10000.0 0.0 0.0


*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:31: 6 ****



Static Truss 7ObjectiveTo find member forces due to a thermal load in a plane truss.

ReferenceGere J. M., and Timoshenko, S. P., Mechanics of Materials, 2nd Edition, PWS Engineering, p.21,Problem 2.6 - 23.

ProblemA symmetric, three-bar truss ABCD undergoes a temperature increase of 20°C in the two outerbars and 70°C in the middle bar. Calculate the forces F1 and F2 in the bars.

E = 200 GPa

α = 14( 10)-6 / °C

A = 900 mm2

1 Static Trusses


Figure 1-10: Plane truss subject to differential thermal loading

Comparison


F1 22,100 22,143 0.2% (negligible)

F2 -31,300 -31,315 0.1% (negligible)

Table 1-11: Comparison of member forces, in N, for static truss no. 7

STAAD InputSTAAD TRUSS :A PLANE TRUSS* FILE: TRUSS10.STD* REFERENCE: MECHANICS OF MATERIALS, GERE AND TIMOSHENKO, 2ND EDITION* PWS ENGINEERING, PAGE 121, PROBLEM 2.6-23*UNITS NEWTON METERJOINT COORDINATES1 -2.12132 2.121322 0.0 2.121323 2.12132 2.121324 0.0 0.0*MEMBER INCIDENCES1 1 42 2 43 3 4UNIT NEWTON MMSMEMBER PROPERTIES1 TO 3 PRI AX 900UNIT NEWTON METERCONSTANTSE 200.0E9 ALLALPHA 14.0E-6 ALL

32 — STAAD.Pro

1 Static Trusses

Static Truss 7

*SUPPORTS1 2 3 PINNED*LOADING 1 TEMPERATURE LOADTEMPERATURE LOAD1 3 TEMP 20 8002 TEMP 70PERFORM ANALYSISPRINT MEMBER FORCESFINISH




2. * FILE: TRUSS10.STD3. * REFERENCE: MECHANICS OF MATERIALS, GERE AND TIMOSHENKO, 2ND EDITION4. * PWS ENGINEERING, PAGE 121, PROBLEM 2.6-235. *6. UNITS NEWTON METER7. JOINT COORDINATES8. 1 -2.12132 2.121329. 2 0.0 2.1213210. 3 2.12132 2.1213211. 4 0.0 0.012. *13. MEMBER INCIDENCES14. 1 1 415. 2 2 416. 3 3 417. UNIT NEWTON MMS18. MEMBER PROPERTIES19. 1 TO 3 PRI AX 90020. UNIT NEWTON METER21. CONSTANTS22. E 200.0E9 ALL23. ALPHA 14.0E-6 ALL24. *25. SUPPORTS26. 1 2 3 PINNED27. *28. LOADING 1 TEMPERATURE LOAD29. TEMPERATURE LOAD30. 1 3 TEMP 20 80031. 2 TEMP 7032. PERFORM ANALYSIS



1 Static Trusses






33. PRINT MEMBER FORCESMEMBER FORCES


MEMBER END FORCES STRUCTURE TYPE = TRUSS-----------------ALL UNITS ARE -- NEWT METE (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 -22142.72 0.00 0.00 0.00 0.00 0.004 22142.72 0.00 0.00 0.00 0.00 0.00

2 1 2 31314.54 0.00 0.00 0.00 0.00 0.004 -31314.54 0.00 0.00 0.00 0.00 0.00

3 1 3 -22142.72 0.00 0.00 0.00 0.00 0.004 22142.72 0.00 0.00 0.00 0.00 0.00





34 — STAAD.Pro

1 Static Trusses

Static Truss 7

2Static Beams

Static Beam 1 35

Static Beam 2 39

Static Beam 3 43

Static Beam 4 47

Static Beam 5 53

Static Beam 6 56

Static Beam 7 59

Static Beam 8 62

Static Beam 9 65

Static Beam 11 72

Static Beam 12 75

Static Beam 13 78

Static Beam 15 87

Static Beam 1ObjectiveTo find the deflection and support reactions due to a trapezoidally varying load applied on partof the span of a pinned-fixed beam.

ReferenceHand calculation using the following reference:

Roark's Formulas for Stress and Strain, Warren C. Young, 6th edition, McGraw-Hill, Table 3, Case(2c), p.103

ProblemThe beam in the following geometric, load, and section properties: a = 3 m, b =4.5 m, wa = 4KN/m, wl = 7 KN/m, IZ=5,000 cm4, E = 200 KN/mm2.


Figure 2-1: Simple supported beam with partial, trapezoidal load

Comparison


OA (radians) 0.0020 0.0020 none

RA (kN) 3.2886 3.2886 none

RB (kN) 21.461 21.461 none

MB(kN·m) 25.9605 25.9605 none

Table 2-1: Comparison of results for static beam no. 1

Where

RA = Vertical reaction at A

OA = Rotation at A

RB = Vertical reaction at B

MB = Moment at B

Note: In the STAAD model, two load cases are used. In case 1, the load is applied using the"MEMBER LOAD - TRAP" option. In case 2, the load is applied using a combination of"MEMBER LOAD - UNI" and "MEMBER LOAD - LIN" options. Both cases yield identical results.

Theoretical Solution

( ) ( )R l a l a l a l a= ( − ) 3 + + ( − ) 4 +A

W

l

W W

l8

3 −

40

3a l a

3 3

( ) ( )O l a l a l a l a= ( − ) + 3 − ( − ) 2 + 3A

W

EIl

W W

EIl

−

48

3 −

240

3a l a

( )R l a R= − −B

W W

A

−

2

a l

M R l l a l a= − ( − ) − ( − )B A

W W W

2

2 −

6

2a l a

Where

l = a + b

36 — STAAD.Pro

2 Static Beams

Static Beam 1

STAAD InputSTAAD PLANE REACTIONS AND DISPLACEMENTS OF A PINNED-FIXED BEAM** FILE : BEAM01.STD** REFERENCE : ROARK'S FORMULAS FOR STRESS & STRAIN* WARREN C. YOUNG, 6TH EDITION, MCGRAW-HILL** TABLE 3, CASE (2C), LOAD ON PARTIAL SPAN*UNIT KNS METERJOINT COORD1 0 0 0 ; 2 3 0 0 ; 3 7.5 0 0*MEMBER INCI1 1 2 2*UNIT CMSMEMBER PROP1 2 PRIS AX 50 IZ 5000*UNIT METERCONSTANTE 200E6 ALLPOISS STEEL ALL*SUPPORT1 PINNED3 FIXED*LOAD 1MEMBER LOAD2 TRAP GY -4.0 -7.0*LOAD 2MEMBER LOAD2 UNI GY -42 LIN GY 0 -3*PERFORM ANALYSIS*PRINT JOINT DISP*UNIT NEWTONPRINT SUPP REACFINISH



1. STAAD PLANE REACTIONS AND DISPLACEMENTS OF A PINNED-FIXED BEAM

2 Static Beams


INPUT FILE: BEAM01.STD2. *3. * FILE : BEAM01.STD4. *5. * REFERENCE : ROARK'S FORMULAS FOR STRESS &AMP; STRAIN6. * WARREN C. YOUNG, 6TH EDITION, MCGRAW-HILL7. *8. * TABLE 3, CASE (2C), LOAD ON PARTIAL SPAN9. *10. UNIT KNS METER11. JOINT COORD12. 1 0 0 0 ; 2 3 0 0 ; 3 7.5 0 013. *14. MEMBER INCI15. 1 1 2 216. *17. UNIT CMS18. MEMBER PROP19. 1 2 PRIS AX 50 IZ 500020. *21. UNIT METER22. CONSTANT23. E 200E6 ALL24. POISS STEEL ALL25. *26. SUPPORT27. 1 PINNED28. 3 FIXED29. *30. LOAD 131. MEMBER LOAD32. 2 TRAP GY -4.0 -7.033. *34. LOAD 235. MEMBER LOAD36. 2 UNI GY -437. 2 LIN GY 0 -338. *REACTIONS AND DISPLACEMENTS OF A PINNED-FIXED BEAM -- PAGE NO. 2

*39. PERFORM ANALYSIS





40. *41. PRINT JOINT DISP

JOINT DISPREACTIONS AND DISPLACEMENTS OF A PINNED-FIXED BEAM -- PAGE NO. 3

*

JOINT DISPLACEMENT (CM RADIANS) STRUCTURE TYPE = PLANE------------------


1 1 0.0000 0.0000 0.0000 0.0000 0.0000 -0.00202 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0020

2 1 0.0000 -0.4626 0.0000 0.0000 0.0000 -0.00062 0.0000 -0.4626 0.0000 0.0000 0.0000 -0.0006

38 — STAAD.Pro

2 Static Beams

Static Beam 1

3 1 0.0000 0.0000 0.0000 0.0000 0.0000 0.00002 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000

************** END OF LATEST ANALYSIS RESULT **************42. *43. UNIT NEWTON44. PRINT SUPP REAC

SUPP REACREACTIONS AND DISPLACEMENTS OF A PINNED-FIXED BEAM -- PAGE NO. 4

*

SUPPORT REACTIONS -UNIT NEWT METE STRUCTURE TYPE = PLANE-----------------


1 1 0.00 3288.60 0.00 0.00 0.00 0.002 0.00 3288.60 0.00 0.00 0.00 0.00

3 1 0.00 21461.40 0.00 0.00 0.00 -25960.502 0.00 21461.40 0.00 0.00 0.00 -25960.50



REACTIONS AND DISPLACEMENTS OF A PINNED-FIXED BEAM -- PAGE NO. 5*


Static Beam 2ObjectiveTo find the support reactions due to a temperature loads applied on a fixed-fixed beam.


Matrix Analysis of Framed Structures, 3rd edition, W.Weaver Jr. & J.M.Gere, Van Nostrand Reinhold,Table B2, Appendix B, p.500

ProblemThe beam in the following geometric, load, and section properties: L = 7.5 m, T = 40° F, T2, T1 =50° F, α = 11.7(10)-6/°F, d = 30 cm, IZ = 5,000 cm4, E =200 KN/mm2.

2 Static Beams


Figure 2-2: Fixed support beam with temperature load

Comparison


Horizontal Reaction at Node A (kN) 468 468 none

Moment at Node A (kN·m) 19.5 19.5 none


Note: In the STAAD model, two load cases are used. In case 1, the uniform expansion isapplied. In case 2, the temperature change between top and bottom flanges is applied.

Theoretical SolutionHorizontal reactions due to case 1 loads:

RA = - RB = EAαΔT = [200(10)6]· [50(10)-4]· [11.7(10)-6]· (40) = 468 kN

Moment reactions due to case 2 loads:

⋅

⋅

⋅

( )

M M kN m= − = = = 19.5A B

αEI T

d

∆11.7(10) 200(10) 5, 000(10) 50

0.3

−6 −6 −8

STAAD InputSTAAD PLANE TEMPERATURE LOAD ON A FIXED-FIXED BEAM** FILE : BEAM02.STD** REFERENCE : MATRIX ANALYSIS OF FRAMED STRUCTURES* GERE & WEAVER, 3RD EDITION, VAN NOSTRAND REINHOLD** TABLE B-2, APPENDIX B, PAGE 500*UNIT KNS METER

40 — STAAD.Pro

2 Static Beams

Static Beam 2

JOINT COORD1 0 0 0 ; 2 3 0 0 ; 3 7.5 0 0*MEMBER INCI1 1 2 2*UNIT CMSMEMBER PROP1 2 PRIS AX 50 IZ 5000 YD 30*UNIT METERCONSTANTE 200E6 ALLPOISS STEEL ALLALPHA 11.7E-6 ALL*SUPPORT1 FIXED3 FIXED*LOAD 1TEMPERATURE LOAD1 2 TEMP 40*LOAD 2TEMPERATURE LOAD1 2 TEMP 0 50*PERFORM ANALYSIS*PRINT SUPP REACFINISH



1. STAAD PLANE TEMPERATURE LOAD ON A FIXED-FIXED BEAMINPUT FILE: BEAM02.STD

2. *3. * FILE : BEAM02.STD4. *5. * REFERENCE : MATRIX ANALYSIS OF FRAMED STRUCTURES6. * GERE &AMP; WEAVER, 3RD EDITION, VAN NOSTRAND REINHOLD7. *8. * TABLE B-2, APPENDIX B, PAGE 5009. *10. UNIT KNS METER11. JOINT COORD12. 1 0 0 0 ; 2 3 0 0 ; 3 7.5 0 013. *14. MEMBER INCI15. 1 1 2 216. *

2 Static Beams


17. UNIT CMS18. MEMBER PROP19. 1 2 PRIS AX 50 IZ 5000 YD 3020. *21. UNIT METER22. CONSTANT23. E 200E6 ALL24. POISS STEEL ALL25. ALPHA 11.7E-6 ALL26. *27. SUPPORT28. 1 FIXED29. 3 FIXED30. *31. LOAD 132. TEMPERATURE LOAD33. 1 2 TEMP 4034. *35. LOAD 236. TEMPERATURE LOAD37. 1 2 TEMP 0 5038. *TEMPERATURE LOAD ON A FIXED-FIXED BEAM -- PAGE NO. 2

*39. PERFORM ANALYSIS





40. *41. PRINT SUPP REAC

SUPP REACTEMPERATURE LOAD ON A FIXED-FIXED BEAM -- PAGE NO. 3

*

SUPPORT REACTIONS -UNIT KNS METE STRUCTURE TYPE = PLANE-----------------


1 1 468.00 0.00 0.00 0.00 0.00 0.002 0.00 0.00 0.00 0.00 0.00 -19.50

3 1 -468.00 0.00 0.00 0.00 0.00 0.002 0.00 0.00 0.00 0.00 0.00 19.50



TEMPERATURE LOAD ON A FIXED-FIXED BEAM -- PAGE NO. 4*

************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *

42 — STAAD.Pro

2 Static Beams

Static Beam 2

************************************************************

Static Beam 3ObjectiveTo find the twist at the free end of a hollow tapered shaft of uniform thickness.


Mechanics of Materials, F.P.Beer & E.R.Johnston, 1981, McGraw-Hill Review Problem 3.120, Page149.

ProblemThe beam in the following figure which has the following geometric, load, and section properties:L = 2 m, outside diameter at fixed end = 80 mm, outside diameter at free end = 40 mm, uniformwall thickness of 10 mm, , IZ = 5,000 cm4, E = 200 KN/mm2, T = 2.0 KNm, and Poisson's ratio =0.3.

2 Static Beams


Figure 2-3: Cantilevered member with a tapered, hollow shaft cross section

Comparison


Twist at free end (radians) 0.0751 0.0751 none


Theoretical SolutionAccording to the reference, the twist at the free end is

44 — STAAD.Pro

2 Static Beams

Static Beam 3

( )Φ =A

TL

πGt

C C

C C4

+A B

A B

2 2

where:

CA = centerline radius at free end = 40 mm/2 - 10 mm/2 = 15 mm

CB = center line radius at fixed end = 80 mm/2 - 10 mm/2 = 35 mm

G= = = 76.9E

ν

kN mm

2(1 + )

200 /

2(1 + 0.3)

2

⋅( )Φ = = 0.0751 rad.A

kN m m

π kN mm mm

mm mm

mm mm

2, 000 ×2, 000

4 × 76.9 / × 10

15 + 35

(15 ) (35 )2 2 2

STAAD Input FileSTAAD SPACE TORSION ON CONICAL SHAFT** FILE : BEAM03.STD** REFERENCE : MECHANICS OF MATERIALS, F.P.BEER & E.R.JOHNSTON* 1981, MCGRAW-HILL** REVIEW PROBLEM 3.120, PAGE 149. TWIST AT FREE END SHOULD BE* ABOUT 0.0751 RADIAN*UNIT KNS METERJOINT COORD1 0 0 0 ; 2 0 2 0MEMBER INCI1 1 2UNIT MMSMEMBER PROP1 PRIS ROUND START 80 END 40 THICK 10CONSTE 200 ALLPOISSON 0.3 ALLSUPPORT1 FIXEDUNIT KNS METERLOAD 1JOINT LOAD2 MY 2.0PERFORM ANALYSISPRINT JOINT DISPFINISH



1. STAAD SPACE TORSION ON CONICAL SHAFT

2 Static Beams


INPUT FILE: BEAM03.STD2. *3. * FILE : BEAM03.STD4. *5. * REFERENCE : MECHANICS OF MATERIALS, F.P.BEER &AMP; E.R.JOHNSTON6. * 1981, MCGRAW-HILL7. *8. * REVIEW PROBLEM 3.120, PAGE 149. TWIST AT FREE END SHOULD BE9. * ABOUT 0.0751 RADIAN10. *11. UNIT KNS METER12. JOINT COORD13. 1 0 0 0 ; 2 0 2 014. MEMBER INCI15. 1 1 216. UNIT MMS17. MEMBER PROP18. 1 PRIS ROUND START 80 END 40 THICK 1019. CONST20. E 200 ALL21. POISSON 0.3 ALL22. SUPPORT23. 1 FIXED24. UNIT KNS METER25. LOAD 126. JOINT LOAD27. 2 MY 2.028. PERFORM ANALYSISTORSION ON CONICAL SHAFT -- PAGE NO. 2

*





29. PRINT JOINT DISPJOINT DISP

TORSION ON CONICAL SHAFT -- PAGE NO. 3*

JOINT DISPLACEMENT (CM RADIANS) STRUCTURE TYPE = SPACE------------------


1 1 0.0000 0.0000 0.0000 0.0000 0.0000 0.00002 1 0.0000 0.0000 0.0000 0.0000 0.0751 0.0000



TORSION ON CONICAL SHAFT -- PAGE NO. 4*

************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** *

46 — STAAD.Pro

2 Static Beams

Static Beam 3

* Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Static Beam 4ObjectiveTo find the deflection and member forces due to an applied load on a propped cantilever beamwith a compression only support.


Manual of Steel Construction, Load and Resistance Factor Design, Second Edition, AmericanInstitute of Steel Construction, 1998, pp. 4-194, 4-197.

ProblemA cantilever beam with an end support capable of resisting only a compressive force is analyzedfor two concentrated loads at 0.6xL 1) +0.5 lb (up) and 2) -0.5 lb (down). E = 10(10)6 psi, width =0.6 in, depth = 0.3 in. L = 4 ft.

Note: A dummy member is used to represent a compression only support

Figure 2-4: Cantilevered member with a compression only support

Comparison


Load Case1

Moment at fixed end (in-lb) -14.4 -14.4 none

Shear at fixed end (lb) 0.50 0.50 none

Deflection at load (.in) 0.295 0.295 none


2 Static Beams



Load Case2

Moment at fixed end (in-lb) 4.032 4.03 none

Shear at fixed end (lb) 0.284 0.28 1.4%

Deflection at load (.in) -0.040 -.0401 none

Theoretical SolutionLoad Case 1:

General solution equations found on p.2-121 of the reference.M x b P b x lb x( < ) = − ( − ) = −0.5 (28.8 − )

At the rigid support, M = 14.4 in-lb.

By inspection, fixed end shear is equal to load value = 0.50 lb.

x b x b∆ < = 3 −

Px

EI6

2

( )( )

in in in= 3 28.8 . − 28.8 . = 0.295 .lb in

psi in

0.5 (28.8 .)

6 10, 000, 000 0.00135 .

2

4

Load Case 2:

General solution equations found on p.2-118 of the reference

( )R in in lb= = 19.2 + 2 48 = 0.216 .

Pb alb in

in1

+ 2 ℓ

2 ℓ

0.5 (48 .)

2(48 .)

2

3

2

3

R2 = P - R1 = 0.50lb - 0.216lb = 0.284lb.

Moment at rigid support:M x b R x P x a( < ) = (ℓ − ) − (ℓ − − )1 lb in lb in in= 0.216 (48 − 0) − 0.5 (48 − 0 − 19.2 ) = −4.032 in lb

Deflection at point of load:

x b x a a x∆ < = 3ℓ − 3ℓ − 3 ℓ +

Pax

EI

−

12 ℓ

3 2 2 22

3

( )

( )( )in in in in in in in in= 3(48 .) − 3(48 .) 28.8 − 3(19.2 .) 48 + (19.2 .) 28.8 = −0.040 .

lb in in

psi in in

−0.5 19.2 (28.8 )

12 10, 000, 000 0.00135 . (48 .)

3 2 2 2

3

4 3

STAAD Input FileSTAAD PLANE :A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORTSTART JOB INFORMATIONENGINEER DATE 06-Mar-12END JOB INFORMATION* FILE: BEAM04.STD** STARDYNE VERIFICATION PROBLEM #16********************************************** THE END SUPPORT IS TO BE DEFINED AS A ** COMPRESSION ONLY SUPPORT. A DUMMY MEMBER,** #7, IS SET AS COMPRESSION ONLY TO MODEL ** THIS. *

48 — STAAD.Pro

2 Static Beams

Static Beam 4

*********************************************SET NL 2************************************************ STAAD.Pro Generated Comment *************************************************1 0. 0. 0. 6 48.0 0. 0.***********************************************UNIT INCHES POUNDJOINT COORDINATES1 0 0 0; 2 9.6 0 0; 3 19.2 0 0; 4 28.8 0 0; 5 38.4 0 0; 6 48 0 0;7 48 -4 0;*7 48. -.01 0.************************************************ STAAD.Pro Generated Comment *************************************************1 1 2 6************************************************MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7;MEMBER PROPERTY AMERICAN1 TO 5 PRIS YD 0.3 ZD 0.6*6 PRISMATIC YD 2.6 PRIS YD 40MEMBER COMPRESSION6DEFINE MATERIAL STARTISOTROPIC MATERIAL1E 1e+007POISSON 0.33END DEFINE MATERIALCONSTANTSMATERIAL MATERIAL1 ALLSUPPORTS1 FIXED7 PINNEDLOAD 1 UPWARDJOINT LOAD4 FY 0.5PERFORM ANALYSISPRINT MEMBER FORCES LIST 1 TO 5PRINT JOINT DISPLACEMENTS LIST 1 TO 6PRINT SUPPORT REACTIONCHANGELOAD 2 DOWNWARDJOINT LOAD4 FY -0.5PERFORM ANALYSISPRINT SUPPORT REACTIONPRINT MEMBER FORCES LIST 1 TO 5PRINT JOINT DISPLACEMENTS LIST 1 TO 6FINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:27:41 ** ** USER ID: Bentley Systems, Inc. *

2 Static Beams


****************************************************

1. STAAD PLANE :A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORTINPUT FILE: BEAM04.STD

2. START JOB INFORMATION3. ENGINEER DATE 06-MAR-124. END JOB INFORMATION5. * FILE: BEAM04.STD6. *7. * STARDYNE VERIFICATION PROBLEM #168. *********************************************9. * THE END SUPPORT IS TO BE DEFINED AS A *10. * COMPRESSION ONLY SUPPORT. A DUMMY MEMBER,*11. * #7, IS SET AS COMPRESSION ONLY TO MODEL *12. * THIS. *13. *********************************************14. SET NL 215. ***********************************************16. * STAAD.PRO GENERATED COMMENT *17. ***********************************************18. *1 0. 0. 0. 6 48.0 0. 0.19. ***********************************************20. UNIT INCHES POUND21. JOINT COORDINATES22. 1 0 0 0; 2 9.6 0 0; 3 19.2 0 0; 4 28.8 0 0; 5 38.4 0 0; 6 48 0 023. 7 48 -4 024. *7 48. -.01 0.25. ***********************************************26. * STAAD.PRO GENERATED COMMENT *27. ***********************************************28. *1 1 2 629. ************************************************30. MEMBER INCIDENCES31. 1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 732. MEMBER PROPERTY AMERICAN33. 1 TO 5 PRIS YD 0.3 ZD 0.634. *6 PRISMATIC YD 2.35. 6 PRIS YD 4036. MEMBER COMPRESSION37. 638. DEFINE MATERIAL START:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 2

39. ISOTROPIC MATERIAL140. E 1E+00741. POISSON 0.3342. END DEFINE MATERIAL43. CONSTANTS44. MATERIAL MATERIAL1 ALL45. SUPPORTS46. 1 FIXED47. 7 PINNED48. LOAD 1 UPWARD49. JOINT LOAD50. 4 FY 0.551. PERFORM ANALYSIS





50 — STAAD.Pro

2 Static Beams

Static Beam 4


**START ITERATION NO. 2*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 7 EQN.NO. 16

LOADS APPLIED OR DISTRIBUTED HERE FROM ELEMENTS WILL BE IGNORED.THIS MAY BE DUE TO ALL MEMBERS AT THIS JOINT BEING RELEASED OREFFECTIVELY RELEASED IN THIS DIRECTION.

**NOTE-Tension/Compression converged after 2 iterations, Case= 152. PRINT MEMBER FORCES LIST 1 TO 5

MEMBER FORCES LIST 1:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 3

MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- POUN INCH (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 0.00 -0.50 0.00 0.00 0.00 -14.402 0.00 0.50 0.00 0.00 0.00 9.60

2 1 2 0.00 -0.50 0.00 0.00 0.00 -9.603 0.00 0.50 0.00 0.00 0.00 4.80

3 1 3 0.00 -0.50 0.00 0.00 0.00 -4.804 0.00 0.50 0.00 0.00 0.00 0.00

4 1 4 0.00 0.00 0.00 0.00 0.00 0.005 0.00 0.00 0.00 0.00 0.00 0.00

5 1 5 0.00 0.00 0.00 0.00 0.00 0.006 0.00 0.00 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************53. PRINT JOINT DISPLACEMENTS LIST 1 TO 6

JOINT DISPLACE LIST 1:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 4

JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE------------------


1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.000002 1 0.00000 0.04370 0.00000 0.00000 0.00000 0.008533 1 0.00000 0.15293 0.00000 0.00000 0.00000 0.013654 1 0.00000 0.29494 0.00000 0.00000 0.00000 0.015365 1 0.00000 0.44239 0.00000 0.00000 0.00000 0.015366 1 0.00000 0.58985 0.00000 0.00000 0.00000 0.01536

************** END OF LATEST ANALYSIS RESULT **************54. PRINT SUPPORT REACTION

SUPPORT REACTION:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 5

SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = PLANE-----------------


1 1 0.00 -0.50 0.00 0.00 0.00 -14.407 1 0.00 0.00 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************55. CHANGE56. LOAD 2 DOWNWARD57. JOINT LOAD58. 4 FY -0.559. PERFORM ANALYSIS


**NOTE-Tension/Compression converged after 1 iterations, Case= 2

2 Static Beams


60. PRINT SUPPORT REACTIONSUPPORT REACTION

:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 6



1 2 0.00 0.28 0.00 0.00 0.00 4.037 2 0.00 0.22 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************61. PRINT MEMBER FORCES LIST 1 TO 5

MEMBER FORCES LIST 1:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 7


1 2 1 0.00 0.28 0.00 0.00 0.00 4.032 0.00 -0.28 0.00 0.00 0.00 -1.31

2 2 2 0.00 0.28 0.00 0.00 0.00 1.313 0.00 -0.28 0.00 0.00 0.00 1.42

3 2 3 0.00 0.28 0.00 0.00 0.00 -1.424 0.00 -0.28 0.00 0.00 0.00 4.15

4 2 4 0.00 -0.22 0.00 0.00 0.00 -4.155 0.00 0.22 0.00 0.00 0.00 2.07

5 2 5 0.00 -0.22 0.00 0.00 0.00 -2.076 0.00 0.22 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************62. PRINT JOINT DISPLACEMENTS LIST 1 TO 6

JOINT DISPLACE LIST 1:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 8



1 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.000002 2 0.00000 -0.01066 0.00000 0.00000 0.00000 -0.001903 2 0.00000 -0.03024 0.00000 0.00000 0.00000 -0.001864 2 0.00000 -0.04012 0.00000 0.00000 0.00000 0.000125 2 0.00000 -0.02714 0.00000 0.00000 0.00000 0.002336 2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00307



:A PROPPED CANTILEVER WITH COMPRESSION ONLY SUPPORT -- PAGE NO. 9************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

52 — STAAD.Pro

2 Static Beams

Static Beam 4

Static Beam 5ObjectiveTo find end rotation due to torques on a stepped cantilever shaft.


Gere J. M., and Timoshenko, S. P., Mechanics of Materials, 2nd Edition, PWS Engineering, Page 171,Problem 3.3 - 1.

ProblemA stepped shaft is subjected to torques as shown in the figure. The material has shear modulus ofelasticity G = 80 Gpa. Determine the angle of twist θx in degrees at the free end.

Figure 2-5: Cantilevered member subject to torsional loads

Comparison

Result Theory STAAD.Pro Difference

Angle of twist (rad.) 0.0427 0.0427 none


Theoretical SolutionMoment of Inertia:

I mm= = 4.021(10)p

π mm

1

(80 / 2)

2

6 44

I mm= = 1.272(10)p

π mm

2

(60 / 2)

2

6 44

I mm= = 0.251(10)p

π mm

2

(40 / 2)

2

6 44

2 Static Beams


Angle of twist is given by:

θ = ∑i

L T

GI

i i

p

= + +mm

mm GPa

mm

mm GPa

mm

mm GPa

5, 800N-mm(500 )

4.021(10) 80

2, 800N-mm(500 )

1.272(10) 80

, 800N-mm(500 )

0.251(10) 806 4 6 4 6 4

= 0.0090 + 0.0138 + 0.0199 = 0.0427

which is equal to 2.446°.

STAAD Input FileSTAAD SPACE :A STEPPED CANTILEVER SHAFT* FILE: BEAM05.STD** REFERENCE: MECHANICS OF MATERIALS, GERE AND TIMOSHENKO, 2ND EDITION* PROBLEM 3.3-1 PAGE 171*UNIT KN METERJOINT COORDINATES1 0.0 0.02 0.5 0.03 1.0 0.04 1.5 0.0MEMBER INCIDENCES1 1 2 3UNIT MMSMEMBER PROPERTIES1 TA ST PIPE OD 80 ID 0.02 TA ST PIPE OD 60 ID 0.03 TA ST PIPE OD 40 ID 0.0UNIT METERCONSTANTSE 200.0E6 ALLPOISSONS .25 ALL*SUPPORTS1 FIXEDUNIT MMSLOADING 1 TORSIONAL MOMENTJOINT LOADS2 MX 3000.03 MX 2000.04 MX 800.0PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 4FINISH



1. STAAD SPACE :A STEPPED CANTILEVER SHAFTINPUT FILE: BEAM05.STD

2. * FILE: BEAM05.STD3. *

54 — STAAD.Pro

2 Static Beams

Static Beam 5

4. * REFERENCE: MECHANICS OF MATERIALS, GERE AND TIMOSHENKO, 2ND EDITION5. * PROBLEM 3.3-1 PAGE 1716. *7. UNIT KN METER8. JOINT COORDINATES9. 1 0.0 0.010. 2 0.5 0.011. 3 1.0 0.012. 4 1.5 0.013. MEMBER INCIDENCES14. 1 1 2 315. UNIT MMS16. MEMBER PROPERTIES17. 1 TA ST PIPE OD 80 ID 0.018. 2 TA ST PIPE OD 60 ID 0.019. 3 TA ST PIPE OD 40 ID 0.020. UNIT METER21. CONSTANTS22. E 200.0E6 ALL23. POISSONS .25 ALL24. *25. SUPPORTS26. 1 FIXED27. UNIT MMS28. LOADING 1 TORSIONAL MOMENT29. JOINT LOADS30. 2 MX 3000.031. 3 MX 2000.032. 4 MX 800.033. PERFORM ANALYSIS:A STEPPED CANTILEVER SHAFT -- PAGE NO. 2

* FILE: BEAM05.STD





34. PRINT JOINT DISPLACEMENTS LIST 4JOINT DISPLACE LIST 4

:A STEPPED CANTILEVER SHAFT -- PAGE NO. 3* FILE: BEAM05.STD



4 1 0.0000 0.0000 0.0000 0.0427 0.0000 0.0000************** END OF LATEST ANALYSIS RESULT **************35. FINISH


:A STEPPED CANTILEVER SHAFT -- PAGE NO. 4* FILE: BEAM05.STD

************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support *

2 Static Beams


* ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Static Beam 6ObjectiveTo find deflections, stress and support reactions due to a uniform load on a beam with one endfixed and the other end supported by a roller.


Roark, R.J., and Young, W.C., Formulas for Stress and Strain, 5th Edition, Page 109, Problem 23.

ProblemA horizontal beam of length 100 in, area 4 in2, height 2 in, and moment of inertia 1.3333 in4 issimply supported at one end and fixed at the other end. The beam is subjected to a uniformloading. Determine the deflection δ at x = 42.15 in., the slope θ at end A, the maximum bendingstress σbend in the beam and the support reactions.

E = 30(10)6 psi

Density = 0.2821 lbs/in3

Figure 2-6: Beam A) problem sketch and B) mathematical model

56 — STAAD.Pro

2 Static Beams

Static Beam 6

Comparison


Reaction at Node 1 (lb) 42.31 42.31 none

Reaction at Node 3 (lb) 70.52 70.52 none

Moment at Node 3 (in-lb) 1,410.4 1410.4 none

Bending Stress, σbend at Node 2 (psi) 585.9 585.9 none

Rotation at Node 1 (rad.) -.000588 -.00059 none

Deflection at Node 2 (in.) -0.01528 -0.01528 none


STAAD Input FileSTAAD PLANE :A FIXED-ROLLER BEAM* FILE: BEAM06.STD** REFERENCE: ROARK AND YOUNG, PAGE 109, NO. 23.*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 42.15 0. 0.; 3 100. 0. 0.MEMBER INCIDENCES1 1 2; 2 2 3MEMBER PROPERTY AMERICAN1 2 PRI AX 4. IZ 1.3333 YD 2.CONSTANTSE 30000000. ALLDENSITY 0.282072 ALLSUPPORTS3 FIXED1 PINNEDLOAD 1 SELF WEIGHTSELFWEIGHT Y -1.PERFORM ANALYSISPRINT ANALYSIS RESULTSPRINT MEMBER STRESSES ALLFINISH



1. STAAD PLANE :A FIXED-ROLLER BEAMINPUT FILE: BEAM06.STD

2 Static Beams


2. * FILE: BEAM06.STD3. *4. * REFERENCE: ROARK AND YOUNG, PAGE 109, NO. 23.5. *6. INPUT WIDTH 727. UNIT INCHES POUND8. JOINT COORDINATES9. 1 0. 0. 0.; 2 42.15 0. 0.; 3 100. 0. 0.10. MEMBER INCIDENCES11. 1 1 2; 2 2 312. MEMBER PROPERTY AMERICAN13. 1 2 PRI AX 4. IZ 1.3333 YD 2.14. CONSTANTS15. E 30000000. ALL16. DENSITY 0.282072 ALL17. SUPPORTS18. 3 FIXED19. 1 PINNED20. LOAD 1 SELF WEIGHT21. SELFWEIGHT Y -1.22. PERFORM ANALYSIS


:A FIXED-ROLLER BEAM -- PAGE NO. 2* FILE: BEAM06.STD





23. PRINT ANALYSIS RESULTSANALYSIS RESULTS




1 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.000592 1 0.00000 -0.01528 0.00000 0.00000 0.00000 0.000003 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000:A FIXED-ROLLER BEAM -- PAGE NO. 4

* FILE: BEAM06.STD



3 1 0.00 70.52 0.00 0.00 0.00 -1410.361 1 0.00 42.31 0.00 0.00 0.00 0.00:A FIXED-ROLLER BEAM -- PAGE NO. 5

* FILE: BEAM06.STD


58 — STAAD.Pro

2 Static Beams

Static Beam 6

1 1 1 0.00 42.31 0.00 0.00 0.00 0.002 0.00 5.25 0.00 0.00 0.00 781.13

2 1 2 0.00 -5.25 0.00 0.00 0.00 -781.133 0.00 70.52 0.00 0.00 0.00 -1410.36

************** END OF LATEST ANALYSIS RESULT **************24. PRINT MEMBER STRESSES ALL

MEMBER STRESSES ALL:A FIXED-ROLLER BEAM -- PAGE NO. 6

* FILE: BEAM06.STD


1 1 .0 0.0 0.0 0.0 0.0 15.9 0.01.0 0.0 C 0.0 585.9 585.9 2.0 0.0

2 1 .0 0.0 0.0 585.9 585.9 2.0 0.01.0 0.0 C 0.0 1057.8 1057.8 26.4 0.0





Static Beam 7ObjectiveTo find support reactions due to an axial load applied at two locations on a column with bothends pinned.


Timoshenko, S., Strength of Materials, Part I, D. Van Nostrand Co., Inc., 3rd Edition, 1956. Page 26,Problem 10.

ProblemFind the support reactions at the end joints 1 and 4.

E = 30(10)6 psi

2 Static Beams


Figure 2-7: Column A) problem sketch and B) mathematical model

Comparison


Reaction at Node 1 (lb) 600 600 none

Reaction at Node 4 (lb) 900 900 none


STAAD Input FileSTAAD TRUSS :A PINNED-PINNED COLUMN* FILE: BEAM07.STD** REFERENCE: TIMOSHENKO, STRENGTH OF MATERIALS, PART 1* PROBLEM 10, PAGE 26*INPUT WIDTH 79UNIT INCHES POUNDJOINT COORDINATES1 48.000 72.000 0.0002 48.000 76.000 0.0003 48.000 79.000 0.0004 48.000 82.000 0.000MEMBER INCIDENCES

60 — STAAD.Pro

2 Static Beams

Static Beam 7

1 1 22 2 33 3 4MEMBER PROPERTY AMERICAN1 TO 3 PRISMATIC AX 1.CONSTANTSE 30000000. ALLSUPPORTS1 4 PINNEDLOAD 1 AXIAL LOADJOINT LOAD3 FY -1000.2 FY -500.PERFORM ANALYSISPRINT SUPPORT REACTIONSFINISH



1. STAAD TRUSS :A PINNED-PINNED COLUMNINPUT FILE: BEAM07.STD

2. * FILE: BEAM07.STD3. *4. * REFERENCE: TIMOSHENKO, STRENGTH OF MATERIALS, PART 15. * PROBLEM 10, PAGE 266. *7. INPUT WIDTH 798. UNIT INCHES POUND9. JOINT COORDINATES10. 1 48.000 72.000 0.00011. 2 48.000 76.000 0.00012. 3 48.000 79.000 0.00013. 4 48.000 82.000 0.00014. MEMBER INCIDENCES15. 1 1 216. 2 2 317. 3 3 418. MEMBER PROPERTY AMERICAN19. 1 TO 3 PRISMATIC AX 1.20. CONSTANTS21. E 30000000. ALL22. SUPPORTS23. 1 4 PINNED24. LOAD 1 AXIAL LOAD25. JOINT LOAD26. 3 FY -1000.27. 2 FY -500.28. PERFORM ANALYSIS


2 Static Beams


:A PINNED-PINNED COLUMN -- PAGE NO. 2* FILE: BEAM07.STD






*WARNING- ZERO STIFFNESS IN DIRECTION 1 AT JOINT 3 EQN.NO. 329. PRINT SUPPORT REACTIONS

SUPPORT REACTION:A PINNED-PINNED COLUMN -- PAGE NO. 3

* FILE: BEAM07.STD

SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = TRUSS-----------------


1 1 0.00 600.00 0.00 0.00 0.00 0.004 1 0.00 900.00 0.00 0.00 0.00 0.00



:A PINNED-PINNED COLUMN -- PAGE NO. 4* FILE: BEAM07.STD


Static Beam 8ObjectiveTo find the stress due to an applied moment at the free end of a cantilever beam with invertedtee section.


Crandall, S.H., and Dahl, N.C., An Introduction to the Mechanics of Solids, McGraw-Hill, Inc., 1959,Page 294, Problem 7.2..

62 — STAAD.Pro

2 Static Beams

Static Beam 8

ProblemFind the maximum bending stress in the beam.

E = 30(10)6 psi

b = 1.5 in., h = 8 in., L = 10 in.

M = 1,000,000 in. - lb.


Comparison


Bending stress, σ (psi) 700 700 none


STAAD Input FileSTAAD PLANE :A CANTILEVERED BEAM OF INVERTED TEE SECTION* FILE: BEAM08.STD** REFERENCE: CRANDALL & DAHL, AN INTRODUCTION TO THE MECHANICS* OF SOLIDS, PAGE294, EX. 7.2*INPUT WIDTH 79UNIT INCHES POUNDJOINT COORDINATES1 0.000 0.000 0.0002 10.000 0.000 0.000MEMBER INCIDENCES1 1 2MEMBER PROPERTY AMERICAN1 PRISMATIC YD 20. ZD 9. YB 16. ZB 1.5CONSTANTSE 30000000. ALLBETA 180. ALLSUPPORTS

2 Static Beams


1 FIXEDLOAD 1 CONSTANT MOMENTJOINT LOAD2 MZ 100000.0PERFORM ANALYSISPRINT MEMBER PROPERTIES ALLPRINT MEMBER STRESSES ALLFINISH

STAAD Output***************************************************** ** STAAD.Pro V8i SELECTseries3 ** Version 20.07.08.20 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= MAR 6, 2012 ** Time= 13:37:57 ** ** USER ID: Bentley Systems *****************************************************

1. STAAD PLANE :A CANTILEVERED BEAM OF INVERTED TEE SECTIONINPUT FILE: beam8.STD

2. * FILE: BEAM08.STD3. *4. * REFERENCE: CRANDALL & DAHL, AN INTRODUCTION TO THE MECHANICS5. * OF SOLIDS, PAGE294, EX. 7.26. *7. INPUT WIDTH 798. UNIT INCHES POUND9. JOINT COORDINATES10. 1 0.000 0.000 0.00011. 2 10.000 0.000 0.00012. MEMBER INCIDENCES13. 1 1 214. MEMBER PROPERTY AMERICAN15. 1 PRISMATIC YD 20. ZD 9. YB 16. ZB 1.516. CONSTANTS17. E 30000000. ALL18. BETA 180. ALL19. SUPPORTS20. 1 FIXED21. LOAD 1 CONSTANT MOMENT22. JOINT LOAD23. 2 MZ 100000.024. PERFORM ANALYSIS



NUMBER OF JOINTS/MEMBER+ELEMENTS/SUPPORTS = 2/ 1/ 1SOLVER USED IS THE IN-CORE ADVANCED SOLVER


25. PRINT MEMBER PROPERTIES ALLMEMBER PROPERTIES. UNIT - INCH-----------------

MEMB PROFILE AX/ IZ/ IY/ IX/AY AZ SZ SY

1 PRISMATIC 60.00 2000.00 247.50 154.8930.00 36.00 142.86 55.00

64 — STAAD.Pro

2 Static Beams

Static Beam 8

************ END OF DATA FROM INTERNAL STORAGE ************

26. PRINT MEMBER STRESSES ALLMEMBER STRESSES---------------ALL UNITS ARE POUN/SQ INCH

MEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z

1 1 .0 0.0 0.0 700.0 700.0 0.0 0.01.00 0.0 0.0 700.0 700.0 0.0 0.0

************** END OF LATEST ANALYSIS RESULT **************

27. FINISH

Static Beam 9ObjectiveTo find deflection and stress at the center due to a uniform, static load on a simply supportedbeam on elastic foundation.


Peterson, F.E., Elastic Analysis for Structural Engineering (EASE2), Example Problem Manual,Engineering Analysis Corporation, Berkeley, CA, 1981.

ProblemFind the vertical deflection and bending stress at the center of the beam.Spacing between

E = 30(10)6 psi

b = 1.0 in., h = 7.114 in., L = 240 in.

wu = 43.3 lb/in.

Figure 2-9: One-half beam for mathematical model

Comparison


Bending stress, σ (psi) 18,052 18,053.29 none

Vertical deflection (in.) 1.0453 1.04549 none


2 Static Beams


STAAD Input FileSTAAD SPACE :A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATION* FILE: BEAM09.STD** REFERENCE: PETERSON, EASE2, EXAMPLE PROBLEM MANUAL*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 0. 7.114 0.; 3 0. 0. 6.; 4 0. 7.114 6.; 5 0. 0. 12.6 0. 7.114 12.; 7 0. 0. 18.; 8 0. 7.114 18.; 9 0. 0. 24.10 0. 7.114 24.; 11 0. 0. 30.; 12 0. 7.114 30.; 13 0. 0. 36.14 0. 7.114 36.; 15 0. 0. 42.; 16 0. 7.114 42.; 17 0. 0. 48.18 0. 7.114 48.; 19 0. 0. 54.; 20 0. 7.114 54.; 21 0. 0. 60.22 0. 7.114 60.; 23 0. 0. 66.; 24 0. 7.114 66.; 25 0. 0. 72.26 0. 7.114 72.; 27 0. 0. 78.; 28 0. 7.114 78.; 29 0. 0. 84.30 0. 7.114 84.; 31 0. 0. 90.; 32 0. 7.114 90.; 33 0. 0. 96.34 0. 7.114 96.; 35 0. 0. 102.; 36 0. 7.114 102.; 37 0. 0. 108.38 0. 7.114 108.; 39 0. 0. 114.; 40 0. 7.114 114.; 41 0. 0. 120.42 0. 7.114 120.ELEMENT INCIDENCES1 1 2 4 3; 2 3 4 6 5; 3 5 6 8 7; 4 7 8 10 9; 5 9 10 12 11; 6 11 12 14 137 13 14 16 15; 8 15 16 18 17; 9 17 18 20 19; 10 19 20 22 2111 21 22 24 23; 12 23 24 26 25; 13 25 26 28 27; 14 27 28 30 2915 29 30 32 31; 16 31 32 34 33; 17 33 34 36 35; 18 35 36 38 3719 37 38 40 39; 20 39 40 42 41ELEMENT PROPERTY1 TO 20 TH 1.CONSTANTSE 30000000. ALLSUPPORTS1 FIXED BUT KFY 78.12541 FIXED BUT FZ MX2 FIXED BUT FY3 5 7 9 11 13 15 17 19 21 23 25 27 29 31 33 35 37 -39 FIXED BUT FZ MX KFY 156.25LOAD 1 UNIFORM LOAD OF 43.4 LBS/INJOINT LOAD4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 FY 260.42 42 FY 130.2PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 1 2PRINT ELEMENT JOINT STRESSES LIST 1 2FINISH



1. STAAD SPACE :A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATIONINPUT FILE: BEAM09.STD

2. * FILE: BEAM09.STD

66 — STAAD.Pro

2 Static Beams

Static Beam 9

3. *4. * REFERENCE: PETERSON, EASE2, EXAMPLE PROBLEM MANUAL5. *6. INPUT WIDTH 727. UNIT INCHES POUND8. JOINT COORDINATES9. 1 0. 0. 0.; 2 0. 7.114 0.; 3 0. 0. 6.; 4 0. 7.114 6.; 5 0. 0. 12.10. 6 0. 7.114 12.; 7 0. 0. 18.; 8 0. 7.114 18.; 9 0. 0. 24.11. 10 0. 7.114 24.; 11 0. 0. 30.; 12 0. 7.114 30.; 13 0. 0. 36.12. 14 0. 7.114 36.; 15 0. 0. 42.; 16 0. 7.114 42.; 17 0. 0. 48.13. 18 0. 7.114 48.; 19 0. 0. 54.; 20 0. 7.114 54.; 21 0. 0. 60.14. 22 0. 7.114 60.; 23 0. 0. 66.; 24 0. 7.114 66.; 25 0. 0. 72.15. 26 0. 7.114 72.; 27 0. 0. 78.; 28 0. 7.114 78.; 29 0. 0. 84.16. 30 0. 7.114 84.; 31 0. 0. 90.; 32 0. 7.114 90.; 33 0. 0. 96.17. 34 0. 7.114 96.; 35 0. 0. 102.; 36 0. 7.114 102.; 37 0. 0. 108.18. 38 0. 7.114 108.; 39 0. 0. 114.; 40 0. 7.114 114.; 41 0. 0. 120.19. 42 0. 7.114 120.20. ELEMENT INCIDENCES21. 1 1 2 4 3; 2 3 4 6 5; 3 5 6 8 7; 4 7 8 10 9; 5 9 10 12 11; 6 11 12 14 1322. 7 13 14 16 15; 8 15 16 18 17; 9 17 18 20 19; 10 19 20 22 2123. 11 21 22 24 23; 12 23 24 26 25; 13 25 26 28 27; 14 27 28 30 2924. 15 29 30 32 31; 16 31 32 34 33; 17 33 34 36 35; 18 35 36 38 3725. 19 37 38 40 39; 20 39 40 42 4126. ELEMENT PROPERTY27. 1 TO 20 TH 1.28. CONSTANTS29. E 30000000. ALL30. SUPPORTS31. 1 FIXED BUT KFY 78.12532. 41 FIXED BUT FZ MX33. 2 FIXED BUT FY34. 3 5 7 9 11 13 15 17 19 21 23 25 27 29 31 33 35 37 -35. 39 FIXED BUT FZ MX KFY 156.2536. LOAD 1 UNIFORM LOAD OF 43.4 LBS/IN37. JOINT LOAD38. 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 FY 260.4:A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATION -- PAGE NO. 2

* FILE: BEAM09.STD39. 2 42 FY 130.240. PERFORM ANALYSIS






41. PRINT JOINT DISPLACEMENTS LIST 1 2JOINT DISPLACE LIST 1

:A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATION -- PAGE NO. 3* FILE: BEAM09.STD

JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = SPACE------------------


1 1 0.00000 1.04548 0.00000 0.00000 0.00000 0.000002 1 0.00000 1.04549 0.00000 0.00000 0.00000 0.00000

2 Static Beams


************** END OF LATEST ANALYSIS RESULT **************42. PRINT ELEMENT JOINT STRESSES LIST 1 2

ELEMENT JOINT STRESSES LIST:A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATION -- PAGE NO. 4

* FILE: BEAM09.STDELEMENT STRESSES FORCE,LENGTH UNITS= POUN INCH----------------

STRESS = FORCE/UNIT WIDTH/THICK, MOMENT = FORCE-LENGTH/UNIT WIDTHELEMENT LOAD SQX SQY MX MY MXY

VONT VONB SX SY SXYTRESCAT TRESCAB

1 1 0.00 0.00 0.00 0.00 0.0037.23 37.23 35.30 0.00 -6.8237.85 37.85

TOP : SMAX= 36.57 SMIN= -1.27 TMAX= 18.92 ANGLE=-10.6BOTT: SMAX= 36.57 SMIN= -1.27 TMAX= 18.92 ANGLE=-10.6JOINT 0.00 0.00 0.00 0.00 0.00

1 18070.97 18070.97 35.32 -18053.28 -6.80TOP : SMAX= 35.32 SMIN= -18053.29 TMAX= 9044.30 ANGLE= 0.0BOTT: SMAX= 35.32 SMIN= -18053.29 TMAX= 9044.30 ANGLE= 0.0JOINT 0.00 0.00 0.00 0.00 0.00

2 18035.63 18035.63 35.32 18053.25 -6.84TOP : SMAX= 18053.26 SMIN= 35.31 TMAX= 9008.97 ANGLE=-90.0BOTT: SMAX= 18053.26 SMIN= 35.31 TMAX= 9008.97 ANGLE=-90.0JOINT 0.00 0.00 0.00 0.00 0.00


3 18070.93 18070.93 35.29 -18053.25 -6.80TOP : SMAX= 35.29 SMIN= -18053.26 TMAX= 9044.27 ANGLE= 0.0BOTT: SMAX= 35.29 SMIN= -18053.26 TMAX= 9044.27 ANGLE= 0.02 1 0.00 0.00 0.00 0.00 0.00

50.05 50.05 35.22 0.00 -20.5354.10 54.10

TOP : SMAX= 44.66 SMIN= -9.44 TMAX= 27.05 ANGLE=-24.7BOTT: SMAX= 44.66 SMIN= -9.44 TMAX= 27.05 ANGLE=-24.7JOINT 0.00 0.00 0.00 0.00 0.00

3 18001.81 18001.81 35.27 -17984.11 -20.48TOP : SMAX= 35.29 SMIN= -17984.13 TMAX= 9009.71 ANGLE= -0.1BOTT: SMAX= 35.29 SMIN= -17984.13 TMAX= 9009.71 ANGLE= -0.1JOINT 0.00 0.00 0.00 0.00 0.00



5 18001.68 18001.68 35.18 -17984.03 -20.48TOP : SMAX= 35.20 SMIN= -17984.05 TMAX= 9009.62 ANGLE= -0.1BOTT: SMAX= 35.20 SMIN= -17984.05 TMAX= 9009.62 ANGLE= -0.1:A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATION -- PAGE NO. 5

* FILE: BEAM09.STD**** MAXIMUM STRESSES AMONG SELECTED PLATES AND CASES ****

MAXIMUM MINIMUM MAXIMUM MAXIMUM MAXIMUMPRINCIPAL PRINCIPAL SHEAR VONMISES TRESCASTRESS STRESS STRESS STRESS STRESS

1.805329E+04 -1.805329E+04 9.044303E+03 5.004862E+01 5.409522E+01PLATE NO. 1 1 1 2 2CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************43. FINISH:A SIMPLY SUPPORTED BEAM ON ELASTIC FOUNDATION -- PAGE NO. 6

* FILE: BEAM09.STD

68 — STAAD.Pro

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Static Beam 9



Deflection and stress for a simple beamObjectiveTo find deflections and stress at the center of a locomotive axle.

ReferenceTimoshenko, S., Strength of Materials, Part- 1, D. Van Nostrand Co., 3rd edition, 1956. page 97,problems 1, 2.

ProblemDetermine the maximum stress in a locomotive axle (as shown in the figure) as well as thedeflection at the middle of the axle.

Diameter = 10 in.,

P = 26000 lbf

E = 30E6 psi

L1 = 13.5 in., L2 = 59 in.

Figure 2-10: Locomotive axle model

2 Static Beams


Comparison



σ 3575.* 3575. 3575.

δ 0.01040 0.01037 0.01037

Table 2-10: Comparison of stress (σ), psi, and Deflection (δ), in. forverification model no. 5

* The value is recalculated.

STAAD InputSTAAD PLANE VERIFICATION PROBLEM NO. 5** REFERENCE 'STRENGTH OF MATERIALS' PART-1 BY S. TIMOSHENKO* PAGE 97 PROBLEM NO. 1 AND 2. ANSWERS ARE 3580 FOR MAX. STRESS* AND 0.104 INCH FOR MAX. DEFLECTION.*UNIT INCH POUNDJOINT COORD1 0. 0. ; 2 13.5 0. ; 3 43. 0. ; 4 72.5 0. ; 5 86. 0.MEMB INCI ; 1 1 2 4MEMB PROP ; 1 TO 4 TABLE ST PIPE OD 10. ID 0.CONSTANTE 30E6 ALLPOISSON STEEL ALLSUPPORT ; 2 4 PINNEDLOADING 1JOINT LOAD ; 1 5 FY -26000.PERFORM ANALYSISPRINT MEMBER STRESSESPRINT DISPLACEMENTSFINISH



1. STAAD PLANE VERIFICATION PROBLEM NO. 5INPUT FILE: VER05.STD

2. *3. * REFERENCE 'STRENGTH OF MATERIALS' PART-1 BY S. TIMOSHENKO4. * PAGE 97 PROBLEM NO. 1 AND 2. ANSWERS ARE 3580 FOR MAX. STRESS5. * AND 0.104 INCH FOR MAX. DEFLECTION.6. *7. UNIT INCH POUND8. JOINT COORD9. 1 0. 0. ; 2 13.5 0. ; 3 43. 0. ; 4 72.5 0. ; 5 86. 0.

70 — STAAD.Pro

2 Static Beams

Static Beam 9

10. MEMB INCI ; 1 1 2 411. MEMB PROP ; 1 TO 4 TABLE ST PIPE OD 10. ID 0.12. CONSTANT13. E 30E6 ALL14. POISSON STEEL ALL15. SUPPORT ; 2 4 PINNED16. LOADING 117. JOINT LOAD ; 1 5 FY -26000.18. PERFORM ANALYSIS





VERIFICATION PROBLEM NO. 5 -- PAGE NO. 2*19. PRINT MEMBER STRESSES

MEMBER STRESSESVERIFICATION PROBLEM NO. 5 -- PAGE NO. 3

*


1 1 .0 0.0 0.0 0.0 0.0 441.4 0.01.0 0.0 C 0.0 3575.3 3575.3 441.4 0.0

2 1 .0 0.0 0.0 3575.3 3575.3 0.0 0.01.0 0.0 C 0.0 3575.3 3575.3 0.0 0.0

3 1 .0 0.0 0.0 3575.3 3575.3 0.0 0.01.0 0.0 C 0.0 3575.3 3575.3 0.0 0.0

4 1 .0 0.0 0.0 3575.3 3575.3 441.4 0.01.0 0.0 C 0.0 0.0 0.0 441.4 0.0

************** END OF LATEST ANALYSIS RESULT **************20. PRINT DISPLACEMENTS

DISPLACEVERIFICATION PROBLEM NO. 5 -- PAGE NO. 4

*



1 1 0.00000 -0.01138 0.00000 0.00000 0.00000 0.000862 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.000703 1 0.00000 0.01037 0.00000 0.00000 0.00000 0.000004 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.000705 1 0.00000 -0.01138 0.00000 0.00000 0.00000 -0.00086




************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from *

2 Static Beams


* Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Static Beam 11ObjectiveTo find deflections and stress at center due to a uniform load on overhangs of a simplysupported beam with overhangs at both ends.


Timoshenko, S., Strength of Materials, Part I, D. Van Nostrand Co., 3rd Edition, 1949, Page 98,Problem 4.

ProblemA standard 30” WF beam is supported as shown below and loaded on the overhangs by auniformly distributed load of 10,000 lb per foot. Determine the maximum stress and deflectionat the center of the beam.

Ax = 50.65 in2

E = 30(10)6 psi

Iz = 7,892 in4


Comparison


Bending stress, σ (psi) 11,400 11,404 none

Vertical deflection (in.) 0.182 0.18246 none


STAAD Input FileSTAAD PLANE :A SIMPLY SUPPORTED BEAM WITH OVERHANG AT BOTH ENDS* FILE BEAM11.STD* REFERENCE: TIMOSHENKO, STRENGTH OF MATERIALS PART 1,

72 — STAAD.Pro

2 Static Beams

Static Beam 11

* PAGE 98, PROBLEM 4*INPUT WIDTH 79UNIT FEET POUNDJOINT COORDINATES1 0.000 0.000 0.0002 10.000 0.000 0.0003 20.000 0.000 0.0004 30.000 0.000 0.0005 40.000 0.000 0.000MEMBER INCIDENCES1 1 22 2 33 3 44 4 5UNIT INCHES POUNDMEMBER PROPERTY AMERICAN1 TO 4 PRISMATIC AX 50.65 IZ 7892. YD 30.CONSTANTSE 30000000. ALLSUPPORTS2 PINNED4 FIXED BUT FX MY MZLOAD 1 UNIFORM LOADMEMBER LOAD1 4 UNI GY -833.3333PERFORM ANALYSISPRINT JOINT DISPLACEMENTS ALLPRINT SUPPORT REACTIONSPRINT MEMBER STRESSES ALLFINISH



1. STAAD PLANE :A SIMPLY SUPPORTED BEAM WITH OVERHANG AT BOTH ENDSINPUT FILE: BEAM11.STD

2. * FILE BEAM11.STD3. * REFERENCE: TIMOSHENKO, STRENGTH OF MATERIALS PART 1,4. * PAGE 98, PROBLEM 45. *6. INPUT WIDTH 797. UNIT FEET POUND8. JOINT COORDINATES9. 1 0.000 0.000 0.00010. 2 10.000 0.000 0.00011. 3 20.000 0.000 0.00012. 4 30.000 0.000 0.00013. 5 40.000 0.000 0.00014. MEMBER INCIDENCES15. 1 1 216. 2 2 317. 3 3 4

2 Static Beams


18. 4 4 519. UNIT INCHES POUND20. MEMBER PROPERTY AMERICAN21. 1 TO 4 PRISMATIC AX 50.65 IZ 7892. YD 30.22. CONSTANTS23. E 30000000. ALL24. SUPPORTS25. 2 PINNED26. 4 FIXED BUT FX MY MZ27. LOAD 1 UNIFORM LOAD28. MEMBER LOAD29. 1 4 UNI GY -833.333330. PERFORM ANALYSIS


:A SIMPLY SUPPORTED BEAM WITH OVERHANG AT BOTH ENDS -- PAGE NO. 2* FILE BEAM11.STD





31. PRINT JOINT DISPLACEMENTS ALLJOINT DISPLACE ALL




1 1 0.00000 -0.45616 0.00000 0.00000 0.00000 0.004052 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.003043 1 0.00000 0.18246 0.00000 0.00000 0.00000 0.000004 1 0.00000 0.00000 0.00000 0.00000 0.00000 -0.003045 1 0.00000 -0.45616 0.00000 0.00000 0.00000 -0.00405

************** END OF LATEST ANALYSIS RESULT **************32. PRINT SUPPORT REACTIONS

SUPPORT REACTION:A SIMPLY SUPPORTED BEAM WITH OVERHANG AT BOTH ENDS -- PAGE NO. 4

* FILE BEAM11.STD



2 1 0.00 100000.00 0.00 0.00 0.00 0.004 1 0.00 100000.00 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************33. PRINT MEMBER STRESSES ALL

MEMBER STRESSES ALL:A SIMPLY SUPPORTED BEAM WITH OVERHANG AT BOTH ENDS -- PAGE NO. 5

* FILE BEAM11.STD


74 — STAAD.Pro

2 Static Beams

Static Beam 11

1 1 .0 0.0 0.0 0.0 0.0 0.0 0.01.0 0.0 C 0.0 11404.0 11404.0 2961.5 0.0

2 1 .0 0.0 0.0 11404.0 11404.0 0.0 0.01.0 0.0 C 0.0 11404.0 11404.0 0.0 0.0

3 1 .0 0.0 0.0 11404.0 11404.0 0.0 0.01.0 0.0 C 0.0 11404.0 11404.0 0.0 0.0

4 1 .0 0.0 0.0 11404.0 11404.0 2961.5 0.01.0 0.0 C 0.0 0.0 0.0 0.0 0.0





Static Beam 12ObjectiveTo find end moments due to a uniform load on a beam with nonuniform sections, fixed at bothends.


McCormack, J.C., Structural Analysis, Intext Educational Publishers, 3rd Edition, 1975.

ProblemFind the moment at the supports. Assume for input a unit width for the beam. Depths are asshown.

E = 30(10)6 psi

w = 4 k/ft

d1 = 10 in., d2 = 20 in.

L1 = 12 ft, L2 = 8 ft

2 Static Beams



Comparison


Moment at Node 1 (in-lb) -98.2 -96.93 1.3%

Moment at Node 2 (in-lb) -217.2 -220.43 1.5%


STAAD InputSTAAD PLANE :A FIXED-FIXED BEAM OF UNIFORM AND TAPERED SECTIONS* FILE: BEAM12.STD* REFERENCE: MCCORMAC, J.C., STRUCTURAL ANALYSIS, INTEXT* EDUCATIONAL PUBLISHERS, NEW YORK, 3RD EDITION, 1975*INPUT WIDTH 72*UNIT INCHES KIPJOINT COORDINATES1 0. 0. 0.; 2 144. 0. 0.; 3 240. 0. 0.MEMBER INCIDENCES1 1 2; 2 3 2MEMBER PROPERTY AMERICAN1 PRI YD 10. ZD 1.2 TAP 20. 1. 10. 1. 1. 1. 1.PRINT MEMBER PROPERTIESCONSTANTSE 30000.0 ALLSUPPORTS1 3 FIXEDLOAD 1 UNIFORM LOAD OVER ENTIRE BEAMUNIT FEET

76 — STAAD.Pro

2 Static Beams

Static Beam 12

MEMBER LOAD1 2 UNI GY -4.0PERFORM ANALYSISPRINT SUPPORT REACTIONSFINISH



1. STAAD PLANE :A FIXED-FIXED BEAM OF UNIFORM AND TAPERED SECTIONSINPUT FILE: BEAM12.STD

2. * FILE: BEAM12.STD3. * REFERENCE: MCCORMAC, J.C., STRUCTURAL ANALYSIS, INTEXT4. * EDUCATIONAL PUBLISHERS, NEW YORK, 3RD EDITION, 19755. *6. INPUT WIDTH 727. *8. UNIT INCHES KIP9. JOINT COORDINATES10. 1 0. 0. 0.; 2 144. 0. 0.; 3 240. 0. 0.11. MEMBER INCIDENCES12. 1 1 2; 2 3 213. MEMBER PROPERTY AMERICAN14. 1 PRI YD 10. ZD 1.15. 2 TAP 20. 1. 10. 1. 1. 1. 1.16. PRINT MEMBER PROPERTIES

MEMBER PROPERTI:A FIXED-FIXED BEAM OF UNIFORM AND TAPERED SECTIONS -- PAGE NO. 2

* FILE: BEAM12.STD

MEMBER PROPERTIES. UNIT - INCH-----------------MEMB PROFILE AX/ IZ/ IY/ IX/

AY AZ SZ SY

1 PRISMATIC 10.00 83.33 0.83 3.128.50 8.50 16.67 1.67

2 TAP ERED 15.00 375.00 1.25 5.0015.00 1.33 41.67 2.50

************ END OF DATA FROM INTERNAL STORAGE ************17. CONSTANTS18. E 30000.0 ALL19. SUPPORTS20. 1 3 FIXED21. LOAD 1 UNIFORM LOAD OVER ENTIRE BEAM22. UNIT FEET23. MEMBER LOAD24. 1 2 UNI GY -4.025. PERFORM ANALYSIS


2 Static Beams






:A FIXED-FIXED BEAM OF UNIFORM AND TAPERED SECTIONS -- PAGE NO. 3* FILE: BEAM12.STD26. PRINT SUPPORT REACTIONS

SUPPORT REACTION:A FIXED-FIXED BEAM OF UNIFORM AND TAPERED SECTIONS -- PAGE NO. 4

* FILE: BEAM12.STD

SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = PLANE-----------------


1 1 0.00 33.83 0.00 0.00 0.00 96.933 1 0.00 46.17 0.00 0.00 0.00 -220.43



:A FIXED-FIXED BEAM OF UNIFORM AND TAPERED SECTIONS -- PAGE NO. 5* FILE: BEAM12.STD


Static Beam 13ObjectiveTo find the maximum deflection and principal stress due to a load on the free end of acantilever beam with tapered section.


Harris, C.O., Introduction to Stress Analysis, The Macmillan Co., 1959. Page 114, Problem 61.

ProblemFind the maximum deflection, δ, and the principal normal stress, σ, in the beam.

E = 30(10)6 psi

P = 10 lb

78 — STAAD.Pro

2 Static Beams

Static Beam 13

d = 3 in., b = 0.5 in.

L = 20

Figure 2-13: Beam with a tapering cross section

Comparison


Maximum deflection at free end (in.) -0.04267 -0.04265 none

Principle stress (psi) 1,600 1,600 none


STAAD Input FileSTAAD PLANE :A CANTILEVER BEAM OF TAPERED SECTION* FILE: BEAM13.STD* REFERENCE: HARRIS, C.O., INTRODUCTION TO STRESS ANALYSIS,* THE MACMILLAN CO., NEW YORK, 1956** USING A TAPERED BEAM ELEMENT*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 2. 0. 0.; 3 4.0 0.0 0.; 4 6.0 0.0 0.; 5 8.0 0. 0.6 10.0 0. 0.; 7 12.0 0. 0.; 8 14.0 0. 0.; 9 16. 0. 0.; 10 18. 0. 0.11 20. 0. 0.MEMBER INCIDENCES1 11 10; 2 10 9; 3 9 8; 4 8 7; 5 7 6; 6 6 5; 7 5 4; 8 4 39 3 2; 10 2 1MEMBER PROPERTY AMERICAN1 TAP 3.0 0.5 2.7 0.5 0.01

2 Static Beams


2 TAP 2.7 0.5 2.4 0.5 0.013 TAP 2.4 0.5 2.1 0.5 0.014 TAP 2.1 0.5 1.8 0.5 0.015 TAP 1.8 0.5 1.5 0.5 0.016 TAP 1.5 0.5 1.2 0.5 0.017 TAP 1.2 0.5 0.9 0.5 0.018 TAP 0.9 0.5 0.6 0.5 0.019 TAP 0.6 0.5 0.3 0.5 0.0110 TAP 0.3 0.5 0.03 0.5 0.01CONSTANTSE 30000000. ALLBETA 90. ALLSUPPORTS11 FIXEDLOAD 1 POINT LOAD AT TIPJOINT LOAD1 FY -10.PERFORM ANALYSISPRINT MEMBER PROPERTIES ALLPRINT MEMBER FORCESPRINT SUPPORT REACTIONSSECTION .5 ALLPRINT MEMBER SECTION FORCES ALLPRINT JOINT DISPLACEMENTS LIST 1PRINT MEMBER STRESSES ALLFINISH



1. STAAD PLANE :A CANTILEVER BEAM OF TAPERED SECTIONINPUT FILE: BEAM13.STD

2. * FILE: BEAM13.STD3. * REFERENCE: HARRIS, C.O., INTRODUCTION TO STRESS ANALYSIS,4. * THE MACMILLAN CO., NEW YORK, 19565. *6. * USING A TAPERED BEAM ELEMENT7. *8. INPUT WIDTH 729. UNIT INCHES POUND10. JOINT COORDINATES11. 1 0. 0. 0.; 2 2. 0. 0.; 3 4.0 0.0 0.; 4 6.0 0.0 0.; 5 8.0 0. 0.12. 6 10.0 0. 0.; 7 12.0 0. 0.; 8 14.0 0. 0.; 9 16. 0. 0.; 10 18. 0. 0.13. 11 20. 0. 0.14. MEMBER INCIDENCES15. 1 11 10; 2 10 9; 3 9 8; 4 8 7; 5 7 6; 6 6 5; 7 5 4; 8 4 316. 9 3 2; 10 2 117. MEMBER PROPERTY AMERICAN18. 1 TAP 3.0 0.5 2.7 0.5 0.0119. 2 TAP 2.7 0.5 2.4 0.5 0.0120. 3 TAP 2.4 0.5 2.1 0.5 0.0121. 4 TAP 2.1 0.5 1.8 0.5 0.0122. 5 TAP 1.8 0.5 1.5 0.5 0.01

80 — STAAD.Pro

2 Static Beams

Static Beam 13

23. 6 TAP 1.5 0.5 1.2 0.5 0.0124. 7 TAP 1.2 0.5 0.9 0.5 0.0125. 8 TAP 0.9 0.5 0.6 0.5 0.0126. 9 TAP 0.6 0.5 0.3 0.5 0.0127. 10 TAP 0.3 0.5 0.03 0.5 0.0128. CONSTANTS29. E 30000000. ALL30. BETA 90. ALL31. SUPPORTS32. 11 FIXED33. LOAD 1 POINT LOAD AT TIP34. JOINT LOAD35. 1 FY -10.36. PERFORM ANALYSIS:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 2

* FILE: BEAM13.STD






37. PRINT MEMBER PROPERTIES ALLMEMBER PROPERTI ALL

:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 3* FILE: BEAM13.STD


AY AZ SZ SY

1 TAP ERED 1.42 0.97 0.03 0.121.42 0.01 0.68 0.12

2 TAP ERED 1.28 0.70 0.03 0.111.28 0.01 0.54 0.11

3 TAP ERED 1.12 0.48 0.02 0.091.12 0.01 0.42 0.09

4 TAP ERED 0.97 0.31 0.02 0.080.97 0.01 0.32 0.08

5 TAP ERED 0.82 0.19 0.02 0.070.82 0.01 0.23 0.07

6 TAP ERED 0.68 0.11 0.01 0.060.68 0.01 0.15 0.06

7 TAP ERED 0.52 0.05 0.01 0.040.52 0.01 0.09 0.04

8 TAP ERED 0.38 0.02 0.01 0.030.38 0.01 0.05 0.03

9 TAP ERED 0.23 0.01 0.00 0.020.23 0.01 0.02 0.02

10 TAP ERED 0.08 0.00 0.00 0.010.08 0.01 0.00 0.01

************ END OF DATA FROM INTERNAL STORAGE ************38. PRINT MEMBER FORCES

MEMBER FORCES:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 4

* FILE: BEAM13.STD

2 Static Beams



1 1 11 0.00 0.00 -10.00 0.00 200.00 0.0010 0.00 0.00 10.00 0.00 -180.00 0.00

2 1 10 0.00 0.00 -10.00 0.00 180.00 0.009 0.00 0.00 10.00 0.00 -160.00 0.00

3 1 9 0.00 0.00 -10.00 0.00 160.00 0.008 0.00 0.00 10.00 0.00 -140.00 0.00

4 1 8 0.00 0.00 -10.00 0.00 140.00 0.007 0.00 0.00 10.00 0.00 -120.00 0.00

5 1 7 0.00 0.00 -10.00 0.00 120.00 0.006 0.00 0.00 10.00 0.00 -100.00 0.00

6 1 6 0.00 0.00 -10.00 0.00 100.00 0.005 0.00 0.00 10.00 0.00 -80.00 0.00

7 1 5 0.00 0.00 -10.00 0.00 80.00 0.004 0.00 0.00 10.00 0.00 -60.00 0.00

8 1 4 0.00 0.00 -10.00 0.00 60.00 0.003 0.00 0.00 10.00 0.00 -40.00 0.00

9 1 3 0.00 0.00 -10.00 0.00 40.00 0.002 0.00 0.00 10.00 0.00 -20.00 0.00

10 1 2 0.00 0.00 -10.00 0.00 20.00 0.001 0.00 0.00 10.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************39. PRINT SUPPORT REACTIONS

SUPPORT REACTION:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 5

* FILE: BEAM13.STD



11 1 0.00 10.00 0.00 0.00 0.00 -200.00************** END OF LATEST ANALYSIS RESULT **************40. SECTION .5 ALL41. PRINT MEMBER SECTION FORCES ALL

MEMBER SECTION FORCES ALL:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 6

* FILE: BEAM13.STD

MEMBER FORCES AT INTERMEDIATE SECTIONS--------------------------------------ALL UNITS ARE -- POUN INCH

MEMB LOAD SEC SHEAR-Y SHEAR-Z MOM-Y MOM-Z

1 1 0.50 0.00 -10.00 190.00 0.002 1 0.50 0.00 -10.00 170.00 0.003 1 0.50 0.00 -10.00 150.00 0.004 1 0.50 0.00 -10.00 130.00 0.005 1 0.50 0.00 -10.00 110.00 0.006 1 0.50 0.00 -10.00 90.00 0.007 1 0.50 0.00 -10.00 70.00 0.008 1 0.50 0.00 -10.00 50.00 0.009 1 0.50 0.00 -10.00 30.00 0.0010 1 0.50 0.00 -10.00 10.00 0.00************** END OF LATEST ANALYSIS RESULT **************42. PRINT JOINT DISPLACEMENTS LIST 1

JOINT DISPLACE LIST 1:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 7

* FILE: BEAM13.STD

JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = PLANE

82 — STAAD.Pro

2 Static Beams

Static Beam 13

------------------JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN

1 1 0.00000 -0.04265 0.00000 0.00000 0.00000 0.00419************** END OF LATEST ANALYSIS RESULT **************43. PRINT MEMBER STRESSES ALL

MEMBER STRESSES ALL:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 8

* FILE: BEAM13.STD


1 1 .0 0.0 1600000.0 0.0 1600000.0 0.0 6666.70.50 0.0 1599999.9 0.0 1599999.9 0.0 7017.51.0 0.0 C1599999.8 0.0 1599999.8 0.0 7407.4

2 1 .0 0.0 1599999.8 0.0 1599999.8 0.0 7407.40.50 0.0 1599999.6 0.0 1599999.6 0.0 7843.11.0 0.0 C1599999.9 0.0 1599999.9 0.0 8333.3

3 1 .0 0.0 1599999.9 0.0 1599999.9 0.0 8333.30.50 0.0 150000.0 0.0 150000.0 0.0 8888.91.0 0.0 C 140000.0 0.0 140000.0 0.0 9523.8

4 1 .0 0.0 140000.0 0.0 140000.0 0.0 9523.80.50 0.0 130000.0 0.0 130000.0 0.0 10256.41.0 0.0 C 120000.0 0.0 120000.0 0.0 11111.1

5 1 .0 0.0 120000.0 0.0 120000.0 0.0 11111.10.50 0.0 110000.0 0.0 110000.0 0.0 12121.21.0 0.0 C 100000.0 0.0 100000.0 0.0 13333.3

6 1 .0 0.0 100000.0 0.0 100000.0 0.0 13333.30.50 0.0 90000.0 0.0 90000.0 0.0 14814.81.0 0.0 C 80000.0 0.0 80000.0 0.0 16666.7

7 1 .0 0.0 80000.0 0.0 80000.0 0.0 16666.70.50 0.0 70000.0 0.0 70000.0 0.0 19047.61.0 0.0 C 60000.0 0.0 60000.0 0.0 22222.2

8 1 .0 0.0 60000.0 0.0 60000.0 0.0 22222.20.50 0.0 50000.0 0.0 50000.0 0.0 26666.71.0 0.0 C 40000.0 0.0 40000.0 0.0 33333.3

9 1 .0 0.0 40000.0 0.0 40000.0 0.0 33333.30.50 0.0 30000.0 0.0 30000.0 0.0 44444.41.0 0.0 C 20000.0 0.0 20000.0 0.0 66666.7

10 1 .0 0.0 20000.0 0.0 20000.0 0.0 66666.7:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 9

* FILE: BEAM13.STD


0.50 0.0 10000.0 0.0 10000.0 0.0 121212.11.0 0.0 C 0.0 0.0 0.0 0.0 666666.6



:A CANTILEVER BEAM OF TAPERED SECTION -- PAGE NO. 10* FILE: BEAM13.STD


2 Static Beams



Temperature load in different materialsObjectiveA rigid bar is suspended by two copper wires and one steel wire. Find the stresses in the wiresdue to a rise in temperature.

ReferenceTimoshenko, S., Strength of Materials, Part 1, D. Van Nostrand Co., 3rd edition, 1956, page 30,problem 9.

ProblemAssuming the horizontal member to be very rigid, determine the stresses in the copper andsteel wires if the temperature rise is 10º F.

Esteel = 30E6 psi, Ecopper = 16E6 psi

αsteel = 70E-7 in/in/°F, αcopper = 92E-7 in/in/°F

AX = 0.1 in2

w = 400 lbf/in.

L = 20 in.

d= 5 in.

Tip:When modeling, assume a large moment of inertia for the horizontal rigid member anddistribute of the concentrated load as uniform.

Figure 2-14: Model of a rigid wire suspended by wires

84 — STAAD.Pro

2 Static Beams

Static Beam 13

Comparison



σSteel (psi) 19,695 19,698 19,698

σCopper (psi) 10,152 10,151 10,151

Table 2-14: Comparison of stress (σ) for verification model #11

STAAD InputSTAAD PLANE VERIFICATION PROB NO 11** THIS EXAMPLE IS TAKEN FROM 'STRENGTH OF MATERIALS' BY* TIMOSHENKO (PART 1), PAGE 30, PROB 9.* THE ANSWERS ARE 19700 PSI AND 10200 PSI.*UNIT INCH POUNDJOINT COORD1 0. 20. ; 2 5. 20. ; 3 10. 20.4 0. 0. ; 5 5. 0. ; 6 10. 0.MEMB INCI1 1 4 3 ; 4 4 5 5MEMB PROP1 2 3 PRI AX 0.1 ; 4 5 PRI AX 1. IZ 100.CONSTANT ; E 30E6 MEMB 2 4 5E 16E6 MEMB 1 3POISSON 0.15 ALLALPHA 92E-7 MEMB 1 3 ; ALPHA 70E-7 MEMB 2MEMB TRUSS ; 1 2 3SUPPORT ; 1 2 3 PINNEDLOADING 1 VERT LOAD + TEMP LOADMEMB LOAD ;4 5 UNI Y -400.TEMP LOAD ; 1 2 3 TEMP 10.PERFORM ANALYSISPRINT STRESSESFINISH



1. STAAD PLANE VERIFICATION PROB NO 11INPUT FILE: VER11.STD

2. *3. * THIS EXAMPLE IS TAKEN FROM 'STRENGTH OF MATERIALS' BY4. * TIMOSHENKO (PART 1), PAGE 30, PROB 9.5. * THE ANSWERS ARE 19700 PSI AND 10200 PSI.6. *7. UNIT INCH POUND

2 Static Beams


8. JOINT COORD9. 1 0. 20. ; 2 5. 20. ; 3 10. 20.10. 4 0. 0. ; 5 5. 0. ; 6 10. 0.11. MEMB INCI12. 1 1 4 3 ; 4 4 5 513. MEMB PROP14. 1 2 3 PRI AX 0.1 ; 4 5 PRI AX 1. IZ 100.15. CONSTANT ; E 30E6 MEMB 2 4 516. E 16E6 MEMB 1 317. POISSON 0.15 ALL18. ALPHA 92E-7 MEMB 1 3 ; ALPHA 70E-7 MEMB 219. MEMB TRUSS ; 1 2 320. SUPPORT ; 1 2 3 PINNED21. LOADING 1 VERT LOAD + TEMP LOAD22. MEMB LOAD ;4 5 UNI Y -400.23. TEMP LOAD ; 1 2 3 TEMP 10.24. PERFORM ANALYSIS


NUMBER OF JOINTS 6 NUMBER OF MEMBERS 5NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 3VERIFICATION PROB NO 11 -- PAGE NO. 2

*




*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 2 EQN.NO. 2*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 3 EQN.NO. 3***WARNING - INSTABILITY AT JOINT 5 DIRECTION = FXPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 1.2000001E+04 L-MATRIX DIAG= 0.0000000E+00 EQN NO 7***NOTE - VERY WEAK SPRING ADDED FOR STABILITY25. PRINT STRESSES

STRESSESVERIFICATION PROB NO 11 -- PAGE NO. 3

*


1 1 .0 10150.8 T 0.0 0.0 10150.8 0.0 0.01.0 10150.8 T 0.0 0.0 10150.8 0.0 0.0

2 1 .0 19698.3 T 0.0 0.0 19698.3 0.0 0.01.0 19698.3 T 0.0 0.0 19698.3 0.0 0.0

3 1 .0 10150.8 T 0.0 0.0 10150.8 0.0 0.01.0 10150.8 T 0.0 0.0 10150.8 0.0 0.0

4 1 .0 0.0 0.0 0.0 0.0 1522.6 0.01.0 0.0 C 0.0 3.8 3.8 1477.4 0.0

5 1 .0 0.0 0.0 3.8 3.8 1477.4 0.01.0 0.0 C 0.0 0.0 0.0 1522.6 0.0



VERIFICATION PROB NO 11 -- PAGE NO. 4*

86 — STAAD.Pro

2 Static Beams

Static Beam 13


Static Beam 15ObjectiveTo find the out-of-plane deflection and stress in a Circular cantilever member with aconcentrated load at the free end.


Timoshenko, S., Strength of Materials, Part I, D. Van Nostrand, 3rd Edition., 1955.

ProblemCalculate the displacement at the free end and the bending stress at the fixed end due to aconcentrated load producing out–of–plane bending.

E = 30(10)6 psi

P = 50 lb

r = 100 in.

Figure 2-15: Curved beam

2 Static Beams


Comparison


Maximum deflection at free end (in.) 2.648 2.647 none

Principle stress (psi) 6,366.0 6,638.1 4.3%


STAAD Input FileSTAAD SPACE :A CURVED BEAM* FILE: BEAM15.STD** REFERENCE: TIMOSHENKO, S., "STENGTH OF MATERIALS, PART I, ELEMENTARY* THEORY AND PROBLEMS", 3RD EDITION, D. VAN NOSTRAND CO.,* INC., NEW YORK, 1955.*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 100. 0. 0.; 2 99.619 0. -8.716; 3 98.481 0. -17.3654 96.593 0. -25.882; 5 93.969 0. -34.202; 6 90.631 0. -42.2627 86.603 0. -50.; 8 81.915 0. -57.358; 9 76.604 0. -64.27910 70.711 0. -70.711; 11 64.279 0. -76.604; 12 57.358 0. -81.91513 50. 0. -86.603; 14 42.262 0. -90.631; 15 34.202 0. -93.96916 25.882 0. -96.593; 17 17.365 0. -98.481; 18 8.716 0. -99.61919 0. 0. -100.MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8; 8 8 9; 9 9 10; 10 10 1111 11 12; 12 12 13; 13 13 14; 14 14 15; 15 15 16; 16 16 17; 17 17 1818 18 19MEMBER PROPERTY AMERICAN1 TO 18 PRI YD 2.0 ZD 2.0 AX 3.14 IX 1.57 IY 0.7854 IZ 0.7854CONSTANTSE 30000000. ALLPOISSON 0.3 ALLSUPPORTS19 FIXEDLOAD 1 POINT LOAD APPLIED AT THE FREE ENDJOINT LOAD1 FY 50.PERFORM ANALYSISPRINT MEMBER STRESSES LIST 18PRINT JOINT DISPLACEMENTS LIST 1FINISH



88 — STAAD.Pro

2 Static Beams

Static Beam 15

1. STAAD SPACE :A CURVED BEAMINPUT FILE: BEAM15.STD

2. * FILE: BEAM15.STD3. *4. * REFERENCE: TIMOSHENKO, S., "STENGTH OF MATERIALS, PART I, ELEMENTARY5. * THEORY AND PROBLEMS", 3RD EDITION, D. VAN NOSTRAND CO.,6. * INC., NEW YORK, 1955.7. *8. INPUT WIDTH 729. UNIT INCHES POUND10. JOINT COORDINATES11. 1 100. 0. 0.; 2 99.619 0. -8.716; 3 98.481 0. -17.36512. 4 96.593 0. -25.882; 5 93.969 0. -34.202; 6 90.631 0. -42.26213. 7 86.603 0. -50.; 8 81.915 0. -57.358; 9 76.604 0. -64.27914. 10 70.711 0. -70.711; 11 64.279 0. -76.604; 12 57.358 0. -81.91515. 13 50. 0. -86.603; 14 42.262 0. -90.631; 15 34.202 0. -93.96916. 16 25.882 0. -96.593; 17 17.365 0. -98.481; 18 8.716 0. -99.61917. 19 0. 0. -100.18. MEMBER INCIDENCES19. 1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8; 8 8 9; 9 9 10; 10 10 1120. 11 11 12; 12 12 13; 13 13 14; 14 14 15; 15 15 16; 16 16 17; 17 17 1821. 18 18 1922. MEMBER PROPERTY AMERICAN23. 1 TO 18 PRI YD 2.0 ZD 2.0 AX 3.14 IX 1.57 IY 0.7854 IZ 0.785424. CONSTANTS25. E 30000000. ALL26. POISSON 0.3 ALL27. SUPPORTS28. 19 FIXED29. LOAD 1 POINT LOAD APPLIED AT THE FREE END30. JOINT LOAD31. 1 FY 50.32. PERFORM ANALYSIS:A CURVED BEAM -- PAGE NO. 2

* FILE: BEAM15.STD





33. PRINT MEMBER STRESSES LIST 18MEMBER STRESSES LIST 18

:A CURVED BEAM -- PAGE NO. 3* FILE: BEAM15.STD


18 1 .0 0.0 0.0 6082.7 6082.7 23.9 0.01.0 0.0 C 0.0 6638.1 6638.1 23.9 0.0

************** END OF LATEST ANALYSIS RESULT **************34. PRINT JOINT DISPLACEMENTS LIST 1

JOINT DISPLACE LIST 1:A CURVED BEAM -- PAGE NO. 4

* FILE: BEAM15.STD


2 Static Beams



1 1 0.00000 2.64658 0.00000 -0.02438 0.00000 0.01076************** END OF LATEST ANALYSIS RESULT **************35. FINISH


:A CURVED BEAM -- PAGE NO. 5* FILE: BEAM15.STD


90 — STAAD.Pro

2 Static Beams

Static Beam 15

3Static Frames

Static Frame 1 91

Static Frame 2 95

Static Frame 3 99

Static Frame 4 102

Static Frame 5 108

Static Frame 10 123

Static Frame 11 127

Static Frame 12 131

Static Frame 1ObjectiveTo find section properties, member forces and support reactions for a 1x1 bay plane frame withmembers of rectangular section.


Timoshenko, S., Strength of Materials, Part I, Elementary Theory and Problems, 2nd Edition, VanNostrand Company, 1940, Pages 188-191,

ProblemThe frame supports a concentrated load at middle of the horizontal member. Verify theinternally calculated section properties, support reactions and bending moments at the ends ofthe horizontal member. Cross-section of beam = square 2” x 2”, Cross-section of verticalmembers: b = 2”, h = 4”

P = 1,000 lb

h = 100 in., l = 120 in.

E = 30(10)6 psi


Figure 3-1: Simple supported beam with partial, trapezoidal load

Comparison


Beam Cross Section Ax (in.2) 4.0 4.0 none

Ix (in.4) 2.25 2.25 none

Iy (in.4) 1.333 1.33 none

Iz (in.4) 1.333 1.33 none

Column Cross Section Ax (in.2) 8.0 8.0 none

Ix (in.4) 7.324 7.32 none

Iy (in.4) 2.667 2.67 none

Iz (in.4) 10.667 10.67 none

Ry (lb) 500 500 none

Rx (lb) 27.55 27.54 none

M(in·lb) 2,754.97 2,754.35 none


92 — STAAD.Pro

3 Static Frames

Static Frame 1

STAAD InputSTAAD PLANE :A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTION* FILE: FR2D01.STD** REFERENCE: TIMOSHENKO, S., STRENGTH OF MATERIALS, PART 1,* 2ND EDITION, D. VAN NOSTRAND CO., 1940,* PAGES 188 THRU 191.*UNIT INCH POUNDSJOINT COORDINATES1 0. 0. 0.2 0. 100. 0. 4 120. 100. 0.5 120. 0. 0.MEMBER INCIDENCES1 1 2 4MEMBER PROPERTIES1 4 PRISMATIC YD 2 ZD 22 3 PRISMATIC YD 4 ZD 2PRINT MEMBER PROPERTIESCONSTANTSE 30E6 ALLSUPPORTS1 5 PINNEDLOAD 1 MID SPANJOINT LOAD3 FY 1000.PERFORM ANALYSISPRINT SUPPORT REACTIONSPRINT MEMBER FORCES LIST 2 3FINISH



1. STAAD PLANE :A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTIONINPUT FILE: FR2D01.STD

2. * FILE: FR2D01.STD3. *4. * REFERENCE: TIMOSHENKO, S., STRENGTH OF MATERIALS, PART 1,5. * 2ND EDITION, D. VAN NOSTRAND CO., 1940,6. * PAGES 188 THRU 191.7. *8. UNIT INCH POUNDS9. JOINT COORDINATES10. 1 0. 0. 0.11. 2 0. 100. 0. 4 120. 100. 0.12. 5 120. 0. 0.13. MEMBER INCIDENCES14. 1 1 2 415. MEMBER PROPERTIES16. 1 4 PRISMATIC YD 2 ZD 2

3 Static Frames


17. 2 3 PRISMATIC YD 4 ZD 218. PRINT MEMBER PROPERTIES

MEMBER PROPERTI:A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTION -- PAGE NO. 2

* FILE: FR2D01.STD


AY AZ SZ SY

1 PRISMATIC 4.00 1.33 1.33 2.253.40 3.40 1.33 1.33

2 PRISMATIC 8.00 10.67 2.67 7.326.80 6.80 5.33 2.67

3 PRISMATIC 8.00 10.67 2.67 7.326.80 6.80 5.33 2.67

4 PRISMATIC 4.00 1.33 1.33 2.253.40 3.40 1.33 1.33

************ END OF DATA FROM INTERNAL STORAGE ************19. CONSTANTS20. E 30E6 ALL21. SUPPORTS22. 1 5 PINNED23. LOAD 1 MID SPAN24. JOINT LOAD25. 3 FY 1000.26. PERFORM ANALYSIS






:A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTION -- PAGE NO. 3* FILE: FR2D01.STD27. PRINT SUPPORT REACTIONS

SUPPORT REACTION:A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTION -- PAGE NO. 4

* FILE: FR2D01.STD



1 1 -27.54 -500.00 0.00 0.00 0.00 0.005 1 27.54 -500.00 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************28. PRINT MEMBER FORCES LIST 2 3

MEMBER FORCES LIST 2:A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTION -- PAGE NO. 5

* FILE: FR2D01.STD


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3 Static Frames

Static Frame 1

2 1 2 -27.54 -500.00 0.00 0.00 0.00 -2754.353 27.54 500.00 0.00 0.00 0.00 -27245.65

3 1 3 -27.54 500.00 0.00 0.00 0.00 27245.654 27.54 -500.00 0.00 0.00 0.00 2754.35



:A 1X1 BAY PLANE FRAME OF RECTANGULAR SECTION -- PAGE NO. 6* FILE: FR2D01.STD


Static Frame 2ObjectiveTwo vertical bars are supported by a rigid bar, which is pinned-supported on one end. Findstresses in vertical bars due to a load at the free end of the rigid bar.

ReferenceHigdon, Ohlsen, Stiles, Weese and Riley, Mechanics of Materials, 3rd Edition, John Wiley & Sons,Page 135, Problem 3-37.

ProblemTBars A and B are connected by rigid links to a fixed support at the top and to a rigid bar at thebottom. Determine the axial stresses in bars A and B when the load P is 177.92888 kN applied asshown.

P = 177.93 kN

AA = 1,290.3 mm2

AB = 1,612.9 mm2

EA = 68.95 GPa

EB = 206.84 GPa

Assume the moment of inertia of member CD to be very large.

3 Static Frames


Figure 3-2: Rigid bar hanging from a pair of rods

Comparison


Stress in A (GPa) 0.17237 0.172389 none

Stress in B (GPa) 0.20684 0.206803 none


STAAD InputSTAAD PLANE :TWO VERTICAL MEMBERS SUPPORT A RIGID BAR* FILE: FR2D02.STD** REFERENCE: MECHANICS OF MATERIALS, HIGDON, OHLSEN, STILES, WEESE* AND RILEY, 3RD EDITION, JOHN WILEY & SONS,* PAGE 135, PROBLEM 3-37*UNIT NEWTON METERJOINT COORDINATES1 0 0 02 .127 0 03 .2032 0 04 .2540 0 05 .127 .254 06 .2032 .254 0*MEMBER INCIDENCES1 1 2 3 1 14 2 5 5 1 1MEMBER PROPERTIES1 TO 3 PRI AX 0.032258 IZ 20.82257E-4

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3 Static Frames

Static Frame 2

4 PRI AX 12.9032E-45 PRI AX 16.1290E-4CONSTANTSE 206.8427E9 MEMBERS 1 TO 3 5E 68.94767E9 MEMBER 4MEMBER TRUSS4 5*SUPPORTS4 PINNED5 6 FIXED*LOADING 1 VERTICAL JOINT LOADJOINT LOAD1 FY -177.92888E3*PERFORM ANALYSISUNITS KNSPRINT STRESSES LIST 4 5FINISH



1. STAAD PLANE :TWO VERTICAL MEMBERS SUPPORT A RIGID BARINPUT FILE: FR2D02.STD

2. * FILE: FR2D02.STD3. *4. * REFERENCE: MECHANICS OF MATERIALS, HIGDON, OHLSEN, STILES, WEESE5. * AND RILEY, 3RD EDITION, JOHN WILEY &AMP; SONS,6. * PAGE 135, PROBLEM 3-377. *8. UNIT NEWTON METER9. JOINT COORDINATES10. 1 0 0 011. 2 .127 0 012. 3 .2032 0 013. 4 .2540 0 014. 5 .127 .254 015. 6 .2032 .254 016. *17. MEMBER INCIDENCES18. 1 1 2 3 1 119. 4 2 5 5 1 120. MEMBER PROPERTIES21. 1 TO 3 PRI AX 0.032258 IZ 20.82257E-422. 4 PRI AX 12.9032E-423. 5 PRI AX 16.1290E-424. CONSTANTS25. E 206.8427E9 MEMBERS 1 TO 3 526. E 68.94767E9 MEMBER 427. MEMBER TRUSS28. 4 5

3 Static Frames


29. *30. SUPPORTS31. 4 PINNED32. 5 6 FIXED33. *34. LOADING 1 VERTICAL JOINT LOAD35. JOINT LOAD36. 1 FY -177.92888E337. *38. PERFORM ANALYSIS:TWO VERTICAL MEMBERS SUPPORT A RIGID BAR -- PAGE NO. 2

* FILE: FR2D02.STD






39. UNITS KNS40. PRINT STRESSES LIST 4 5

STRESSES LIST 4 5:TWO VERTICAL MEMBERS SUPPORT A RIGID BAR -- PAGE NO. 3

* FILE: FR2D02.STD

MEMBER STRESSES---------------ALL UNITS ARE KNS /SQ METEMEMB LD SECT AXIAL BEND-Y BEND-Z COMBINED SHEAR-Y SHEAR-Z

4 1 .0 172388.9 T 0.0 0.0 172388.9 0.0 0.01.0 172388.9 T 0.0 0.0 172388.9 0.0 0.0

5 1 .0 206802.9 T 0.0 0.0 206802.9 0.0 0.01.0 206802.9 T 0.0 0.0 206802.9 0.0 0.0



:TWO VERTICAL MEMBERS SUPPORT A RIGID BAR -- PAGE NO. 4* FILE: FR2D02.STD


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Static Frame 2

Static Frame 3ObjectiveFind deflection due to load at the free end of a cantilever plane bent.

ReferenceKinney, J. S., Indeterminate Structural Analysis, Addison - Wesley Publishing Co., 1957, Page 13,Problem 4 - 38.

ProblemFind the vertical, horizontal and rotational deflection components of point A.

E = 30,000 ksi

I = 200 in4

A = 10 in2

Figure 3-3: Bent plate frame

Comparison


Deflection right, δx (in) 0.53 0.53056 none

Deflection down, δy (in) 1.16 -1.17109 <1%

Rotation, θ (rad) 0.0049 0.00488 none

Table 3-3: Comparison of results for static frame no.3

3 Static Frames


STAAD InputSTAAD PLANE :A CANTILEVER PLANE BENT* FILE: FR2D03.STD** REFERENCE: INDETERMINATE STRUCTURAL ANALYSIS, KINNEY, 1957,* ADISON-WESLEY PUBLISHING CO., PAGE 113, PROBLEM 4-38*UNIT KIP FTJOINT COORDINATES1 0 32 0 03 4 04 14 105 22 10*MEMBER INCIDENCES1 1 2 4 1 1UNIT INCHESMEMBER PROPERTIES1 TO 4 PRI AX 10 IZ 200CONSTANTSE 30000 ALL*SUPPORTS5 FIXED*LOADING 1 HORIZONTAL JOINT LOADJOINT LOAD1 FX 3.0*PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 1FINISH



1. STAAD PLANE :A CANTILEVER PLANE BENTINPUT FILE: FR2D03.STD

2. * FILE: FR2D03.STD3. *4. * REFERENCE: INDETERMINATE STRUCTURAL ANALYSIS, KINNEY, 1957,5. * ADISON-WESLEY PUBLISHING CO., PAGE 113, PROBLEM 4-386. *7. UNIT KIP FT8. JOINT COORDINATES9. 1 0 310. 2 0 011. 3 4 012. 4 14 1013. 5 22 10

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3 Static Frames

Static Frame 3

14. *15. MEMBER INCIDENCES16. 1 1 2 4 1 117. UNIT INCHES18. MEMBER PROPERTIES19. 1 TO 4 PRI AX 10 IZ 20020. CONSTANTS21. E 30000 ALL22. *23. SUPPORTS24. 5 FIXED25. *26. LOADING 1 HORIZONTAL JOINT LOAD27. JOINT LOAD28. 1 FX 3.029. *30. PERFORM ANALYSIS


:A CANTILEVER PLANE BENT -- PAGE NO. 2* FILE: FR2D03.STD









1 1 0.53056 -1.17109 0.00000 0.00000 0.00000 0.00488************** END OF LATEST ANALYSIS RESULT **************32. FINISH




3 Static Frames


Static Frame 4ObjectiveTo find the bending moments due to lateral joint loads in a 3x2 bay plane frame.

ReferenceNoris and Wilbur, Elementary Structural Analysis, 2nd Edition, McGraw – Hill, Inc., Page 304.

ProblemDetermine the bending moments in the members of frame.

E = 30,000 ksi

IAE = IEI = 240 3

IBF = IFJ = 480 in4

ICG = IGK = 600 in4

IDH = IHL = 360 in4

IEF = IIJ = 600 in4

IFG = IJK = 1,200 in4

IGH = IKL = 1,800 in4

Figure 3-4: 3x2 bay plane frame

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3 Static Frames

Static Frame 4

Comparison

3 Static Frames



Bending in member (ft-kips) AE 29.6 29.80 <1%

EA 25.1 25.21 none

EI 6.5 6.44 <1%

IE 10.6 10.48 1.1%

BF 60.9 61.03 none

FB 53.7 53.69 none

FJ 18.3 18.50 1.1%

JF 24.8 24.84 none

CG 76.8 76.70 none

GC 68.3 68.24 none

GK 25.2 25.25 none

KG 32.4 32.52 none

DH 45.6 45.45 none

HD 40.1 39.87 <1%

HL 13.5 13.58 <1%

LH 18.5 18.39 <1%

EF 31.6 -31.65 none

FE 29.5 -29.35 <1%

IJ 10.6 -10.48 1.1%

JI 10.0 -9.79 2.1%

FG 42.5 -42.84 <1%

GF 41.3 -41.71 <1%

JK 14.8 -15.05 1.7%

KJ 14.4 -14.71 2.2%

GH 52.2 -51.78 <1%

HG 53.6 -53.45 none

KL 18.0 -17.81 1.1%

LK 18.5 -18.39 <1%


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3 Static Frames

Static Frame 4

STAAD InputSTAAD PLANE :A 3X2 BAY PLANE FRAME* FILE: FR2D04.STD** REFERENCE: ELEMENTARY STRUCTURAL ANALYSIS, NORIS AND WILBUR, 2ND* EDITION. MCGRAW-HILL BOOK COMPANY, PAGE 304, WORKOUT PROBLEM*UNIT KIP FTJOINT COORDINATES1 0 02 0 203 0 354 20 05 20 206 20 357 45 08 45 209 45 3510 75 011 75 2012 75 35*MEMBER INCIDENCES1 1 2 23 4 5 45 7 8 67 10 11 89 2 5 11 1 312 3 6 14 1 3UNIT INCHESMEMBER PROPERTIES1 2 PRI AX 10 IZ 2403 4 PRI AX 15 IZ 4805 6 PRI AX 20 IZ 6007 8 PRI AX 12 IZ 3609 12 PRI AX 20 IZ 60010 13 PRI AX 30 IZ 120011 14 PRI AX 35 IZ 1800CONSTANTSE 30000 ALL*SUPPORTS1 4 7 10 FIXED*LOADING 1 HORIZONTAL JOINT LOADJOINT LOADS2 3 FX 10.0*UNIT FTPERFORM ANALYSISPRINT MEMBER FORCES ALLFINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 *

3 Static Frames


* Time= 12:29: 4 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD PLANE :A 3X2 BAY PLANE FRAMEINPUT FILE: FR2D04.STD

2. * FILE: FR2D04.STD3. *4. * REFERENCE: ELEMENTARY STRUCTURAL ANALYSIS, NORIS AND WILBUR, 2ND5. * EDITION. MCGRAW-HILL BOOK COMPANY, PAGE 304, WORKOUT PROBLEM6. *7. UNIT KIP FT8. JOINT COORDINATES9. 1 0 010. 2 0 2011. 3 0 3512. 4 20 013. 5 20 2014. 6 20 3515. 7 45 016. 8 45 2017. 9 45 3518. 10 75 019. 11 75 2020. 12 75 3521. *22. MEMBER INCIDENCES23. 1 1 2 224. 3 4 5 425. 5 7 8 626. 7 10 11 827. 9 2 5 11 1 328. 12 3 6 14 1 329. UNIT INCHES30. MEMBER PROPERTIES31. 1 2 PRI AX 10 IZ 24032. 3 4 PRI AX 15 IZ 48033. 5 6 PRI AX 20 IZ 60034. 7 8 PRI AX 12 IZ 36035. 9 12 PRI AX 20 IZ 60036. 10 13 PRI AX 30 IZ 120037. 11 14 PRI AX 35 IZ 180038. CONSTANTS:A 3X2 BAY PLANE FRAME -- PAGE NO. 2

* FILE: FR2D04.STD39. E 30000 ALL40. *41. SUPPORTS42. 1 4 7 10 FIXED43. *44. LOADING 1 HORIZONTAL JOINT LOAD45. JOINT LOADS46. 2 3 FX 10.047. *48. UNIT FT49. PERFORM ANALYSIS



NUMBER OF JOINTS 12 NUMBER OF MEMBERS 14NUMBER OF PLATES 0 NUMBER OF SOLIDS 0

106 — STAAD.Pro

3 Static Frames

Static Frame 4

NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 4



50. PRINT MEMBER FORCES ALLMEMBER FORCES ALL

:A 3X2 BAY PLANE FRAME -- PAGE NO. 3* FILE: FR2D04.STD

MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- KIP FT (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 -4.06 2.75 0.00 0.00 0.00 29.802 4.06 -2.75 0.00 0.00 0.00 25.21

2 1 2 -1.01 1.13 0.00 0.00 0.00 6.443 1.01 -1.13 0.00 0.00 0.00 10.48

3 1 4 -0.51 5.74 0.00 0.00 0.00 61.035 0.51 -5.74 0.00 0.00 0.00 53.69

4 1 5 -0.18 2.89 0.00 0.00 0.00 18.506 0.18 -2.89 0.00 0.00 0.00 24.84

5 1 7 -0.14 7.25 0.00 0.00 0.00 76.708 0.14 -7.25 0.00 0.00 0.00 68.24

6 1 8 -0.02 3.85 0.00 0.00 0.00 25.259 0.02 -3.85 0.00 0.00 0.00 32.52

7 1 10 4.71 4.27 0.00 0.00 0.00 45.4511 -4.71 -4.27 0.00 0.00 0.00 39.87

8 1 11 1.21 2.13 0.00 0.00 0.00 13.5812 -1.21 -2.13 0.00 0.00 0.00 18.39

9 1 2 8.38 -3.05 0.00 0.00 0.00 -31.655 -8.38 3.05 0.00 0.00 0.00 -29.35

10 1 5 5.53 -3.38 0.00 0.00 0.00 -42.848 -5.53 3.38 0.00 0.00 0.00 -41.71

11 1 8 2.14 -3.51 0.00 0.00 0.00 -51.7811 -2.14 3.51 0.00 0.00 0.00 -53.45

12 1 3 8.87 -1.01 0.00 0.00 0.00 -10.486 -8.87 1.01 0.00 0.00 0.00 -9.79

13 1 6 5.98 -1.19 0.00 0.00 0.00 -15.059 -5.98 1.19 0.00 0.00 0.00 -14.71

14 1 9 2.13 -1.21 0.00 0.00 0.00 -17.8112 -2.13 1.21 0.00 0.00 0.00 -18.39

:A 3X2 BAY PLANE FRAME -- PAGE NO. 4* FILE: FR2D04.STD************** END OF LATEST ANALYSIS RESULT **************51. FINISH



3 Static Frames


Static Frame 5ObjectiveTo find member forces and moments due to a temperature load on a Zee shaped plane bent.

ReferenceSeeley, F.B., and Smith, J.O., Advanced Mechanics of Materials, 2nd Edition, John Wiley and Sons,1955, Pages 494-497.

ProblemCalculate reactions and maximum moments in the structure due to a temperature increase of430 ºF. Do not consider shear deformation.

E = 26,400 ksi

α = 7.26744 x 10-6 in/in/ºF

OD = 12 in

ID = 10.255 in

Figure 3-5: Frame subject to temperature change

Comparison


Horizontal reaction (lbs) 8,980 8,949.43 none


108 — STAAD.Pro

3 Static Frames

Static Frame 5


Vertical reaction (lbs) 7,756 7,729.42 none

Moment at supports (in-lb) 783,750 781,127.75 none

Moment at node 2 (in-lb) 1,077,656 1,073,932.00 none

STAAD InputSTAAD PLANE :A FIXED-FIXED ZEE SHAPED PLANE BENT* FILE: FR2D05.STD** REFERENCE: SEELEY* OF MATERIALS* PAGES 494-497*SET SHEARUNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.2 240. 0. 0.3 240. 240. 0.4 480. 240. 0.MEMBER INCIDENCES1 1 2 3MEMBER PROPERTIES1 TO 3 TA ST PIPE OD 12. ID 10.255PRINT MEMBER PROPERTIESCONSTANTSE 26.4E6 ALLALPHA 7.26744E-6* DONOT PROVIDE POISSON'S RATIO, NO SHEAR DEFORMATION CONSIDEREDSUPPORT1 4 FIXEDLOAD 1TEMPERATURE LOAD1 TO 3 TEMP 430.PERFORM ANALYSISPRINT SUPPORT REACTIONSPRINT MEMBER FORCES LIST 1FINISH



1. STAAD PLANE :A FIXED-FIXED ZEE SHAPED PLANE BENTINPUT FILE: FR2D05.STD

2. * FILE: FR2D05.STD3. *4. * REFERENCE: SEELEY

3 Static Frames


5. * OF MATERIALS6. * PAGES 494-4977. *8. SET SHEAR9. UNIT INCHES POUND10. JOINT COORDINATES11. 1 0. 0. 0.12. 2 240. 0. 0.13. 3 240. 240. 0.14. 4 480. 240. 0.15. MEMBER INCIDENCES16. 1 1 2 317. MEMBER PROPERTIES18. 1 TO 3 TA ST PIPE OD 12. ID 10.25519. PRINT MEMBER PROPERTIES

MEMBER PROPERTI:A FIXED-FIXED ZEE SHAPED PLANE BENT -- PAGE NO. 2

* FILE: FR2D05.STD


AY AZ SZ SY

1 ST PIP E 30.50 474.99 474.99 949.9716.72 16.72 79.16 79.16

2 ST PIP E 30.50 474.99 474.99 949.9716.72 16.72 79.16 79.16

3 ST PIP E 30.50 474.99 474.99 949.9716.72 16.72 79.16 79.16

************ END OF DATA FROM INTERNAL STORAGE ************20. CONSTANTS21. E 26.4E6 ALL22. ALPHA 7.26744E-623. * DONOT PROVIDE POISSON'S RATIO, NO SHEAR DEFORMATION CONSIDERED24. SUPPORT25. 1 4 FIXED26. LOAD 127. TEMPERATURE LOAD28. 1 TO 3 TEMP 430.29. PERFORM ANALYSIS






:A FIXED-FIXED ZEE SHAPED PLANE BENT -- PAGE NO. 3* FILE: FR2D05.STD30. PRINT SUPPORT REACTIONS

SUPPORT REACTION:A FIXED-FIXED ZEE SHAPED PLANE BENT -- PAGE NO. 4

* FILE: FR2D05.STD



110 — STAAD.Pro

3 Static Frames

Static Frame 5

1 1 8949.43 7729.42 0.00 0.00 0.00 781127.754 1 -8949.43 -7729.42 0.00 0.00 0.00 781127.75

************** END OF LATEST ANALYSIS RESULT **************31. PRINT MEMBER FORCES LIST 1

MEMBER FORCES LIST 1:A FIXED-FIXED ZEE SHAPED PLANE BENT -- PAGE NO. 5

* FILE: FR2D05.STD


1 1 1 8949.43 7729.42 0.00 0.00 0.00 781127.752 -8949.43 -7729.42 0.00 0.00 0.00 1073932.00



:A FIXED-FIXED ZEE SHAPED PLANE BENT -- PAGE NO. 6* FILE: FR2D05.STD


Support Reactions for a Simple FrameObjectiveTo find support reactions due to a load at the free end of a cantilever bent plate with anintermediate support.

ReferenceTimoshenko, S., Strength of Materials, Part 1, D. Van Nostrand Co., Inc., 3rd edition, 1956, page346, problem 2.

ProblemDetermine the reaction of the system as shown in the figure.

P = 1 kip

L = 10 in

3 Static Frames


Figure 3-6: Cantilever model

Comparison



Rx 1.5 1.5 1.5

Table 3-6: Comparison of reaction, in kips, for verification problem no. 4

STAAD InputSTAAD PLANE VERIFICATION PROBLEM NO. 4** REFERENCE 'STRENGTH OF MATERIALS' PART-1 BY S. TIMOSHENKO* PAGE 346 PROBLEM NO. 2. THE ANSWER IN THE BOOK AFTER* RECALCULATION = 1.5*UNIT INCH KIPJOINT COORD1 0. 0. ; 2 0. 10. ; 3 0. 20. ; 4 10. 20.MEMB INCI1 1 2 3MEMB PROP ; 1 2 3 PRIS AX 10. IZ 100.CONSTANTE 3000. ALLPOISSON CONCRETE ALLSUPPORT1 FIXED ; 2 FIXED BUT FY MZLOADING 1JOINT LOAD ; 4 FY -1.PERFORM ANALYSPRINT REACTIONFINI


112 — STAAD.Pro

3 Static Frames

Static Frame 5



2. *3. * REFERENCE 'STRENGTH OF MATERIALS' PART-1 BY S. TIMOSHENKO4. * PAGE 346 PROBLEM NO. 2. THE ANSWER IN THE BOOK AFTER5. * RECALCULATION = 1.56. *7. UNIT INCH KIP8. JOINT COORD9. 1 0. 0. ; 2 0. 10. ; 3 0. 20. ; 4 10. 20.10. MEMB INCI11. 1 1 2 312. MEMB PROP ; 1 2 3 PRIS AX 10. IZ 100.13. CONSTANT14. E 3000. ALL15. POISSON CONCRETE ALL16. SUPPORT17. 1 FIXED ; 2 FIXED BUT FY MZ18. LOADING 119. JOINT LOAD ; 4 FY -1.20. PERFORM ANALYS





VERIFICATION PROBLEM NO. 4 -- PAGE NO. 2*21. PRINT REACTION

REACTIONVERIFICATION PROBLEM NO. 4 -- PAGE NO. 3

*

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = PLANE-----------------


1 1 1.50 1.00 0.00 0.00 0.00 -5.002 1 -1.50 0.00 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************22. FINI




3 Static Frames



Plane Frame with no SideswayObjectiveTo find the maximum moment due to a uniform load on the horizontal member in a 1x1 bayplane frame.

ReferenceMcCormack, J. C., Structural Analysis, Intext Educational Publishers, 3rd edition, 1975, page 383,example 22 - 5.

ProblemDetermine the maximum moment in the frame.

E and I same for all members.

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3 Static Frames

Static Frame 5

Figure 3-7: 1x1 bay plane frame

Comparison



MMax 44.40 44.44 44.44

Table 3-7: Comparison of moment, in kip-ft, for verification problem no. 6

STAAD InputSTAAD PLANE VERIFICATION PROBLEM NO. 6** REFERENCE 'STRUCTURAL ANALYSIS' BY JACK C. McCORMACK,* PAGE 383 EXAMPLE 22-5, PLANE FRAME WITH NO SIDESWAY* ANSWER - MAX BENDING = 44.4 FT-KIP*UNIT FT KIPJOINT COORD1 0. 0. ; 2 0. 20. ; 3 20. 20. ; 4 20. 0.MEMB INCI ; 1 1 2 3MEMB PROP ; 1 2 3 PRIS AX 1. IZ 0.05CONSTANTE 4132E3 ALLPOISSON STEEL ALL

3 Static Frames


SUPPORT ; 1 4 FIXEDLOADING 1 ; MEMB LOAD ; 2 UNI Y -2.0PERFORM ANALPRINT FORCESFINISH




2. *3. * REFERENCE 'STRUCTURAL ANALYSIS' BY JACK C. MCCORMACK,4. * PAGE 383 EXAMPLE 22-5, PLANE FRAME WITH NO SIDESWAY5. * ANSWER - MAX BENDING = 44.4 FT-KIP6. *7. UNIT FT KIP8. JOINT COORD9. 1 0. 0. ; 2 0. 20. ; 3 20. 20. ; 4 20. 0.10. MEMB INCI ; 1 1 2 311. MEMB PROP ; 1 2 3 PRIS AX 1. IZ 0.0512. CONSTANT13. E 4132E3 ALL14. POISSON STEEL ALL15. SUPPORT ; 1 4 FIXED16. LOADING 1 ; MEMB LOAD ; 2 UNI Y -2.017. PERFORM ANAL





18. PRINT FORCESVERIFICATION PROBLEM NO. 6 -- PAGE NO. 2

*FORCES


MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- KIP FEET (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 20.00 -3.33 0.00 0.00 0.00 -22.212 -20.00 3.33 0.00 0.00 0.00 -44.44

2 1 2 3.33 20.00 0.00 0.00 0.00 44.44

116 — STAAD.Pro

3 Static Frames

Static Frame 5

3 -3.33 20.00 0.00 0.00 0.00 -44.443 1 3 20.00 3.33 0.00 0.00 0.00 44.44

4 -20.00 -3.33 0.00 0.00 0.00 22.21************** END OF LATEST ANALYSIS RESULT **************19. FINISH




Unequal Plane frame with SideswayObjectiveTo find the maximum moment due to a concentrated load on the horizontal member in a 1x1 bayplane frame.

ReferenceMcCormack, J. C., Structural Analysis, Intext Educational Publishers, 3rd edition, 1975, page 385,problem 22 - 6.

ProblemDetermine the maximum moment in the structure.

P = 30 kip

H1 = 20 ft, H3 = 30 ft

L = 30 ft, with P occurring at 10 ft from Leg #1

E and I same for all members

3 Static Frames


Figure 3-8: Unequal leg bay model

Comparison



MMax 69.40 69.44 69.44

Table 3-8: Comparison of max. moment, in kip-ft, for verification model no. 8

STAAD InputSTAAD PLANE VERIFICATION PROBLEM NO. 8** PLANE FRAME WITH SIDESWAY. REFERENCE 'STRUCTURAL ANALYSIS'* BY JACK McCORMACK. PAGE 385 PROB 22-6.* ANSWER - MAX BENDING IN MEMB 1 = 69.4 KIP-FT*UNIT FT KIPJOINT COORD1 0. 10. ; 2 0 30 ; 3 30 30 ; 4 30 0MEMB INCI1 1 2 3MEMB PROP AMERICAN1 2 3 TAB ST W12X26CONSTANTE 4176E3POISSON STEEL ALLSUPPORT ; 1 4 FIXEDLOAD 1 VERTICAL LOADMEMBER LOAD2 CON Y -30. 10.PERFORM ANALYSISPRINT FORCESFINISH


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3 Static Frames

Static Frame 5



2. *3. * PLANE FRAME WITH SIDESWAY. REFERENCE 'STRUCTURAL ANALYSIS'4. * BY JACK MCCORMACK. PAGE 385 PROB 22-6.5. * ANSWER - MAX BENDING IN MEMB 1 = 69.4 KIP-FT6. *7. UNIT FT KIP8. JOINT COORD9. 1 0. 10. ; 2 0 30 ; 3 30 30 ; 4 30 010. MEMB INCI11. 1 1 2 312. MEMB PROP AMERICAN13. 1 2 3 TAB ST W12X2614. CONSTANT15. E 4176E316. POISSON STEEL ALL17. SUPPORT ; 1 4 FIXED18. LOAD 1 VERTICAL LOAD19. MEMBER LOAD20. 2 CON Y -30. 10.21. PERFORM ANALYSIS




TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 6VERIFICATION PROBLEM NO. 8 -- PAGE NO. 2

*

22. PRINT FORCESFORCES


MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- KIP FEET (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 20.09 -3.74 0.00 0.00 0.00 -5.342 -20.09 3.74 0.00 0.00 0.00 -69.44

2 1 2 3.74 20.09 0.00 0.00 0.00 69.443 -3.74 9.91 0.00 0.00 0.00 -66.66

3 1 3 9.91 3.74 0.00 0.00 0.00 66.664 -9.91 -3.74 0.00 0.00 0.00 45.51


*********** END OF THE STAAD.Pro RUN ***********

3 Static Frames


**** DATE= DEC 13,2013 TIME= 12:30:54 ****VERIFICATION PROBLEM NO. 8 -- PAGE NO. 4

************************************************************** For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Multiple level plane frame with horizontal loadsObjectiveTo find the maximum moment due to lateral joint loads in a 1x2 bay plane frame.

ReferenceMcCormack, J. C., Structural Analysis, Intext Educational Publishers, 3rd edition, 1975, page 388,example 22 - 7.

ProblemDetermine the maximum moment in the frame.

L = 20 ft

H3 = 20 kip, H5 = 10 kip

E and I same for all members.

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3 Static Frames

Static Frame 5

Figure 3-9: Two story frame model

Comparison



MMax 176.40 178.01 178.01

Table 3-9: Comparison of max. moment, in kip-ft, for verification problem no.9

STAAD InputSTAAD PLANE VERIFICATION PROB NO. 9** MULTIPLE LEVEL PLANE FRAME WITH HORIZONTAL LOAD.* REFERENCE 'STRUCTURAL ANALYSIS' BY JACK McCORMACK,* PAGE 388, PROB 22-7. ANSWER - MAX MOM IN MEMB 1 = 176.4 K-F*UNIT FT KIPJOINT COORD1 0 0 0 5 0 40 0 2 ; 2 20 0 0 6 20 40 0 2MEMB INCI1 1 3 2 ; 3 3 5 4 ; 5 3 4 ; 6 5 6MEMB PROP1 TO 6 PRI AX .2 IZ .1CONSTANTE 4176E3POISSON STEEL ALL

3 Static Frames


SUPPORT ; 1 2 FIXEDLOAD 1 HORIZONTAL LOADJOINT LOAD3 FX 20 ; 5 FX 10PERFORM ANALYSPRINT FORCESFINISH



1. STAAD PLANE VERIFICATION PROB NO. 9INPUT FILE: VER09.STD

2. *3. * MULTIPLE LEVEL PLANE FRAME WITH HORIZONTAL LOAD.4. * REFERENCE 'STRUCTURAL ANALYSIS' BY JACK MCCORMACK,5. * PAGE 388, PROB 22-7. ANSWER - MAX MOM IN MEMB 1 = 176.4 K-F6. *7. UNIT FT KIP8. JOINT COORD9. 1 0 0 0 5 0 40 0 2 ; 2 20 0 0 6 20 40 0 210. MEMB INCI11. 1 1 3 2 ; 3 3 5 4 ; 5 3 4 ; 6 5 612. MEMB PROP13. 1 TO 6 PRI AX .2 IZ .114. CONSTANT15. E 4176E316. POISSON STEEL ALL17. SUPPORT ; 1 2 FIXED18. LOAD 1 HORIZONTAL LOAD19. JOINT LOAD20. 3 FX 20 ; 5 FX 1021. PERFORM ANALYS




TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 12VERIFICATION PROB NO. 9 -- PAGE NO. 2

*

22. PRINT FORCESFORCES

VERIFICATION PROB NO. 9 -- PAGE NO. 3*

MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------

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3 Static Frames

Static Frame 5

ALL UNITS ARE -- KIP FEET (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 -22.26 15.06 0.00 0.00 0.00 178.013 22.26 -15.06 0.00 0.00 0.00 123.16

2 1 2 22.26 14.94 0.00 0.00 0.00 176.734 -22.26 -14.94 0.00 0.00 0.00 122.10

3 1 3 -6.51 4.97 0.00 0.00 0.00 34.495 6.51 -4.97 0.00 0.00 0.00 64.93

4 1 4 6.51 5.03 0.00 0.00 0.00 35.346 -6.51 -5.03 0.00 0.00 0.00 65.24

5 1 3 9.91 -15.75 0.00 0.00 0.00 -157.654 -9.91 15.75 0.00 0.00 0.00 -157.44

6 1 5 5.03 -6.51 0.00 0.00 0.00 -64.936 -5.03 6.51 0.00 0.00 0.00 -65.24





Static Frame 10ObjectiveTo find the displacements at the nodes of a frame due to movements of supports.

ReferenceC.K. Wang, Intermediate Structural Analysis, International Student Edition, 1983, McGraw Hill,Section 2.11, p47.

ProblemCalculate the deflections at node B and support D.

3 Static Frames


Figure 3-10: Frame subject to imposed displacements

Load Cases:

1. Vertical displacement of 1 cm at Node A

2. Vertical displacement of 1 cm at Node B

Comparison


LoadCase 1

Horizontal displacement atnode B (cm)

1.25 -1.25 none


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Static Frame 10


Rotation at node B 0.001667 0.0017 none

Horizontal displacement atnode D (cm)

0.4167 -0.4167 none

LoadCase 2

Horizontal displacement atnode B (cm)

1.25 1.25 none

Rotation at node B 0.001667 0.0017 none

Horizontal displacement atnode D (cm)

0.4167 0.4167 none

STAAD InputSTAAD PLANE DEFLECTIONS DUE TO MOVEMENT OF SUPPORTS** FILE: FR2D10.STD** REFERENCE: INTERMEDIATE STRUCTURAL ANALYSIS, C.K.WANG* INTERNATIONAL STUDENT EDITION, 1983, MCGRAW HILL* SECTION 2.11, PAGE 47*UNIT METER KNJOINT COORDINATES1 0 0 0; 2 0 7.5 0; 3 6 7.5 0; 4 6 2.5 0*MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4*UNIT CM KNMEMBER PROPERTY1 3 PRIS AX 2400 IZ 72E42 PRIS AX 4800 IZ 144E4CONSTANTSE CONCRETE ALLPOISS CONC ALL*SUPP1 PINNED4 FIXED BUT FX MZ*LOAD 1SUPP DISP1 FY -1.*LOAD 2SUPP DISP4 FY -1.*PERFORM ANALYSIS*LOAD LIST 1PRINT JOINT DISP*LOAD LIST 2PRINT JOINT DISP*FINISH

3 Static Frames




1. STAAD PLANE DEFLECTIONS DUE TO MOVEMENT OF SUPPORTSINPUT FILE: FR2D10.STD

2. *3. * FILE: FR2D10.STD4. *5. * REFERENCE: INTERMEDIATE STRUCTURAL ANALYSIS, C.K.WANG6. * INTERNATIONAL STUDENT EDITION, 1983, MCGRAW HILL7. * SECTION 2.11, PAGE 478. *9. UNIT METER KN10. JOINT COORDINATES11. 1 0 0 0; 2 0 7.5 0; 3 6 7.5 0; 4 6 2.5 012. *13. MEMBER INCIDENCES14. 1 1 2; 2 2 3; 3 3 415. *16. UNIT CM KN17. MEMBER PROPERTY18. 1 3 PRIS AX 2400 IZ 72E419. 2 PRIS AX 4800 IZ 144E420. CONSTANTS21. E CONCRETE ALL22. POISS CONC ALL23. *24. SUPP25. 1 PINNED26. 4 FIXED BUT FX MZ27. *28. LOAD 129. SUPP DISP30. 1 FY -1.31. *32. LOAD 233. SUPP DISP34. 4 FY -1.35. *36. PERFORM ANALYSISDEFLECTIONS DUE TO MOVEMENT OF SUPPORTS -- PAGE NO. 2

*





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Static Frame 10

37. *38. LOAD LIST 139. PRINT JOINT DISP

JOINT DISPDEFLECTIONS DUE TO MOVEMENT OF SUPPORTS -- PAGE NO. 3

*



1 1 0.0000 -1.0000 0.0000 0.0000 0.0000 0.00172 1 -1.2500 -1.0000 0.0000 0.0000 0.0000 0.00173 1 -1.2500 0.0000 0.0000 0.0000 0.0000 0.00174 1 -0.4167 0.0000 0.0000 0.0000 0.0000 0.0017

************** END OF LATEST ANALYSIS RESULT **************40. *41. LOAD LIST 242. PRINT JOINT DISP

JOINT DISPDEFLECTIONS DUE TO MOVEMENT OF SUPPORTS -- PAGE NO. 4

*



1 2 0.0000 0.0000 0.0000 0.0000 0.0000 -0.00172 2 1.2500 0.0000 0.0000 0.0000 0.0000 -0.00173 2 1.2500 -1.0000 0.0000 0.0000 0.0000 -0.00174 2 0.4167 -1.0000 0.0000 0.0000 0.0000 -0.0017

************** END OF LATEST ANALYSIS RESULT **************43. *44. FINISH


DEFLECTIONS DUE TO MOVEMENT OF SUPPORTS -- PAGE NO. 5*


Static Frame 11ObjectiveTo find the member forces in a 1x2 bay plane frame with members of rectangular section.

ReferenceManual of Steel Construction – Allowable Stress Design, AISC, 9th Edition, 1989.

3 Static Frames


ProblemThe frame supports a uniformly distributed load and concentrated loads. Calculate the bendingmoment and shear force at the mid point of the beam of the first bay.

E = 30,000 ksi

Columns are 12”x24”, beams are 12”x30”


Comparison


Load Case 1 Moment , M (in-kips) 3,375 3,360.15 none

Shear, V (kips) 68.75 68.75 none

Load Case 2 Moment, M (in-kips) 2,430 2,425.12 none

Shear, V (kips) 22.50 22.68 <1%


STAAD InputSTAAD PLANE :A PLANE FRAME* FILE: FR2D11.STD** REFERENCE: "MANUAL OF STEEL CONSTRUCTION-ALLOWABLE STRESS DESIGN",* AISC, CHICAGO, ILLINOIS, 1989.*UNIT FEET KIPSJOINT COORDINATES1 0.0 0.0 ; 2 18.0 0.03 36.0 0.0 ; 4 0.0 10.05 18.0 10.0 ; 6 36.0 10.0MEMBER INCIDENCES1 1 4 ; 2 2 5 ; 3 3 6 ; 4 4 55 5 6UNIT INCHMEMBER PROPERTIES1 TO 3 PRISMATIC AX 10000000.0 IZ 13824.04 5 PRISMATIC AX 10000000.0 IZ 27000.0MEMBER RELEASES1 3 5 END MZ4 START MZSUPPORTS1 3 FIXED

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Static Frame 11

2 PINNEDUNIT INCHCONSTANTSE 30000.0 ALLUNIT FEETLOAD 1 VERTICAL POINT LOADSJOINT LOADS4 6 FY -50.05 FY -100.0MEMBER LOADS4 CON GY -100.0 9.05 CON GY -100.0 9.0LOAD 2 VERTICAL UNIFORM LOADSMEMBER LOADS4 UNI GY -10.05 UNI GY -10.0PERFORM ANALYSISUNIT INCH KIPSECTION .501 MEMBER 4PRINT SECTION FORCES LIST 4FINISH



1. STAAD PLANE :A PLANE FRAMEINPUT FILE: FR2D11.STD

2. * FILE: FR2D11.STD3. *4. * REFERENCE: "MANUAL OF STEEL CONSTRUCTION-ALLOWABLE STRESS DESIGN",5. * AISC, CHICAGO, ILLINOIS, 1989.6. *7. UNIT FEET KIPS8. JOINT COORDINATES9. 1 0.0 0.0 ; 2 18.0 0.010. 3 36.0 0.0 ; 4 0.0 10.011. 5 18.0 10.0 ; 6 36.0 10.012. MEMBER INCIDENCES13. 1 1 4 ; 2 2 5 ; 3 3 6 ; 4 4 514. 5 5 615. UNIT INCH16. MEMBER PROPERTIES17. 1 TO 3 PRISMATIC AX 10000000.0 IZ 13824.018. 4 5 PRISMATIC AX 10000000.0 IZ 27000.019. MEMBER RELEASES20. 1 3 5 END MZ21. 4 START MZ22. SUPPORTS23. 1 3 FIXED24. 2 PINNED25. UNIT INCH26. CONSTANTS27. E 30000.0 ALL

3 Static Frames


28. UNIT FEET29. LOAD 1 VERTICAL POINT LOADS30. JOINT LOADS31. 4 6 FY -50.032. 5 FY -100.033. MEMBER LOADS34. 4 CON GY -100.0 9.035. 5 CON GY -100.0 9.036. LOAD 2 VERTICAL UNIFORM LOADS37. MEMBER LOADS38. 4 UNI GY -10.0:A PLANE FRAME -- PAGE NO. 2

* FILE: FR2D11.STD39. 5 UNI GY -10.040. PERFORM ANALYSIS







*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 6 EQN.NO. 1041. UNIT INCH KIP42. SECTION .501 MEMBER 443. PRINT SECTION FORCES LIST 4

SECTION FORCES LIST 4:A PLANE FRAME -- PAGE NO. 3

* FILE: FR2D11.STD

MEMBER FORCES AT INTERMEDIATE SECTIONS--------------------------------------ALL UNITS ARE -- KIP INCH

MEMB LOAD SEC SHEAR-Y SHEAR-Z MOM-Y MOM-Z

4 1 0.50 -68.75 0.00 0.00 -3360.152 0.50 -22.68 0.00 0.00 -2425.12



:A PLANE FRAME -- PAGE NO. 4* FILE: FR2D11.STD


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3 Static Frames

Static Frame 11

Static Frame 12ObjectiveTo find the forces in the members of a truss structure due to fabrication defect in the length ofone bar which is 0.75 cm too short.

ReferenceC.K. Wang, Intermediate Structural Analysis, International Student Edition, 1983, McGraw Hill,Section 10.13, p.387

.

ProblemStructure to be solved as a truss. To achieve this in the STAAD model, instead of declaring themtruss members, define them as frame members, and release MZ at both ends of all members. Inthe above figure, the area of cross section of the members is as follows.

1 TO 4 = 20 cm2

5, 6 = 24 cm2

7, 8 = 30 cm2

9, 10 = 15 cm2


3 Static Frames


Comparison

Member Number Theory STAAD.Pro Difference

1 280.56 (C) -280.57 none

2 50.86 (T) 50.86 none

3 127.99 (C) -127.99 none

4 101.72 (T) 101.72 none

5 134.14 (C) -134.14 none

6 57.85 (C) -57.85 none

7 63.57 (C) -63.57 none

8 127.14 (C) -127.15 none

9 287.13 (T) 287.13 none

10 223.56 (T) 223.56 none

Table 3-12: Comparison of axial force results (kN) for static frame no.12

STAAD InputSTAAD PLANE EFFECT OF FABRICATION DEFECT - PRESTRAIN** FILE: FR2D12.STD** REFERENCE: INTERMEDIATE STRUCTURAL ANALYSIS, C.K.WANG* INTERNATIONAL STUDENT EDITION, 1983, MCGRAW HILL* SECTION 10.13, PAGE 387*UNIT METER KNJOINT COORDINATES1 2.4 1.8 0; 2 4.8 1.8 0; 3 0 0 0; 4 2.4 0 0; 5 4.8 0 0; 6 7.2 0 0*MEMBER INCIDENCES1 1 2; 2 3 4; 3 4 5; 4 5 6; 5 4 1; 6 5 2; 7 3 1; 8 2 6; 9 1 5; 10 4 2*UNIT CMSMEMB PROP1 TO 4 PRIS AX 20 IZ 100E-45 6 PRIS AX 24 IZ 100E-47 8 PRIS AX 30 IZ 100E-49 10 PRIS AX 15 IZ 100E-4*CONSTE 20000 ALLPOISSON STEEL ALL** ALL MOMENTS RELEASED TO SIMULATE TRUSS ACTIONMEMBER RELEASE1 TO 10 START MZ1 TO 10 END MZ*SUPPORT3 PINNED5 6 FIXED BUT FX MZ

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3 Static Frames

Static Frame 12

*LOAD 1TEMPERATURE LOAD9 STRAIN -0.75*PERF ANALYUNIT NEWTONPRINT MEMBER FORCES*FINISH



1. STAAD PLANE EFFECT OF FABRICATION DEFECT - PRESTRAININPUT FILE: FR2D12.STD

2. *3. * FILE: FR2D12.STD4. *5. * REFERENCE: INTERMEDIATE STRUCTURAL ANALYSIS, C.K.WANG6. * INTERNATIONAL STUDENT EDITION, 1983, MCGRAW HILL7. * SECTION 10.13, PAGE 3878. *9. UNIT METER KN10. JOINT COORDINATES11. 1 2.4 1.8 0; 2 4.8 1.8 0; 3 0 0 0; 4 2.4 0 0; 5 4.8 0 0; 6 7.2 0 012. *13. MEMBER INCIDENCES14. 1 1 2; 2 3 4; 3 4 5; 4 5 6; 5 4 1; 6 5 2; 7 3 1; 8 2 6; 9 1 5; 10 4 215. *16. UNIT CMS17. MEMB PROP18. 1 TO 4 PRIS AX 20 IZ 100E-419. 5 6 PRIS AX 24 IZ 100E-420. 7 8 PRIS AX 30 IZ 100E-421. 9 10 PRIS AX 15 IZ 100E-422. *23. CONST24. E 20000 ALL25. POISSON STEEL ALL26. *27. * ALL MOMENTS RELEASED TO SIMULATE TRUSS ACTION28. MEMBER RELEASE29. 1 TO 10 START MZ30. 1 TO 10 END MZ31. *32. SUPPORT33. 3 PINNED34. 5 6 FIXED BUT FX MZ35. *36. LOAD 137. TEMPERATURE LOAD38. 9 STRAIN -0.75

3 Static Frames


EFFECT OF FABRICATION DEFECT - PRESTRAIN -- PAGE NO. 2*39. *40. PERF ANALY






*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 2 EQN.NO. 6*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 3 EQN.NO. 7*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 4 EQN.NO. 10*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 5 EQN.NO. 12*WARNING- ZERO STIFFNESS IN DIRECTION 6 AT JOINT 6 EQN.NO. 14

41. UNIT NEWTON42. PRINT MEMBER FORCES

MEMBER FORCESEFFECT OF FABRICATION DEFECT - PRESTRAIN -- PAGE NO. 3

*

MEMBER END FORCES STRUCTURE TYPE = PLANE-----------------ALL UNITS ARE -- NEWT CMS (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 280565.47 0.00 0.00 0.00 0.00 0.002-280565.47 0.00 0.00 0.00 0.00 0.00

2 1 3 -50858.10 0.00 0.00 0.00 0.00 0.004 50858.10 0.00 0.00 0.00 0.00 0.00

3 1 4 127991.15 0.00 0.00 0.00 0.00 0.005-127991.15 0.00 0.00 0.00 0.00 0.00

4 1 5-101716.20 0.00 0.00 0.00 0.00 0.006 101716.20 0.00 0.00 0.00 0.00 0.00

5 1 4 134136.94 0.00 0.00 0.00 0.00 0.001-134136.94 0.00 0.00 0.00 0.00 0.00

6 1 5 57849.79 0.00 0.00 0.00 0.00 0.002 -57849.79 0.00 0.00 0.00 0.00 0.00

7 1 3 63572.63 0.00 0.00 0.00 0.00 0.001 -63572.63 0.00 0.00 0.00 0.00 0.00

8 1 2 127145.26 0.00 0.00 0.00 0.00 0.006-127145.26 0.00 0.00 0.00 0.00 0.00

9 1 1-287134.19 0.00 0.00 0.00 0.00 0.005 287134.19 0.00 0.00 0.00 0.00 0.00

10 1 4-223561.58 0.00 0.00 0.00 0.00 0.002 223561.58 0.00 0.00 0.00 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************43. *44. FINISHEFFECT OF FABRICATION DEFECT - PRESTRAIN -- PAGE NO. 4

************ END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:29:20 ****

************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** *

134 — STAAD.Pro

3 Static Frames

Static Frame 12

* Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Forces in a Space FrameObjectiveTo find the maximum axial force and moment due to load and moment applied at a joint in aSpace frame.

ReferenceWeaver Jr., W., Computer Programs for Structural Analysis, page 146, problem 8.

ProblemDetermine the maximum axial force and moment in the space structure.

F = 2 kip, P = 1 kip, M = 120 in·kip

L = 120 in.

E = 30E3 ksi,

AX = 11 in2

IX = 83 in4

IY = 56 in4

IZ = 56 in4

Figure 3-13: Space frame model

3 Static Frames


Comparison



FMax (kips) 1.47 1.47 1.47

MY,Max (in·kip) 84.04 84.04 84.04

MZ,Max (in·kip) 95.319 96.120 96.120

Table 3-13: Comparison of max. Force, F, and max. Moments,M, forverification problem no. 10

STAAD InputSTAAD SPACE VERIFICATION PROB NO. 10** REFERENCE 'COMPUTER PROGRAMS FOR STRUCTURAL ANALYSIS'* BY WILLIAM WEAVER JR. PAGE 146 STRUCTURE NO. 8.* ANSWER - MAX AXIAL FORCE= 1.47 (MEMB 3)* MAX BEND-Y= 84.04, MAX BEND-Z= 95.319 (BOTH MEMB 3)*UNIT INCH KIPJOINT COORD1 0 120 0 ; 2 240 120 03 0 0 0 ; 4 360 0 120MEMB INCI1 1 2 ; 2 3 1 ; 3 2 4MEMB PROP1 2 3 PRIS AX 11. IX 83. IY 56. IZ 56CONSTANT ; E 30000. ALLPOISS .25 ALLSUPPORT3 4 FIXEDLOAD 1 JOINT LOADJOINT LOAD1 FX 2. ; 2 FY -1. ; 2 MZ -120.PERFORM ANALPRINT ANALYSIS RESULTFINISH



1. STAAD SPACE VERIFICATION PROB NO. 10INPUT FILE: VER10.STD

2. *3. * REFERENCE 'COMPUTER PROGRAMS FOR STRUCTURAL ANALYSIS'4. * BY WILLIAM WEAVER JR. PAGE 146 STRUCTURE NO. 8.5. * ANSWER - MAX AXIAL FORCE= 1.47 (MEMB 3)

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3 Static Frames

Static Frame 12

6. * MAX BEND-Y= 84.04, MAX BEND-Z= 95.319 (BOTH MEMB 3)7. *8. UNIT INCH KIP9. JOINT COORD10. 1 0 120 0 ; 2 240 120 011. 3 0 0 0 ; 4 360 0 12012. MEMB INCI13. 1 1 2 ; 2 3 1 ; 3 2 414. MEMB PROP15. 1 2 3 PRIS AX 11. IX 83. IY 56. IZ 5616. CONSTANT ; E 30000. ALL17. POISS .25 ALL18. SUPPORT19. 3 4 FIXED20. LOAD 1 JOINT LOAD21. JOINT LOAD22. 1 FX 2. ; 2 FY -1. ; 2 MZ -120.23. PERFORM ANAL


NUMBER OF JOINTS 4 NUMBER OF MEMBERS 3NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2VERIFICATION PROB NO. 10 -- PAGE NO. 2

*



24. PRINT ANALYSIS RESULTANALYSIS RESULT




1 1 0.22267 0.00016 -0.17182 -0.00255 0.00217 -0.002132 1 0.22202 -0.48119 -0.70161 -0.00802 0.00101 -0.004353 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.000004 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000VERIFICATION PROB NO. 10 -- PAGE NO. 4

*

SUPPORT REACTIONS -UNIT KIP INCH STRUCTURE TYPE = SPACE-----------------


3 1 -1.10 -0.43 0.22 48.78 -17.97 96.124 1 -0.90 1.43 -0.22 123.08 47.25 -11.72VERIFICATION PROB NO. 10 -- PAGE NO. 5

*

MEMBER END FORCES STRUCTURE TYPE = SPACE-----------------ALL UNITS ARE -- KIP INCH (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 1 1 0.90 -0.43 0.22 22.71 -17.97 -36.372 -0.90 0.43 -0.22 -22.71 -34.18 -67.36

2 1 3 -0.43 1.10 0.22 -17.97 -48.78 96.121 0.43 -1.10 -0.22 17.97 22.71 36.37

3 1 2 1.47 -0.71 -0.48 -37.02 15.69 -53.28

3 Static Frames


4 -1.47 0.71 0.48 37.02 84.04 -95.32************** END OF LATEST ANALYSIS RESULT **************25. FINISH




138 — STAAD.Pro

3 Static Frames

Static Frame 12

4Static Plate/Shell Elements


















Static Element 1ObjectiveTo find deflections and element stresses due to loads at the free end of a Cantilever beam oftubular section. The beam is modeled using plate/shell elements.

ReferenceTimoshenko, S., Strength of Materials, Part I, Elementary Theory and Problems, 2nd Edition, VanNostrand Company, 1940.


ProblemA cantilever beam is made of a tubular section. Using plate/shell elements calculate thedeflection at the free end and axial stress at the center of the beam for the following free endloads:

P = 1,000 lb

Mx = 2,000 in-lb

My = 2,500 in-lb

V = 1,000 lb

Figure 4-1: Cantilever beam modeled with elements

140 — STAAD.Pro

4 Static Plate/Shell Elements

Static Element 1

Figure 4-2: STAAD.Pro Model showing Node numbers

Figure 4-3: Element numbers at a) the middle section and b) the free end

(a) (b)

Average deflection for nodes 11, 22, 33, 44, 55, 66, 77, 88, 99 and 10 due to load case 3 (My):

d = [4(0.07431) + 4(0.07384) + 2(0.07374)]/10 = 0.074008



Average deflection for nodes 11, 22, 33, 44, 55, 66, 77, 88, 99 and 10 due to load case 4 (V):

d = [4(-0.41123) + 4(-0.41124) + 2(-0.41057)]/10 = 0.41110

Average bending stress for nodes 76, 86, 126, and 136 due to load case 3 (My):

σ = 4(5551.52)/4 = 5551.52 psi

Average bending stress for nodes 71, 81, 121, and 131 due to load case 4 (V):

σ = 4(42074.63)/4 = 42074.63 psi

Comparison


Free end deflection due toaxial load, P (in)

Nodes 11, 44,66, 99

0.004 0.00410 2.5%

Nodes 22,33,55, 77, 88, 110

0.004 0.00401 none

Axial stress at the middleof the beam due to axial

load, P (psi)

Elements 46,66, 96, 116

2,000 2,000.02 none

Elements 56,106

2,000 1,991.15 none

Elements 76,86, 126, 136

2,000 2,004,19 none

In plane shear stress atthe free end due totorque, Mx (psi)

Elements50,70,100,120

3,333 3,333.55 none

Elements 60,110

3,333 3,325.54 none

Elements80,90,130,140

3,333 3,342.23 none

Avg. free end deflection at the center dueto moment, My (in)

0.0741 0.074008 none

Avg. free end bending stress at the centerdue to moment, My (psi)

5,647 5,551.52 1.7%

Avg. free end deflection at the center dueto shear, V (in)

0.4152 -0.41110 <1%

Avg. free end bending stress at the centerdue to shear, V (psi)

42,913 42,074.63 2.0%


STAAD InputSTAAD SPACE :A CANTILEVER BEAM OF TUBULAR SECTION* FILE: PLATE01.STD*

142 — STAAD.Pro


Static Element 1

* REFERENCES: 1. TIMOSHENKO, S., STRENGTH OF MATERIALS, PART 1,* 2ND EDITION, D. VAN NOSTRAND COMPANY, 1940* 2. SEELEY, F. B., AND SMITH, J.O., ADVANCED MECHANICS* OF MATERIALS, 2ND EDITION, JOHN WILEY AND SONS, 1955** STARDYNE VERIFICATION PROBLEM #2UNIT IN POUNDJOINT COORDINATES1 0. 0. 0. 11 20. 0. 0.REPEAT 3 0. 1. 0.REPEAT 2 0. 0. 1.REPEAT 3 0. -1. 0.REPEAT 1 0. 0. -1.MEMBER INCIDENCES1 1 2 1011 34 35 2021 56 57 3031 89 90 40ELEMENT INCIDENCES41 1 2 13 12 TO 50REPEAT 8 10 11131 100 101 2 1 TO 140MEMBER TRUSS1 TO 40MEMBER PROPERTIES1 TO 40 PRISMATIC AX .0005ELEMENT PROPERTIES41 TO 140 TH 0.05CONSTANTSE 10.E6 MEMB 41 TO 140E 1000 MEMB 1 TO 40SUPPORT1 TO 100 BY 11 FIXEDLOAD 1 AXIAL LOADJOINT LOAD11 TO 110 BY 11 FX 100.LOAD 2 TORQUEJOINT LOAD11 FZ -86.21 FY 80.4322 33 FY 169.4444 FZ 86.21 FY 80.4355 FZ 162.2366 FZ 86.21 FY -80.4377 88 FY -169.4499 FZ -86.21 FY -80.43110 FZ -162.23LOAD 3 END MOMENTJOINT LOAD44 55 66 FX -258.633 77 FX -86.322 88 FX 86.311 99 110 FX 258.6LOAD 4 SHEARJOINT LOAD11 44 66 99 FY -66.22 33 77 88 FY -184.0PERFORM ANALYSISLOAD LIST 1 2 3 4PRINT JOINT DISPLACEMENTS LIST 11 TO 110 BY 11LOAD LIST 1PRINT ELEMENT STRESSES LIST 46 TO 136 BY 10LOAD LIST 2PRINT ELEMENT STRESSES LIST 50 TO 140 BY 10LOAD LIST 3PRINT ELEMENT STRESSES LIST 45 TO 135 BY 10 46 TO 136 BY 10*



LOAD LIST 4PRINT ELEMENT STRESSES LIST 41 TO 131 BY 10FINISH



1. STAAD SPACE :A CANTILEVER BEAM OF TUBULAR SECTIONINPUT FILE: PLATE01.STD

2. * FILE: PLATE01.STD3. *4. * REFERENCES: 1. TIMOSHENKO, S., STRENGTH OF MATERIALS, PART 1,5. * 2ND EDITION, D. VAN NOSTRAND COMPANY, 19406. * 2. SEELEY, F. B., AND SMITH, J.O., ADVANCED MECHANICS7. * OF MATERIALS, 2ND EDITION, JOHN WILEY AND SONS, 19558. *9. * STARDYNE VERIFICATION PROBLEM #210. UNIT IN POUND11. JOINT COORDINATES12. 1 0. 0. 0. 11 20. 0. 0.13. REPEAT 3 0. 1. 0.14. REPEAT 2 0. 0. 1.15. REPEAT 3 0. -1. 0.16. REPEAT 1 0. 0. -1.17. MEMBER INCIDENCES18. 1 1 2 1019. 11 34 35 2020. 21 56 57 3021. 31 89 90 4022. ELEMENT INCIDENCES23. 41 1 2 13 12 TO 5024. REPEAT 8 10 1125. 131 100 101 2 1 TO 14026. MEMBER TRUSS27. 1 TO 4028. MEMBER PROPERTIES29. 1 TO 40 PRISMATIC AX .000530. ELEMENT PROPERTIES31. 41 TO 140 TH 0.0532. CONSTANTS33. E 10.E6 MEMB 41 TO 14034. E 1000 MEMB 1 TO 4035. SUPPORT36. 1 TO 100 BY 11 FIXED37. LOAD 1 AXIAL LOAD38. JOINT LOAD:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 2

* FILE: PLATE01.STD39. 11 TO 110 BY 11 FX 100.40. LOAD 2 TORQUE41. JOINT LOAD42. 11 FZ -86.21 FY 80.4343. 22 33 FY 169.44

144 — STAAD.Pro


Static Element 1

44. 44 FZ 86.21 FY 80.4345. 55 FZ 162.2346. 66 FZ 86.21 FY -80.4347. 77 88 FY -169.4448. 99 FZ -86.21 FY -80.4349. 110 FZ -162.2350. LOAD 3 END MOMENT51. JOINT LOAD52. 44 55 66 FX -258.653. 33 77 FX -86.354. 22 88 FX 86.355. 11 99 110 FX 258.656. LOAD 4 SHEAR57. JOINT LOAD58. 11 44 66 99 FY -66.59. 22 33 77 88 FY -184.060. PERFORM ANALYSIS


** WARNING ** A SOFT MATERIAL WITH (1.0 / 3.150E+03) TIMES THE STIFFNESS OFCONCRETE ENTERED. PLEASE CHECK.

**WARNING** AX MISSING or SMALL FOR MEMBER 1**WARNING** AX MISSING or SMALL FOR MEMBER 2**WARNING** AX MISSING or SMALL FOR MEMBER 3**WARNING** AX MISSING or SMALL FOR MEMBER 4**WARNING** AX MISSING or SMALL FOR MEMBER 5**WARNING** AX MISSING or SMALL FOR MEMBER 6**WARNING** AX MISSING or SMALL FOR MEMBER 7**WARNING** AX MISSING or SMALL FOR MEMBER 8**WARNING** AX MISSING or SMALL FOR MEMBER 9**WARNING** AX MISSING or SMALL FOR MEMBER 10**WARNING** AX MISSING or SMALL FOR MEMBER 11**WARNING** AX MISSING or SMALL FOR MEMBER 12**WARNING** AX MISSING or SMALL FOR MEMBER 13**WARNING** AX MISSING or SMALL FOR MEMBER 14**WARNING** AX MISSING or SMALL FOR MEMBER 15**WARNING** AX MISSING or SMALL FOR MEMBER 16**WARNING** AX MISSING or SMALL FOR MEMBER 17**WARNING** AX MISSING or SMALL FOR MEMBER 18**WARNING** AX MISSING or SMALL FOR MEMBER 19**WARNING** AX MISSING or SMALL FOR MEMBER 20**WARNING** AX MISSING or SMALL FOR MEMBER 21

:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 3* FILE: PLATE01.STD**WARNING** AX MISSING or SMALL FOR MEMBER 22**WARNING** AX MISSING or SMALL FOR MEMBER 23**WARNING** AX MISSING or SMALL FOR MEMBER 24**WARNING** AX MISSING or SMALL FOR MEMBER 25**WARNING** AX MISSING or SMALL FOR MEMBER 26**WARNING** AX MISSING or SMALL FOR MEMBER 27**WARNING** AX MISSING or SMALL FOR MEMBER 28**WARNING** AX MISSING or SMALL FOR MEMBER 29**WARNING** AX MISSING or SMALL FOR MEMBER 30**WARNING** AX MISSING or SMALL FOR MEMBER 31**WARNING** AX MISSING or SMALL FOR MEMBER 32**WARNING** AX MISSING or SMALL FOR MEMBER 33**WARNING** AX MISSING or SMALL FOR MEMBER 34**WARNING** AX MISSING or SMALL FOR MEMBER 35**WARNING** AX MISSING or SMALL FOR MEMBER 36**WARNING** AX MISSING or SMALL FOR MEMBER 37**WARNING** AX MISSING or SMALL FOR MEMBER 38**WARNING** AX MISSING or SMALL FOR MEMBER 39



**WARNING** AX MISSING or SMALL FOR MEMBER 40





61. LOAD LIST 1 2 3 462. PRINT JOINT DISPLACEMENTS LIST 11 TO 110 BY 11

JOINT DISPLACE LIST 11:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 4

* FILE: PLATE01.STD



11 1 0.00410 0.00024 0.00020 -0.00005 -0.00082 0.000932 -0.00035 0.01443 -0.02268 0.01498 0.00067 0.000013 0.01142 0.07431 0.00056 0.00039 -0.00233 0.008464 -0.04451 -0.41123 -0.00026 -0.00119 0.00184 -0.02863

22 1 0.00401 0.00004 -0.00001 -0.00010 0.00013 0.000122 -0.00011 0.01446 -0.00757 0.01505 0.00058 0.000073 0.00371 0.07384 0.00015 -0.00031 0.00034 0.006384 -0.01476 -0.41124 -0.00036 0.00050 -0.00013 -0.02764

33 1 0.00401 -0.00004 -0.00001 0.00010 0.00013 -0.000122 0.00011 0.01446 0.00757 0.01505 -0.00058 0.000073 -0.00371 0.07384 -0.00015 -0.00031 -0.00034 0.006384 0.01476 -0.41124 0.00036 0.00050 0.00013 -0.02764

44 1 0.00410 -0.00024 0.00020 0.00005 -0.00082 -0.000932 0.00035 0.01443 0.02268 0.01498 -0.00067 0.000013 -0.01142 0.07431 -0.00056 0.00039 0.00233 0.008464 0.04451 -0.41123 0.00026 -0.00119 -0.00184 -0.02863

55 1 0.00401 -0.00011 0.00000 0.00000 0.00000 0.000272 0.00000 0.00000 0.02265 0.01404 -0.00059 0.000003 -0.01111 0.07374 0.00000 0.00000 0.00000 0.006964 0.04414 -0.41057 0.00000 0.00000 0.00000 -0.03079

66 1 0.00410 -0.00024 -0.00020 -0.00005 0.00082 -0.000932 -0.00035 -0.01443 0.02268 0.01498 -0.00067 -0.000013 -0.01142 0.07431 0.00056 -0.00039 -0.00233 0.008464 0.04451 -0.41123 -0.00026 0.00119 0.00184 -0.02863

77 1 0.00401 -0.00004 0.00001 -0.00010 -0.00013 -0.000122 -0.00011 -0.01446 0.00757 0.01505 -0.00058 -0.000073 -0.00371 0.07384 0.00015 0.00031 0.00034 0.006384 0.01476 -0.41124 -0.00036 -0.00050 -0.00013 -0.02764

88 1 0.00401 0.00004 0.00001 0.00010 -0.00013 0.000122 0.00011 -0.01446 -0.00757 0.01505 0.00058 -0.000073 0.00371 0.07384 -0.00015 0.00031 -0.00034 0.006384 -0.01476 -0.41124 0.00036 -0.00050 0.00013 -0.02764

99 1 0.00410 0.00024 -0.00020 0.00005 0.00082 0.000932 0.00035 -0.01443 -0.02268 0.01498 0.00067 -0.000013 0.01142 0.07431 -0.00056 -0.00039 0.00233 0.008464 -0.04451 -0.41123 0.00026 0.00119 -0.00184 -0.02863

110 1 0.00401 0.00011 0.00000 0.00000 0.00000 -0.000272 0.00000 0.00000 -0.02265 0.01404 0.00059 0.000003 0.01111 0.07374 0.00000 0.00000 0.00000 0.006964 -0.04414 -0.41057 0.00000 0.00000 0.00000 -0.03079

:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 5* FILE: PLATE01.STD************** END OF LATEST ANALYSIS RESULT **************63. LOAD LIST 1

146 — STAAD.Pro


Static Element 1

64. PRINT ELEMENT STRESSES LIST 46 TO 136 BY 10ELEMENT STRESSES LIST 46

:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 6* FILE: PLATE01.STDELEMENT STRESSES FORCE,LENGTH UNITS= POUN IN----------------



46 1 0.02 0.00 0.00 0.00 0.001998.93 1998.62 2000.02 2.49 -0.242000.58 1999.46

TOP : SMAX= 2000.58 SMIN= 3.31 TMAX= 998.64 ANGLE= 0.0BOTT: SMAX= 1999.46 SMIN= 1.67 TMAX= 998.89 ANGLE= 0.0

56 1 -0.01 0.00 0.00 0.00 0.001994.35 1994.87 1991.57 -6.07 0.001997.15 1998.13

TOP : SMAX= 1991.55 SMIN= -5.60 TMAX= 998.57 ANGLE= 0.0BOTT: SMAX= 1991.59 SMIN= -6.53 TMAX= 999.06 ANGLE= 0.0

66 1 0.02 0.00 0.00 0.00 0.001998.93 1998.62 2000.02 2.49 0.242000.58 1999.46


76 1 -0.04 0.00 0.00 0.00 0.002003.32 2003.71 2004.19 1.36 -0.812003.44 2004.95

TOP : SMAX= 2003.44 SMIN= 0.24 TMAX= 1001.60 ANGLE= 0.0BOTT: SMAX= 2004.95 SMIN= 2.48 TMAX= 1001.24 ANGLE= -0.1

86 1 -0.04 0.00 0.00 0.00 0.002003.32 2003.71 2004.19 1.36 0.812003.44 2004.95


96 1 0.02 0.00 0.00 0.00 0.001998.93 1998.62 2000.02 2.49 -0.242000.58 1999.46


106 1 -0.01 0.00 0.00 0.00 0.001994.35 1994.87 1991.57 -6.07 0.001997.15 1998.13


116 1 0.02 0.00 0.00 0.00 0.001998.93 1998.62 2000.02 2.49 0.242000.58 1999.46

TOP : SMAX= 2000.58 SMIN= 3.31 TMAX= 998.64 ANGLE= 0.0BOTT: SMAX= 1999.46 SMIN= 1.67 TMAX= 998.89 ANGLE= 0.0:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 7

* FILE: PLATE01.STDELEMENT STRESSES FORCE,LENGTH UNITS= POUN IN----------------



126 1 -0.04 0.00 0.00 0.00 0.002003.32 2003.71 2004.19 1.36 -0.812003.44 2004.95


136 1 -0.04 0.00 0.00 0.00 0.002003.32 2003.71 2004.19 1.36 0.812003.44 2004.95




**** MAXIMUM STRESSES AMONG SELECTED PLATES AND CASES ****MAXIMUM MINIMUM MAXIMUM MAXIMUM MAXIMUMPRINCIPAL PRINCIPAL SHEAR VONMISES TRESCASTRESS STRESS STRESS STRESS STRESS

2.004949E+03 -6.534168E+00 1.001600E+03 2.003712E+03 2.004949E+03PLATE NO. 76 56 76 76 76CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************65. LOAD LIST 266. PRINT ELEMENT STRESSES LIST 50 TO 140 BY 10

ELEMENT STRESSES LIST 50:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 8




50 2 -2.88 1.41 -0.01 -0.02 -0.035636.28 5911.95 -0.36 18.30 3333.556508.14 6826.34


60 2 0.00 1.42 0.00 0.00 -0.085445.08 6074.93 0.00 0.00 3325.546287.44 7014.73


70 2 2.88 1.41 0.01 0.02 -0.035636.28 5911.95 0.36 -18.30 3333.556508.14 6826.34


80 2 -3.78 -1.42 0.02 0.06 -0.035674.31 5906.56 1.32 -11.09 3342.236551.26 6819.29


90 2 3.78 -1.42 -0.02 -0.06 -0.035674.31 5906.56 -1.32 11.09 3342.236551.26 6819.29


100 2 -2.88 1.41 -0.01 -0.02 -0.035636.28 5911.95 -0.36 18.30 3333.556508.14 6826.34


110 2 0.00 1.42 0.00 0.00 -0.085445.08 6074.93 0.00 0.00 3325.546287.44 7014.73


120 2 2.88 1.41 0.01 0.02 -0.035636.28 5911.95 0.36 -18.30 3333.556508.14 6826.34

TOP : SMAX= 3280.32 SMIN= -3227.82 TMAX= 3254.07 ANGLE= 45.1BOTT: SMAX= 3368.98 SMIN= -3457.36 TMAX= 3413.17 ANGLE= 44.8:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 9


STRESS = FORCE/UNIT WIDTH/THICK, MOMENT = FORCE-LENGTH/UNIT WIDTH

148 — STAAD.Pro


Static Element 1

ELEMENT LOAD SQX SQY MX MY MXYVONT VONB SX SY SXYTRESCAT TRESCAB

130 2 -3.78 -1.42 0.02 0.06 -0.035674.31 5906.56 1.32 -11.09 3342.236551.26 6819.29


140 2 3.78 -1.42 -0.02 -0.06 -0.035674.31 5906.56 -1.32 11.09 3342.236551.26 6819.29



3.511688E+03 -3.511688E+03 3.507364E+03 6.074933E+03 7.014728E+03PLATE NO. 90 80 60 60 60CASE NO. 2 2 2 2 2********************END OF ELEMENT FORCES********************67. LOAD LIST 368. PRINT ELEMENT STRESSES LIST 45 TO 135 BY 10 46 TO 136 BY 10





45 3 -0.02 0.01 0.00 0.00 0.003703.79 3702.75 3703.80 1.06 -0.173704.34 3704.36

TOP : SMAX= 3703.23 SMIN= -1.11 TMAX= 1852.17 ANGLE= 0.0BOTT: SMAX= 3704.36 SMIN= 3.23 TMAX= 1850.57 ANGLE= 0.0

55 3 0.00 0.02 0.00 0.00 0.002.87 1.59 0.00 0.00 -1.293.32 1.83


65 3 0.02 0.01 0.00 0.00 0.003703.79 3702.75 -3703.80 -1.06 -0.173704.34 3704.36

TOP : SMAX= 1.11 SMIN= -3703.23 TMAX= 1852.17 ANGLE= 90.0BOTT: SMAX= -3.23 SMIN= -3704.36 TMAX= 1850.57 ANGLE=-90.0

75 3 -0.81 -0.01 0.04 0.00 0.015463.48 5646.25 -5554.57 0.18 1.315464.40 5647.48

TOP : SMAX= -1.84 SMIN= -5464.40 TMAX= 2731.28 ANGLE= 89.7BOTT: SMAX= 2.48 SMIN= -5645.01 TMAX= 2823.74 ANGLE=-89.7

85 3 -0.81 0.01 0.04 0.00 -0.015463.48 5646.25 -5554.57 0.18 -1.315464.40 5647.48

TOP : SMAX= -1.84 SMIN= -5464.40 TMAX= 2731.28 ANGLE=-89.7BOTT: SMAX= 2.48 SMIN= -5645.01 TMAX= 2823.74 ANGLE= 89.7

95 3 0.02 -0.01 0.00 0.00 0.003703.79 3702.75 -3703.80 -1.06 0.173704.34 3704.36

TOP : SMAX= 1.11 SMIN= -3703.23 TMAX= 1852.17 ANGLE=-90.0BOTT: SMAX= -3.23 SMIN= -3704.36 TMAX= 1850.57 ANGLE= 90.0

105 3 0.00 -0.02 0.00 0.00 0.002.87 1.59 0.00 0.00 1.293.32 1.83

TOP : SMAX= 1.66 SMIN= -1.66 TMAX= 1.66 ANGLE= 90.0



BOTT: SMAX= 0.92 SMIN= -0.92 TMAX= 0.92 ANGLE= 90.0115 3 -0.02 -0.01 0.00 0.00 0.00

3703.79 3702.75 3703.80 1.06 0.173704.34 3704.36

TOP : SMAX= 3703.23 SMIN= -1.11 TMAX= 1852.17 ANGLE= 0.0BOTT: SMAX= 3704.36 SMIN= 3.23 TMAX= 1850.57 ANGLE= 0.0:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 11




125 3 0.81 0.01 -0.04 0.00 -0.015463.48 5646.25 5554.57 -0.18 -1.315464.40 5647.48

TOP : SMAX= 5464.40 SMIN= 1.84 TMAX= 2731.28 ANGLE= -0.3BOTT: SMAX= 5645.01 SMIN= -2.48 TMAX= 2823.74 ANGLE= 0.3

135 3 0.81 -0.01 -0.04 0.00 0.015463.48 5646.25 5554.57 -0.18 1.315464.40 5647.48

TOP : SMAX= 5464.40 SMIN= 1.84 TMAX= 2731.28 ANGLE= 0.3BOTT: SMAX= 5645.01 SMIN= -2.48 TMAX= 2823.74 ANGLE= -0.3

46 3 0.03 0.03 0.00 0.00 0.003704.99 3703.08 3709.20 10.35 -1.863709.14 3709.27


56 3 0.00 0.03 0.00 0.00 0.004.19 1.52 0.00 0.00 1.654.83 1.75


66 3 -0.03 0.03 0.00 0.00 0.003704.99 3703.08 -3709.20 -10.35 -1.863709.14 3709.27

TOP : SMAX= -8.31 SMIN= -3709.14 TMAX= 1850.41 ANGLE=-90.0BOTT: SMAX= -12.39 SMIN= -3709.27 TMAX= 1848.44 ANGLE=-90.0

76 3 -1.04 -0.03 0.04 0.00 0.015459.11 5640.90 -5551.52 -3.75 4.915462.11 5641.41

TOP : SMAX= -6.01 SMIN= -5462.11 TMAX= 2728.05 ANGLE= 89.6BOTT: SMAX= -1.02 SMIN= -5641.41 TMAX= 2820.19 ANGLE=-89.7

86 3 -1.04 0.03 0.04 0.00 -0.015459.11 5640.90 -5551.52 -3.75 -4.915462.11 5641.41

TOP : SMAX= -6.01 SMIN= -5462.11 TMAX= 2728.05 ANGLE=-89.6BOTT: SMAX= -1.02 SMIN= -5641.41 TMAX= 2820.19 ANGLE= 89.7

96 3 -0.03 -0.03 0.00 0.00 0.003704.99 3703.08 -3709.20 -10.35 1.863709.14 3709.27

TOP : SMAX= -8.31 SMIN= -3709.14 TMAX= 1850.41 ANGLE= 90.0BOTT: SMAX= -12.39 SMIN= -3709.27 TMAX= 1848.44 ANGLE= 90.0:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 12




106 3 0.00 -0.03 0.00 0.00 0.004.19 1.52 0.00 0.00 -1.654.83 1.75

TOP : SMAX= 2.42 SMIN= -2.42 TMAX= 2.42 ANGLE= 90.0

150 — STAAD.Pro


Static Element 1

BOTT: SMAX= 0.88 SMIN= -0.88 TMAX= 0.88 ANGLE= 90.0116 3 0.03 -0.03 0.00 0.00 0.00

3704.99 3703.08 3709.20 10.35 1.863709.14 3709.27


126 3 1.04 0.03 -0.04 0.00 -0.015459.11 5640.90 5551.52 3.75 -4.915462.11 5641.41

TOP : SMAX= 5462.11 SMIN= 6.01 TMAX= 2728.05 ANGLE= -0.4BOTT: SMAX= 5641.41 SMIN= 1.02 TMAX= 2820.19 ANGLE= 0.3

136 3 1.04 -0.03 -0.04 0.00 0.015459.11 5640.90 5551.52 3.75 4.915462.11 5641.41



5.645007E+03 -5.645007E+03 2.823742E+03 5.646246E+03 5.647484E+03PLATE NO. 125 75 75 75 75CASE NO. 3 3 3 3 3********************END OF ELEMENT FORCES********************69. *70. LOAD LIST 471. PRINT ELEMENT STRESSES LIST 41 TO 131 BY 10





41 4 -14.20 10.26 -0.04 -0.03 0.0128183.86 28061.26 -28424.34 -2007.57 -3462.3228963.74 28777.50


51 4 0.00 -1.14 0.00 0.00 -0.025356.82 5150.93 0.00 0.00 -3033.326185.52 5947.78


61 4 14.20 10.26 0.04 0.03 0.0128183.86 28061.26 28424.34 2007.57 -3462.3228963.74 28777.50

TOP : SMAX= 28963.74 SMIN= 1630.57 TMAX= 13666.59 ANGLE= -7.3BOTT: SMAX= 28777.50 SMIN= 1492.00 TMAX= 13642.75 ANGLE= -7.4

71 4 21.02 -14.62 -0.33 -0.06 -0.0639671.99 41111.66 42074.63 3650.80 692.9641300.99 42874.24


81 4 21.02 14.62 -0.33 -0.06 0.0639671.99 41111.66 42074.63 3650.80 -692.9641300.99 42874.24

TOP : SMAX= 41300.99 SMIN= 3488.38 TMAX= 18906.30 ANGLE= -0.8BOTT: SMAX= 42874.24 SMIN= 3787.25 TMAX= 19543.50 ANGLE= -1.2

91 4 14.20 -10.26 0.04 0.03 -0.0128183.86 28061.26 28424.34 2007.57 3462.3228963.74 28777.50




101 4 0.00 1.14 0.00 0.00 0.025356.82 5150.93 0.00 0.00 3033.326185.52 5947.78


111 4 -14.20 -10.26 -0.04 -0.03 -0.0128183.86 28061.26 -28424.34 -2007.57 3462.3228963.74 28777.50

TOP : SMAX= -1630.57 SMIN= -28963.74 TMAX= 13666.59 ANGLE= 82.7BOTT: SMAX= -1492.00 SMIN= -28777.50 TMAX= 13642.75 ANGLE= 82.6:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 14




121 4 -21.02 14.62 0.33 0.06 0.0639671.99 41111.66 -42074.63 -3650.80 -692.9641300.99 42874.24


131 4 -21.02 -14.62 0.33 0.06 -0.0639671.99 41111.66 -42074.63 -3650.80 692.9641300.99 42874.24

TOP : SMAX= -3488.38 SMIN= -41300.99 TMAX= 18906.30 ANGLE= 89.2BOTT: SMAX= -3787.25 SMIN= -42874.24 TMAX= 19543.50 ANGLE= 88.8


4.287424E+04 -4.287424E+04 1.954350E+04 4.111166E+04 4.287424E+04PLATE NO. 71 121 71 71 71CASE NO. 4 4 4 4 4********************END OF ELEMENT FORCES********************72. FINISH:A CANTILEVER BEAM OF TUBULAR SECTION -- PAGE NO. 15

* FILE: PLATE01.STD*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:29:26 ****


Static Element 2ObjectiveTo find the free end deflection due to a joint load on a Cantilever beam modeled usingPlate/shell elements.

152 — STAAD.Pro


Static Element 2

ReferenceHand calculation.

ProblemUsing the finite element method calculate the deflection of the free end of the cantilever beam.

E = 4,278 ksi

h = 10 in

b = 5 in

Figure 4-4: Fixed support beam with temperature load

Theoretical SolutionMoment of Inertia:

I = (5 in)(10 in)3/12 = 416.7 in4

Deflection at free end:

δ = PL3/(3EI) = (2k)(60in)3/[3(4,278 ksi)(416.7 in4)] = 0.0808 in

Comparison


Deflection at node B (in) 0.0808 0.08246 2.1%

Table 4-2: Comparison of results for static element no.2

Note: In the STAAD model, two load cases are used. In case 1, the uniform expansion is applied.In case 2, the temperature change between top and bottom flanges is applied.

STAAD InputSTAAD SPACE :A CANTILEVER BEAM* FILE: PLATE02.STD**REFERENCE : HAND CALCULATION*UNITS KIPS INCHESJOINT COORDINATES1 0. 0. 0. 145 60. 0. 0. 62 0. 2.0 0. 146 60. 2.0 0. 63 0. 4.0 0. 147 60. 4.0 0. 64 0. 6.0 0. 148 60. 6.0 0. 6



5 0. 8.0 0. 149 60. 8.0 0. 66 0. 10.0 0. 150 60. 10. 0. 6*ELEMENT INCIDENCES1 7 1 2 8 TO 116 5 62 8 2 3 9 TO 117 5 63 9 3 4 10 TO 118 5 64 10 4 5 11 TO 119 5 65 11 5 6 12 TO 120 5 6ELEMENT PROPERTIES1 TO 120 THICKNESS 5.ELEMENT PLANE STRESS1 TO 120CONSTANTSE 4278. ALL*SUPPORTS1 2 5 6 FIXED BUT FY3 4 FIXED*LOADING 1 VERTICAL JOINT LOADSJOINTS LOADS145 146 147 148 149 150 FY -0.33333333*PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 145 TO 150FINISH



1. STAAD SPACE :A CANTILEVER BEAMINPUT FILE: PLATE02.STD

2. * FILE: PLATE02.STD3. *4. *REFERENCE : HAND CALCULATION5. *6. UNITS KIPS INCHES7. JOINT COORDINATES8. 1 0. 0. 0. 145 60. 0. 0. 69. 2 0. 2.0 0. 146 60. 2.0 0. 610. 3 0. 4.0 0. 147 60. 4.0 0. 611. 4 0. 6.0 0. 148 60. 6.0 0. 612. 5 0. 8.0 0. 149 60. 8.0 0. 613. 6 0. 10.0 0. 150 60. 10. 0. 614. *15. ELEMENT INCIDENCES16. 1 7 1 2 8 TO 116 5 617. 2 8 2 3 9 TO 117 5 618. 3 9 3 4 10 TO 118 5 619. 4 10 4 5 11 TO 119 5 620. 5 11 5 6 12 TO 120 5 621. ELEMENT PROPERTIES

154 — STAAD.Pro


Static Element 2

22. 1 TO 120 THICKNESS 5.23. ELEMENT PLANE STRESS24. 1 TO 12025. CONSTANTS26. E 4278. ALL27. *28. SUPPORTS29. 1 2 5 6 FIXED BUT FY30. 3 4 FIXED31. *32. LOADING 1 VERTICAL JOINT LOADS33. JOINTS LOADS34. 145 146 147 148 149 150 FY -0.3333333335. *36. PERFORM ANALYSIS:A CANTILEVER BEAM -- PAGE NO. 2

* FILE: PLATE02.STD







*WARNING- ZERO STIFFNESS IN DIRECTION 4 AT JOINT 7 EQN.NO. 5*WARNING- ZERO STIFFNESS IN DIRECTION 5 AT JOINT 7 EQN.NO. 6*WARNING- ZERO STIFFNESS IN DIRECTION 3 AT JOINT 13 EQN.NO. 10*WARNING- ZERO STIFFNESS IN DIRECTION 4 AT JOINT 13 EQN.NO. 11*WARNING- ZERO STIFFNESS IN DIRECTION 5 AT JOINT 13 EQN.NO. 12*WARNING- ZERO STIFFNESS IN DIRECTION 3 AT JOINT 19 EQN.NO. 16*WARNING- ZERO STIFFNESS IN DIRECTION 4 AT JOINT 19 EQN.NO. 17*WARNING- ZERO STIFFNESS IN DIRECTION 5 AT JOINT 19 EQN.NO. 18*WARNING- ZERO STIFFNESS IN DIRECTION 3 AT JOINT 25 EQN.NO. 22*WARNING- ZERO STIFFNESS IN DIRECTION 4 AT JOINT 25 EQN.NO. 23*WARNING- ZERO STIFFNESS IN DIRECTION 5 AT JOINT 25 EQN.NO. 24

**WARNING - THERE WERE MORE THAN 12 DOF WITH ZERO STIFFNESS.THE FIRST 12 ARE LISTED ABOVE.TOTAL # TRANSLATIONAL= 144 TOTAL # ROTATIONAL= 288

37. PRINT JOINT DISPLACEMENTS LIST 145 TO 150JOINT DISPLACE LIST 145

:A CANTILEVER BEAM -- PAGE NO. 3* FILE: PLATE02.STD



145 1 -0.01016 -0.08255 0.00000 0.00000 0.00000 -0.00188146 1 -0.00605 -0.08249 0.00000 0.00000 0.00000 -0.00177147 1 -0.00201 -0.08246 0.00000 0.00000 0.00000 -0.00174148 1 0.00201 -0.08246 0.00000 0.00000 0.00000 -0.00174149 1 0.00605 -0.08249 0.00000 0.00000 0.00000 -0.00177150 1 0.01016 -0.08255 0.00000 0.00000 0.00000 -0.00188************** END OF LATEST ANALYSIS RESULT **************



38. FINISH:A CANTILEVER BEAM -- PAGE NO. 4



Static Element 3ObjectiveDeflection and moments for plate-bending finite element.

ReferenceSimple hand calculation by considering the entire structure as a cantilever beam.

ProblemA simple cantilever plate is divided into 12 4-noded finite elements. A uniform pressure load isapplied and the maximum deflection at the tip of the cantilever and the maximum bending atthe support are calculated.

t = 25 mm

w = 5 N/mm2

156 — STAAD.Pro


Static Element 3

Figure 4-5: Model

Comparison


Max. Deflection (mm) 18.51 18.20 none

Max. Moment (kN-m) 22.50 22.50 none

Table 4-3: Comparison of results for plate bending finite element

Theoretical SolutionMaximum deflection is equal to WL3/8EI, where:

⋅

⋅

( )( )∆ = = = 18.51 mmmax

5 300 100 (300)

8 210 10

4050(10)

218.75(10)

3

3 100 253

12

9

9

Maximum Moment:

⋅M = = = 22.5(10) NmmWL

max 2

5(300)(100)(300)

2

6

STAAD Input

Tip: You can copy and paste this content directly into a .std file to run in STAAD.Pro.

STAAD SPACE FINITE ELEMENT VERIFICATION** FILE : PLATE03.STD** DEFLECTION OF A CANTILEVER PLATE UNDER UNIFORM PRESSURE.* COMPARISON WITH ESTABLISHED FORMULA (WL^3/8EI)*UNIT KNS MMS



JOINT COORDINATES1 0 0 0 7 300 0 0REPEAT 2 0 50 0*ELEMENT INCIDENCE1 1 2 9 8 TO 6REPEAT 1 6 7*ELEMENT PROP1 TO 12 THICK 25.0*CONSTANTE 210.0 ALLPOISSON STEEL ALL*SUPPORT1 8 15 FIXED*UNIT NEWTONLOAD 1 5N/SQ.MM. UNIFORM LOADELEMENT LOAD1 TO 12 PRESSURE 5.0*PERFORM ANALYSIS*PRINT DISPLACEMENT LIST 14*UNIT KN METERPRINT REACTIONFINISH



1. STAAD SPACE FINITE ELEMENT VERIFICATIONINPUT FILE: PLATE03.STD

2. *3. * FILE : PLATE03.STD4. *5. * DEFLECTION OF A CANTILEVER PLATE UNDER UNIFORM PRESSURE.6. * COMPARISON WITH ESTABLISHED FORMULA (WL^3/8EI)7. *8. UNIT KNS MMS9. JOINT COORDINATES10. 1 0 0 0 7 300 0 011. REPEAT 2 0 50 012. *13. ELEMENT INCIDENCE14. 1 1 2 9 8 TO 615. REPEAT 1 6 716. *17. ELEMENT PROP18. 1 TO 12 THICK 25.0

158 — STAAD.Pro


Static Element 3

19. *20. CONSTANT21. E 210.0 ALL22. POISSON STEEL ALL23. *24. SUPPORT25. 1 8 15 FIXED26. *27. UNIT NEWTON28. LOAD 1 5N/SQ.MM. UNIFORM LOAD29. ELEMENT LOAD30. 1 TO 12 PRESSURE 5.031. *32. PERFORM ANALYSISFINITE ELEMENT VERIFICATION -- PAGE NO. 2

*





33. *34. PRINT DISPLACEMENT LIST 14

DISPLACE LIST 14FINITE ELEMENT VERIFICATION -- PAGE NO. 3

*



14 1 0.0000 0.0000 1.8159 0.0000 -0.0813 0.0000************** END OF LATEST ANALYSIS RESULT **************35. *36. UNIT KN METER37. PRINT REACTION

REACTIONFINITE ELEMENT VERIFICATION -- PAGE NO. 4

*

SUPPORT REACTIONS -UNIT KN METE STRUCTURE TYPE = SPACE-----------------


1 1 0.00 0.00 -18.91 -1.54 5.47 0.008 1 0.00 0.00 -112.19 0.00 11.56 0.0015 1 0.00 0.00 -18.91 1.54 5.47 0.00

************** END OF LATEST ANALYSIS RESULT **************38. FINISHFINITE ELEMENT VERIFICATION -- PAGE NO. 5






Static Element 4ObjectiveUsing plate/shell elements, find maximum bending stress due to a force couple on a curvedcantilever beam.

ReferenceTimoshenko, S., Strength of Materials, Part I, 3rd Edition, Van Nostrand Co., 1956.

ProblemFind the maximum bending stress

E = 3000.0 ksi.

Poisson’s ratio = 0.3.

t = 1.0 in.

P = 100 lbs

160 — STAAD.Pro


Static Element 4

Figure 4-6: Cantilevered, curved plate with coupling load at free end

Comparison


Inside stress (psi) 655.0 634.8 3.1%

Outside stress (psi) 555.0 556.5 none

Table 4-4: Comparison of results for problem

STAAD Input


STAAD SPACE :CURVED BEAM WITH PLATE ELEMENTS* FILE: PLATE04.STD** REFERENCE: TIMOSHENKO, S., "STENGTH OF MATERIALS, PART I, ELEMENTARY* THEORY AND PROBLEMS", 3RD EDITION, D. VAN NOSTRAND CO.,* INC., NEW YORK, 1956.*UNIT INCHES POUND



JOINT COORDINATES1 4.5 0. 0.; 2 0. 4.5 0.; 3 0.781 4.432 0.; 4 1.539 4.229 0.5 2.25 3.897 0.; 6 2.893 3.447 0.; 7 3.447 2.893 0.; 8 3.897 2.25 0.9 4.229 1.539 0.; 10 4.432 0.781 0.; 11 4.25 0. 0.0; 12 0. 4.25 0.013 0.738 4.185 0.0; 14 1.454 3.994 0.0; 15 2.125 3.681 0.016 2.732 3.256 0.0; 17 3.256 2.732 0.0; 18 3.681 2.125 0.019 3.994 1.454 0.0; 20 4.185 0.738 0.0; 21 4. 0. 0.0; 22 0. 4. 0.023 0.695 3.939 0.0; 24 1.368 3.759 0.0; 25 2. 3.464 0.026 2.571 3.064 0.0; 27 3.064 2.571 0.0; 28 3.464 2. 0.029 3.759 1.368 0.0; 30 3.939 0.695 0.0; 31 3.75 0. 0.032 0. 3.75 0.0; 33 0.651 3.693 0.0; 34 1.283 3.524 0.035 1.875 3.248 0.0; 36 2.41 2.873 0.0; 37 2.873 2.41 0.038 3.248 1.875 0.0; 39 3.524 1.283 0.0; 40 3.693 0.651 0.041 3.5 0. 0.0; 42 0. 3.5 0.0; 43 0.608 3.447 0.0; 44 1.197 3.289 0.045 1.75 3.031 0.0; 46 2.25 2.681 0.0; 47 2.681 2.25 0.048 3.031 1.75 0.0; 49 3.289 1.197 0.0; 50 3.447 0.608 0.0ELEMENT INCIDENCES1 2 3 13 12; 2 3 4 14 13; 3 4 5 15 14; 4 5 6 16 15; 5 6 7 17 166 7 8 18 17; 7 8 9 19 18; 8 9 10 20 19; 9 10 1 11 20; 10 12 13 23 2211 13 14 24 23; 12 14 15 25 24; 13 15 16 26 25; 14 16 17 27 2615 17 18 28 27; 16 18 19 29 28; 17 19 20 30 29; 18 20 11 21 3019 22 23 33 32; 20 23 24 34 33; 21 24 25 35 34; 22 25 26 36 3523 26 27 37 36; 24 27 28 38 37; 25 28 29 39 38; 26 29 30 40 3927 30 21 31 40; 28 32 33 43 42; 29 33 34 44 43; 30 34 35 45 4431 35 36 46 45; 32 36 37 47 46; 33 37 38 48 47; 34 38 39 49 4835 39 40 50 49; 36 40 31 41 50ELEMENT PROPERTY1 TO 36 TH 1.CONSTANTSE 30000000. ALLPOISSONS .3 ALLSUPPORTS1 11 21 31 41 FIXEDLOAD 1 100 IN-IBJOINT LOAD2 FX 100.42 FX -100.PERFORM ANALYSISPRINT SUPPORT REACTIONSPRINT ELEMENT JOINT STRESSES LIST 9 36FINISH



1. STAAD SPACE :CURVED BEAM WITH PLATE ELEMENTSINPUT FILE: PLATE04.STD

2. * FILE: PLATE04.STD3. *4. * REFERENCE: TIMOSHENKO, S., "STENGTH OF MATERIALS, PART I, ELEMENTARY5. * THEORY AND PROBLEMS", 3RD EDITION, D. VAN NOSTRAND CO.,6. * INC., NEW YORK, 1956.7. *

162 — STAAD.Pro


Static Element 4

8. UNIT INCHES POUND9. JOINT COORDINATES10. 1 4.5 0. 0.; 2 0. 4.5 0.; 3 0.781 4.432 0.; 4 1.539 4.229 0.11. 5 2.25 3.897 0.; 6 2.893 3.447 0.; 7 3.447 2.893 0.; 8 3.897 2.25 0.12. 9 4.229 1.539 0.; 10 4.432 0.781 0.; 11 4.25 0. 0.0; 12 0. 4.25 0.013. 13 0.738 4.185 0.0; 14 1.454 3.994 0.0; 15 2.125 3.681 0.014. 16 2.732 3.256 0.0; 17 3.256 2.732 0.0; 18 3.681 2.125 0.015. 19 3.994 1.454 0.0; 20 4.185 0.738 0.0; 21 4. 0. 0.0; 22 0. 4. 0.016. 23 0.695 3.939 0.0; 24 1.368 3.759 0.0; 25 2. 3.464 0.017. 26 2.571 3.064 0.0; 27 3.064 2.571 0.0; 28 3.464 2. 0.018. 29 3.759 1.368 0.0; 30 3.939 0.695 0.0; 31 3.75 0. 0.019. 32 0. 3.75 0.0; 33 0.651 3.693 0.0; 34 1.283 3.524 0.020. 35 1.875 3.248 0.0; 36 2.41 2.873 0.0; 37 2.873 2.41 0.021. 38 3.248 1.875 0.0; 39 3.524 1.283 0.0; 40 3.693 0.651 0.022. 41 3.5 0. 0.0; 42 0. 3.5 0.0; 43 0.608 3.447 0.0; 44 1.197 3.289 0.023. 45 1.75 3.031 0.0; 46 2.25 2.681 0.0; 47 2.681 2.25 0.024. 48 3.031 1.75 0.0; 49 3.289 1.197 0.0; 50 3.447 0.608 0.025. ELEMENT INCIDENCES26. 1 2 3 13 12; 2 3 4 14 13; 3 4 5 15 14; 4 5 6 16 15; 5 6 7 17 1627. 6 7 8 18 17; 7 8 9 19 18; 8 9 10 20 19; 9 10 1 11 20; 10 12 13 23 2228. 11 13 14 24 23; 12 14 15 25 24; 13 15 16 26 25; 14 16 17 27 2629. 15 17 18 28 27; 16 18 19 29 28; 17 19 20 30 29; 18 20 11 21 3030. 19 22 23 33 32; 20 23 24 34 33; 21 24 25 35 34; 22 25 26 36 3531. 23 26 27 37 36; 24 27 28 38 37; 25 28 29 39 38; 26 29 30 40 3932. 27 30 21 31 40; 28 32 33 43 42; 29 33 34 44 43; 30 34 35 45 4433. 31 35 36 46 45; 32 36 37 47 46; 33 37 38 48 47; 34 38 39 49 4834. 35 39 40 50 49; 36 40 31 41 5035. ELEMENT PROPERTY36. 1 TO 36 TH 1.37. CONSTANTS38. E 30000000. ALL:CURVED BEAM WITH PLATE ELEMENTS -- PAGE NO. 2

* FILE: PLATE04.STD39. POISSONS .3 ALL40. SUPPORTS41. 1 11 21 31 41 FIXED42. LOAD 1 100 IN-IB43. JOINT LOAD44. 2 FX 100.45. 42 FX -100.46. PERFORM ANALYSIS






:CURVED BEAM WITH PLATE ELEMENTS -- PAGE NO. 3* FILE: PLATE04.STD

SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = SPACE-----------------


1 1 -15.30 61.91 0.00 0.00 0.00 -2.0911 1 3.80 69.53 0.00 0.00 0.00 0.7221 1 12.47 5.36 0.00 0.00 0.00 1.2131 1 11.58 -66.95 0.00 0.00 0.00 1.7541 1 -12.55 -69.85 0.00 0.00 0.00 -1.59



************** END OF LATEST ANALYSIS RESULT **************48. PRINT ELEMENT JOINT STRESSES LIST 9 36

ELEMENT JOINT STRESSES LIST:CURVED BEAM WITH PLATE ELEMENTS -- PAGE NO. 4

* FILE: PLATE04.STDELEMENT STRESSES FORCE,LENGTH UNITS= POUN INCH----------------



9 1 0.00 0.00 0.00 0.00 0.00432.15 432.15 -433.11 -2.49 8.94433.30 433.30

TOP : SMAX= -2.31 SMIN= -433.30 TMAX= 215.50 ANGLE= 88.8BOTT: SMAX= -2.31 SMIN= -433.30 TMAX= 215.50 ANGLE= 88.8JOINT 0.00 0.00 0.00 0.00 0.0010 592.15 592.15 -560.35 58.12 15.37

TOP : SMAX= 58.50 SMIN= -560.73 TMAX= 309.62 ANGLE= 88.6BOTT: SMAX= 58.50 SMIN= -560.73 TMAX= 309.62 ANGLE= 88.6JOINT 0.00 0.00 0.00 0.00 0.00

1 527.90 527.90 -556.47 -63.65 11.40TOP : SMAX= -63.39 SMIN= -556.73 TMAX= 246.67 ANGLE= 88.7BOTT: SMAX= -63.39 SMIN= -556.73 TMAX= 246.67 ANGLE= 88.7JOINT 0.00 0.00 0.00 0.00 0.0011 285.05 285.05 -310.92 -64.85 13.47

TOP : SMAX= -64.11 SMIN= -311.65 TMAX= 123.77 ANGLE= 86.9BOTT: SMAX= -64.11 SMIN= -311.65 TMAX= 123.77 ANGLE= 86.9JOINT 0.00 0.00 0.00 0.00 0.0020 351.99 351.99 -318.48 58.96 8.48


36 1 0.00 0.00 0.00 0.00 0.00457.10 457.10 473.43 34.66 2.24473.44 473.44

TOP : SMAX= 473.44 SMIN= 34.64 TMAX= 219.40 ANGLE= 0.3BOTT: SMAX= 473.44 SMIN= 34.64 TMAX= 219.40 ANGLE= 0.3JOINT 0.00 0.00 0.00 0.00 0.0040 314.58 314.58 298.80 -24.94 -23.18

TOP : SMAX= 300.45 SMIN= -26.59 TMAX= 163.52 ANGLE= -4.1BOTT: SMAX= 300.45 SMIN= -26.59 TMAX= 163.52 ANGLE= -4.1JOINT 0.00 0.00 0.00 0.00 0.0031 247.25 247.25 282.26 108.74 10.51

TOP : SMAX= 282.90 SMIN= 108.11 TMAX= 87.39 ANGLE= 3.5BOTT: SMAX= 282.90 SMIN= 108.11 TMAX= 87.39 ANGLE= 3.5JOINT 0.00 0.00 0.00 0.00 0.0041 594.55 594.55 634.80 95.42 25.72

TOP : SMAX= 636.02 SMIN= 94.20 TMAX= 270.91 ANGLE= 2.7BOTT: SMAX= 636.02 SMIN= 94.20 TMAX= 270.91 ANGLE= 2.7JOINT 0.00 0.00 0.00 0.00 0.0050 680.99 680.99 656.97 -43.84 -21.63

TOP : SMAX= 657.64 SMIN= -44.51 TMAX= 351.08 ANGLE= -1.8BOTT: SMAX= 657.64 SMIN= -44.51 TMAX= 351.08 ANGLE= -1.8:CURVED BEAM WITH PLATE ELEMENTS -- PAGE NO. 5

* FILE: PLATE04.STD**** MAXIMUM STRESSES AMONG SELECTED PLATES AND CASES ****


6.576412E+02 -5.607281E+02 3.510752E+02 4.571006E+02 4.734369E+02PLATE NO. 36 9 36 36 36CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************49. FINISH:CURVED BEAM WITH PLATE ELEMENTS -- PAGE NO. 6

* FILE: PLATE04.STD

164 — STAAD.Pro


Static Element 4



Static Element 5ObjectiveA simply-supported equilateral triangle is subjected to a linear thermal gradient. The deflectionsand bending moments are calculated.

ReferenceTimoshenko, S. and Woinowsky-Krieger, S., Theory of Plates and Shells, McGraw Hill, 1959, pp. 92-97.

ProblemThe purpose of this example is to demonstrate the ability of STAAD to calculate the response ofa structure when thermally-loaded plate elements are utilized. The STAAD model considers one-half of the plate, modeled using 49 quad elements and seven tri plate elements. For specifyinginclined supports, an auxiliary coordinate system is defined along the edge (see second figurebelow) not parallel to a global axis.

E = 10 x 106 lb/in2

υ = 0.3

α = 12 (10)-6 in/in °F

ΔT = Ttop – Tbottom = 4500

t = 0.1 inches

a = 3.0 inches



Figure 4-7: Simply-supported, equilateral triangle with thermal load

166 — STAAD.Pro


Static Element 5

Figure 4-8: Finite element model of a simply-supported, equilateral triangle

Comparison


Z deflection at center ofelement along x-axis (in)

Node 6 0.02331 0.02331 none

Maximum (magnitude)bending moment along x-axis

(in-lb/in)

Mx atElement 8

-36.16 -36.15 none

Mx atElement14

-64.29 -65.64 2.1%

My atElement 1

-42.59 -42.59 none

My atElement 8

-8.839 -8.838 none

Twisting moment along y-axis at center of elements

(in-lb/in)

Mxy atElement55

36.19 36.06 none


The results show excellent agreement for displacements and for quad plate element stressesexcept in the few instances where the magnitude of the answers is very small. The tri plate



elements are lower order elements, and it is therefore not unusual for these elements to showpoorer agreement than quads where mesh size is smaller.

Theoretical SolutionFrom page 96 of the reference:

M = − 1 +x

α TEt x∆

24

32 ′

( )x= − 1 + = −22.5 1 +

x12(10) 450.0 10(10) (0.1)

24

3

3

′

−6 6 2′

M x= − 1 − = −22.5 1 −y

α TEt x∆

24

3 ′2 ′

M =xyα TEt y∆

8

2 ( )y y= = 22.5

12(10) 450.0 10(10) (0.1)

8(3)

−6 6 2

w x y x ax ay= − 3 − − +

α T ν

t

∆ (1 + )

4

′ 3 2 ′ ′ 2 2 4

27

3

x y x x y= 0.00585 − 3 − 3 − 3 + 4′3

2 ′ ′2

2

The origin of the x' axis in the reference is located at a/3, or 1 inch from the edge. Therefore:

x' = x-1

Upon substitution:

Mx = -22.5x

My = -22.5 (2 - x)

Mxy = 22.5y

w = 0.00585 (x3 – 6x2 + 9x – 3y2x)

STAAD Input


STAAD SPACE :SIMPLY SUPPORTED PLATE THERMAL* FILE: PLATE05.STD** AN EQUILATERAL TRIANGLE WITH LINEAR THERMAL GRADIENT* STARDYNE VERIFICATION SVM18** EXPECTED ANSWERS* DEFLECTION OF NODE 6 , IN THE X3 DIRECTION* THEORY .02331* STARDYNE .02331* STAAD .02331** INTERNAL MOMENTS IN QUAD PLATE NO 8* MX MY* THEORY -36.16 -8.864* STARDYNE -36.16 -8.864* STAAD -36.15 -8.84*INPUT WIDTH 79UNIT INCHES POUNDJOINT COORDINATES1 0 0 0; 2 0.214286 0 0; 3 0.428571 0 0; 4 0.642857 0 0; 5 0.857143 0 06 1.07143 0 0; 7 1.28571 0 0; 8 1.5 0 0; 9 1.71429 0 0; 10 1.92857 0 011 2.14286 0 0; 12 2.35714 0 0; 13 2.57143 0 0; 14 2.78571 0 015 3 0 0; 16 2.78571 0.123718 0; 17 0 0.247436 0

168 — STAAD.Pro


Static Element 5

18 0.214286 0.247436 0; 19 0.428571 0.247436 0; 20 0.642857 0.247436 021 0.857143 0.247436 0; 22 1.07143 0.247436 0; 23 1.28571 0.247436 024 1.5 0.247436 0; 25 1.71429 0.247436 0; 26 1.92857 0.247436 027 2.14286 0.247436 0; 28 2.35714 0.247436 0; 29 2.57143 0.247436 030 2.35714 0.371154 0; 31 0 0.494872 0; 32 0.214286 0.494872 033 0.428571 0.494872 0; 34 0.642857 0.494872 0; 35 0.857143 0.494872 036 1.07143 0.494872 0; 37 1.28571 0.494872 0; 38 1.5 0.494872 039 1.71429 0.494872 0; 40 1.92857 0.494872 0; 41 2.14286 0.494872 042 1.92857 0.61859 0; 43 0 0.742307 0; 44 0.214286 0.742307 045 0.428571 0.742307 0; 46 0.642857 0.742307 0; 47 0.857143 0.742307 048 1.07143 0.742307 0; 49 1.28571 0.742307 0; 50 1.5 0.742307 051 1.71429 0.742307 0; 52 1.5 0.866025 0; 53 0 0.989743 054 0.214286 0.989743 0; 55 0.428571 0.989743 0; 56 0.642857 0.989743 057 0.857143 0.989743 0; 58 1.07143 0.989743 0; 59 1.28571 0.989743 060 1.07143 1.11346 0; 61 0 1.23718 0; 62 0.214286 1.23718 063 0.428571 1.23718 0; 64 0.642857 1.23718 0; 65 0.857143 1.23718 066 0.642857 1.3609 0; 67 0 1.48461 0; 68 0.214285 1.48461 069 0.428571 1.48461 0; 70 0.214286 1.60833 0; 71 0 1.73205 0*72 3 1.73205 0ELEMENT INCIDENCES SHELL1 1 2 18 17; 2 2 3 19 18; 3 3 4 20 19; 4 4 5 21 20; 5 5 6 22 216 6 7 23 22; 7 7 8 24 23; 8 8 9 25 24; 9 9 10 26 25; 10 10 11 27 2611 11 12 28 27; 12 12 13 29 28; 13 13 14 16 29; 14 14 15 1615 17 18 32 31; 16 18 19 33 32; 17 19 20 34 33; 18 20 21 35 3419 21 22 36 35; 20 22 23 37 36; 21 23 24 38 37; 22 24 25 39 3823 25 26 40 39; 24 26 27 41 40; 25 27 28 30 41; 26 28 29 3027 31 32 44 43; 28 32 33 45 44; 29 33 34 46 45; 30 34 35 47 4631 35 36 48 47; 32 36 37 49 48; 33 37 38 50 49; 34 38 39 51 5035 39 40 42 51; 36 40 41 42; 37 43 44 54 53; 38 44 45 55 5439 45 46 56 55; 40 46 47 57 56; 41 47 48 58 57; 42 48 49 59 5843 49 50 52 59; 44 50 51 52; 45 53 54 62 61; 46 54 55 63 6247 55 56 64 63; 48 56 57 65 64; 49 57 58 60 65; 50 58 59 6051 61 62 68 67; 52 62 63 69 68; 53 63 64 66 69; 54 64 65 6655 67 68 70 71; 56 68 69 70DEFINE MATERIAL STARTISOTROPIC ALUMINUME 1E+007POISSON 0.3ALPHA 1.2E-005END DEFINE MATERIALCONSTANTSMATERIAL ALUMINUM MEMB 1 TO 56ELEMENT PROPERTY1 TO 56 THICK 0.1SUPPORTS16 29 30 41 42 51 52 59 60 65 66 69 70 INCL REFJT 15 FIXED BUT FX MX MZ2 TO 14 FIXED BUT FX FZ MY MZ17 31 43 53 61 67 FIXED BUT FY MY MZ1 FIXED BUT MY MZ15 71 FIXED*72 FIXEDLOAD 1 UNIFORM BENDING TEMPERATURETEMPERATURE LOAD1 TO 56 TEMP 0.0 450.PERFORM ANALYSIS PRINT STATIC CHECKPRINT JOINT DISP LIST 2 TO 14PRINT ELEMENT JOINT STRESSES LIST 8FINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 *



* Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:29:31 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE :SIMPLY SUPPORTED PLATE THERMALINPUT FILE: PLATE05.STD

2. * FILE: PLATE05.STD3. *4. * AN EQUILATERAL TRIANGLE WITH LINEAR THERMAL GRADIENT5. * STARDYNE VERIFICATION SVM186. *7. * EXPECTED ANSWERS8. * DEFLECTION OF NODE 6 , IN THE X3 DIRECTION9. * THEORY .0233110. * STARDYNE .0233111. * STAAD .0233112. *13. * INTERNAL MOMENTS IN QUAD PLATE NO 814. * MX MY15. * THEORY -36.16 -8.86416. * STARDYNE -36.16 -8.86417. * STAAD -36.15 -8.8418. *19. INPUT WIDTH 7920. UNIT INCHES POUND21. JOINT COORDINATES22. 1 0 0 0; 2 0.214286 0 0; 3 0.428571 0 0; 4 0.642857 0 0; 5 0.857143 0 023. 6 1.07143 0 0; 7 1.28571 0 0; 8 1.5 0 0; 9 1.71429 0 0; 10 1.92857 0 024. 11 2.14286 0 0; 12 2.35714 0 0; 13 2.57143 0 0; 14 2.78571 0 025. 15 3 0 0; 16 2.78571 0.123718 0; 17 0 0.247436 026. 18 0.214286 0.247436 0; 19 0.428571 0.247436 0; 20 0.642857 0.247436 027. 21 0.857143 0.247436 0; 22 1.07143 0.247436 0; 23 1.28571 0.247436 028. 24 1.5 0.247436 0; 25 1.71429 0.247436 0; 26 1.92857 0.247436 029. 27 2.14286 0.247436 0; 28 2.35714 0.247436 0; 29 2.57143 0.247436 030. 30 2.35714 0.371154 0; 31 0 0.494872 0; 32 0.214286 0.494872 031. 33 0.428571 0.494872 0; 34 0.642857 0.494872 0; 35 0.857143 0.494872 032. 36 1.07143 0.494872 0; 37 1.28571 0.494872 0; 38 1.5 0.494872 033. 39 1.71429 0.494872 0; 40 1.92857 0.494872 0; 41 2.14286 0.494872 034. 42 1.92857 0.61859 0; 43 0 0.742307 0; 44 0.214286 0.742307 035. 45 0.428571 0.742307 0; 46 0.642857 0.742307 0; 47 0.857143 0.742307 036. 48 1.07143 0.742307 0; 49 1.28571 0.742307 0; 50 1.5 0.742307 037. 51 1.71429 0.742307 0; 52 1.5 0.866025 0; 53 0 0.989743 038. 54 0.214286 0.989743 0; 55 0.428571 0.989743 0; 56 0.642857 0.989743 0:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 2

* FILE: PLATE05.STD39. 57 0.857143 0.989743 0; 58 1.07143 0.989743 0; 59 1.28571 0.989743 040. 60 1.07143 1.11346 0; 61 0 1.23718 0; 62 0.214286 1.23718 041. 63 0.428571 1.23718 0; 64 0.642857 1.23718 0; 65 0.857143 1.23718 042. 66 0.642857 1.3609 0; 67 0 1.48461 0; 68 0.214285 1.48461 043. 69 0.428571 1.48461 0; 70 0.214286 1.60833 0; 71 0 1.73205 044. *72 3 1.73205 045. ELEMENT INCIDENCES SHELL46. 1 1 2 18 17; 2 2 3 19 18; 3 3 4 20 19; 4 4 5 21 20; 5 5 6 22 2147. 6 6 7 23 22; 7 7 8 24 23; 8 8 9 25 24; 9 9 10 26 25; 10 10 11 27 2648. 11 11 12 28 27; 12 12 13 29 28; 13 13 14 16 29; 14 14 15 1649. 15 17 18 32 31; 16 18 19 33 32; 17 19 20 34 33; 18 20 21 35 3450. 19 21 22 36 35; 20 22 23 37 36; 21 23 24 38 37; 22 24 25 39 3851. 23 25 26 40 39; 24 26 27 41 40; 25 27 28 30 41; 26 28 29 3052. 27 31 32 44 43; 28 32 33 45 44; 29 33 34 46 45; 30 34 35 47 4653. 31 35 36 48 47; 32 36 37 49 48; 33 37 38 50 49; 34 38 39 51 5054. 35 39 40 42 51; 36 40 41 42; 37 43 44 54 53; 38 44 45 55 54

170 — STAAD.Pro


Static Element 5

55. 39 45 46 56 55; 40 46 47 57 56; 41 47 48 58 57; 42 48 49 59 5856. 43 49 50 52 59; 44 50 51 52; 45 53 54 62 61; 46 54 55 63 6257. 47 55 56 64 63; 48 56 57 65 64; 49 57 58 60 65; 50 58 59 6058. 51 61 62 68 67; 52 62 63 69 68; 53 63 64 66 69; 54 64 65 6659. 55 67 68 70 71; 56 68 69 7060. DEFINE MATERIAL START61. ISOTROPIC ALUMINUM62. E 1E+00763. POISSON 0.364. ALPHA 1.2E-00565. END DEFINE MATERIAL66. CONSTANTS67. MATERIAL ALUMINUM MEMB 1 TO 5668. ELEMENT PROPERTY69. 1 TO 56 THICK 0.170. SUPPORTS71. 16 29 30 41 42 51 52 59 60 65 66 69 70 INCL REFJT 15 FIXED BUT FX MX MZ72. 2 TO 14 FIXED BUT FX FZ MY MZ73. 17 31 43 53 61 67 FIXED BUT FY MY MZ74. 1 FIXED BUT MY MZ75. 15 71 FIXED76. *72 FIXED77. LOAD 1 UNIFORM BENDING TEMPERATURE78. TEMPERATURE LOAD79. 1 TO 56 TEMP 0.0 450.80. PERFORM ANALYSIS PRINT STATIC CHECK


NUMBER OF JOINTS 71 NUMBER OF MEMBERS 0NUMBER OF PLATES 56 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 35:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 3

* FILE: PLATE05.STD



:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 4* FILE: PLATE05.STD

STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1UNIFORM BENDING TEMPERATURE

TOTAL APPLIED LOAD 1***TOTAL APPLIED LOAD ( POUN INCH ) SUMMARY (LOADING 1 )

SUMMATION FORCE-X = 0.0000000E+00SUMMATION FORCE-Y = 0.0000000E+00SUMMATION FORCE-Z = -4.9303804E-29SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= -6.2406563E-14 MY= -5.8980595E-14 MZ= 0.0000000E+00

TOTAL REACTION LOAD 1***TOTAL REACTION LOAD( POUN INCH ) SUMMARY (LOADING 1 )

SUMMATION FORCE-X = 0.0000000E+00SUMMATION FORCE-Y = 0.0000000E+00SUMMATION FORCE-Z = -4.0794188E-12SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= -1.9667426E-12 MY= 8.2095783E-12 MZ= 0.0000000E+00

MAXIMUM DISPLACEMENTS ( INCH /RADIANS) (LOADING 1)MAXIMUMS AT NODE

X = 0.00000E+00 0Y = 0.00000E+00 0Z = 2.33148E-02 6RX= -4.58405E-02 52RY= -5.27664E-02 1RZ= 0.00000E+00 0

************ END OF DATA FROM INTERNAL STORAGE ************



81. PRINT JOINT DISP LIST 2 TO 14JOINT DISP LIST 2

:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 5* FILE: PLATE05.STD



2 1 0.00000 0.00000 0.00973 0.00000 -0.03853 0.000003 1 0.00000 0.00000 0.01658 0.00000 -0.02590 0.000004 1 0.00000 0.00000 0.02090 0.00000 -0.01489 0.000005 1 0.00000 0.00000 0.02303 0.00000 -0.00549 0.000006 1 0.00000 0.00000 0.02331 0.00000 0.00230 0.000007 1 0.00000 0.00000 0.02211 0.00000 0.00848 0.000008 1 0.00000 0.00000 0.01975 0.00000 0.01305 0.000009 1 0.00000 0.00000 0.01658 0.00000 0.01600 0.0000010 1 0.00000 0.00000 0.01295 0.00000 0.01735 0.0000011 1 0.00000 0.00000 0.00921 0.00000 0.01709 0.0000012 1 0.00000 0.00000 0.00570 0.00000 0.01518 0.0000013 1 0.00000 0.00000 0.00276 0.00000 0.01165 0.0000014 1 0.00000 0.00000 0.00075 0.00000 0.00672 0.00000

************** END OF LATEST ANALYSIS RESULT **************82. PRINT ELEMENT JOINT STRESSES LIST 8

ELEMENT JOINT STRESSES LIST:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 6




8 1 2.23 1.01 -36.15 -8.84 2.7919799.74 19799.74 0.00 0.00 0.0021861.08 21861.08

TOP : SMAX= -5134.01 SMIN= -21861.08 TMAX= 8363.53 ANGLE= 84.2BOTT: SMAX= 21861.08 SMIN= 5134.01 TMAX= 8363.53 ANGLE= -5.8JOINT -4.50 -1.02 -35.37 -11.73 1.92

8 18829.74 18829.74 0.00 0.00 0.00TOP : SMAX= -6945.22 SMIN= -21315.87 TMAX= 7185.32 ANGLE= 85.4BOTT: SMAX= 21315.87 SMIN= 6945.22 TMAX= 7185.32 ANGLE= -4.6JOINT -4.50 3.05 -36.95 -5.96 1.93

9 20715.56 20715.56 0.00 0.00 0.00TOP : SMAX= -3504.11 SMIN= -22244.13 TMAX= 9370.01 ANGLE= 86.4BOTT: SMAX= 22244.13 SMIN= 3504.11 TMAX= 9370.01 ANGLE= -3.6JOINT 8.97 3.05 -36.79 -5.89 3.6525 20883.86 20883.86 0.00 0.00 0.00

TOP : SMAX= -3281.80 SMIN= -22330.46 TMAX= 9524.33 ANGLE= 83.4BOTT: SMAX= 22330.46 SMIN= 3281.80 TMAX= 9524.33 ANGLE= -6.6JOINT 8.97 -1.02 -35.50 -11.77 3.6424 19168.58 19168.58 0.00 0.00 0.00

TOP : SMAX= -6732.25 SMIN= -21626.52 TMAX= 7447.13 ANGLE= 81.5BOTT: SMAX= 21626.52 SMIN= 6732.25 TMAX= 7447.13 ANGLE= -8.5


2.233046E+04 -2.233046E+04 9.524329E+03 1.979974E+04 2.186108E+04PLATE NO. 8 8 8 8 8CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************83. FINISH:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 7

* FILE: PLATE05.STD:SIMPLY SUPPORTED PLATE THERMAL -- PAGE NO. 8

172 — STAAD.Pro


Static Element 5



Static Element 6ObjectiveA circular plate is fixed along its perimeter. Using plate/shell elements, find the deflection at thecenter, maximum bending stress due to a uniformly distributed load, and a concentrated load atthe center.

ReferenceTimoshenko, S., Strength of Materials, Part II, 3rd Edition, Van Nostrand Co., 1956, pp.96, 96, 103.

ProblemThe circular plate shown below is subject to two load cases. Load 1 is a uniform pressure, w, andload 2 is a concentrated force, P, at the center. Determine:

l deflection at the center for both load cases

l bending stress at the support for both load cases

l moment at the center for load case 1

E = 30,000.0 ksi

Poisson’s ratio = 0.3

r = 40 in.

t = 1 in.

w = 6 psi.

P = 7,539.82 lbs



Figure 4-9: Finite element model of a circular plate

Comparison


LoadCase 1

σbend (psi) 7,200 6,887a 4.3%

δmax (in) (Y translation atNode 127)

-0.0874

-0.08618 1.4%

Moment at center (in-lb/in) 780 806.1b 3.4%

LoadCase 2

σbend (psi) 3,600 3,700c 2.8%

δmax (in) (Y translation atNode 127)

-0.0874

-0.08646 1.0%


a. In element 9 at node 10, My = 1,147.91 in-lb/in. This yields σbend = 1,147.91(6) = 6,887 psi.

b. In element 109 at node 127, Mx = 811.88 in-lb/in and My = 800.33 in-lb/in, the average ofwhich is 806.1 in-lb/in.

c. In element 9 at node 10, My = 616.69 in-lb/in. This yields σbend = 616.19(6) = 3,700 psi.

Theoretical SolutionCalcs

STAAD Input


STAAD SPACE :A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER* FILE: PLATE06.STD** REFERENCE: TIMOSHENKO, S., STRENGTH OF MATERIALS* PART II, ADVANCED THEORY AND PROBLEMS* PAGES 96, 97, AND 103.*INPUT WIDTH 79UNIT INCHES POUND

174 — STAAD.Pro


Static Element 6

JOINT COORDINATES1 40. 0. 0.; 2 37.588 0. -13.681; 3 30.642 0. -25.712; 4 20. 0. -34.6415 6.946 0. -39.392; 6 -6.946 0. -39.392; 7 -20. 0. -34.6418 -30.642 0. -25.711; 9 -37.588 0. -13.681; 10 -40. 0. 0.; 11 -37.588 0. 13.68112 -30.642 0. 25.712; 13 -20. 0. 34.641; 14 -6.946 0. 39.39215 6.946 0. 39.392; 16 20. 0. 34.641; 17 30.642 0. 25.711; 18 37.588 0. 13.68119 30. 0. 0.; 20 28.191 0. -10.261; 21 22.981 0. -19.284; 22 15. 0. -25.98123 5.209 0. -29.544; 24 -5.209 0. -29.544; 25 -15. 0. -25.98126 -22.981 0. -19.284; 27 -28.191 0. -10.261; 28 -30. 0. 0.29 -28.191 0. 10.261; 30 -22.981 0. 19.284; 31 -15. 0. 25.98132 -5.209 0. 29.544; 33 5.21 0. 29.544; 34 15. 0. 25.981; 35 22.981 0. 19.28436 28.191 0. 10.261; 37 20. 0. 0.; 38 18.794 0. -6.84; 39 15.321 0. -12.85640 10. 0. -17.321; 41 3.473 0. -19.696; 42 -3.473 0. -19.696; 43 -10. 0. -17.3244 -15.321 0. -12.856; 45 -18.794 0. -6.84; 46 -20. 0. 0.; 47 -18.794 0. 6.8448 -15.321 0. 12.856; 49 -10. 0. 17.321; 50 -3.473 0. 19.69651 3.473 0. 19.696; 52 10. 0. 17.32; 53 15.321 0. 12.856; 54 18.794 0. 6.8455 15. 0. 0.; 56 14.095 0. -5.13; 57 11.491 0. -9.642; 58 7.5 0. -12.9959 2.605 0. -14.772; 60 -2.605 0. -14.772; 61 -7.5 0. -12.9962 -11.491 0. -9.642; 63 -14.095 0. -5.13; 64 -15. 0. 0.; 65 -14.095 0. 5.1366 -11.491 0. 9.642; 67 -7.5 0. 12.99; 68 -2.605 0. 14.772; 69 2.605 0. 14.77270 7.5 0. 12.99; 71 11.491 0. 9.642; 72 14.095 0. 5.13; 73 10. 0. 0.74 9.397 0. -3.42; 75 7.66 0. -6.428; 76 5. 0. -8.66; 77 1.736 0. -9.84878 -1.736 0. -9.848; 79 -5. 0. -8.66; 80 -7.66 0. -6.428; 81 -9.397 0. -3.4282 -10. 0. 0.; 83 -9.397 0. 3.42; 84 -7.66 0. 6.428; 85 -5. 0. 8.6686 -1.736 0. 9.848; 87 1.737 0. 9.848; 88 5. 0. 8.66; 89 7.66 0. 6.42890 9.397 0. 3.42; 91 7. 0. 0.; 92 6.578 0. -2.394; 93 5.362 0. -4.594 3.5 0. -6.062; 95 1.216 0. -6.894; 96 -1.216 0. -6.894; 97 -3.5 0. -6.06298 -5.362 0. -4.5; 99 -6.578 0. -2.394; 100 -7. 0. 0.; 101 -6.578 0. 2.394102 -5.362 0. 4.5; 103 -3.5 0. 6.062; 104 -1.216 0. 6.894; 105 1.216 0. 6.894106 3.5 0. 6.062; 107 5.362 0. 4.5; 108 6.578 0. 2.394; 109 3. 0. 0.110 2.819 0. -1.026; 111 2.298 0. -1.928; 112 1.5 0. -2.598113 0.521 0. -2.954; 114 -0.521 0. -2.954; 115 -1.5 0. -2.598116 -2.298 0. -1.928; 117 -2.819 0. -1.026; 118 -3. 0. 0.; 119 -2.819 0. 1.026120 -2.298 0. 1.928; 121 -1.5 0. 2.598; 122 -0.521 0. 2.954; 123 0.521 0. 2.954124 1.5 0. 2.598; 125 2.298 0. 1.928; 126 2.819 0. 1.026; 127 0. 0. 0.ELEMENT INCIDENCES1 1 2 20 19; 2 2 3 21 20; 3 3 4 22 21; 4 4 5 23 22; 5 5 6 24 23; 6 6 7 25 247 7 8 26 25; 8 8 9 27 26; 9 9 10 28 27; 10 10 11 29 28; 11 11 12 30 2912 12 13 31 30; 13 13 14 32 31; 14 14 15 33 32; 15 15 16 34 33; 16 16 17 35 3417 17 18 36 35; 18 18 1 19 36; 19 19 20 38 37; 20 20 21 39 38; 21 21 22 40 3922 22 23 41 40; 23 23 24 42 41; 24 24 25 43 42; 25 25 26 44 43; 26 26 27 45 4427 27 28 46 45; 28 28 29 47 46; 29 29 30 48 47; 30 30 31 49 48; 31 31 32 50 4932 32 33 51 50; 33 33 34 52 51; 34 34 35 53 52; 35 35 36 54 53; 36 36 19 37 5437 37 38 56 55; 38 38 39 57 56; 39 39 40 58 57; 40 40 41 59 58; 41 41 42 60 5942 42 43 61 60; 43 43 44 62 61; 44 44 45 63 62; 45 45 46 64 63; 46 46 47 65 6447 47 48 66 65; 48 48 49 67 66; 49 49 50 68 67; 50 50 51 69 68; 51 51 52 70 6952 52 53 71 70; 53 53 54 72 71; 54 54 37 55 72; 55 55 56 74 73; 56 56 57 75 7457 57 58 76 75; 58 58 59 77 76; 59 59 60 78 77; 60 60 61 79 78; 61 61 62 80 7962 62 63 81 80; 63 63 64 82 81; 64 64 65 83 82; 65 65 66 84 83; 66 66 67 85 8467 67 68 86 85; 68 68 69 87 86; 69 69 70 88 87; 70 70 71 89 88; 71 71 72 90 8972 72 55 73 90; 73 73 74 92 91; 74 74 75 93 92; 75 75 76 94 93; 76 76 77 95 9477 77 78 96 95; 78 78 79 97 96; 79 79 80 98 97; 80 80 81 99 98; 81 81 82 100 9982 82 83 101 100; 83 83 84 102 101; 84 84 85 103 102; 85 85 86 104 10386 86 87 105 104; 87 87 88 106 105; 88 88 89 107 106; 89 89 90 108 10790 90 73 91 108; 91 91 92 110 109; 92 92 93 111 110; 93 93 94 112 11194 94 95 113 112; 95 95 96 114 113; 96 96 97 115 114; 97 97 98 116 11598 98 99 117 116; 99 99 100 118 117; 100 100 101 119 118; 101 101 102 120 119102 102 103 121 120; 103 103 104 122 121; 104 104 105 123 122105 105 106 124 123; 106 106 107 125 124; 107 107 108 126 125108 108 91 109 126; 109 127 109 110; 110 110 111 127; 111 127 111 112112 112 113 127; 113 127 113 114; 114 114 115 127; 115 127 115 116116 116 117 127; 117 127 117 118; 118 127 109 126; 119 126 125 127120 127 125 124; 121 124 123 127; 122 127 123 122; 123 122 121 127124 127 121 120; 125 120 119 127; 126 127 119 118ELEMENT PROPERTY1 TO 126 TH 1.



CONSTANTSE 30000000. ALLPOISSON 0.3 ALLSUPPORTS1 TO 18 FIXED*LOAD 1 UNIFORM LOADELEMENT LOAD1 TO 126 PRESSURE GY -6.0*LOAD 2 POINT LOADJOINT LOAD127 FY -7539.819*PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 127LOAD LIST 1PRINT ELEMENT JOINT STRESSES LIST 9 109LOAD LIST 2PRINT ELEMENT JOINT STRESSES LIST 9FINISH



1. STAAD SPACE :A CIRCULAR PLATE-FIXED ALONG ITS PERIMETERINPUT FILE: PLATE06.STD

2. * FILE: PLATE06.STD3. *4. * REFERENCE: TIMOSHENKO, S., STRENGTH OF MATERIALS5. * PART II, ADVANCED THEORY AND PROBLEMS6. * PAGES 96, 97, AND 103.7. *8. INPUT WIDTH 799. UNIT INCHES POUND10. JOINT COORDINATES11. 1 40. 0. 0.; 2 37.588 0. -13.681; 3 30.642 0. -25.712; 4 20. 0. -34.64112. 5 6.946 0. -39.392; 6 -6.946 0. -39.392; 7 -20. 0. -34.64113. 8 -30.642 0. -25.711; 9 -37.588 0. -13.681; 10 -40. 0. 0.; 11 -37.588 0. 13.68114. 12 -30.642 0. 25.712; 13 -20. 0. 34.641; 14 -6.946 0. 39.39215. 15 6.946 0. 39.392; 16 20. 0. 34.641; 17 30.642 0. 25.711; 18 37.588 0. 13.68116. 19 30. 0. 0.; 20 28.191 0. -10.261; 21 22.981 0. -19.284; 22 15. 0. -25.98117. 23 5.209 0. -29.544; 24 -5.209 0. -29.544; 25 -15. 0. -25.98118. 26 -22.981 0. -19.284; 27 -28.191 0. -10.261; 28 -30. 0. 0.19. 29 -28.191 0. 10.261; 30 -22.981 0. 19.284; 31 -15. 0. 25.98120. 32 -5.209 0. 29.544; 33 5.21 0. 29.544; 34 15. 0. 25.981; 35 22.981 0. 19.28421. 36 28.191 0. 10.261; 37 20. 0. 0.; 38 18.794 0. -6.84; 39 15.321 0. -12.85622. 40 10. 0. -17.321; 41 3.473 0. -19.696; 42 -3.473 0. -19.696; 43 -10. 0. -17.3223. 44 -15.321 0. -12.856; 45 -18.794 0. -6.84; 46 -20. 0. 0.; 47 -18.794 0. 6.8424. 48 -15.321 0. 12.856; 49 -10. 0. 17.321; 50 -3.473 0. 19.69625. 51 3.473 0. 19.696; 52 10. 0. 17.32; 53 15.321 0. 12.856; 54 18.794 0. 6.8426. 55 15. 0. 0.; 56 14.095 0. -5.13; 57 11.491 0. -9.642; 58 7.5 0. -12.9927. 59 2.605 0. -14.772; 60 -2.605 0. -14.772; 61 -7.5 0. -12.99

176 — STAAD.Pro


Static Element 6

28. 62 -11.491 0. -9.642; 63 -14.095 0. -5.13; 64 -15. 0. 0.; 65 -14.095 0. 5.1329. 66 -11.491 0. 9.642; 67 -7.5 0. 12.99; 68 -2.605 0. 14.772; 69 2.605 0. 14.77230. 70 7.5 0. 12.99; 71 11.491 0. 9.642; 72 14.095 0. 5.13; 73 10. 0. 0.31. 74 9.397 0. -3.42; 75 7.66 0. -6.428; 76 5. 0. -8.66; 77 1.736 0. -9.84832. 78 -1.736 0. -9.848; 79 -5. 0. -8.66; 80 -7.66 0. -6.428; 81 -9.397 0. -3.4233. 82 -10. 0. 0.; 83 -9.397 0. 3.42; 84 -7.66 0. 6.428; 85 -5. 0. 8.6634. 86 -1.736 0. 9.848; 87 1.737 0. 9.848; 88 5. 0. 8.66; 89 7.66 0. 6.42835. 90 9.397 0. 3.42; 91 7. 0. 0.; 92 6.578 0. -2.394; 93 5.362 0. -4.536. 94 3.5 0. -6.062; 95 1.216 0. -6.894; 96 -1.216 0. -6.894; 97 -3.5 0. -6.06237. 98 -5.362 0. -4.5; 99 -6.578 0. -2.394; 100 -7. 0. 0.; 101 -6.578 0. 2.39438. 102 -5.362 0. 4.5; 103 -3.5 0. 6.062; 104 -1.216 0. 6.894; 105 1.216 0. 6.894:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 2

* FILE: PLATE06.STD39. 106 3.5 0. 6.062; 107 5.362 0. 4.5; 108 6.578 0. 2.394; 109 3. 0. 0.40. 110 2.819 0. -1.026; 111 2.298 0. -1.928; 112 1.5 0. -2.59841. 113 0.521 0. -2.954; 114 -0.521 0. -2.954; 115 -1.5 0. -2.59842. 116 -2.298 0. -1.928; 117 -2.819 0. -1.026; 118 -3. 0. 0.; 119 -2.819 0. 1.02643. 120 -2.298 0. 1.928; 121 -1.5 0. 2.598; 122 -0.521 0. 2.954; 123 0.521 0. 2.95444. 124 1.5 0. 2.598; 125 2.298 0. 1.928; 126 2.819 0. 1.026; 127 0. 0. 0.45. ELEMENT INCIDENCES46. 1 1 2 20 19; 2 2 3 21 20; 3 3 4 22 21; 4 4 5 23 22; 5 5 6 24 23; 6 6 7 25 2447. 7 7 8 26 25; 8 8 9 27 26; 9 9 10 28 27; 10 10 11 29 28; 11 11 12 30 2948. 12 12 13 31 30; 13 13 14 32 31; 14 14 15 33 32; 15 15 16 34 33; 16 16 17 35 3449. 17 17 18 36 35; 18 18 1 19 36; 19 19 20 38 37; 20 20 21 39 38; 21 21 22 40 3950. 22 22 23 41 40; 23 23 24 42 41; 24 24 25 43 42; 25 25 26 44 43; 26 26 27 45 4451. 27 27 28 46 45; 28 28 29 47 46; 29 29 30 48 47; 30 30 31 49 48; 31 31 32 50 4952. 32 32 33 51 50; 33 33 34 52 51; 34 34 35 53 52; 35 35 36 54 53; 36 36 19 37 5453. 37 37 38 56 55; 38 38 39 57 56; 39 39 40 58 57; 40 40 41 59 58; 41 41 42 60 5954. 42 42 43 61 60; 43 43 44 62 61; 44 44 45 63 62; 45 45 46 64 63; 46 46 47 65 6455. 47 47 48 66 65; 48 48 49 67 66; 49 49 50 68 67; 50 50 51 69 68; 51 51 52 70 6956. 52 52 53 71 70; 53 53 54 72 71; 54 54 37 55 72; 55 55 56 74 73; 56 56 57 75 7457. 57 57 58 76 75; 58 58 59 77 76; 59 59 60 78 77; 60 60 61 79 78; 61 61 62 80 7958. 62 62 63 81 80; 63 63 64 82 81; 64 64 65 83 82; 65 65 66 84 83; 66 66 67 85 8459. 67 67 68 86 85; 68 68 69 87 86; 69 69 70 88 87; 70 70 71 89 88; 71 71 72 90 8960. 72 72 55 73 90; 73 73 74 92 91; 74 74 75 93 92; 75 75 76 94 93; 76 76 77 95 9461. 77 77 78 96 95; 78 78 79 97 96; 79 79 80 98 97; 80 80 81 99 98; 81 81 82 100 9962. 82 82 83 101 100; 83 83 84 102 101; 84 84 85 103 102; 85 85 86 104 10363. 86 86 87 105 104; 87 87 88 106 105; 88 88 89 107 106; 89 89 90 108 10764. 90 90 73 91 108; 91 91 92 110 109; 92 92 93 111 110; 93 93 94 112 11165. 94 94 95 113 112; 95 95 96 114 113; 96 96 97 115 114; 97 97 98 116 11566. 98 98 99 117 116; 99 99 100 118 117; 100 100 101 119 118; 101 101 102 120 11967. 102 102 103 121 120; 103 103 104 122 121; 104 104 105 123 12268. 105 105 106 124 123; 106 106 107 125 124; 107 107 108 126 12569. 108 108 91 109 126; 109 127 109 110; 110 110 111 127; 111 127 111 11270. 112 112 113 127; 113 127 113 114; 114 114 115 127; 115 127 115 11671. 116 116 117 127; 117 127 117 118; 118 127 109 126; 119 126 125 12772. 120 127 125 124; 121 124 123 127; 122 127 123 122; 123 122 121 12773. 124 127 121 120; 125 120 119 127; 126 127 119 11874. ELEMENT PROPERTY75. 1 TO 126 TH 1.76. CONSTANTS77. E 30000000. ALL78. POISSON 0.3 ALL79. SUPPORTS80. 1 TO 18 FIXED81. *82. LOAD 1 UNIFORM LOAD83. ELEMENT LOAD84. 1 TO 126 PRESSURE GY -6.085. *86. LOAD 2 POINT LOAD87. JOINT LOAD88. 127 FY -7539.81989. *90. PERFORM ANALYSIS:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 3



* FILE: PLATE06.STD






:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 4* FILE: PLATE06.STD



127 1 0.00000 -0.08618 0.00000 0.00000 0.00000 0.000002 0.00000 -0.08646 0.00000 0.00000 0.00000 -0.00001

************** END OF LATEST ANALYSIS RESULT **************92. LOAD LIST 193. PRINT ELEMENT JOINT STRESSES LIST 9 109

ELEMENT JOINT STRESSES LIST:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 5




9 1 0.00 -103.62 115.36 719.90 0.014018.27 4018.27 0.00 0.00 0.004319.40 4319.40

TOP : SMAX= 4319.40 SMIN= 692.18 TMAX= 1813.61 ANGLE= 90.0BOTT: SMAX= -692.18 SMIN= -4319.40 TMAX= 1813.61 ANGLE= 0.0JOINT 14.39 -113.81 338.29 1147.77 123.92

9 6263.05 6263.05 0.00 0.00 0.00TOP : SMAX= 6997.90 SMIN= 1918.50 TMAX= 2539.70 ANGLE= 81.5BOTT: SMAX= -1918.50 SMIN= -6997.90 TMAX= 2539.70 ANGLE= -8.5JOINT -14.38 -113.83 338.35 1147.91 -123.9110 6263.75 6263.75 0.00 0.00 0.00

TOP : SMAX= 6998.72 SMIN= 1918.87 TMAX= 2539.93 ANGLE=-81.5BOTT: SMAX= -1918.87 SMIN= -6998.72 TMAX= 2539.93 ANGLE= 8.5JOINT -10.79 -93.43 -124.84 381.27 -175.7028 3292.73 3292.73 0.00 0.00 0.00

TOP : SMAX= 2617.74 SMIN= -1079.14 TMAX= 1848.44 ANGLE=-72.6BOTT: SMAX= 1079.14 SMIN= -2617.74 TMAX= 1848.44 ANGLE= 17.4JOINT 10.79 -93.42 -124.84 381.32 175.7527 3293.22 3293.22 0.00 0.00 0.00

TOP : SMAX= 2618.18 SMIN= -1079.25 TMAX= 1848.71 ANGLE= 72.6BOTT: SMAX= 1079.25 SMIN= -2618.18 TMAX= 1848.71 ANGLE=-17.4

109 1 6.37 1.93 -799.52 -799.67 -0.214797.59 4797.59 0.00 0.00 0.004798.94 4798.94

TOP : SMAX= -4796.24 SMIN= -4798.94 TMAX= 1.35 ANGLE=-35.3BOTT: SMAX= 4798.94 SMIN= 4796.24 TMAX= 1.35 ANGLE= 54.7JOINT 6.37 1.93 -811.88 -800.33 -0.21127 4837.01 4837.01 0.00 0.00 0.00

TOP : SMAX= -4801.97 SMIN= -4871.30 TMAX= 34.67 ANGLE=-88.9BOTT: SMAX= 4871.30 SMIN= 4801.97 TMAX= 34.67 ANGLE= 1.1JOINT 6.37 1.93 -792.77 -800.33 -0.21

178 — STAAD.Pro


Static Element 6

109 4779.46 4779.46 0.00 0.00 0.00TOP : SMAX= -4756.58 SMIN= -4802.02 TMAX= 22.72 ANGLE= -1.6BOTT: SMAX= 4802.02 SMIN= 4756.58 TMAX= 22.72 ANGLE= 88.4JOINT 6.37 1.93 -793.92 -798.36 -0.21110 4776.89 4776.89 0.00 0.00 0.00

TOP : SMAX= -4763.47 SMIN= -4790.19 TMAX= 13.36 ANGLE= -2.7BOTT: SMAX= 4790.19 SMIN= 4763.47 TMAX= 13.36 ANGLE= 87.3:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 6



6.998719E+03 -6.998719E+03 2.539927E+03 4.797590E+03 4.798941E+03PLATE NO. 9 9 9 109 109CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************94. LOAD LIST 295. PRINT ELEMENT JOINT STRESSES LIST 9

ELEMENT JOINT STRESSES LIST:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 7




9 2 0.00 -34.32 75.98 484.41 0.012707.43 2707.43 0.00 0.00 0.002906.43 2906.43

TOP : SMAX= 2906.43 SMIN= 455.87 TMAX= 1225.28 ANGLE= 90.0BOTT: SMAX= -455.87 SMIN= -2906.43 TMAX= 1225.28 ANGLE= 0.0JOINT 4.34 -37.38 188.37 616.60 52.05

9 3328.03 3328.03 0.00 0.00 0.00TOP : SMAX= 3737.03 SMIN= 1092.83 TMAX= 1322.10 ANGLE= 83.2BOTT: SMAX= -1092.83 SMIN= -3737.03 TMAX= 1322.10 ANGLE= -6.8JOINT -4.33 -37.39 188.41 616.69 -52.0410 3328.45 3328.45 0.00 0.00 0.00

TOP : SMAX= 3737.54 SMIN= 1093.08 TMAX= 1322.23 ANGLE=-83.2BOTT: SMAX= -1093.08 SMIN= -3737.54 TMAX= 1322.23 ANGLE= 6.8JOINT -3.25 -31.25 -36.94 382.08 -70.3328 2519.30 2519.30 0.00 0.00 0.00

TOP : SMAX= 2361.41 SMIN= -290.59 TMAX= 1326.00 ANGLE=-80.7BOTT: SMAX= 290.59 SMIN= -2361.41 TMAX= 1326.00 ANGLE= 9.3JOINT 3.25 -31.24 -36.95 382.09 70.3627 2519.50 2519.50 0.00 0.00 0.00

TOP : SMAX= 2361.54 SMIN= -290.69 TMAX= 1326.12 ANGLE= 80.7BOTT: SMAX= 290.69 SMIN= -2361.54 TMAX= 1326.12 ANGLE= -9.3


3.737541E+03 -3.737541E+03 1.326119E+03 2.707434E+03 2.906431E+03PLATE NO. 9 9 9 9 9CASE NO. 2 2 2 2 2********************END OF ELEMENT FORCES********************96. FINISH:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 8

* FILE: PLATE06.STD:A CIRCULAR PLATE-FIXED ALONG ITS PERIMETER -- PAGE NO. 9






Static Element 7ObjectiveTo find the displacements at the free end of a warped cantilever plate due to in-plane load andout of plane loads.

ReferenceMacNeal, R.H. and Harder, R.C., A Proposed Standard Set of Problems to Test Finite ElementAccuracy, Finite Element in Analysis and Design 1, 1985.

ProblemThe finite element model is as shown below: Find the displacements at the tip in the directionof the loads. Loading is unit forces at the free end: in plane and out of plane.

E = 29000.0 ksi.

L = 12.0 in.

B = 1.1 in.

t = 0.22 in.

Twist = 90º (root to tip)


Figure 4-10: Finite element model of warped, cantilever plate

Comparison


δ due to in-plane load (in) 5.424(10)-3 5.590(10)-3 3.1%

δ due to out-of-plane load (in) 1.754(10)-3 1.950(10)-3 11.2%


180 — STAAD.Pro


Static Element 7

STAAD Input


STAAD SPACE :A WARPED CANTILEVER PLATE* FILE: PLATE07.STD** REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS* TO TEST FINITE ELEMENT ACCURACY,* FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND* 1985INPUT WIDTH 72*UNIT INCHES POUNDJOINT COORDINATES1 0. -0.55 0.; 2 1. -0.545 -0.072; 3 2. -0.531 -0.142; 4 3. -0.508 -0.215 4. -0.476 -0.275; 6 5. -0.436 -0.335; 7 6. -0.389 -0.3898 7. -0.335 -0.436; 9 8. -0.275 -0.476; 10 9. -0.21 -0.50811 10. -0.142 -0.531; 12 11. -0.072 -0.545; 13 12. 0. -0.55; 14 0. 0. 0.15 1. 0. 0.; 16 2. 0. 0.; 17 3. 0. 0.; 18 4. 0. 0.; 19 5. 0. 0.20 6. 0. 0.; 21 7. 0. 0.; 22 8. 0. 0.; 23 9. 0. 0.; 24 10. 0. 0.25 11. 0. 0.; 26 12. 0. 0.; 27 0. 0.55 0.; 28 1. 0.545 0.07229 2. 0.531 0.142; 30 3. 0.508 0.21; 31 4. 0.476 0.27532 5. 0.436 0.335; 33 6. 0.389 0.389; 34 7. 0.335 0.43635 8. 0.275 0.476; 36 9. 0.21 0.508; 37 10. 0.142 0.53138 11. 0.072 0.545; 39 12. 0. 0.55ELEMENT INCIDENCES1 1 2 15; 2 15 14 1; 3 14 15 28; 4 28 27 14; 5 2 3 16; 6 16 15 27 15 16 29; 8 29 28 15; 9 3 4 17; 10 17 16 3; 11 16 17 30; 12 30 29 1613 4 5 18; 14 18 17 4; 15 17 18 31; 16 31 30 17; 17 5 6 19; 18 19 18 519 18 19 32; 20 32 31 18; 21 6 7 20; 22 20 19 6; 23 19 20 3324 33 32 19; 25 7 8 21; 26 21 20 7; 27 20 21 34; 28 34 33 20; 29 8 9 2230 22 21 8; 31 21 22 35; 32 35 34 21; 33 9 10 23; 34 23 22 935 22 23 36; 36 36 35 22; 37 36 37 24; 38 24 23 36; 39 23 24 1140 11 10 23; 41 37 38 25; 42 25 24 37; 43 24 25 12; 44 12 11 2445 38 39 26; 46 26 25 38; 47 25 26 13; 48 13 12 25ELEMENT PROPERTY1 TO 48 TH 0.32CONSTANTSE 28999994. ALLPOISSON 0.22 ALLSUPPORTS1 14 27 FIXEDLOAD 1 UNIT LOAD AT TIP, OUT OF PLANEJOINT LOAD13 39 FY 0.2526 FY 0.50LOAD 2 UNIT LOAD AT TIP, IN PLANEJOINT LOAD13 39 FZ 0.2526 FZ 0.50PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 13 26 39FINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. *



* Date= DEC 13, 2013 ** Time= 12:29:34 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE :A WARPED CANTILEVER PLATEINPUT FILE: PLATE07.STD

2. * FILE: PLATE07.STD3. *4. * REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS5. * TO TEST FINITE ELEMENT ACCURACY,6. * FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND7. * 19858. INPUT WIDTH 729. *10. UNIT INCHES POUND11. JOINT COORDINATES12. 1 0. -0.55 0.; 2 1. -0.545 -0.072; 3 2. -0.531 -0.142; 4 3. -0.508 -0.2113. 5 4. -0.476 -0.275; 6 5. -0.436 -0.335; 7 6. -0.389 -0.38914. 8 7. -0.335 -0.436; 9 8. -0.275 -0.476; 10 9. -0.21 -0.50815. 11 10. -0.142 -0.531; 12 11. -0.072 -0.545; 13 12. 0. -0.55; 14 0. 0. 0.16. 15 1. 0. 0.; 16 2. 0. 0.; 17 3. 0. 0.; 18 4. 0. 0.; 19 5. 0. 0.17. 20 6. 0. 0.; 21 7. 0. 0.; 22 8. 0. 0.; 23 9. 0. 0.; 24 10. 0. 0.18. 25 11. 0. 0.; 26 12. 0. 0.; 27 0. 0.55 0.; 28 1. 0.545 0.07219. 29 2. 0.531 0.142; 30 3. 0.508 0.21; 31 4. 0.476 0.27520. 32 5. 0.436 0.335; 33 6. 0.389 0.389; 34 7. 0.335 0.43621. 35 8. 0.275 0.476; 36 9. 0.21 0.508; 37 10. 0.142 0.53122. 38 11. 0.072 0.545; 39 12. 0. 0.5523. ELEMENT INCIDENCES24. 1 1 2 15; 2 15 14 1; 3 14 15 28; 4 28 27 14; 5 2 3 16; 6 16 15 225. 7 15 16 29; 8 29 28 15; 9 3 4 17; 10 17 16 3; 11 16 17 30; 12 30 29 1626. 13 4 5 18; 14 18 17 4; 15 17 18 31; 16 31 30 17; 17 5 6 19; 18 19 18 527. 19 18 19 32; 20 32 31 18; 21 6 7 20; 22 20 19 6; 23 19 20 3328. 24 33 32 19; 25 7 8 21; 26 21 20 7; 27 20 21 34; 28 34 33 20; 29 8 9 2229. 30 22 21 8; 31 21 22 35; 32 35 34 21; 33 9 10 23; 34 23 22 930. 35 22 23 36; 36 36 35 22; 37 36 37 24; 38 24 23 36; 39 23 24 1131. 40 11 10 23; 41 37 38 25; 42 25 24 37; 43 24 25 12; 44 12 11 2432. 45 38 39 26; 46 26 25 38; 47 25 26 13; 48 13 12 2533. ELEMENT PROPERTY34. 1 TO 48 TH 0.3235. CONSTANTS36. E 28999994. ALL37. POISSON 0.22 ALL38. SUPPORTS:A WARPED CANTILEVER PLATE -- PAGE NO. 2

* FILE: PLATE07.STD39. 1 14 27 FIXED40. LOAD 1 UNIT LOAD AT TIP, OUT OF PLANE41. JOINT LOAD42. 13 39 FY 0.2543. 26 FY 0.5044. LOAD 2 UNIT LOAD AT TIP, IN PLANE45. JOINT LOAD46. 13 39 FZ 0.2547. 26 FZ 0.5048. PERFORM ANALYSIS




182 — STAAD.Pro


Static Element 7


49. PRINT JOINT DISPLACEMENTS LIST 13 26 39JOINT DISPLACE LIST 13

:A WARPED CANTILEVER PLATE -- PAGE NO. 3* FILE: PLATE07.STD



13 1 -0.00015 0.00202 -0.00195 0.00000 0.00022 0.000362 0.00035 -0.00195 0.00559 0.00000 -0.00060 -0.00028

26 1 0.00000 0.00202 -0.00195 0.00000 0.00022 0.000362 0.00000 -0.00195 0.00559 0.00000 -0.00060 -0.00028

39 1 0.00015 0.00202 -0.00195 0.00000 0.00022 0.000352 -0.00034 -0.00195 0.00559 0.00000 -0.00060 -0.00028

************** END OF LATEST ANALYSIS RESULT **************50. FINISH:A WARPED CANTILEVER PLATE -- PAGE NO. 4



Static Element 8ObjectiveA Cylindrical roof is supported along two circular edges. Using plate/shell elements, find thevertical deflection at the center of the free edge, principal stresses at the center of the supportand center of the free edge (top and bottom of the roof plate) due to uniformly distributedgravity load.

ReferenceScordelis, A.C. and Lo, K.S., "Computer Analysis of Cylindrical Shells", Journal of the AmericanConcrete Institute, Vol. 61, May 1964.

ProblemFor the cylindrical roof shell calculate the following deflection and stresses due to the gravityload.

The vertical deflection, δy, at the center of the free edge.

Principal stresses, σmax and σmin, at the center line section at the vertical angle (top and bottomof the roof plate element). Principal stresses, σmax and σmin, at the center section of the freeedge (top and bottom of the roof plate element).



E = 4.32(10)8 psf

t = 3.0 in.

Poisson’s ratio = 0.0 in theory (0.01001 in STAAD)

w = 90 psf (uniform on surface).

L = 50 feet.

r = 25 feet, 40º sector either side of vertical

Boundary conditions: simply supported on circular edges

Figure 4-11: Finite element model of cylindrical roof structure

Comparison


δy, at the center of the free edge (in) (xtranslation at node 63)

-3.703 -3.7922 2.4%

σ at center (ft-kip) Bottom 191.23 191.59a none

Top 218.74 -218.65a none

σ at free edge (ft-kip)

Bottom 215.57 208.85b 3.1%

Top 340.7 340.05b none

Table 4-8: Comparison of results for cylindrical roof structure

a. Plate 7, Joint 55, SMAX and SMIN

b. Plate 111, Joint 63, SMAX

184 — STAAD.Pro


Static Element 8

STAAD Input


STAAD SPACE SCORDELIS-LO ROOF* FILE: PLATE08.STD* A CYLINDRICAL ROOF SUPPORTED ALONG TWO CIRCULAR EDGES** REFERENCE: SCORDELIS, A.C., AND LO K. S., COMPUTER ANALYSIS* OF CYLINDRICAL SHELLS, JOURNAL OF THE AMERICAN CONCRETE* INSTITUTE, VOL. 61, MAY 1964.*INPUT WIDTH 72UNIT FEET POUNDJOINT COORDINATES1 0. 25. 0.; 2 2.179 24.905 0.; 3 4.341 24.62 0.; 4 6.471 24.148 0.5 8.551 23.492 0.; 6 10.566 22.658 0.; 7 12.5 21.651 0.8 14.339 20.479 0.; 9 16.07 19.151 0.; 10 0. 25. 4.16711 2.179 24.905 4.167; 12 4.341 24.62 4.167; 13 6.471 24.148 4.16714 8.551 23.492 4.167; 15 10.566 22.658 4.167; 16 12.5 21.651 4.16717 14.339 20.479 4.167; 18 16.07 19.151 4.167; 19 0. 25. 8.33420 2.179 24.905 8.334; 21 4.341 24.62 8.334; 22 6.471 24.148 8.33423 8.551 23.492 8.334; 24 10.566 22.658 8.334; 25 12.5 21.651 8.33426 14.339 20.479 8.334; 27 16.07 19.151 8.334; 28 0. 25. 12.50129 2.179 24.905 12.501; 30 4.341 24.62 12.501; 31 6.471 24.148 12.50132 8.551 23.492 12.501; 33 10.566 22.658 12.501; 34 12.5 21.651 12.50135 14.339 20.479 12.501; 36 16.07 19.151 12.501; 37 0. 25. 16.66838 2.179 24.905 16.668; 39 4.341 24.62 16.668; 40 6.471 24.148 16.66841 8.551 23.492 16.668; 42 10.566 22.658 16.668; 43 12.5 21.651 16.66844 14.339 20.479 16.668; 45 16.07 19.151 16.668; 46 0. 25. 20.83547 2.179 24.905 20.835; 48 4.341 24.62 20.835; 49 6.471 24.148 20.83550 8.551 23.492 20.835; 51 10.566 22.658 20.835; 52 12.5 21.651 20.83553 14.339 20.479 20.835; 54 16.07 19.151 20.835; 55 0. 25. 25.00256 2.179 24.905 25.002; 57 4.341 24.62 25.002; 58 6.471 24.148 25.00259 8.551 23.492 25.002; 60 10.566 22.658 25.002; 61 12.5 21.651 25.00262 14.339 20.479 25.002; 63 16.07 19.151 25.002; 64 0. 25. 29.16965 2.179 24.905 29.169; 66 4.341 24.62 29.169; 67 6.471 24.148 29.16968 8.551 23.492 29.169; 69 10.566 22.658 29.169; 70 12.5 21.651 29.16971 14.339 20.479 29.169; 72 16.07 19.151 29.169; 73 0. 25. 33.33674 2.179 24.905 33.336; 75 4.341 24.62 33.336; 76 6.471 24.148 33.33677 8.551 23.492 33.336; 78 10.566 22.658 33.336; 79 12.5 21.651 33.33680 14.339 20.479 33.336; 81 16.07 19.151 33.336; 82 0. 25. 37.50383 2.179 24.905 37.503; 84 4.341 24.62 37.503; 85 6.471 24.148 37.50386 8.551 23.492 37.503; 87 10.566 22.658 37.503; 88 12.5 21.651 37.50389 14.339 20.479 37.503; 90 16.07 19.151 37.503; 91 0. 25. 41.6792 2.179 24.905 41.67; 93 4.341 24.62 41.67; 94 6.471 24.148 41.6795 8.551 23.492 41.67; 96 10.566 22.658 41.67; 97 12.5 21.651 41.6798 14.339 20.479 41.67; 99 16.07 19.151 41.67; 100 0. 25. 45.837101 2.179 24.905 45.837; 102 4.341 24.62 45.837; 103 6.471 24.148 45.837104 8.551 23.492 45.837; 105 10.566 22.658 45.837106 12.5 21.651 45.837; 107 14.339 20.479 45.837108 16.07 19.151 45.837; 109 0. 25. 50.004; 110 2.179 24.905 50.004111 4.341 24.62 50.004; 112 6.471 24.148 50.004; 113 8.551 23.492 50.004114 10.566 22.658 50.004; 115 12.5 21.651 50.004116 14.339 20.479 50.004; 117 16.07 19.151 50.004; 118 -2.179 24.905 0.119 -4.341 24.62 0.; 120 -6.471 24.148 0.; 121 -8.551 23.492 0.122 -10.566 22.658 0.; 123 -12.5 21.651 0.; 124 -14.339 20.479 0.125 -16.07 19.151 0.; 126 -2.179 24.905 4.167; 127 -4.341 24.62 4.167128 -6.471 24.148 4.167; 129 -8.551 23.492 4.167130 -10.566 22.658 4.167; 131 -12.5 21.651 4.167132 -14.339 20.479 4.167; 133 -16.07 19.151 4.167134 -2.179 24.905 8.334; 135 -4.341 24.62 8.334; 136 -6.471 24.148 8.334137 -8.551 23.492 8.334; 138 -10.566 22.658 8.334139 -12.5 21.651 8.334; 140 -14.339 20.479 8.334



141 -16.07 19.151 8.334; 142 -2.179 24.905 12.501143 -4.341 24.62 12.501; 144 -6.471 24.148 12.501145 -8.551 23.492 12.501; 146 -10.566 22.658 12.501147 -12.5 21.651 12.501; 148 -14.339 20.479 12.501149 -16.07 19.151 12.501; 150 -2.179 24.905 16.668151 -4.341 24.62 16.668; 152 -6.471 24.148 16.668153 -8.551 23.492 16.668; 154 -10.566 22.658 16.668155 -12.5 21.651 16.668; 156 -14.339 20.479 16.668157 -16.07 19.151 16.668; 158 -2.179 24.905 20.835159 -4.341 24.62 20.835; 160 -6.471 24.148 20.835161 -8.551 23.492 20.835; 162 -10.566 22.658 20.835163 -12.5 21.651 20.835; 164 -14.339 20.479 20.835165 -16.07 19.151 20.835; 166 -2.179 24.905 25.002167 -4.341 24.62 25.002; 168 -6.471 24.148 25.002169 -8.551 23.492 25.002; 170 -10.566 22.658 25.002171 -12.5 21.651 25.002; 172 -14.339 20.479 25.002173 -16.07 19.151 25.002; 174 -2.179 24.905 29.169175 -4.341 24.62 29.169; 176 -6.471 24.148 29.169177 -8.551 23.492 29.169; 178 -10.566 22.658 29.169179 -12.5 21.651 29.169; 180 -14.339 20.479 29.169181 -16.07 19.151 29.169; 182 -2.179 24.905 33.336183 -4.341 24.62 33.336; 184 -6.471 24.148 33.336185 -8.551 23.492 33.336; 186 -10.566 22.658 33.336187 -12.5 21.651 33.336; 188 -14.339 20.479 33.336189 -16.07 19.151 33.336; 190 -2.179 24.905 37.503191 -4.341 24.62 37.503; 192 -6.471 24.148 37.503193 -8.551 23.492 37.503; 194 -10.566 22.658 37.503195 -12.5 21.651 37.503; 196 -14.339 20.479 37.503197 -16.07 19.151 37.503; 198 -2.179 24.905 41.67199 -4.341 24.62 41.67; 200 -6.471 24.148 41.67; 201 -8.551 23.492 41.67202 -10.566 22.658 41.67; 203 -12.5 21.651 41.67204 -14.339 20.479 41.67; 205 -16.07 19.151 41.67206 -2.179 24.905 45.837; 207 -4.341 24.62 45.837208 -6.471 24.148 45.837; 209 -8.551 23.492 45.837210 -10.566 22.658 45.837; 211 -12.5 21.651 45.837212 -14.339 20.479 45.837; 213 -16.07 19.151 45.837214 -2.179 24.905 50.004; 215 -4.341 24.62 50.004216 -6.471 24.148 50.004; 217 -8.551 23.492 50.004218 -10.566 22.658 50.004; 219 -12.5 21.651 50.004220 -14.339 20.479 50.004; 221 -16.07 19.151 50.004ELEMENT INCIDENCES1 1 2 10; 2 10 2 11; 3 11 2 3; 4 11 3 12; 5 12 3 4; 6 4 13 12; 7 4 5 148 14 13 4; 9 5 15 14; 10 5 6 15; 11 15 7 16; 12 16 7 17; 13 17 7 814 8 18 17; 15 8 9 18; 16 6 7 15; 17 10 11 19; 18 19 11 20; 19 20 11 1220 20 12 21; 21 21 12 13; 22 13 22 21; 23 13 14 23; 24 23 22 1325 14 24 23; 26 14 15 24; 27 24 16 25; 28 25 16 26; 29 26 16 1730 17 27 26; 31 17 18 27; 32 15 16 24; 33 19 20 28; 34 28 20 2935 29 20 21; 36 29 21 30; 37 30 21 22; 38 22 31 30; 39 22 23 3240 32 31 22; 41 23 33 32; 42 23 24 33; 43 33 25 34; 44 34 25 3545 35 25 26; 46 26 36 35; 47 26 27 36; 48 24 25 33; 49 28 29 3750 37 29 38; 51 38 29 30; 52 38 30 39; 53 39 30 31; 54 31 40 3955 31 32 41; 56 41 40 31; 57 32 42 41; 58 32 33 42; 59 42 34 4360 43 34 44; 61 44 34 35; 62 35 45 44; 63 35 36 45; 64 33 34 4265 37 38 46; 66 46 38 47; 67 47 38 39; 68 47 39 48; 69 48 39 4070 40 49 48; 71 40 41 50; 72 50 49 40; 73 41 51 50; 74 41 42 5175 51 43 52; 76 52 43 53; 77 53 43 44; 78 44 54 53; 79 44 45 5480 42 43 51; 81 46 47 55; 82 55 47 56; 83 56 47 48; 84 56 48 5785 57 48 49; 86 49 58 57; 87 49 50 59; 88 59 58 49; 89 50 60 5990 50 51 60; 91 60 52 61; 92 61 52 62; 93 62 52 53; 94 53 63 6295 53 54 63; 96 51 52 60; 97 55 56 64; 98 64 56 65; 99 65 56 57100 65 57 66; 101 66 57 58; 102 58 67 66; 103 58 59 68; 104 68 67 58105 59 69 68; 106 59 60 69; 107 69 61 70; 108 70 61 71; 109 71 61 62110 62 72 71; 111 62 63 72; 112 60 61 69; 113 64 65 73; 114 73 65 74115 74 65 66; 116 74 66 75; 117 75 66 67; 118 67 76 75; 119 67 68 77120 77 76 67; 121 68 78 77; 122 68 69 78; 123 78 70 79; 124 79 70 80125 80 70 71; 126 71 81 80; 127 71 72 81; 128 69 70 78; 129 73 74 82

186 — STAAD.Pro


Static Element 8

130 82 74 83; 131 83 74 75; 132 83 75 84; 133 84 75 76; 134 76 85 84135 76 77 86; 136 86 85 76; 137 77 87 86; 138 77 78 87; 139 87 79 88140 88 79 89; 141 89 79 80; 142 80 90 89; 143 80 81 90; 144 78 79 87145 82 83 91; 146 91 83 92; 147 92 83 84; 148 92 84 93; 149 93 84 85150 85 94 93; 151 85 86 95; 152 95 94 85; 153 86 96 95; 154 86 87 96155 96 88 97; 156 97 88 98; 157 98 88 89; 158 89 99 98; 159 89 90 99160 87 88 96; 161 91 92 100; 162 100 92 101; 163 101 92 93164 101 93 102; 165 102 93 94; 166 94 103 102; 167 94 95 104168 104 103 94; 169 95 105 104; 170 95 96 105; 171 105 97 106172 106 97 107; 173 107 97 98; 174 98 108 107; 175 98 99 108176 96 97 105; 177 100 101 109; 178 109 101 110; 179 110 101 102180 110 102 111; 181 111 102 103; 182 103 112 111; 183 103 104 113184 113 112 103; 185 104 114 113; 186 104 105 114; 187 114 106 115188 115 106 116; 189 116 106 107; 190 107 117 116; 191 107 108 117192 105 106 114; 193 1 118 10; 194 10 118 126; 195 126 118 119196 126 119 127; 197 127 119 120; 198 120 128 127; 199 120 121 129200 129 128 120; 201 121 130 129; 202 121 122 130; 203 130 123 131204 131 123 132; 205 132 123 124; 206 124 133 132; 207 124 125 133208 122 123 130; 209 10 126 19; 210 19 126 134; 211 134 126 127212 134 127 135; 213 135 127 128; 214 128 136 135; 215 128 129 137216 137 136 128; 217 129 138 137; 218 129 130 138; 219 138 131 139220 139 131 140; 221 140 131 132; 222 132 141 140; 223 132 133 141224 130 131 138; 225 19 134 28; 226 28 134 142; 227 142 134 135228 142 135 143; 229 143 135 136; 230 136 144 143; 231 136 137 145232 145 144 136; 233 137 146 145; 234 137 138 146; 235 146 139 147236 147 139 148; 237 148 139 140; 238 140 149 148; 239 140 141 149240 138 139 146; 241 28 142 37; 242 37 142 150; 243 150 142 143244 150 143 151; 245 151 143 144; 246 144 152 151; 247 144 145 153248 153 152 144; 249 145 154 153; 250 145 146 154; 251 154 147 155252 155 147 156; 253 156 147 148; 254 148 157 156; 255 148 149 157256 146 147 154; 257 37 150 46; 258 46 150 158; 259 158 150 151260 158 151 159; 261 159 151 152; 262 152 160 159; 263 152 153 161264 161 160 152; 265 153 162 161; 266 153 154 162; 267 162 155 163268 163 155 164; 269 164 155 156; 270 156 165 164; 271 156 157 165272 154 155 162; 273 46 158 55; 274 55 158 166; 275 166 158 159276 166 159 167; 277 167 159 160; 278 160 168 167; 279 160 161 169280 169 168 160; 281 161 170 169; 282 161 162 170; 283 170 163 171284 171 163 172; 285 172 163 164; 286 164 173 172; 287 164 165 173288 162 163 170; 289 55 166 64; 290 64 166 174; 291 174 166 167292 174 167 175; 293 175 167 168; 294 168 176 175; 295 168 169 177296 177 176 168; 297 169 178 177; 298 169 170 178; 299 178 171 179300 179 171 180; 301 180 171 172; 302 172 181 180; 303 172 173 181304 170 171 178; 305 64 174 73; 306 73 174 182; 307 182 174 175308 182 175 183; 309 183 175 176; 310 176 184 183; 311 176 177 185312 185 184 176; 313 177 186 185; 314 177 178 186; 315 186 179 187316 187 179 188; 317 188 179 180; 318 180 189 188; 319 180 181 189320 178 179 186; 321 73 182 82; 322 82 182 190; 323 190 182 183324 190 183 191; 325 191 183 184; 326 184 192 191; 327 184 185 193328 193 192 184; 329 185 194 193; 330 185 186 194; 331 194 187 195332 195 187 196; 333 196 187 188; 334 188 197 196; 335 188 189 197336 186 187 194; 337 82 190 91; 338 91 190 198; 339 198 190 191340 198 191 199; 341 199 191 192; 342 192 200 199; 343 192 193 201344 201 200 192; 345 193 202 201; 346 193 194 202; 347 202 195 203348 203 195 204; 349 204 195 196; 350 196 205 204; 351 196 197 205352 194 195 202; 353 91 198 100; 354 100 198 206; 355 206 198 199356 206 199 207; 357 207 199 200; 358 200 208 207; 359 200 201 209360 209 208 200; 361 201 210 209; 362 201 202 210; 363 210 203 211364 211 203 212; 365 212 203 204; 366 204 213 212; 367 204 205 213368 202 203 210; 369 100 206 109; 370 109 206 214; 371 214 206 207372 214 207 215; 373 215 207 208; 374 208 216 215; 375 208 209 217376 217 216 208; 377 209 218 217; 378 209 210 218; 379 218 211 219380 219 211 220; 381 220 211 212; 382 212 221 220; 383 212 213 221384 210 211 218ELEMENT PROPERTY1 TO 384 TH 0.25CONSTANTS



E 432000000. ALLDENSITY 360. ALLSUPPORTS1 TO 9 109 TO 125 214 TO 221 FIXED BUT FZ MX MY*LOAD 1 DEAD LOAD (SELFWEIGHT OF 90 PSF)SELFWEIGHT Y -1.PERFORM ANALYSISUNIT KIP FEETPRINT JOINT DISPLACEMENTS LIST 55 63 173PRINT ELEMENT JOINT STRESSES LIST 97 111FINISH



1. STAAD SPACE SCORDELIS-LO ROOFINPUT FILE: PLATE08.STD

2. * FILE: PLATE08.STD3. * A CYLINDRICAL ROOF SUPPORTED ALONG TWO CIRCULAR EDGES4. *5. * REFERENCE: SCORDELIS, A.C., AND LO K. S., COMPUTER ANALYSIS6. * OF CYLINDRICAL SHELLS, JOURNAL OF THE AMERICAN CONCRETE7. * INSTITUTE, VOL. 61, MAY 1964.8. *9. INPUT WIDTH 7210. UNIT FEET POUND11. JOINT COORDINATES12. 1 0. 25. 0.; 2 2.179 24.905 0.; 3 4.341 24.62 0.; 4 6.471 24.148 0.13. 5 8.551 23.492 0.; 6 10.566 22.658 0.; 7 12.5 21.651 0.14. 8 14.339 20.479 0.; 9 16.07 19.151 0.; 10 0. 25. 4.16715. 11 2.179 24.905 4.167; 12 4.341 24.62 4.167; 13 6.471 24.148 4.16716. 14 8.551 23.492 4.167; 15 10.566 22.658 4.167; 16 12.5 21.651 4.16717. 17 14.339 20.479 4.167; 18 16.07 19.151 4.167; 19 0. 25. 8.33418. 20 2.179 24.905 8.334; 21 4.341 24.62 8.334; 22 6.471 24.148 8.33419. 23 8.551 23.492 8.334; 24 10.566 22.658 8.334; 25 12.5 21.651 8.33420. 26 14.339 20.479 8.334; 27 16.07 19.151 8.334; 28 0. 25. 12.50121. 29 2.179 24.905 12.501; 30 4.341 24.62 12.501; 31 6.471 24.148 12.50122. 32 8.551 23.492 12.501; 33 10.566 22.658 12.501; 34 12.5 21.651 12.50123. 35 14.339 20.479 12.501; 36 16.07 19.151 12.501; 37 0. 25. 16.66824. 38 2.179 24.905 16.668; 39 4.341 24.62 16.668; 40 6.471 24.148 16.66825. 41 8.551 23.492 16.668; 42 10.566 22.658 16.668; 43 12.5 21.651 16.66826. 44 14.339 20.479 16.668; 45 16.07 19.151 16.668; 46 0. 25. 20.83527. 47 2.179 24.905 20.835; 48 4.341 24.62 20.835; 49 6.471 24.148 20.83528. 50 8.551 23.492 20.835; 51 10.566 22.658 20.835; 52 12.5 21.651 20.83529. 53 14.339 20.479 20.835; 54 16.07 19.151 20.835; 55 0. 25. 25.00230. 56 2.179 24.905 25.002; 57 4.341 24.62 25.002; 58 6.471 24.148 25.00231. 59 8.551 23.492 25.002; 60 10.566 22.658 25.002; 61 12.5 21.651 25.00232. 62 14.339 20.479 25.002; 63 16.07 19.151 25.002; 64 0. 25. 29.16933. 65 2.179 24.905 29.169; 66 4.341 24.62 29.169; 67 6.471 24.148 29.16934. 68 8.551 23.492 29.169; 69 10.566 22.658 29.169; 70 12.5 21.651 29.16935. 71 14.339 20.479 29.169; 72 16.07 19.151 29.169; 73 0. 25. 33.33636. 74 2.179 24.905 33.336; 75 4.341 24.62 33.336; 76 6.471 24.148 33.336

188 — STAAD.Pro


Static Element 8

37. 77 8.551 23.492 33.336; 78 10.566 22.658 33.336; 79 12.5 21.651 33.33638. 80 14.339 20.479 33.336; 81 16.07 19.151 33.336; 82 0. 25. 37.503SCORDELIS-LO ROOF -- PAGE NO. 2

* FILE: PLATE08.STD39. 83 2.179 24.905 37.503; 84 4.341 24.62 37.503; 85 6.471 24.148 37.50340. 86 8.551 23.492 37.503; 87 10.566 22.658 37.503; 88 12.5 21.651 37.50341. 89 14.339 20.479 37.503; 90 16.07 19.151 37.503; 91 0. 25. 41.6742. 92 2.179 24.905 41.67; 93 4.341 24.62 41.67; 94 6.471 24.148 41.6743. 95 8.551 23.492 41.67; 96 10.566 22.658 41.67; 97 12.5 21.651 41.6744. 98 14.339 20.479 41.67; 99 16.07 19.151 41.67; 100 0. 25. 45.83745. 101 2.179 24.905 45.837; 102 4.341 24.62 45.837; 103 6.471 24.148 45.83746. 104 8.551 23.492 45.837; 105 10.566 22.658 45.83747. 106 12.5 21.651 45.837; 107 14.339 20.479 45.83748. 108 16.07 19.151 45.837; 109 0. 25. 50.004; 110 2.179 24.905 50.00449. 111 4.341 24.62 50.004; 112 6.471 24.148 50.004; 113 8.551 23.492 50.00450. 114 10.566 22.658 50.004; 115 12.5 21.651 50.00451. 116 14.339 20.479 50.004; 117 16.07 19.151 50.004; 118 -2.179 24.905 0.52. 119 -4.341 24.62 0.; 120 -6.471 24.148 0.; 121 -8.551 23.492 0.53. 122 -10.566 22.658 0.; 123 -12.5 21.651 0.; 124 -14.339 20.479 0.54. 125 -16.07 19.151 0.; 126 -2.179 24.905 4.167; 127 -4.341 24.62 4.16755. 128 -6.471 24.148 4.167; 129 -8.551 23.492 4.16756. 130 -10.566 22.658 4.167; 131 -12.5 21.651 4.16757. 132 -14.339 20.479 4.167; 133 -16.07 19.151 4.16758. 134 -2.179 24.905 8.334; 135 -4.341 24.62 8.334; 136 -6.471 24.148 8.33459. 137 -8.551 23.492 8.334; 138 -10.566 22.658 8.33460. 139 -12.5 21.651 8.334; 140 -14.339 20.479 8.33461. 141 -16.07 19.151 8.334; 142 -2.179 24.905 12.50162. 143 -4.341 24.62 12.501; 144 -6.471 24.148 12.50163. 145 -8.551 23.492 12.501; 146 -10.566 22.658 12.50164. 147 -12.5 21.651 12.501; 148 -14.339 20.479 12.50165. 149 -16.07 19.151 12.501; 150 -2.179 24.905 16.66866. 151 -4.341 24.62 16.668; 152 -6.471 24.148 16.66867. 153 -8.551 23.492 16.668; 154 -10.566 22.658 16.66868. 155 -12.5 21.651 16.668; 156 -14.339 20.479 16.66869. 157 -16.07 19.151 16.668; 158 -2.179 24.905 20.83570. 159 -4.341 24.62 20.835; 160 -6.471 24.148 20.83571. 161 -8.551 23.492 20.835; 162 -10.566 22.658 20.83572. 163 -12.5 21.651 20.835; 164 -14.339 20.479 20.83573. 165 -16.07 19.151 20.835; 166 -2.179 24.905 25.00274. 167 -4.341 24.62 25.002; 168 -6.471 24.148 25.00275. 169 -8.551 23.492 25.002; 170 -10.566 22.658 25.00276. 171 -12.5 21.651 25.002; 172 -14.339 20.479 25.00277. 173 -16.07 19.151 25.002; 174 -2.179 24.905 29.16978. 175 -4.341 24.62 29.169; 176 -6.471 24.148 29.16979. 177 -8.551 23.492 29.169; 178 -10.566 22.658 29.16980. 179 -12.5 21.651 29.169; 180 -14.339 20.479 29.16981. 181 -16.07 19.151 29.169; 182 -2.179 24.905 33.33682. 183 -4.341 24.62 33.336; 184 -6.471 24.148 33.33683. 185 -8.551 23.492 33.336; 186 -10.566 22.658 33.33684. 187 -12.5 21.651 33.336; 188 -14.339 20.479 33.33685. 189 -16.07 19.151 33.336; 190 -2.179 24.905 37.50386. 191 -4.341 24.62 37.503; 192 -6.471 24.148 37.50387. 193 -8.551 23.492 37.503; 194 -10.566 22.658 37.50388. 195 -12.5 21.651 37.503; 196 -14.339 20.479 37.50389. 197 -16.07 19.151 37.503; 198 -2.179 24.905 41.6790. 199 -4.341 24.62 41.67; 200 -6.471 24.148 41.67; 201 -8.551 23.492 41.6791. 202 -10.566 22.658 41.67; 203 -12.5 21.651 41.6792. 204 -14.339 20.479 41.67; 205 -16.07 19.151 41.6793. 206 -2.179 24.905 45.837; 207 -4.341 24.62 45.83794. 208 -6.471 24.148 45.837; 209 -8.551 23.492 45.837SCORDELIS-LO ROOF -- PAGE NO. 3

* FILE: PLATE08.STD95. 210 -10.566 22.658 45.837; 211 -12.5 21.651 45.83796. 212 -14.339 20.479 45.837; 213 -16.07 19.151 45.83797. 214 -2.179 24.905 50.004; 215 -4.341 24.62 50.00498. 216 -6.471 24.148 50.004; 217 -8.551 23.492 50.004



99. 218 -10.566 22.658 50.004; 219 -12.5 21.651 50.004100. 220 -14.339 20.479 50.004; 221 -16.07 19.151 50.004101. ELEMENT INCIDENCES102. 1 1 2 10; 2 10 2 11; 3 11 2 3; 4 11 3 12; 5 12 3 4; 6 4 13 12; 7 4 5 14103. 8 14 13 4; 9 5 15 14; 10 5 6 15; 11 15 7 16; 12 16 7 17; 13 17 7 8104. 14 8 18 17; 15 8 9 18; 16 6 7 15; 17 10 11 19; 18 19 11 20; 19 20 11 12105. 20 20 12 21; 21 21 12 13; 22 13 22 21; 23 13 14 23; 24 23 22 13106. 25 14 24 23; 26 14 15 24; 27 24 16 25; 28 25 16 26; 29 26 16 17107. 30 17 27 26; 31 17 18 27; 32 15 16 24; 33 19 20 28; 34 28 20 29108. 35 29 20 21; 36 29 21 30; 37 30 21 22; 38 22 31 30; 39 22 23 32109. 40 32 31 22; 41 23 33 32; 42 23 24 33; 43 33 25 34; 44 34 25 35110. 45 35 25 26; 46 26 36 35; 47 26 27 36; 48 24 25 33; 49 28 29 37111. 50 37 29 38; 51 38 29 30; 52 38 30 39; 53 39 30 31; 54 31 40 39112. 55 31 32 41; 56 41 40 31; 57 32 42 41; 58 32 33 42; 59 42 34 43113. 60 43 34 44; 61 44 34 35; 62 35 45 44; 63 35 36 45; 64 33 34 42114. 65 37 38 46; 66 46 38 47; 67 47 38 39; 68 47 39 48; 69 48 39 40115. 70 40 49 48; 71 40 41 50; 72 50 49 40; 73 41 51 50; 74 41 42 51116. 75 51 43 52; 76 52 43 53; 77 53 43 44; 78 44 54 53; 79 44 45 54117. 80 42 43 51; 81 46 47 55; 82 55 47 56; 83 56 47 48; 84 56 48 57118. 85 57 48 49; 86 49 58 57; 87 49 50 59; 88 59 58 49; 89 50 60 59119. 90 50 51 60; 91 60 52 61; 92 61 52 62; 93 62 52 53; 94 53 63 62120. 95 53 54 63; 96 51 52 60; 97 55 56 64; 98 64 56 65; 99 65 56 57121. 100 65 57 66; 101 66 57 58; 102 58 67 66; 103 58 59 68; 104 68 67 58122. 105 59 69 68; 106 59 60 69; 107 69 61 70; 108 70 61 71; 109 71 61 62123. 110 62 72 71; 111 62 63 72; 112 60 61 69; 113 64 65 73; 114 73 65 74124. 115 74 65 66; 116 74 66 75; 117 75 66 67; 118 67 76 75; 119 67 68 77125. 120 77 76 67; 121 68 78 77; 122 68 69 78; 123 78 70 79; 124 79 70 80126. 125 80 70 71; 126 71 81 80; 127 71 72 81; 128 69 70 78; 129 73 74 82127. 130 82 74 83; 131 83 74 75; 132 83 75 84; 133 84 75 76; 134 76 85 84128. 135 76 77 86; 136 86 85 76; 137 77 87 86; 138 77 78 87; 139 87 79 88129. 140 88 79 89; 141 89 79 80; 142 80 90 89; 143 80 81 90; 144 78 79 87130. 145 82 83 91; 146 91 83 92; 147 92 83 84; 148 92 84 93; 149 93 84 85131. 150 85 94 93; 151 85 86 95; 152 95 94 85; 153 86 96 95; 154 86 87 96132. 155 96 88 97; 156 97 88 98; 157 98 88 89; 158 89 99 98; 159 89 90 99133. 160 87 88 96; 161 91 92 100; 162 100 92 101; 163 101 92 93134. 164 101 93 102; 165 102 93 94; 166 94 103 102; 167 94 95 104135. 168 104 103 94; 169 95 105 104; 170 95 96 105; 171 105 97 106136. 172 106 97 107; 173 107 97 98; 174 98 108 107; 175 98 99 108137. 176 96 97 105; 177 100 101 109; 178 109 101 110; 179 110 101 102138. 180 110 102 111; 181 111 102 103; 182 103 112 111; 183 103 104 113139. 184 113 112 103; 185 104 114 113; 186 104 105 114; 187 114 106 115140. 188 115 106 116; 189 116 106 107; 190 107 117 116; 191 107 108 117141. 192 105 106 114; 193 1 118 10; 194 10 118 126; 195 126 118 119142. 196 126 119 127; 197 127 119 120; 198 120 128 127; 199 120 121 129143. 200 129 128 120; 201 121 130 129; 202 121 122 130; 203 130 123 131144. 204 131 123 132; 205 132 123 124; 206 124 133 132; 207 124 125 133145. 208 122 123 130; 209 10 126 19; 210 19 126 134; 211 134 126 127146. 212 134 127 135; 213 135 127 128; 214 128 136 135; 215 128 129 137147. 216 137 136 128; 217 129 138 137; 218 129 130 138; 219 138 131 139148. 220 139 131 140; 221 140 131 132; 222 132 141 140; 223 132 133 141149. 224 130 131 138; 225 19 134 28; 226 28 134 142; 227 142 134 135150. 228 142 135 143; 229 143 135 136; 230 136 144 143; 231 136 137 145

SCORDELIS-LO ROOF -- PAGE NO. 4* FILE: PLATE08.STD151. 232 145 144 136; 233 137 146 145; 234 137 138 146; 235 146 139 147152. 236 147 139 148; 237 148 139 140; 238 140 149 148; 239 140 141 149153. 240 138 139 146; 241 28 142 37; 242 37 142 150; 243 150 142 143154. 244 150 143 151; 245 151 143 144; 246 144 152 151; 247 144 145 153155. 248 153 152 144; 249 145 154 153; 250 145 146 154; 251 154 147 155156. 252 155 147 156; 253 156 147 148; 254 148 157 156; 255 148 149 157157. 256 146 147 154; 257 37 150 46; 258 46 150 158; 259 158 150 151158. 260 158 151 159; 261 159 151 152; 262 152 160 159; 263 152 153 161159. 264 161 160 152; 265 153 162 161; 266 153 154 162; 267 162 155 163160. 268 163 155 164; 269 164 155 156; 270 156 165 164; 271 156 157 165161. 272 154 155 162; 273 46 158 55; 274 55 158 166; 275 166 158 159162. 276 166 159 167; 277 167 159 160; 278 160 168 167; 279 160 161 169

190 — STAAD.Pro


Static Element 8

163. 280 169 168 160; 281 161 170 169; 282 161 162 170; 283 170 163 171164. 284 171 163 172; 285 172 163 164; 286 164 173 172; 287 164 165 173165. 288 162 163 170; 289 55 166 64; 290 64 166 174; 291 174 166 167166. 292 174 167 175; 293 175 167 168; 294 168 176 175; 295 168 169 177167. 296 177 176 168; 297 169 178 177; 298 169 170 178; 299 178 171 179168. 300 179 171 180; 301 180 171 172; 302 172 181 180; 303 172 173 181169. 304 170 171 178; 305 64 174 73; 306 73 174 182; 307 182 174 175170. 308 182 175 183; 309 183 175 176; 310 176 184 183; 311 176 177 185171. 312 185 184 176; 313 177 186 185; 314 177 178 186; 315 186 179 187172. 316 187 179 188; 317 188 179 180; 318 180 189 188; 319 180 181 189173. 320 178 179 186; 321 73 182 82; 322 82 182 190; 323 190 182 183174. 324 190 183 191; 325 191 183 184; 326 184 192 191; 327 184 185 193175. 328 193 192 184; 329 185 194 193; 330 185 186 194; 331 194 187 195176. 332 195 187 196; 333 196 187 188; 334 188 197 196; 335 188 189 197177. 336 186 187 194; 337 82 190 91; 338 91 190 198; 339 198 190 191178. 340 198 191 199; 341 199 191 192; 342 192 200 199; 343 192 193 201179. 344 201 200 192; 345 193 202 201; 346 193 194 202; 347 202 195 203180. 348 203 195 204; 349 204 195 196; 350 196 205 204; 351 196 197 205181. 352 194 195 202; 353 91 198 100; 354 100 198 206; 355 206 198 199182. 356 206 199 207; 357 207 199 200; 358 200 208 207; 359 200 201 209183. 360 209 208 200; 361 201 210 209; 362 201 202 210; 363 210 203 211184. 364 211 203 212; 365 212 203 204; 366 204 213 212; 367 204 205 213185. 368 202 203 210; 369 100 206 109; 370 109 206 214; 371 214 206 207186. 372 214 207 215; 373 215 207 208; 374 208 216 215; 375 208 209 217187. 376 217 216 208; 377 209 218 217; 378 209 210 218; 379 218 211 219188. 380 219 211 220; 381 220 211 212; 382 212 221 220; 383 212 213 221189. 384 210 211 218190. ELEMENT PROPERTY191. 1 TO 384 TH 0.25192. CONSTANTS193. E 432000000. ALL194. DENSITY 360. ALL195. SUPPORTS196. 1 TO 9 109 TO 125 214 TO 221 FIXED BUT FZ MX MY197. *198. LOAD 1 DEAD LOAD (SELFWEIGHT OF 90 PSF)199. SELFWEIGHT Y -1.200. PERFORM ANALYSIS

SCORDELIS-LO ROOF -- PAGE NO. 5* FILE: PLATE08.STD






***WARNING - INSTABILITY AT JOINT 206 DIRECTION = FZPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 2.4552447E+04 L-MATRIX DIAG= -1.0004442E-10 EQN NO 1155***NOTE - VERY WEAK SPRING ADDED FOR STABILITY201. UNIT KIP FEET202. PRINT JOINT DISPLACEMENTS LIST 55 63 173JOINT DISPLACE LIST 55


JOINT DISPLACEMENT (INCH RADIANS) STRUCTURE TYPE = SPACE



------------------JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN

55 1 0.00000 0.56452 0.00248 0.00000 0.00000 0.0000063 1 -2.01523 -3.79217 0.00257 -0.00010 -0.00019 -0.03358173 1 2.01523 -3.79217 0.00257 -0.00010 0.00019 0.03358************** END OF LATEST ANALYSIS RESULT **************203. PRINT ELEMENT JOINT STRESSES LIST 97 111ELEMENT JOINT STRESSES LIST

SCORDELIS-LO ROOF -- PAGE NO. 7* FILE: PLATE08.STDELEMENT STRESSES FORCE,LENGTH UNITS= KIP FEET----------------



97 1 0.14 0.05 -2.11 -0.40 0.00198.97 173.69 -13.98 -3.29 1.06216.63 188.68

TOP : SMAX= -42.03 SMIN= -216.63 TMAX= 87.30 ANGLE= 89.7BOTT: SMAX= 188.68 SMIN= 35.45 TMAX= 76.61 ANGLE= 0.4JOINT 0.14 0.05 -2.14 -0.42 0.0055 200.49 175.81 -13.53 -2.90 1.06



TOP : SMAX= -38.02 SMIN= -219.99 TMAX= 90.98 ANGLE= 89.7BOTT: SMAX= 190.25 SMIN= 32.22 TMAX= 79.01 ANGLE= 0.4

111 1 0.27 -0.23 0.00 0.61 0.05322.58 207.93 -11.55 257.88 -13.36328.08 214.41

TOP : SMAX= 316.78 SMIN= -11.30 TMAX= 164.04 ANGLE=-88.6BOTT: SMAX= 200.79 SMIN= -13.61 TMAX= 107.20 ANGLE=-85.0JOINT 0.27 -0.23 -0.09 0.69 0.0562 299.64 160.94 -3.76 226.50 -13.36

TOP : SMAX= 293.01 SMIN= -12.85 TMAX= 152.93 ANGLE=-88.5BOTT: SMAX= 162.39 SMIN= 2.94 TMAX= 79.73 ANGLE=-83.3JOINT 0.27 -0.23 0.05 0.69 0.0563 339.48 214.27 -3.76 273.57 -13.36

TOP : SMAX= 340.05 SMIN= 1.16 TMAX= 169.45 ANGLE=-88.6BOTT: SMAX= 208.85 SMIN= -10.45 TMAX= 109.65 ANGLE=-85.2JOINT 0.27 -0.23 0.05 0.45 0.0572 328.94 249.83 -27.13 273.57 -13.36

TOP : SMAX= 317.28 SMIN= -22.21 TMAX= 169.74 ANGLE=-88.6BOTT: SMAX= 231.36 SMIN= -33.54 TMAX= 132.45 ANGLE=-86.0SCORDELIS-LO ROOF -- PAGE NO. 8



3.400522E+02 -2.199874E+02 1.697424E+02 3.225765E+02 3.280787E+02PLATE NO. 111 97 111 111 111CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************204. FINISH



192 — STAAD.Pro


Static Element 8


Static Element 9ObjectiveTo find the displacement in the direction of the load due to a unit load applied at the quadrantsof a quarter of a spherical shell.


ProblemFor the quarter of a spherical shell find the displacement in the direction of the load.

E = 6.825(10)7 psi


t = 0.04 inches

r = 10 in.

Unit forces on quadrants

Boundary conditions:

Vertical restraint at center of free edge

Symmetry defines boundary conditions



Figure 4-12: Model

Comparison


Deflection, δ (in) 0.094 0.09342 <1%


STAAD Input


STAAD SPACE :A QUARTER OF A SHERICAL SHELL* FILE: PLATE09.STD** REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS* TO TEST FINITE ELEMENT ACCURACY,* FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND* 1985*INPUT WIDTH 72UNIT INCH POUNDJOINT COORDINATES1 10. 0. 0.; 2 0. 0. 10.; 3 1.951 0. 9.808; 4 3.827 0. 9.2395 5.556 0. 8.315; 6 7.071 0. 7.071; 7 8.315 0. 5.556; 8 9.239 0. 3.8279 9.808 0. 1.951; 10 9.877 1.564 0.; 11 0. 1.564 9.87712 1.927 1.564 9.687; 13 3.78 1.564 9.125; 14 5.487 1.564 8.212

194 — STAAD.Pro


Static Element 9

15 6.984 1.564 6.984; 16 8.212 1.564 5.487; 17 9.125 1.564 3.7818 9.687 1.564 1.927; 19 9.511 3.09 0.; 20 0. 3.09 9.51121 1.856 3.09 9.328; 22 3.64 3.09 8.787; 23 5.284 3.09 7.90824 6.725 3.09 6.725; 25 7.908 3.09 5.284; 26 8.787 3.09 3.6427 9.328 3.09 1.855; 28 8.91 4.54 0.; 29 0. 4.54 8.9130 1.738 4.54 8.739; 31 3.41 4.54 8.232; 32 4.95 4.54 7.40833 6.3 4.54 6.3; 34 7.408 4.54 4.95; 35 8.232 4.54 3.4136 8.739 4.54 1.738; 37 8.09 5.878 0.; 38 0. 5.878 8.0939 1.578 5.878 7.935; 40 3.096 5.878 7.474; 41 4.495 5.878 6.72742 5.721 5.878 5.72; 43 6.727 5.878 4.495; 44 7.474 5.878 3.09645 7.935 5.878 1.578; 46 7.071 7.071 0.; 47 0. 7.071 7.07148 1.379 7.071 6.935; 49 2.706 7.071 6.533; 50 3.928 7.071 5.87951 5. 7.071 5.; 52 5.879 7.071 3.928; 53 6.533 7.071 2.70654 6.935 7.071 1.379; 55 5.878 8.09 0.; 56 0. 8.09 5.87857 1.147 8.09 5.765; 58 2.249 8.09 5.431; 59 3.266 8.09 4.88760 4.156 8.09 4.156; 61 4.887 8.09 3.266; 62 5.431 8.09 2.24963 5.765 8.09 1.147; 64 4.54 8.91 0.; 65 0. 8.91 4.5466 0.886 8.91 4.453; 67 1.737 8.91 4.194; 68 2.522 8.91 3.77569 3.21 8.91 3.21; 70 3.775 8.91 2.522; 71 4.194 8.91 1.73772 4.453 8.91 0.886; 73 3.09 9.511 0.; 74 0. 9.511 3.0975 0.603 9.511 3.031; 76 1.182 9.511 2.855; 77 1.717 9.511 2.56978 2.185 9.511 2.185; 79 2.569 9.511 1.717; 80 2.855 9.511 1.18281 3.031 9.511 0.603ELEMENT INCIDENCES1 2 3 12 11; 2 3 4 13 12; 3 4 5 14 13; 4 5 6 15 14; 5 6 7 16 156 7 8 17 16; 7 8 9 18 17; 8 9 1 10 18; 9 11 12 21 20; 10 12 13 22 2111 13 14 23 22; 12 14 15 24 23; 13 15 16 25 24; 14 16 17 26 2515 17 18 27 26; 16 18 10 19 27; 17 20 21 30 29; 18 21 22 31 3019 22 23 32 31; 20 23 24 33 32; 21 24 25 34 33; 22 25 26 35 3423 26 27 36 35; 24 27 19 28 36; 25 29 30 39 38; 26 30 31 40 3927 31 32 41 40; 28 32 33 42 41; 29 33 34 43 42; 30 34 35 44 4331 35 36 45 44; 32 36 28 37 45; 33 38 39 48 47; 34 39 40 49 4835 40 41 50 49; 36 41 42 51 50; 37 42 43 52 51; 38 43 44 53 5239 44 45 54 53; 40 45 37 46 54; 41 47 48 57 56; 42 48 49 58 5743 49 50 59 58; 44 50 51 60 59; 45 51 52 61 60; 46 52 53 62 6147 53 54 63 62; 48 54 46 55 63; 49 56 57 66 65; 50 57 58 67 6651 58 59 68 67; 52 59 60 69 68; 53 60 61 70 69; 54 61 62 71 7055 62 63 72 71; 56 63 55 64 72; 57 65 66 75 74; 58 66 67 76 7559 67 68 77 76; 60 68 69 78 77; 61 69 70 79 78; 62 70 71 80 7963 71 72 81 80; 64 72 64 73 81ELEMENT PROPERTY1 TO 64 TH 0.04CONSTANTSE 68250000. ALLPOISSON 0.3 ALLSUPPORTS1 10 19 28 37 46 55 64 73 FIXED BUT FX FY MZ2 11 20 29 38 47 56 65 74 FIXED BUT FY FZ MX6 FIXED BUT FX FZ MX MY MZLOAD 1 UNIT FORCE ON QUADRANTJOINT LOAD2 FZ 1.01 FX -1.0PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 1 2FINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of *



* Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:29:38 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE :A QUARTER OF A SHERICAL SHELLINPUT FILE: PLATE09.STD

2. * FILE: PLATE09.STD3. *4. * REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS5. * TO TEST FINITE ELEMENT ACCURACY,6. * FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND7. * 19858. *9. INPUT WIDTH 7210. UNIT INCH POUND11. JOINT COORDINATES12. 1 10. 0. 0.; 2 0. 0. 10.; 3 1.951 0. 9.808; 4 3.827 0. 9.23913. 5 5.556 0. 8.315; 6 7.071 0. 7.071; 7 8.315 0. 5.556; 8 9.239 0. 3.82714. 9 9.808 0. 1.951; 10 9.877 1.564 0.; 11 0. 1.564 9.87715. 12 1.927 1.564 9.687; 13 3.78 1.564 9.125; 14 5.487 1.564 8.21216. 15 6.984 1.564 6.984; 16 8.212 1.564 5.487; 17 9.125 1.564 3.7817. 18 9.687 1.564 1.927; 19 9.511 3.09 0.; 20 0. 3.09 9.51118. 21 1.856 3.09 9.328; 22 3.64 3.09 8.787; 23 5.284 3.09 7.90819. 24 6.725 3.09 6.725; 25 7.908 3.09 5.284; 26 8.787 3.09 3.6420. 27 9.328 3.09 1.855; 28 8.91 4.54 0.; 29 0. 4.54 8.9121. 30 1.738 4.54 8.739; 31 3.41 4.54 8.232; 32 4.95 4.54 7.40822. 33 6.3 4.54 6.3; 34 7.408 4.54 4.95; 35 8.232 4.54 3.4123. 36 8.739 4.54 1.738; 37 8.09 5.878 0.; 38 0. 5.878 8.0924. 39 1.578 5.878 7.935; 40 3.096 5.878 7.474; 41 4.495 5.878 6.72725. 42 5.721 5.878 5.72; 43 6.727 5.878 4.495; 44 7.474 5.878 3.09626. 45 7.935 5.878 1.578; 46 7.071 7.071 0.; 47 0. 7.071 7.07127. 48 1.379 7.071 6.935; 49 2.706 7.071 6.533; 50 3.928 7.071 5.87928. 51 5. 7.071 5.; 52 5.879 7.071 3.928; 53 6.533 7.071 2.70629. 54 6.935 7.071 1.379; 55 5.878 8.09 0.; 56 0. 8.09 5.87830. 57 1.147 8.09 5.765; 58 2.249 8.09 5.431; 59 3.266 8.09 4.88731. 60 4.156 8.09 4.156; 61 4.887 8.09 3.266; 62 5.431 8.09 2.24932. 63 5.765 8.09 1.147; 64 4.54 8.91 0.; 65 0. 8.91 4.5433. 66 0.886 8.91 4.453; 67 1.737 8.91 4.194; 68 2.522 8.91 3.77534. 69 3.21 8.91 3.21; 70 3.775 8.91 2.522; 71 4.194 8.91 1.73735. 72 4.453 8.91 0.886; 73 3.09 9.511 0.; 74 0. 9.511 3.0936. 75 0.603 9.511 3.031; 76 1.182 9.511 2.855; 77 1.717 9.511 2.56937. 78 2.185 9.511 2.185; 79 2.569 9.511 1.717; 80 2.855 9.511 1.18238. 81 3.031 9.511 0.603:A QUARTER OF A SHERICAL SHELL -- PAGE NO. 2

* FILE: PLATE09.STD39. ELEMENT INCIDENCES40. 1 2 3 12 11; 2 3 4 13 12; 3 4 5 14 13; 4 5 6 15 14; 5 6 7 16 1541. 6 7 8 17 16; 7 8 9 18 17; 8 9 1 10 18; 9 11 12 21 20; 10 12 13 22 2142. 11 13 14 23 22; 12 14 15 24 23; 13 15 16 25 24; 14 16 17 26 2543. 15 17 18 27 26; 16 18 10 19 27; 17 20 21 30 29; 18 21 22 31 3044. 19 22 23 32 31; 20 23 24 33 32; 21 24 25 34 33; 22 25 26 35 3445. 23 26 27 36 35; 24 27 19 28 36; 25 29 30 39 38; 26 30 31 40 3946. 27 31 32 41 40; 28 32 33 42 41; 29 33 34 43 42; 30 34 35 44 4347. 31 35 36 45 44; 32 36 28 37 45; 33 38 39 48 47; 34 39 40 49 4848. 35 40 41 50 49; 36 41 42 51 50; 37 42 43 52 51; 38 43 44 53 5249. 39 44 45 54 53; 40 45 37 46 54; 41 47 48 57 56; 42 48 49 58 5750. 43 49 50 59 58; 44 50 51 60 59; 45 51 52 61 60; 46 52 53 62 6151. 47 53 54 63 62; 48 54 46 55 63; 49 56 57 66 65; 50 57 58 67 6652. 51 58 59 68 67; 52 59 60 69 68; 53 60 61 70 69; 54 61 62 71 7053. 55 62 63 72 71; 56 63 55 64 72; 57 65 66 75 74; 58 66 67 76 7554. 59 67 68 77 76; 60 68 69 78 77; 61 69 70 79 78; 62 70 71 80 7955. 63 71 72 81 80; 64 72 64 73 8156. ELEMENT PROPERTY

196 — STAAD.Pro


Static Element 9

57. 1 TO 64 TH 0.0458. CONSTANTS59. E 68250000. ALL60. POISSON 0.3 ALL61. SUPPORTS62. 1 10 19 28 37 46 55 64 73 FIXED BUT FX FY MZ63. 2 11 20 29 38 47 56 65 74 FIXED BUT FY FZ MX64. 6 FIXED BUT FX FZ MX MY MZ65. LOAD 1 UNIT FORCE ON QUADRANT66. JOINT LOAD67. 2 FZ 1.068. 1 FX -1.069. PERFORM ANALYSIS






:A QUARTER OF A SHERICAL SHELL -- PAGE NO. 3* FILE: PLATE09.STD



1 1 -0.09335 -0.04663 0.00000 0.00000 0.00000 -0.018932 1 0.00000 0.04665 0.09342 -0.01898 0.00000 0.00000

************** END OF LATEST ANALYSIS RESULT **************71. FINISH:A QUARTER OF A SHERICAL SHELL -- PAGE NO. 4



Static Element 10ObjectiveA thick cylindrical plate supported along 2 radial edges. Find the radial displacement, radialstress, tangential stress and longitudinal stress at inner surface due to a unit pressure applied atthe inner surface.




ProblemLoading is unit pressure at inner radius

E = 1(10)6 psi


Inner radius = 3.0 in

Outer radius = 9.0 in

Figure 4-13: Semi-circular plate finite element model

Comparison


Radial deflection (10-3 in) 4.582 4.650a 1.5%

Radial stress (psi) -1.00 -0.95b 5.0%


198 — STAAD.Pro


Static Element 10


Tangential stress (psi) 1.25 1.26b 0.8%

Longitudinal stress (psi) 0.075 0.080 7.0%

a. Radial displacements are measured along FY at node 102 and FX at node 101.

b. On element 82, at node 102, SX is tangential stress, SY is radial stress.

STAAD Input


STAAD SPACE :A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL EDGES* FILE: PLATE10.STD** REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS* TO TEST FINITE ELEMENT ACCURACY,* FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND* 1985*INPUT WIDTH 72*UNIT INCHES POUNDJOINT COORDINATES1 9. 0. 0.; 2 0. 9. 0.; 3 1.563 8.863 0.; 4 3.078 8.457 0.5 4.5 7.794 0.; 6 5.785 6.894 0.; 7 6.894 5.785 0.; 8 7.794 4.5 0.9 8.457 3.078 0.; 10 8.863 1.563 0.; 11 7.875 0. 0.; 12 0. 7.875 0.13 1.367 7.755 0.; 14 2.693 7.4 0.; 15 3.938 6.82 0.; 16 5.062 6.033 0.17 6.033 5.062 0.; 18 6.82 3.937 0.; 19 7.4 2.693 0.; 20 7.755 1.367 0.21 6.75 0. 0.; 22 0. 6.75 0.; 23 1.172 6.647 0.; 24 2.309 6.343 0.25 3.375 5.846 0.; 26 4.339 5.171 0.; 27 5.171 4.339 0.28 5.846 3.375 0.; 29 6.343 2.309 0.; 30 6.647 1.172 0.; 31 5.975 0. 0.32 0. 5.975 0.; 33 1.038 5.884 0.; 34 2.044 5.615 0.; 35 2.988 5.174 0.36 3.841 4.577 0.; 37 4.577 3.841 0.; 38 5.175 2.987 0.39 5.615 2.044 0.; 40 5.884 1.038 0.; 41 5.2 0. 0.; 42 0. 5.2 0.43 0.903 5.121 0.; 44 1.779 4.886 0.; 45 2.6 4.503 0.; 46 3.343 3.983 0.47 3.983 3.342 0.; 48 4.503 2.6 0.; 49 4.886 1.778 0.; 50 5.121 0.903 0.51 4.7 0. 0.; 52 0. 4.7 0.; 53 0.816 4.629 0.; 54 1.608 4.417 0.55 2.35 4.07 0.; 56 3.021 3.6 0.; 57 3.6 3.021 0.; 58 4.07 2.35 0.59 4.417 1.607 0.; 60 4.629 0.816 0.; 61 4.2 0. 0.; 62 0. 4.2 0.63 0.729 4.136 0.; 64 1.436 3.947 0.; 65 2.1 3.637 0.; 66 2.7 3.217 0.67 3.217 2.7 0.; 68 3.637 2.1 0.; 69 3.947 1.436 0.; 70 4.136 0.729 0.71 3.85 0. 0.; 72 0. 3.85 0.; 73 0.669 3.792 0.; 74 1.317 3.618 0.75 1.925 3.334 0.; 76 2.475 2.949 0.; 77 2.949 2.475 0.78 3.334 1.925 0.; 79 3.618 1.317 0.; 80 3.792 0.669 0.; 81 3.5 0. 0.82 0. 3.5 0.; 83 0.608 3.447 0.; 84 1.197 3.289 0.; 85 1.75 3.031 0.86 2.25 2.681 0.; 87 2.681 2.25 0.; 88 3.031 1.75 0.; 89 3.289 1.197 0.90 3.447 0.608 0.; 91 3.25 0. 0.; 92 0. 3.25 0.; 93 0.564 3.201 0.94 1.112 3.054 0.; 95 1.625 2.815 0.; 96 2.089 2.49 0.; 97 2.49 2.089 0.98 2.815 1.625 0.; 99 3.054 1.112 0.; 100 3.201 0.564 0.; 101 3. 0. 0.102 0. 3. 0.; 103 0.521 2.954 0.; 104 1.026 2.819 0.; 105 1.5 2.598 0.106 1.928 2.298 0.; 107 2.298 1.928 0.; 108 2.598 1.5 0.109 2.819 1.026 0.; 110 2.954 0.521 0.ELEMENT INCIDENCES1 2 3 13 12; 2 3 4 14 13; 3 4 5 15 14; 4 5 6 16 15; 5 6 7 17 166 7 8 18 17; 7 8 9 19 18; 8 9 10 20 19; 9 10 1 11 20; 10 12 13 23 2211 13 14 24 23; 12 14 15 25 24; 13 15 16 26 25; 14 16 17 27 2615 17 18 28 27; 16 18 19 29 28; 17 19 20 30 29; 18 20 11 21 3019 22 23 33 32; 20 23 24 34 33; 21 24 25 35 34; 22 25 26 36 3523 26 27 37 36; 24 27 28 38 37; 25 28 29 39 38; 26 29 30 40 3927 30 21 31 40; 28 32 33 43 42; 29 33 34 44 43; 30 34 35 45 44



31 35 36 46 45; 32 36 37 47 46; 33 37 38 48 47; 34 38 39 49 4835 39 40 50 49; 36 40 31 41 50; 37 42 43 53 52; 38 43 44 54 5339 44 45 55 54; 40 45 46 56 55; 41 46 47 57 56; 42 47 48 58 5743 48 49 59 58; 44 49 50 60 59; 45 50 41 51 60; 46 52 53 63 6247 53 54 64 63; 48 54 55 65 64; 49 55 56 66 65; 50 56 57 67 6651 57 58 68 67; 52 58 59 69 68; 53 59 60 70 69; 54 60 51 61 7055 62 63 73 72; 56 63 64 74 73; 57 64 65 75 74; 58 65 66 76 7559 66 67 77 76; 60 67 68 78 77; 61 68 69 79 78; 62 69 70 80 7963 70 61 71 80; 64 72 73 83 82; 65 73 74 84 83; 66 74 75 85 8467 75 76 86 85; 68 76 77 87 86; 69 77 78 88 87; 70 78 79 89 8871 79 80 90 89; 72 80 71 81 90; 73 82 83 93 92; 74 83 84 94 9375 84 85 95 94; 76 85 86 96 95; 77 86 87 97 96; 78 87 88 98 9779 88 89 99 98; 80 89 90 100 99; 81 90 81 91 100; 82 92 93 103 10283 93 94 104 103; 84 94 95 105 104; 85 95 96 106 105; 86 96 97 107 10687 97 98 108 107; 88 98 99 109 108; 89 99 100 110 109; 90 100 91 101 110ELEMENT PROPERTY1 TO 90 TH 1.CONSTANTSE 1000000.0 ALLPOISSON 0.3 ALLSUPPORTS2 12 22 32 42 52 62 72 82 92 102 FIXED BUT FY1 11 21 31 41 51 61 71 81 91 101 FIXED BUT FXLOAD 1 UNIT PRESSURE AT INNER RADIUSJOINT LOAD101 FX 0.2618110 FX 0.5156 FY 0.0909109 FX 0.4920 FY 0.1791108 FX 0.4534 FY 0.2618107 FX 0.4011 FY 0.3366106 FX 0.3366 FY 0.4011105 FX 0.2618 FY 0.4534104 FX 0.1791 FY 0.4920103 FX 0.0909 FY 0.5156102 FY 0.2618* CREATED LOAD 2 IN ORDER TO PRINT DISPLACEMENT VALUESLOAD 2 MULTIPLY LOAD BY 1000REPEAT LOAD1 1000.PERFORM ANALYSISLOAD LIST 2PRINT JOINT DISPLACEMENTS LIST 102 101 107LOAD LIST 1PRINT ELEMENT JOINT STRESSES LIST 82 83 89 90FINISH



1. STAAD SPACE :A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL EDGESINPUT FILE: PLATE10.STD

2. * FILE: PLATE10.STD3. *

200 — STAAD.Pro


Static Element 10

4. * REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS5. * TO TEST FINITE ELEMENT ACCURACY,6. * FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND7. * 19858. *9. INPUT WIDTH 7210. *11. UNIT INCHES POUND12. JOINT COORDINATES13. 1 9. 0. 0.; 2 0. 9. 0.; 3 1.563 8.863 0.; 4 3.078 8.457 0.14. 5 4.5 7.794 0.; 6 5.785 6.894 0.; 7 6.894 5.785 0.; 8 7.794 4.5 0.15. 9 8.457 3.078 0.; 10 8.863 1.563 0.; 11 7.875 0. 0.; 12 0. 7.875 0.16. 13 1.367 7.755 0.; 14 2.693 7.4 0.; 15 3.938 6.82 0.; 16 5.062 6.033 0.17. 17 6.033 5.062 0.; 18 6.82 3.937 0.; 19 7.4 2.693 0.; 20 7.755 1.367 0.18. 21 6.75 0. 0.; 22 0. 6.75 0.; 23 1.172 6.647 0.; 24 2.309 6.343 0.19. 25 3.375 5.846 0.; 26 4.339 5.171 0.; 27 5.171 4.339 0.20. 28 5.846 3.375 0.; 29 6.343 2.309 0.; 30 6.647 1.172 0.; 31 5.975 0. 0.21. 32 0. 5.975 0.; 33 1.038 5.884 0.; 34 2.044 5.615 0.; 35 2.988 5.174 0.22. 36 3.841 4.577 0.; 37 4.577 3.841 0.; 38 5.175 2.987 0.23. 39 5.615 2.044 0.; 40 5.884 1.038 0.; 41 5.2 0. 0.; 42 0. 5.2 0.24. 43 0.903 5.121 0.; 44 1.779 4.886 0.; 45 2.6 4.503 0.; 46 3.343 3.983 0.25. 47 3.983 3.342 0.; 48 4.503 2.6 0.; 49 4.886 1.778 0.; 50 5.121 0.903 0.26. 51 4.7 0. 0.; 52 0. 4.7 0.; 53 0.816 4.629 0.; 54 1.608 4.417 0.27. 55 2.35 4.07 0.; 56 3.021 3.6 0.; 57 3.6 3.021 0.; 58 4.07 2.35 0.28. 59 4.417 1.607 0.; 60 4.629 0.816 0.; 61 4.2 0. 0.; 62 0. 4.2 0.29. 63 0.729 4.136 0.; 64 1.436 3.947 0.; 65 2.1 3.637 0.; 66 2.7 3.217 0.30. 67 3.217 2.7 0.; 68 3.637 2.1 0.; 69 3.947 1.436 0.; 70 4.136 0.729 0.31. 71 3.85 0. 0.; 72 0. 3.85 0.; 73 0.669 3.792 0.; 74 1.317 3.618 0.32. 75 1.925 3.334 0.; 76 2.475 2.949 0.; 77 2.949 2.475 0.33. 78 3.334 1.925 0.; 79 3.618 1.317 0.; 80 3.792 0.669 0.; 81 3.5 0. 0.34. 82 0. 3.5 0.; 83 0.608 3.447 0.; 84 1.197 3.289 0.; 85 1.75 3.031 0.35. 86 2.25 2.681 0.; 87 2.681 2.25 0.; 88 3.031 1.75 0.; 89 3.289 1.197 0.36. 90 3.447 0.608 0.; 91 3.25 0. 0.; 92 0. 3.25 0.; 93 0.564 3.201 0.37. 94 1.112 3.054 0.; 95 1.625 2.815 0.; 96 2.089 2.49 0.; 97 2.49 2.089 0.38. 98 2.815 1.625 0.; 99 3.054 1.112 0.; 100 3.201 0.564 0.; 101 3. 0. 0.:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 2

* FILE: PLATE10.STD39. 102 0. 3. 0.; 103 0.521 2.954 0.; 104 1.026 2.819 0.; 105 1.5 2.598 0.40. 106 1.928 2.298 0.; 107 2.298 1.928 0.; 108 2.598 1.5 0.41. 109 2.819 1.026 0.; 110 2.954 0.521 0.42. ELEMENT INCIDENCES43. 1 2 3 13 12; 2 3 4 14 13; 3 4 5 15 14; 4 5 6 16 15; 5 6 7 17 1644. 6 7 8 18 17; 7 8 9 19 18; 8 9 10 20 19; 9 10 1 11 20; 10 12 13 23 2245. 11 13 14 24 23; 12 14 15 25 24; 13 15 16 26 25; 14 16 17 27 2646. 15 17 18 28 27; 16 18 19 29 28; 17 19 20 30 29; 18 20 11 21 3047. 19 22 23 33 32; 20 23 24 34 33; 21 24 25 35 34; 22 25 26 36 3548. 23 26 27 37 36; 24 27 28 38 37; 25 28 29 39 38; 26 29 30 40 3949. 27 30 21 31 40; 28 32 33 43 42; 29 33 34 44 43; 30 34 35 45 4450. 31 35 36 46 45; 32 36 37 47 46; 33 37 38 48 47; 34 38 39 49 4851. 35 39 40 50 49; 36 40 31 41 50; 37 42 43 53 52; 38 43 44 54 5352. 39 44 45 55 54; 40 45 46 56 55; 41 46 47 57 56; 42 47 48 58 5753. 43 48 49 59 58; 44 49 50 60 59; 45 50 41 51 60; 46 52 53 63 6254. 47 53 54 64 63; 48 54 55 65 64; 49 55 56 66 65; 50 56 57 67 6655. 51 57 58 68 67; 52 58 59 69 68; 53 59 60 70 69; 54 60 51 61 7056. 55 62 63 73 72; 56 63 64 74 73; 57 64 65 75 74; 58 65 66 76 7557. 59 66 67 77 76; 60 67 68 78 77; 61 68 69 79 78; 62 69 70 80 7958. 63 70 61 71 80; 64 72 73 83 82; 65 73 74 84 83; 66 74 75 85 8459. 67 75 76 86 85; 68 76 77 87 86; 69 77 78 88 87; 70 78 79 89 8860. 71 79 80 90 89; 72 80 71 81 90; 73 82 83 93 92; 74 83 84 94 9361. 75 84 85 95 94; 76 85 86 96 95; 77 86 87 97 96; 78 87 88 98 9762. 79 88 89 99 98; 80 89 90 100 99; 81 90 81 91 100; 82 92 93 103 10263. 83 93 94 104 103; 84 94 95 105 104; 85 95 96 106 105; 86 96 97 107 10664. 87 97 98 108 107; 88 98 99 109 108; 89 99 100 110 109; 90 100 91 101 11065. ELEMENT PROPERTY66. 1 TO 90 TH 1.67. CONSTANTS



68. E 1000000.0 ALL69. POISSON 0.3 ALL70. SUPPORTS71. 2 12 22 32 42 52 62 72 82 92 102 FIXED BUT FY72. 1 11 21 31 41 51 61 71 81 91 101 FIXED BUT FX73. LOAD 1 UNIT PRESSURE AT INNER RADIUS74. JOINT LOAD75. 101 FX 0.261876. 110 FX 0.5156 FY 0.090977. 109 FX 0.4920 FY 0.179178. 108 FX 0.4534 FY 0.261879. 107 FX 0.4011 FY 0.336680. 106 FX 0.3366 FY 0.401181. 105 FX 0.2618 FY 0.453482. 104 FX 0.1791 FY 0.492083. 103 FX 0.0909 FY 0.515684. 102 FY 0.261885. * CREATED LOAD 2 IN ORDER TO PRINT DISPLACEMENT VALUES86. LOAD 2 MULTIPLY LOAD BY 100087. REPEAT LOAD88. 1 1000.89. PERFORM ANALYSIS:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 3

* FILE: PLATE10.STD





90. LOAD LIST 291. PRINT JOINT DISPLACEMENTS LIST 102 101 107

JOINT DISPLACE LIST 102:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 4

* FILE: PLATE10.STD



102 2 0.00000 0.00465 0.00000 0.00000 0.00000 0.00000101 2 0.00465 0.00000 0.00000 0.00000 0.00000 0.00000107 2 0.00357 0.00299 0.00000 0.00000 0.00000 0.00000************** END OF LATEST ANALYSIS RESULT **************92. LOAD LIST 193. PRINT ELEMENT JOINT STRESSES LIST 82 83 89 90

ELEMENT JOINT STRESSES LIST:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 5




82 1 0.00 0.00 0.00 0.00 0.001.81 1.81 1.17 -0.91 0.002.08 2.08

TOP : SMAX= 1.17 SMIN= -0.91 TMAX= 1.04 ANGLE= 0.0BOTT: SMAX= 1.17 SMIN= -0.91 TMAX= 1.04 ANGLE= 0.0JOINT 0.00 0.00 0.00 0.00 0.00

202 — STAAD.Pro


Static Element 10

92 1.69 1.69 1.07 -0.88 -0.08TOP : SMAX= 1.07 SMIN= -0.88 TMAX= 0.98 ANGLE= -2.3BOTT: SMAX= 1.07 SMIN= -0.88 TMAX= 0.98 ANGLE= -2.3JOINT 0.00 0.00 0.00 0.00 0.0093 1.69 1.69 1.07 -0.88 0.08

TOP : SMAX= 1.07 SMIN= -0.88 TMAX= 0.98 ANGLE= 2.3BOTT: SMAX= 1.07 SMIN= -0.88 TMAX= 0.98 ANGLE= 2.3JOINT 0.00 0.00 0.00 0.00 0.00103 1.93 1.93 1.26 -0.95 0.08

TOP : SMAX= 1.26 SMIN= -0.95 TMAX= 1.11 ANGLE= 2.1BOTT: SMAX= 1.26 SMIN= -0.95 TMAX= 1.11 ANGLE= 2.1JOINT 0.00 0.00 0.00 0.00 0.00102 1.93 1.93 1.26 -0.95 -0.08

TOP : SMAX= 1.26 SMIN= -0.95 TMAX= 1.11 ANGLE= -2.0BOTT: SMAX= 1.26 SMIN= -0.95 TMAX= 1.11 ANGLE= -2.0

83 1 0.00 0.00 0.00 0.00 0.001.81 1.81 1.17 -0.92 0.002.08 2.08


TOP : SMAX= 1.07 SMIN= -0.88 TMAX= 0.98 ANGLE= -2.3BOTT: SMAX= 1.07 SMIN= -0.88 TMAX= 0.98 ANGLE= -2.3JOINT 0.00 0.00 0.00 0.00 0.0094 1.69 1.69 1.06 -0.88 0.08




89 1 0.00 0.00 0.00 0.00 0.001.81 1.81 1.17 -0.92 0.002.08 2.08

TOP : SMAX= 1.17 SMIN= -0.92 TMAX= 1.04 ANGLE= 0.0BOTT: SMAX= 1.17 SMIN= -0.92 TMAX= 1.04 ANGLE= 0.0:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 6




JOINT 0.00 0.00 0.00 0.00 0.0099 1.69 1.69 1.06 -0.88 -0.08





90 1 0.00 0.00 0.00 0.00 0.00



1.81 1.81 1.17 -0.91 0.002.08 2.08





TOP : SMAX= 1.26 SMIN= -0.95 TMAX= 1.11 ANGLE= -2.1BOTT: SMAX= 1.26 SMIN= -0.95 TMAX= 1.11 ANGLE= -2.1:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 7



1.263807E+00 -9.557952E-01 1.109365E+00 1.807750E+00 2.082329E+00PLATE NO. 82 83 82 89 89CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************94. FINISH:A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL -- PAGE NO. 8



Static Element 11ObjectiveTo find the vertical deflection and bending moments at several points due to a unit pressure ona thin rectangular plate simply supported along 4 edges.

ReferenceTimoshenko, S. and Woinowsky-Kreiger, S., Theory of Plates and Shells, McGraw-Hill, 2nd Edition,1959, Pages 113-117.

204 — STAAD.Pro


Static Element 11

ProblemLoading is unit pressure (1 psi) over entire surface.

E = 1 x 106 psi


Length = 16 in.

Width = 10 in.

Thickness = 0.2 in

Figure 4-14: Model

Comparison


Vertical deflection, δ (in) at joint 162 0.036 0.035490 1.2%

166 0.113 0.11230 1.0%

306 0.025 0.024780 1.4%

Bending moment, Mx (in-lb) at joint 9 1.763 1.640 7.0%

89 8.513 8.410 1.2%

96 1.098 1.050 4.4%





Bending moment, My (in-lb) at joint 9 0.897 0.860 4.1%

89 4.873 4.800 1.3%

96 1.108 0.990 10.7%

Theoretical SolutionCalcs

STAAD Input


1. STAAD SPACE :A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL EDGES2. * FILE: PLATE10.STD3. *4. * REFERENCE: MACNEAL AND HARDER, A PROPOSED STANDARD SET OF PROBLEMS5. * TO TEST FINITE ELEMENT ACCURACY,6. * FINITE ELEMENT IN ANALYSIS AND DESIGN 1, NORTH HOLLAND7. * 19858. *9. INPUT WIDTH 7210. *11. UNIT INCHES POUND12. JOINT COORDINATES13. 1 9. 0. 0.; 2 0. 9. 0.; 3 1.563 8.863 0.; 4 3.078 8.457 0.14. 5 4.5 7.794 0.; 6 5.785 6.894 0.; 7 6.894 5.785 0.; 8 7.794 4.5 0.15. 9 8.457 3.078 0.; 10 8.863 1.563 0.; 11 7.875 0. 0.; 12 0. 7.875 0.16. 13 1.367 7.755 0.; 14 2.693 7.4 0.; 15 3.938 6.82 0.; 16 5.062 6.033 0.17. 17 6.033 5.062 0.; 18 6.82 3.937 0.; 19 7.4 2.693 0.; 20 7.755 1.367 0.18. 21 6.75 0. 0.; 22 0. 6.75 0.; 23 1.172 6.647 0.; 24 2.309 6.343 0.19. 25 3.375 5.846 0.; 26 4.339 5.171 0.; 27 5.171 4.339 0.20. 28 5.846 3.375 0.; 29 6.343 2.309 0.; 30 6.647 1.172 0.; 31 5.975 0. 0.21. 32 0. 5.975 0.; 33 1.038 5.884 0.; 34 2.044 5.615 0.; 35 2.988 5.174 0.22. 36 3.841 4.577 0.; 37 4.577 3.841 0.; 38 5.175 2.987 0.23. 39 5.615 2.044 0.; 40 5.884 1.038 0.; 41 5.2 0. 0.; 42 0. 5.2 0.24. 43 0.903 5.121 0.; 44 1.779 4.886 0.; 45 2.6 4.503 0.; 46 3.343 3.983 0.25. 47 3.983 3.342 0.; 48 4.503 2.6 0.; 49 4.886 1.778 0.; 50 5.121 0.903 0.26. 51 4.7 0. 0.; 52 0. 4.7 0.; 53 0.816 4.629 0.; 54 1.608 4.417 0.27. 55 2.35 4.07 0.; 56 3.021 3.6 0.; 57 3.6 3.021 0.; 58 4.07 2.35 0.28. 59 4.417 1.607 0.; 60 4.629 0.816 0.; 61 4.2 0. 0.; 62 0. 4.2 0.29. 63 0.729 4.136 0.; 64 1.436 3.947 0.; 65 2.1 3.637 0.; 66 2.7 3.217 0.30. 67 3.217 2.7 0.; 68 3.637 2.1 0.; 69 3.947 1.436 0.; 70 4.136 0.729 0.31. 71 3.85 0. 0.; 72 0. 3.85 0.; 73 0.669 3.792 0.; 74 1.317 3.618 0.32. 75 1.925 3.334 0.; 76 2.475 2.949 0.; 77 2.949 2.475 0.33. 78 3.334 1.925 0.; 79 3.618 1.317 0.; 80 3.792 0.669 0.; 81 3.5 0. 0.34. 82 0. 3.5 0.; 83 0.608 3.447 0.; 84 1.197 3.289 0.; 85 1.75 3.031 0.35. 86 2.25 2.681 0.; 87 2.681 2.25 0.; 88 3.031 1.75 0.; 89 3.289 1.197 0.36. 90 3.447 0.608 0.; 91 3.25 0. 0.; 92 0. 3.25 0.; 93 0.564 3.201 0.37. 94 1.112 3.054 0.; 95 1.625 2.815 0.; 96 2.089 2.49 0.; 97 2.49 2.089 0.38. 98 2.815 1.625 0.; 99 3.054 1.112 0.; 100 3.201 0.564 0.; 101 3. 0. 0.39. 102 0. 3. 0.; 103 0.521 2.954 0.; 104 1.026 2.819 0.; 105 1.5 2.598 0.40. 106 1.928 2.298 0.; 107 2.298 1.928 0.; 108 2.598 1.5 0.41. 109 2.819 1.026 0.; 110 2.954 0.521 0.42. ELEMENT INCIDENCES43. 1 2 3 13 12; 2 3 4 14 13; 3 4 5 15 14; 4 5 6 16 15; 5 6 7 17 1644. 6 7 8 18 17; 7 8 9 19 18; 8 9 10 20 19; 9 10 1 11 20; 10 12 13 23 2245. 11 13 14 24 23; 12 14 15 25 24; 13 15 16 26 25; 14 16 17 27 2646. 15 17 18 28 27; 16 18 19 29 28; 17 19 20 30 29; 18 20 11 21 30

206 — STAAD.Pro


Static Element 11

47. 19 22 23 33 32; 20 23 24 34 33; 21 24 25 35 34; 22 25 26 36 3548. 23 26 27 37 36; 24 27 28 38 37; 25 28 29 39 38; 26 29 30 40 3949. 27 30 21 31 40; 28 32 33 43 42; 29 33 34 44 43; 30 34 35 45 4450. 31 35 36 46 45; 32 36 37 47 46; 33 37 38 48 47; 34 38 39 49 4851. 35 39 40 50 49; 36 40 31 41 50; 37 42 43 53 52; 38 43 44 54 5352. 39 44 45 55 54; 40 45 46 56 55; 41 46 47 57 56; 42 47 48 58 5753. 43 48 49 59 58; 44 49 50 60 59; 45 50 41 51 60; 46 52 53 63 6254. 47 53 54 64 63; 48 54 55 65 64; 49 55 56 66 65; 50 56 57 67 6655. 51 57 58 68 67; 52 58 59 69 68; 53 59 60 70 69; 54 60 51 61 7056. 55 62 63 73 72; 56 63 64 74 73; 57 64 65 75 74; 58 65 66 76 7557. 59 66 67 77 76; 60 67 68 78 77; 61 68 69 79 78; 62 69 70 80 7958. 63 70 61 71 80; 64 72 73 83 82; 65 73 74 84 83; 66 74 75 85 8459. 67 75 76 86 85; 68 76 77 87 86; 69 77 78 88 87; 70 78 79 89 8860. 71 79 80 90 89; 72 80 71 81 90; 73 82 83 93 92; 74 83 84 94 93

61. 75 84 85 95 94; 76 85 86 96 95; 77 86 87 97 96; 78 87 88 98 9762. 79 88 89 99 98; 80 89 90 100 99; 81 90 81 91 100; 82 92 93 103 10263. 83 93 94 104 103; 84 94 95 105 104; 85 95 96 106 105; 86 96 97 107 10664. 87 97 98 108 107; 88 98 99 109 108; 89 99 100 110 109; 90 100 91 101 11065. ELEMENT PROPERTY66. 1 TO 90 TH 1.67. CONSTANTS68. E 1000000.0 ALL69. POISSON 0.3 ALL70. SUPPORTS71. 2 12 22 32 42 52 62 72 82 92 102 FIXED BUT FY72. 1 11 21 31 41 51 61 71 81 91 101 FIXED BUT FX73. LOAD 1 UNIT PRESSURE AT INNER RADIUS74. JOINT LOAD75. 101 FX 0.261876. 110 FX 0.5156 FY 0.090977. 109 FX 0.4920 FY 0.179178. 108 FX 0.4534 FY 0.261879. 107 FX 0.4011 FY 0.336680. 106 FX 0.3366 FY 0.401181. 105 FX 0.2618 FY 0.453482. 104 FX 0.1791 FY 0.492083. 103 FX 0.0909 FY 0.515684. 102 FY 0.261885. * CREATED LOAD 2 IN ORDER TO PRINT DISPLACEMENT VALUES86. LOAD 2 MULTIPLY LOAD BY 100087. REPEAT LOAD88. 1 1000.89. PERFORM ANALYSIS90. LOAD LIST 291. PRINT JOINT DISPLACEMENTS LIST 102 101 10792. LOAD LIST 193. PRINT ELEMENT JOINT STRESSES LIST 82 83 89 90



1. 1. STAAD SPACE :A THICK WALLED CYLINDER PLATE SUPPORTED ALONG 2 RADIAL EDGES



INPUT FILE: PLATE11.STD*** ERROR *** ABOVE COMMAND IS NOT RECOGNIZED. LINE IGNORED.DATA-CHECK MODE IS ENTERED.



Static Element 12ObjectiveTo find the bending moment due to thermal load through the thickness of a square plate.

ReferenceTimoshenko, S., Strength of Materials, D. Van Nostrand Co., 3rd Edition,1956.

ProblemTemperature varies 100°F linearly through the thickness of a square plate that is fixed on theedges. Calculate the bending moment on the edges and the maximum bending stress.

E = 30,000.0 ksi, α = 70(10)–7 in/in/°F

Size = 5” x 5”, Thickness = 0.5 in


Figure 4-15: Model

Comparison


Moment (in-lb/in) 625.0 625.0 none

Maximum stress (psi) 15,000 15,000 none


208 — STAAD.Pro


Static Element 12

STAAD Input


STAAD SPACE :THERMAL LOADING OF A PLATE* FILE: PLATE12.STD** REFERENCE: TIMOSHENKO, S., "STENGTH OF MATERIALS," 3RD EDITION,* D. VAN NOSTRAND CO., 1956.*UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 5. 0. 0.; 3 0. 5. 0.; 4 5. 5. 0.ELEMENT INCIDENCES1 1 2 4 3ELEMENT PROPERTY1 TH 0.5CONSTANTSE 30000000. ALLPOISSON 0.3 ALLALPHA 0.000007 ALLSUPPORTS1 TO 4 FIXEDLOAD 1 NON UNIFORM HEATING OF THE PLATETEMPERATURE LOAD1 TEMP 0 100PERFORM ANALYSISPRINT ELEMENT JOINT STRESSES ALLFINISH



1. STAAD SPACE :THERMAL LOADING OF A PLATEINPUT FILE: PLATE12.STD

2. * FILE: PLATE12.STD3. *4. * REFERENCE: TIMOSHENKO, S., "STENGTH OF MATERIALS," 3RD EDITION,5. * D. VAN NOSTRAND CO., 1956.6. *7. UNIT INCHES POUND8. JOINT COORDINATES9. 1 0. 0. 0.; 2 5. 0. 0.; 3 0. 5. 0.; 4 5. 5. 0.10. ELEMENT INCIDENCES11. 1 1 2 4 312. ELEMENT PROPERTY13. 1 TH 0.514. CONSTANTS15. E 30000000. ALL16. POISSON 0.3 ALL17. ALPHA 0.000007 ALL18. SUPPORTS



19. 1 TO 4 FIXED20. LOAD 1 NON UNIFORM HEATING OF THE PLATE**WARNING** - ALL DEGREES OF FREEDOM FIXED.STAAD WILL INFINITESIMALLY RELEASE MOMENT-X AT FIRST JOINT ENTERED.21. TEMPERATURE LOAD22. 1 TEMP 0 10023. PERFORM ANALYSIS:THERMAL LOADING OF A PLATE -- PAGE NO. 2

* FILE: PLATE12.STD





24. PRINT ELEMENT JOINT STRESSES ALLELEMENT JOINT STRESSES ALL

:THERMAL LOADING OF A PLATE -- PAGE NO. 3* FILE: PLATE12.STDELEMENT STRESSES FORCE,LENGTH UNITS= POUN INCH----------------



1 1 0.00 0.00 -625.00 -625.00 0.0015000.00 15000.00 0.00 0.00 0.0015000.00 15000.00

TOP : SMAX= -15000.00 SMIN= -15000.00 TMAX= 0.00 ANGLE= 90.0BOTT: SMAX= 15000.00 SMIN= 15000.00 TMAX= 0.00 ANGLE= 90.0JOINT 0.00 0.00 -625.00 -625.00 0.00

1 15000.00 15000.00 0.00 0.00 0.00TOP : SMAX= -15000.00 SMIN= -15000.00 TMAX= 0.00 ANGLE= 90.0BOTT: SMAX= 15000.00 SMIN= 15000.00 TMAX= 0.00 ANGLE= 90.0JOINT 0.00 0.00 -625.00 -625.00 0.00



3 15000.00 15000.00 0.00 0.00 0.00TOP : SMAX= -15000.00 SMIN= -15000.00 TMAX= 0.00 ANGLE= 90.0BOTT: SMAX= 15000.00 SMIN= 15000.00 TMAX= 0.00 ANGLE= 90.0


1.500000E+04 -1.500000E+04 7.781867E-04 1.500000E+04 1.500000E+04PLATE NO. 1 1 1 1 1CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************25. FINISH:THERMAL LOADING OF A PLATE -- PAGE NO. 4



210 — STAAD.Pro


Static Element 12


Static Element 13ObjectiveTo find the vertical deflection and bending moments due to an unit pressure in a rectangularplate simply supported along four edges.

ReferencesMartin, H. C., Stiffness Matrix for a Triangular Sandwich Element in Bending, NASA TechnicalReport 32-1158, October, 1967.

Timoshenko, S., Strength of Materials, D. Van Nostrand Co., 3rd Edition,1956.

Salerno, V. L., and Goldberg, M. A., Effect of Shear Deformations on the Bending of RectangularPlates, March 1960, Pages 54-58.

ProblemFind the vertical deflection at the points shown in the sketch and the bending stress at thecenter of a 20 in. square plate subjected to a uniform pressure of 1 ksi. Use a quarter of theplate assuming proper boundary conditions along the lines of symmetry.

E = 10,000.0 ksi

Thickness = 5 in




Figure 4-16: Model

Comparison


δ1 6.826 6.864 0.6%

δ9 2.322 2.343 0.9%

δ73 2.684 2.707 0.9%

Table 4-13: Vertical deflections due to unit pressure, 10-3 in


σ, element 1 (psi) 5,071 4,908 3.2%

Table 4-14: Maximum bending stress due to unit pressure

STAAD Input


STAAD SPACE :A SIMPLY SUPPORTED PLATE WITH TRIANGULAR ELEMENTSINPUT WIDTH 72* FILE: PLATE13.STD*

212 — STAAD.Pro


Static Element 13

UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0. 11 10. 0. 0.REPEAT 10 0. 0. 1.ELEMENT INCIDENCES1 1 2 12; 2 2 3 13; 3 3 4 14; 4 4 5 15; 5 5 6 16; 6 6 7 17; 7 7 8 188 8 9 19; 9 9 10 20; 10 10 11 21; 11 12 2 13; 12 13 3 14; 13 14 4 1514 15 5 16; 15 16 6 17; 16 17 7 18; 17 18 8 19; 18 19 9 20; 19 20 10 2120 21 11 22; 21 12 13 23; 22 13 14 24; 23 14 15 25; 24 15 16 2625 16 17 27; 26 17 18 28; 27 18 19 29; 28 19 20 30; 29 20 21 3130 21 22 32; 31 23 13 24; 32 24 14 25; 33 25 15 26; 34 26 16 2735 27 17 28; 36 28 18 29; 37 29 19 30; 38 30 20 31; 39 31 21 3240 32 22 33; 41 23 24 34; 42 24 25 35; 43 25 26 36; 44 26 27 3745 27 28 38; 46 28 29 39; 47 29 30 40; 48 30 31 41; 49 31 32 4250 32 33 43; 51 34 24 35; 52 35 25 36; 53 36 26 37; 54 37 27 3855 38 28 39; 56 39 29 40; 57 40 30 41; 58 41 31 42; 59 42 32 4360 43 33 44; 61 34 35 45; 62 35 36 46; 63 36 37 47; 64 37 38 4865 38 39 49; 66 39 40 50; 67 40 41 51; 68 41 42 52; 69 42 43 5370 43 44 54; 71 45 35 46; 72 46 36 47; 73 47 37 48; 74 48 38 4975 49 39 50; 76 50 40 51; 77 51 41 52; 78 52 42 53; 79 53 43 5480 54 44 55; 81 45 46 56; 82 46 47 57; 83 47 48 58; 84 48 49 5985 49 50 60; 86 50 51 61; 87 51 52 62; 88 52 53 63; 89 53 54 6490 54 55 65; 91 56 46 57; 92 57 47 58; 93 58 48 59; 94 59 49 6095 60 50 61; 96 61 51 62; 97 62 52 63; 98 63 53 64; 99 64 54 65100 65 55 66; 101 56 57 67; 102 57 58 68; 103 58 59 69; 104 59 60 70105 60 61 71; 106 61 62 72; 107 62 63 73; 108 63 64 74; 109 64 65 75110 65 66 76; 111 67 57 68; 112 68 58 69; 113 69 59 70; 114 70 60 71115 71 61 72; 116 72 62 73; 117 73 63 74; 118 74 64 75; 119 75 65 76120 76 66 77; 121 67 68 78; 122 68 69 79; 123 69 70 80; 124 70 71 81125 71 72 82; 126 72 73 83; 127 73 74 84; 128 74 75 85; 129 75 76 86130 76 77 87; 131 78 68 79; 132 79 69 80; 133 80 70 81; 134 81 71 82135 82 72 83; 136 83 73 84; 137 84 74 85; 138 85 75 86; 139 86 76 87140 87 77 88; 141 78 79 89; 142 79 80 90; 143 80 81 91; 144 81 82 92145 82 83 93; 146 83 84 94; 147 84 85 95; 148 85 86 96; 149 86 87 97150 87 88 98; 151 89 79 90; 152 90 80 91; 153 91 81 92; 154 92 82 93155 93 83 94; 156 94 84 95; 157 95 85 96; 158 96 86 97; 159 97 87 98160 98 88 99; 161 89 90 100; 162 90 91 101; 163 91 92 102164 92 93 103; 165 93 94 104; 166 94 95 105; 167 95 96 106168 96 97 107; 169 97 98 108; 170 98 99 109; 171 100 90 101172 101 91 102; 173 102 92 103; 174 103 93 104; 175 104 94 105176 105 95 106; 177 106 96 107; 178 107 97 108; 179 108 98 109180 109 99 110; 181 100 101 111; 182 101 102 112; 183 102 103 113184 103 104 114; 185 104 105 115; 186 105 106 116; 187 106 107 117188 107 108 118; 189 108 109 119; 190 109 110 120; 191 111 101 112192 112 102 113; 193 113 103 114; 194 114 104 115; 195 115 105 116196 116 106 117; 197 117 107 118; 198 118 108 119; 199 119 109 120200 120 110 121ELEMENT PROPERTY1 TO 200 THICKNESS 5.CONSTANTE 1E7 ALLPOISSON .4 ALLSUPPORT1 FIXED BUT FY2 TO 10 BY 1 FIXED BUT FX FY MZ12 TO 100 BY 11 FIXED BUT FY FZ MX11 TO 110 BY 11 FIXED BUT MZ111 TO 120 BY 1 FIXED BUT MX121 FIXEDLOAD 1 UNIFORM PRESSUREELEMENT LOAD1 TO 200 PR -1000.PERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 1 9 73PRINT ELEMENT STRESSES LIST 1FINISH





1. STAAD SPACE :A SIMPLY SUPPORTED PLATE WITH TRIANGULAR ELEMENTSINPUT FILE: PLATE13.STD

2. INPUT WIDTH 723. * FILE: PLATE13.STD4. *5. UNIT INCHES POUND6. JOINT COORDINATES7. 1 0. 0. 0. 11 10. 0. 0.8. REPEAT 10 0. 0. 1.9. ELEMENT INCIDENCES10. 1 1 2 12; 2 2 3 13; 3 3 4 14; 4 4 5 15; 5 5 6 16; 6 6 7 17; 7 7 8 1811. 8 8 9 19; 9 9 10 20; 10 10 11 21; 11 12 2 13; 12 13 3 14; 13 14 4 1512. 14 15 5 16; 15 16 6 17; 16 17 7 18; 17 18 8 19; 18 19 9 20; 19 20 10 2113. 20 21 11 22; 21 12 13 23; 22 13 14 24; 23 14 15 25; 24 15 16 2614. 25 16 17 27; 26 17 18 28; 27 18 19 29; 28 19 20 30; 29 20 21 3115. 30 21 22 32; 31 23 13 24; 32 24 14 25; 33 25 15 26; 34 26 16 2716. 35 27 17 28; 36 28 18 29; 37 29 19 30; 38 30 20 31; 39 31 21 3217. 40 32 22 33; 41 23 24 34; 42 24 25 35; 43 25 26 36; 44 26 27 3718. 45 27 28 38; 46 28 29 39; 47 29 30 40; 48 30 31 41; 49 31 32 4219. 50 32 33 43; 51 34 24 35; 52 35 25 36; 53 36 26 37; 54 37 27 3820. 55 38 28 39; 56 39 29 40; 57 40 30 41; 58 41 31 42; 59 42 32 4321. 60 43 33 44; 61 34 35 45; 62 35 36 46; 63 36 37 47; 64 37 38 4822. 65 38 39 49; 66 39 40 50; 67 40 41 51; 68 41 42 52; 69 42 43 5323. 70 43 44 54; 71 45 35 46; 72 46 36 47; 73 47 37 48; 74 48 38 4924. 75 49 39 50; 76 50 40 51; 77 51 41 52; 78 52 42 53; 79 53 43 5425. 80 54 44 55; 81 45 46 56; 82 46 47 57; 83 47 48 58; 84 48 49 5926. 85 49 50 60; 86 50 51 61; 87 51 52 62; 88 52 53 63; 89 53 54 6427. 90 54 55 65; 91 56 46 57; 92 57 47 58; 93 58 48 59; 94 59 49 6028. 95 60 50 61; 96 61 51 62; 97 62 52 63; 98 63 53 64; 99 64 54 6529. 100 65 55 66; 101 56 57 67; 102 57 58 68; 103 58 59 69; 104 59 60 7030. 105 60 61 71; 106 61 62 72; 107 62 63 73; 108 63 64 74; 109 64 65 7531. 110 65 66 76; 111 67 57 68; 112 68 58 69; 113 69 59 70; 114 70 60 7132. 115 71 61 72; 116 72 62 73; 117 73 63 74; 118 74 64 75; 119 75 65 7633. 120 76 66 77; 121 67 68 78; 122 68 69 79; 123 69 70 80; 124 70 71 8134. 125 71 72 82; 126 72 73 83; 127 73 74 84; 128 74 75 85; 129 75 76 8635. 130 76 77 87; 131 78 68 79; 132 79 69 80; 133 80 70 81; 134 81 71 8236. 135 82 72 83; 136 83 73 84; 137 84 74 85; 138 85 75 86; 139 86 76 8737. 140 87 77 88; 141 78 79 89; 142 79 80 90; 143 80 81 91; 144 81 82 9238. 145 82 83 93; 146 83 84 94; 147 84 85 95; 148 85 86 96; 149 86 87 97:A SIMPLY SUPPORTED PLATE WITH TRIANGULAR ELEMENTS -- PAGE NO. 2

39. 150 87 88 98; 151 89 79 90; 152 90 80 91; 153 91 81 92; 154 92 82 9340. 155 93 83 94; 156 94 84 95; 157 95 85 96; 158 96 86 97; 159 97 87 9841. 160 98 88 99; 161 89 90 100; 162 90 91 101; 163 91 92 10242. 164 92 93 103; 165 93 94 104; 166 94 95 105; 167 95 96 10643. 168 96 97 107; 169 97 98 108; 170 98 99 109; 171 100 90 10144. 172 101 91 102; 173 102 92 103; 174 103 93 104; 175 104 94 10545. 176 105 95 106; 177 106 96 107; 178 107 97 108; 179 108 98 10946. 180 109 99 110; 181 100 101 111; 182 101 102 112; 183 102 103 11347. 184 103 104 114; 185 104 105 115; 186 105 106 116; 187 106 107 117

214 — STAAD.Pro


Static Element 13

48. 188 107 108 118; 189 108 109 119; 190 109 110 120; 191 111 101 11249. 192 112 102 113; 193 113 103 114; 194 114 104 115; 195 115 105 11650. 196 116 106 117; 197 117 107 118; 198 118 108 119; 199 119 109 12051. 200 120 110 12152. ELEMENT PROPERTY53. 1 TO 200 THICKNESS 5.54. CONSTANT55. E 1E7 ALL56. POISSON .4 ALL57. SUPPORT58. 1 FIXED BUT FY59. 2 TO 10 BY 1 FIXED BUT FX FY MZ60. 12 TO 100 BY 11 FIXED BUT FY FZ MX61. 11 TO 110 BY 11 FIXED BUT MZ62. 111 TO 120 BY 1 FIXED BUT MX63. 121 FIXED64. LOAD 1 UNIFORM PRESSURE65. ELEMENT LOAD66. 1 TO 200 PR -1000.67. PERFORM ANALYSIS





68. PRINT JOINT DISPLACEMENTS LIST 1 9 73JOINT DISPLACE LIST 1

:A SIMPLY SUPPORTED PLATE WITH TRIANGULAR ELEMENTS -- PAGE NO. 3



1 1 0.00000 0.00686 0.00000 0.00000 0.00000 0.000009 1 0.00000 0.00234 0.00000 0.00000 0.00000 -0.0008073 1 0.00000 0.00271 0.00000 0.00040 0.00000 -0.00040

************** END OF LATEST ANALYSIS RESULT **************69. PRINT ELEMENT STRESSES LIST 1

ELEMENT STRESSES LIST 1:A SIMPLY SUPPORTED PLATE WITH TRIANGULAR ELEMENTS -- PAGE NO. 4

ELEMENT STRESSES FORCE,LENGTH UNITS= POUN INCH----------------



1 1 33.33 33.33 -20451.07 -20451.07 0.004908.26 4908.26 0.00 0.00 0.004908.26 4908.26

TOP : SMAX= -4908.26 SMIN= -4908.26 TMAX= 0.00 ANGLE= 90.0BOTT: SMAX= 4908.26 SMIN= 4908.26 TMAX= 0.00 ANGLE= 90.0


4.908257E+03 -4.908257E+03 0.000000E+00 4.908257E+03 4.908257E+03PLATE NO. 1 1 1 1 1CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************70. FINISH



:A SIMPLY SUPPORTED PLATE WITH TRIANGULAR ELEMENTS -- PAGE NO. 5*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:29:44 ****


Static Element 14ObjectiveTo find element stress due to joint load at the fixed end of a tapered plate with one end fixed.

ReferenceCrandall, S.H., & Dahl, N.C., An Introduction to the Mechanics of Solids, McGraw – Hill, Inc., 1959.

ProblemThe tapered plate structure is loaded at the free end. Calculate the maximum stress at themidspan.

E = 30,000.0 ksi

Thickness = 2 in


P = 4 kips

Figure 4-17: Model

ComparisonThe STAAD.Pro result is taken as average of stress in elements 9 and 11 at node 16 = 0.5(8,333.35 + 8,359.62) = 8,346.5.


Maximum stress at the center (psi) 8,333 8,346.5 0.2%


216 — STAAD.Pro


Static Element 14

STAAD Input


STAAD SPACE :A TAPERED BEAM WITH PLATE ELEMENTS* FILE: PLATE14.STD** REFERENCE: CRANDALL, S. H., AND DAHL, N.C., "AN INTRODUCTION TO THE* MECHANICS OF SOLIDS," MCGRAW-HILL BOOK CO., INC.,* NEW YORK, 1978*INPUT WIDTH 79UNIT INCHES POUNDJOINT COORDINATES1 50.000 0.000 0.0002 50.000 -4.500 0.0003 50.000 -9.000 0.0004 45.000 0.000 0.0005 45.000 -4.200 0.0006 45.000 -8.400 0.0007 40.000 0.000 0.0008 40.000 -3.900 0.0009 40.000 -7.800 0.00010 35.000 0.000 0.00011 35.000 -3.600 0.00012 35.000 -7.200 0.00013 30.000 0.000 0.00014 30.000 -3.300 0.00015 30.000 -6.600 0.00016 25.000 0.000 0.00017 25.000 -3.000 0.00018 25.000 -6.000 0.00019 20.000 0.000 0.00020 20.000 -2.700 0.00021 20.000 -5.400 0.00022 15.000 0.000 0.00023 15.000 -2.400 0.00024 15.000 -4.800 0.00025 10.000 0.000 0.00026 10.000 -2.100 0.00027 10.000 -4.200 0.00028 5.000 0.000 0.00029 5.000 -1.800 0.00030 5.000 -3.600 0.00031 0.000 0.000 0.00032 0.000 -1.500 0.00033 0.000 -3.000 0.000ELEMENT INCIDENCES1 4 5 2 12 5 6 3 23 7 8 5 44 8 9 6 55 10 11 8 76 11 12 9 87 13 14 11 108 14 15 12 119 16 17 14 1310 17 18 15 1411 19 20 17 1612 20 21 18 1713 22 23 20 1914 23 24 21 2015 25 26 23 2216 26 27 24 23



17 28 29 26 2518 29 30 27 2619 31 32 29 2820 32 33 30 29ELEMENT PROPERTY1 TO 20 TH 2.CONSTANTSE 30000000. ALLPOISSON 0.2 ALLSUPPORTS1 TO 3 FIXEDLOAD 1 POINT LOADJOINT LOAD31 FY -4000.PERFORM ANALYSISPRINT ELEMENT JOINT STRESSES LIST 9 11FINISH



1. STAAD SPACE :A TAPERED BEAM WITH PLATE ELEMENTSINPUT FILE: PLATE14.STD

2. * FILE: PLATE14.STD3. *4. * REFERENCE: CRANDALL, S. H., AND DAHL, N.C., "AN INTRODUCTION TO THE5. * MECHANICS OF SOLIDS," MCGRAW-HILL BOOK CO., INC.,6. * NEW YORK, 19787. *8. INPUT WIDTH 799. UNIT INCHES POUND10. JOINT COORDINATES11. 1 50.000 0.000 0.00012. 2 50.000 -4.500 0.00013. 3 50.000 -9.000 0.00014. 4 45.000 0.000 0.00015. 5 45.000 -4.200 0.00016. 6 45.000 -8.400 0.00017. 7 40.000 0.000 0.00018. 8 40.000 -3.900 0.00019. 9 40.000 -7.800 0.00020. 10 35.000 0.000 0.00021. 11 35.000 -3.600 0.00022. 12 35.000 -7.200 0.00023. 13 30.000 0.000 0.00024. 14 30.000 -3.300 0.00025. 15 30.000 -6.600 0.00026. 16 25.000 0.000 0.00027. 17 25.000 -3.000 0.00028. 18 25.000 -6.000 0.00029. 19 20.000 0.000 0.00030. 20 20.000 -2.700 0.00031. 21 20.000 -5.400 0.000

218 — STAAD.Pro


Static Element 14

32. 22 15.000 0.000 0.00033. 23 15.000 -2.400 0.00034. 24 15.000 -4.800 0.00035. 25 10.000 0.000 0.00036. 26 10.000 -2.100 0.00037. 27 10.000 -4.200 0.00038. 28 5.000 0.000 0.000:A TAPERED BEAM WITH PLATE ELEMENTS -- PAGE NO. 2

* FILE: PLATE14.STD39. 29 5.000 -1.800 0.00040. 30 5.000 -3.600 0.00041. 31 0.000 0.000 0.00042. 32 0.000 -1.500 0.00043. 33 0.000 -3.000 0.00044. ELEMENT INCIDENCES45. 1 4 5 2 146. 2 5 6 3 247. 3 7 8 5 448. 4 8 9 6 549. 5 10 11 8 750. 6 11 12 9 851. 7 13 14 11 1052. 8 14 15 12 1153. 9 16 17 14 1354. 10 17 18 15 1455. 11 19 20 17 1656. 12 20 21 18 1757. 13 22 23 20 1958. 14 23 24 21 2059. 15 25 26 23 2260. 16 26 27 24 2361. 17 28 29 26 2562. 18 29 30 27 2663. 19 31 32 29 2864. 20 32 33 30 2965. ELEMENT PROPERTY66. 1 TO 20 TH 2.67. CONSTANTS68. E 30000000. ALL69. POISSON 0.2 ALL70. SUPPORTS71. 1 TO 3 FIXED72. LOAD 1 POINT LOAD73. JOINT LOAD74. 31 FY -4000.75. PERFORM ANALYSIS





:A TAPERED BEAM WITH PLATE ELEMENTS -- PAGE NO. 3* FILE: PLATE14.STD76. PRINT ELEMENT JOINT STRESSES LIST 9 11

ELEMENT JOINT STRESSES LIST:A TAPERED BEAM WITH PLATE ELEMENTS -- PAGE NO. 4


STRESS = FORCE/UNIT WIDTH/THICK, MOMENT = FORCE-LENGTH/UNIT WIDTH



ELEMENT LOAD SQX SQY MX MY MXYVONT VONB SX SY SXYTRESCAT TRESCAB

9 1 0.00 0.00 0.00 0.00 0.004157.59 4157.59 -4.32 4153.58 -71.594160.36 4160.36

TOP : SMAX= 4154.81 SMIN= -5.55 TMAX= 2080.18 ANGLE=-89.0BOTT: SMAX= 4154.81 SMIN= -5.55 TMAX= 2080.18 ANGLE=-89.0JOINT 0.00 0.00 0.00 0.00 0.0016 8372.99 8372.99 -78.55 8333.17 38.19

TOP : SMAX= 8333.35 SMIN= -78.72 TMAX= 4206.03 ANGLE= 89.7BOTT: SMAX= 8333.35 SMIN= -78.72 TMAX= 4206.03 ANGLE= 89.7JOINT 0.00 0.00 0.00 0.00 0.0017 343.34 343.34 42.49 3.59 -196.82

TOP : SMAX= 220.82 SMIN= -174.74 TMAX= 197.78 ANGLE=-42.2BOTT: SMAX= 220.82 SMIN= -174.74 TMAX= 197.78 ANGLE=-42.2JOINT 0.00 0.00 0.00 0.00 0.0014 295.01 295.01 -107.35 -73.48 -161.24

TOP : SMAX= 71.72 SMIN= -252.54 TMAX= 162.13 ANGLE=-48.0BOTT: SMAX= 71.72 SMIN= -252.54 TMAX= 162.13 ANGLE=-48.0JOINT 0.00 0.00 0.00 0.00 0.0013 8295.66 8295.66 93.65 8341.38 62.12


11 1 0.00 0.00 0.00 0.00 0.004155.63 4155.63 -4.64 4149.10 -107.914159.35 4159.35

TOP : SMAX= 4151.91 SMIN= -7.44 TMAX= 2079.67 ANGLE=-88.5BOTT: SMAX= 4151.91 SMIN= -7.44 TMAX= 2079.67 ANGLE=-88.5JOINT 0.00 0.00 0.00 0.00 0.0019 8323.84 8323.84 -72.93 8286.88 37.52


TOP : SMAX= 260.40 SMIN= -212.54 TMAX= 236.47 ANGLE=-39.5BOTT: SMAX= 260.40 SMIN= -212.54 TMAX= 236.47 ANGLE=-39.5JOINT 0.00 0.00 0.00 0.00 0.0017 377.42 377.42 -132.29 -39.10 -207.04

TOP : SMAX= 126.52 SMIN= -297.91 TMAX= 212.21 ANGLE=-51.3BOTT: SMAX= 126.52 SMIN= -297.91 TMAX= 212.21 ANGLE=-51.3JOINT 0.00 0.00 0.00 0.00 0.0016 8319.08 8319.08 82.05 8359.26 54.91

TOP : SMAX= 8359.62 SMIN= 81.68 TMAX= 4138.97 ANGLE= 89.6BOTT: SMAX= 8359.62 SMIN= 81.68 TMAX= 4138.97 ANGLE= 89.6:A TAPERED BEAM WITH PLATE ELEMENTS -- PAGE NO. 5



8.359622E+03 -2.979080E+02 4.206035E+03 4.157588E+03 4.160359E+03PLATE NO. 11 11 9 9 9CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************77. FINISH:A TAPERED BEAM WITH PLATE ELEMENTS -- PAGE NO. 6


************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu *

220 — STAAD.Pro


Static Element 14

* Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Static Element 15ObjectiveTo find the normal stress on the edge of a circular hole in the center of a rectangular plate.

ReferenceYoung, W. C., Roark’s Formulas for Stress and Strain, McGraw-Hill Inc., 6th Edition, 1989 (Page 732,Type 7).

ProblemFind the normal stress on the edge of the circular hole for the plate shown, when an in-planeload causes tension. Use a one-quarter, doubly symmetric model.

Figure 4-18: One quarter of rectangular plate with hole

E = 30,000.0 ksi

Size = 12.10 in x 7.0 in, Thickness = 0.1 in

Fillet radius = 1 in


P = 2,000 lbs



Figure 4-19: Model with nodes and elements labeled

Comparison


Stress on fillet (node 1, plate 1) (psi) 9.475 9.489 <1%


STAAD Input


STAAD PLANE :STRESS CONCENTRATION IN A PLATE* FILE: PLATE15.STD** REFERENCE: "ROARK'S FORMULAS FOR STRESS AND STRAIN", YOUNG W. C.,* SIXTH EDITION, MCGRAW-HILL, PAGE 732.* 7. GENERAL CIRCULAR HOLE IN CENTER OF A MEMBER OF RECTANGULAR CROSS SECTION* 1/4 MODEL DOUBLY SYMMETRIC* D = 7.0 INCHES WIDTH* R = 1.0 INCH HOLE RADIUS* T = 0.1 INCH THICKNESS* L = 12.1 INCH LENGTH* LOAD = 2000 POUNDS* THEORETICAL RESULTS* AVERAGE STRESS AT ENDS = 2857 PSI (7 INCH WIDTH)* AVERAGE NOMINAL STRESS AT CENTER = 4000 PSI (7-5 INCH WIDTH)* K STRESS CONCENTRATION FACTOR = 2.3688* MAXIMUM STRESS AT EDGE OF HOLE = 2.3688 * 4000 = 9475 PSI* STAAD RESULTS* MAXIMUM STRESS AT EDGE OF HOLE = 9489 PSI* K STRESS CONCENTRATION FACTOR = 2.37225* PERCENT ERROR = 0.15%*UNIT INCHES POUND

222 — STAAD.Pro


Static Element 15

JOINT COORDINATES1 0.000 1.000 0.0002 -0.174 0.985 0.0003 -0.342 0.940 0.0004 -0.500 0.866 0.0005 -0.643 0.766 0.0006 -0.766 0.643 0.0007 -0.866 0.500 0.0008 -0.940 0.342 0.0009 -0.985 0.174 0.00010 -1.000 0.000 0.00011 0.000 1.200 0.00012 -0.208 1.182 0.00013 -0.410 1.128 0.00014 -0.600 1.039 0.00015 -0.771 0.919 0.00016 -0.919 0.771 0.00017 -1.039 0.600 0.00018 -1.128 0.410 0.00019 -1.182 0.208 0.00020 -1.200 0.000 0.00021 0.000 1.400 0.00022 -0.243 1.379 0.00023 -0.479 1.316 0.00024 -0.700 1.212 0.00025 -0.900 1.072 0.00026 -1.072 0.900 0.00027 -1.212 0.700 0.00028 -1.316 0.479 0.00029 -1.379 0.243 0.00030 -1.400 0.000 0.00031 0.000 1.600 0.00032 -0.278 1.576 0.00033 -0.547 1.504 0.00034 -0.800 1.386 0.00035 -1.028 1.226 0.00036 -1.226 1.028 0.00037 -1.386 0.800 0.00038 -1.504 0.547 0.00039 -1.576 0.278 0.00040 -1.600 0.000 0.00041 -1.101 1.500 0.00042 -1.500 1.101 0.00043 -1.500 1.500 0.00044 0.000 1.800 0.00045 -0.300 1.800 0.00046 -0.600 1.800 0.00047 -0.900 1.800 0.00048 -1.200 1.800 0.00049 -1.500 1.800 0.00050 0.000 2.225 0.00051 -0.300 2.225 0.00052 -0.600 2.225 0.00053 -0.900 2.225 0.00054 -1.200 2.225 0.00055 -1.500 2.225 0.00056 0.000 2.650 0.00057 -0.300 2.650 0.00058 -0.600 2.650 0.00059 -0.900 2.650 0.00060 -1.200 2.650 0.00061 -1.500 2.650 0.00062 0.000 3.075 0.00063 -0.300 3.075 0.00064 -0.600 3.075 0.00065 -0.900 3.075 0.000



66 -1.200 3.075 0.00067 -1.500 3.075 0.00068 0.000 3.500 0.00069 -0.300 3.500 0.00070 -0.600 3.500 0.00071 -0.900 3.500 0.00072 -1.200 3.500 0.00073 -1.500 3.500 0.00074 -1.800 0.000 0.00075 -2.225 0.000 0.00076 -2.650 0.000 0.00077 -3.075 0.000 0.00078 -3.500 0.000 0.00079 -3.925 0.000 0.00080 -4.350 0.000 0.00081 -4.775 0.000 0.00082 -5.200 0.000 0.00083 -5.625 0.000 0.00084 -6.050 0.000 0.00085 -1.800 0.300 0.00086 -2.225 0.300 0.00087 -2.650 0.300 0.00088 -3.075 0.300 0.00089 -3.500 0.300 0.00090 -3.925 0.300 0.00091 -4.350 0.300 0.00092 -4.775 0.300 0.00093 -5.200 0.300 0.00094 -5.625 0.300 0.00095 -6.050 0.300 0.00096 -1.800 0.600 0.00097 -2.225 0.600 0.00098 -2.650 0.600 0.00099 -3.075 0.600 0.000100 -3.500 0.600 0.000101 -3.925 0.600 0.000102 -4.350 0.600 0.000103 -4.775 0.600 0.000104 -5.200 0.600 0.000105 -5.625 0.600 0.000106 -6.050 0.600 0.000107 -1.800 0.900 0.000108 -2.225 0.900 0.000109 -2.650 0.900 0.000110 -3.075 0.900 0.000111 -3.500 0.900 0.000112 -3.925 0.900 0.000113 -4.350 0.900 0.000114 -4.775 0.900 0.000115 -5.200 0.900 0.000116 -5.625 0.900 0.000117 -6.050 0.900 0.000118 -1.800 1.200 0.000119 -2.225 1.200 0.000120 -2.650 1.200 0.000121 -3.075 1.200 0.000122 -3.500 1.200 0.000123 -3.925 1.200 0.000124 -4.350 1.200 0.000125 -4.775 1.200 0.000126 -5.200 1.200 0.000127 -5.625 1.200 0.000128 -6.050 1.200 0.000129 -1.800 1.500 0.000130 -2.225 1.500 0.000131 -2.650 1.500 0.000

224 — STAAD.Pro


Static Element 15

132 -3.075 1.500 0.000133 -3.500 1.500 0.000134 -3.925 1.500 0.000135 -4.350 1.500 0.000136 -4.775 1.500 0.000137 -5.200 1.500 0.000138 -5.625 1.500 0.000139 -6.050 1.500 0.000140 -1.800 1.800 0.000141 -2.225 1.800 0.000142 -2.650 1.800 0.000143 -3.075 1.800 0.000144 -3.500 1.800 0.000145 -3.925 1.800 0.000146 -4.350 1.800 0.000147 -4.775 1.800 0.000148 -5.200 1.800 0.000149 -5.625 1.800 0.000150 -6.050 1.800 0.000151 -1.800 2.225 0.000152 -2.225 2.225 0.000153 -2.650 2.225 0.000154 -3.075 2.225 0.000155 -3.500 2.225 0.000156 -3.925 2.225 0.000157 -4.350 2.225 0.000158 -4.775 2.225 0.000159 -5.200 2.225 0.000160 -5.625 2.225 0.000161 -6.050 2.225 0.000162 -1.800 2.650 0.000163 -2.225 2.650 0.000164 -2.650 2.650 0.000165 -3.075 2.650 0.000166 -3.500 2.650 0.000167 -3.925 2.650 0.000168 -4.350 2.650 0.000169 -4.775 2.650 0.000170 -5.200 2.650 0.000171 -5.625 2.650 0.000172 -6.050 2.650 0.000173 -1.800 3.075 0.000174 -2.225 3.075 0.000175 -2.650 3.075 0.000176 -3.075 3.075 0.000177 -3.500 3.075 0.000178 -3.925 3.075 0.000179 -4.350 3.075 0.000180 -4.775 3.075 0.000181 -5.200 3.075 0.000182 -5.625 3.075 0.000183 -6.050 3.075 0.000184 -1.800 3.500 0.000185 -2.225 3.500 0.000186 -2.650 3.500 0.000187 -3.075 3.500 0.000188 -3.500 3.500 0.000189 -3.925 3.500 0.000190 -4.350 3.500 0.000191 -4.775 3.500 0.000192 -5.200 3.500 0.000193 -5.625 3.500 0.000194 -6.050 3.500 0.000201 -1.301 1.301 0.000ELEMENT INCIDENCES SHELL1 1 11 12 2



2 2 12 13 33 3 13 14 44 4 14 15 55 5 15 16 66 6 16 17 77 7 17 18 88 8 18 19 99 9 19 20 1011 11 21 22 1212 12 22 23 1313 13 23 24 1414 14 24 25 1515 15 25 26 1616 16 26 27 1717 17 27 28 1818 18 28 29 1919 19 29 30 2021 21 31 32 2222 22 32 33 2323 23 33 34 2424 24 34 35 2525 25 35 36 2626 26 36 37 2727 27 37 38 2828 28 38 39 2929 29 39 40 3031 31 44 45 3232 32 45 3333 33 47 3434 34 47 4135 34 41 3536 35 41 20137 35 201 3638 36 201 4239 36 42 3740 37 42 10741 37 107 3842 38 85 3943 39 85 74 4044 45 46 3345 46 47 3346 47 48 4147 41 48 4348 41 43 20149 201 43 4250 42 43 11851 42 118 10752 38 107 9653 38 96 8554 48 49 4355 43 129 11856 43 49 140 12957 74 85 86 7558 75 86 87 7659 76 87 88 7760 77 88 89 7861 78 89 90 7962 79 90 91 8063 80 91 92 8164 81 92 93 8265 82 93 94 8366 83 94 95 8477 85 96 97 8678 86 97 98 8779 87 98 99 8880 88 99 100 89

226 — STAAD.Pro


Static Element 15

81 89 100 101 9082 90 101 102 9183 91 102 103 9284 92 103 104 9385 93 104 105 9486 94 105 106 9597 96 107 108 9798 97 108 109 9899 98 109 110 99100 99 110 111 100101 100 111 112 101102 101 112 113 102103 102 113 114 103104 103 114 115 104105 104 115 116 105106 105 116 117 106117 107 118 119 108118 108 119 120 109119 109 120 121 110120 110 121 122 111121 111 122 123 112122 112 123 124 113123 113 124 125 114124 114 125 126 115125 115 126 127 116126 116 127 128 117137 118 129 130 119138 119 130 131 120139 120 131 132 121140 121 132 133 122141 122 133 134 123142 123 134 135 124143 124 135 136 125144 125 136 137 126145 126 137 138 127146 127 138 139 128157 129 140 141 130158 130 141 142 131159 131 142 143 132160 132 143 144 133161 133 144 145 134162 134 145 146 135163 135 146 147 136164 136 147 148 137165 137 148 149 138166 138 149 150 139171 44 50 51 45172 45 51 52 46173 46 52 53 47174 47 53 54 48175 48 54 55 49176 49 55 151 140177 140 151 152 141178 141 152 153 142179 142 153 154 143180 143 154 155 144181 144 155 156 145182 145 156 157 146183 146 157 158 147184 147 158 159 148185 148 159 160 149186 149 160 161 150191 50 56 57 51192 51 57 58 52193 52 58 59 53194 53 59 60 54



195 54 60 61 55196 55 61 162 151197 151 162 163 152198 152 163 164 153199 153 164 165 154200 154 165 166 155201 155 166 167 156202 156 167 168 157203 157 168 169 158204 158 169 170 159205 159 170 171 160206 160 171 172 161211 56 62 63 57212 57 63 64 58213 58 64 65 59214 59 65 66 60215 60 66 67 61216 61 67 173 162217 162 173 174 163218 163 174 175 164219 164 175 176 165220 165 176 177 166221 166 177 178 167222 167 178 179 168223 168 179 180 169224 169 180 181 170225 170 181 182 171226 171 182 183 172231 62 68 69 63232 63 69 70 64233 64 70 71 65234 65 71 72 66235 66 72 73 67236 67 73 184 173237 173 184 185 174238 174 185 186 175239 175 186 187 176240 176 187 188 177241 177 188 189 178242 178 189 190 179243 179 190 191 180244 180 191 192 181245 181 192 193 182246 182 193 194 183ELEMENT PROPERTY1 TO 9 11 TO 19 21 TO 29 31 TO 66 77 TO 86 THICKNESS 0.197 TO 106 117 TO 126 137 TO 146 157 TO 166 171 TO 186 191 TO 205 -206 THICKNESS 0.1211 TO 226 231 TO 246 THICKNESS 0.1ELEMENT PLANE STRESS1 TO 9 11 TO 19 21 TO 29 31 TO 66 77 TO 86 97 TO 106 117 TO 126 137 -138 TO 146 157 TO 166 171 TO 186 191 TO 206 211 TO 226 231 TO 246CONSTANTSE 3E+007 ALLPOISSON 0.3 ALLSUPPORTS10 20 30 40 74 TO 84 FIXED BUT FX1 11 21 31 44 50 56 62 68 FIXED BUT FYLOAD 1 TENSILE LOADJOINT LOAD84 FX -42.85795 106 117 128 139 FX -85.714150 FX -103.571161 172 183 FX -121.428194 FX -60.714PERFORM ANALYSIS PRINT STATIC CHECK

228 — STAAD.Pro


Static Element 15

PRINT JOINT DISP LIST 6 84PRINT ELEMENT JOINT STRESSES LIST 1FINISH



1. STAAD PLANE :STRESS CONCENTRATION IN A PLATEINPUT FILE: PLATE15.STD

2. * FILE: PLATE15.STD3. *4. * REFERENCE: "ROARK'S FORMULAS FOR STRESS AND STRAIN", YOUNG W. C.,5. * SIXTH EDITION, MCGRAW-HILL, PAGE 732.6. * 7. GENERAL CIRCULAR HOLE IN CENTER OF A MEMBER OF RECTANGULAR CROSS SECTION7. * 1/4 MODEL DOUBLY SYMMETRIC8. * D = 7.0 INCHES WIDTH9. * R = 1.0 INCH HOLE RADIUS10. * T = 0.1 INCH THICKNESS11. * L = 12.1 INCH LENGTH12. * LOAD = 2000 POUNDS13. * THEORETICAL RESULTS14. * AVERAGE STRESS AT ENDS = 2857 PSI (7 INCH WIDTH)15. * AVERAGE NOMINAL STRESS AT CENTER = 4000 PSI (7-5 INCH WIDTH)16. * K STRESS CONCENTRATION FACTOR = 2.368817. * MAXIMUM STRESS AT EDGE OF HOLE = 2.3688 * 4000 = 9475 PSI18. * STAAD RESULTS19. * MAXIMUM STRESS AT EDGE OF HOLE = 9489 PSI20. * K STRESS CONCENTRATION FACTOR = 2.3722521. * PERCENT ERROR = 0.15%22. *23. UNIT INCHES POUND24. JOINT COORDINATES25. 1 0.000 1.000 0.00026. 2 -0.174 0.985 0.00027. 3 -0.342 0.940 0.00028. 4 -0.500 0.866 0.00029. 5 -0.643 0.766 0.00030. 6 -0.766 0.643 0.00031. 7 -0.866 0.500 0.00032. 8 -0.940 0.342 0.00033. 9 -0.985 0.174 0.00034. 10 -1.000 0.000 0.00035. 11 0.000 1.200 0.00036. 12 -0.208 1.182 0.00037. 13 -0.410 1.128 0.00038. 14 -0.600 1.039 0.000:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 2

* FILE: PLATE15.STD39. 15 -0.771 0.919 0.00040. 16 -0.919 0.771 0.00041. 17 -1.039 0.600 0.00042. 18 -1.128 0.410 0.00043. 19 -1.182 0.208 0.000



44. 20 -1.200 0.000 0.00045. 21 0.000 1.400 0.00046. 22 -0.243 1.379 0.00047. 23 -0.479 1.316 0.00048. 24 -0.700 1.212 0.00049. 25 -0.900 1.072 0.00050. 26 -1.072 0.900 0.00051. 27 -1.212 0.700 0.00052. 28 -1.316 0.479 0.00053. 29 -1.379 0.243 0.00054. 30 -1.400 0.000 0.00055. 31 0.000 1.600 0.00056. 32 -0.278 1.576 0.00057. 33 -0.547 1.504 0.00058. 34 -0.800 1.386 0.00059. 35 -1.028 1.226 0.00060. 36 -1.226 1.028 0.00061. 37 -1.386 0.800 0.00062. 38 -1.504 0.547 0.00063. 39 -1.576 0.278 0.00064. 40 -1.600 0.000 0.00065. 41 -1.101 1.500 0.00066. 42 -1.500 1.101 0.00067. 43 -1.500 1.500 0.00068. 44 0.000 1.800 0.00069. 45 -0.300 1.800 0.00070. 46 -0.600 1.800 0.00071. 47 -0.900 1.800 0.00072. 48 -1.200 1.800 0.00073. 49 -1.500 1.800 0.00074. 50 0.000 2.225 0.00075. 51 -0.300 2.225 0.00076. 52 -0.600 2.225 0.00077. 53 -0.900 2.225 0.00078. 54 -1.200 2.225 0.00079. 55 -1.500 2.225 0.00080. 56 0.000 2.650 0.00081. 57 -0.300 2.650 0.00082. 58 -0.600 2.650 0.00083. 59 -0.900 2.650 0.00084. 60 -1.200 2.650 0.00085. 61 -1.500 2.650 0.00086. 62 0.000 3.075 0.00087. 63 -0.300 3.075 0.00088. 64 -0.600 3.075 0.00089. 65 -0.900 3.075 0.00090. 66 -1.200 3.075 0.00091. 67 -1.500 3.075 0.00092. 68 0.000 3.500 0.00093. 69 -0.300 3.500 0.00094. 70 -0.600 3.500 0.000:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 3

* FILE: PLATE15.STD95. 71 -0.900 3.500 0.00096. 72 -1.200 3.500 0.00097. 73 -1.500 3.500 0.00098. 74 -1.800 0.000 0.00099. 75 -2.225 0.000 0.000100. 76 -2.650 0.000 0.000101. 77 -3.075 0.000 0.000102. 78 -3.500 0.000 0.000103. 79 -3.925 0.000 0.000104. 80 -4.350 0.000 0.000105. 81 -4.775 0.000 0.000106. 82 -5.200 0.000 0.000107. 83 -5.625 0.000 0.000

230 — STAAD.Pro


Static Element 15

108. 84 -6.050 0.000 0.000109. 85 -1.800 0.300 0.000110. 86 -2.225 0.300 0.000111. 87 -2.650 0.300 0.000112. 88 -3.075 0.300 0.000113. 89 -3.500 0.300 0.000114. 90 -3.925 0.300 0.000115. 91 -4.350 0.300 0.000116. 92 -4.775 0.300 0.000117. 93 -5.200 0.300 0.000118. 94 -5.625 0.300 0.000119. 95 -6.050 0.300 0.000120. 96 -1.800 0.600 0.000121. 97 -2.225 0.600 0.000122. 98 -2.650 0.600 0.000123. 99 -3.075 0.600 0.000124. 100 -3.500 0.600 0.000125. 101 -3.925 0.600 0.000126. 102 -4.350 0.600 0.000127. 103 -4.775 0.600 0.000128. 104 -5.200 0.600 0.000129. 105 -5.625 0.600 0.000130. 106 -6.050 0.600 0.000131. 107 -1.800 0.900 0.000132. 108 -2.225 0.900 0.000133. 109 -2.650 0.900 0.000134. 110 -3.075 0.900 0.000135. 111 -3.500 0.900 0.000136. 112 -3.925 0.900 0.000137. 113 -4.350 0.900 0.000138. 114 -4.775 0.900 0.000139. 115 -5.200 0.900 0.000140. 116 -5.625 0.900 0.000141. 117 -6.050 0.900 0.000142. 118 -1.800 1.200 0.000143. 119 -2.225 1.200 0.000144. 120 -2.650 1.200 0.000145. 121 -3.075 1.200 0.000146. 122 -3.500 1.200 0.000147. 123 -3.925 1.200 0.000148. 124 -4.350 1.200 0.000149. 125 -4.775 1.200 0.000150. 126 -5.200 1.200 0.000

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 4* FILE: PLATE15.STD151. 127 -5.625 1.200 0.000152. 128 -6.050 1.200 0.000153. 129 -1.800 1.500 0.000154. 130 -2.225 1.500 0.000155. 131 -2.650 1.500 0.000156. 132 -3.075 1.500 0.000157. 133 -3.500 1.500 0.000158. 134 -3.925 1.500 0.000159. 135 -4.350 1.500 0.000160. 136 -4.775 1.500 0.000161. 137 -5.200 1.500 0.000162. 138 -5.625 1.500 0.000163. 139 -6.050 1.500 0.000164. 140 -1.800 1.800 0.000165. 141 -2.225 1.800 0.000166. 142 -2.650 1.800 0.000167. 143 -3.075 1.800 0.000168. 144 -3.500 1.800 0.000169. 145 -3.925 1.800 0.000170. 146 -4.350 1.800 0.000171. 147 -4.775 1.800 0.000



172. 148 -5.200 1.800 0.000173. 149 -5.625 1.800 0.000174. 150 -6.050 1.800 0.000175. 151 -1.800 2.225 0.000176. 152 -2.225 2.225 0.000177. 153 -2.650 2.225 0.000178. 154 -3.075 2.225 0.000179. 155 -3.500 2.225 0.000180. 156 -3.925 2.225 0.000181. 157 -4.350 2.225 0.000182. 158 -4.775 2.225 0.000183. 159 -5.200 2.225 0.000184. 160 -5.625 2.225 0.000185. 161 -6.050 2.225 0.000186. 162 -1.800 2.650 0.000187. 163 -2.225 2.650 0.000188. 164 -2.650 2.650 0.000189. 165 -3.075 2.650 0.000190. 166 -3.500 2.650 0.000191. 167 -3.925 2.650 0.000192. 168 -4.350 2.650 0.000193. 169 -4.775 2.650 0.000194. 170 -5.200 2.650 0.000195. 171 -5.625 2.650 0.000196. 172 -6.050 2.650 0.000197. 173 -1.800 3.075 0.000198. 174 -2.225 3.075 0.000199. 175 -2.650 3.075 0.000200. 176 -3.075 3.075 0.000201. 177 -3.500 3.075 0.000202. 178 -3.925 3.075 0.000203. 179 -4.350 3.075 0.000204. 180 -4.775 3.075 0.000205. 181 -5.200 3.075 0.000206. 182 -5.625 3.075 0.000

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 5* FILE: PLATE15.STD207. 183 -6.050 3.075 0.000208. 184 -1.800 3.500 0.000209. 185 -2.225 3.500 0.000210. 186 -2.650 3.500 0.000211. 187 -3.075 3.500 0.000212. 188 -3.500 3.500 0.000213. 189 -3.925 3.500 0.000214. 190 -4.350 3.500 0.000215. 191 -4.775 3.500 0.000216. 192 -5.200 3.500 0.000217. 193 -5.625 3.500 0.000218. 194 -6.050 3.500 0.000219. 201 -1.301 1.301 0.000220. ELEMENT INCIDENCES SHELL221. 1 1 11 12 2222. 2 2 12 13 3223. 3 3 13 14 4224. 4 4 14 15 5225. 5 5 15 16 6226. 6 6 16 17 7227. 7 7 17 18 8228. 8 8 18 19 9229. 9 9 19 20 10230. 11 11 21 22 12231. 12 12 22 23 13232. 13 13 23 24 14233. 14 14 24 25 15234. 15 15 25 26 16235. 16 16 26 27 17

232 — STAAD.Pro


Static Element 15

236. 17 17 27 28 18237. 18 18 28 29 19238. 19 19 29 30 20239. 21 21 31 32 22240. 22 22 32 33 23241. 23 23 33 34 24242. 24 24 34 35 25243. 25 25 35 36 26244. 26 26 36 37 27245. 27 27 37 38 28246. 28 28 38 39 29247. 29 29 39 40 30248. 31 31 44 45 32249. 32 32 45 33250. 33 33 47 34251. 34 34 47 41252. 35 34 41 35253. 36 35 41 201254. 37 35 201 36255. 38 36 201 42256. 39 36 42 37257. 40 37 42 107258. 41 37 107 38259. 42 38 85 39260. 43 39 85 74 40261. 44 45 46 33262. 45 46 47 33

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 6* FILE: PLATE15.STD263. 46 47 48 41264. 47 41 48 43265. 48 41 43 201266. 49 201 43 42267. 50 42 43 118268. 51 42 118 107269. 52 38 107 96270. 53 38 96 85271. 54 48 49 43272. 55 43 129 118273. 56 43 49 140 129274. 57 74 85 86 75275. 58 75 86 87 76276. 59 76 87 88 77277. 60 77 88 89 78278. 61 78 89 90 79279. 62 79 90 91 80280. 63 80 91 92 81281. 64 81 92 93 82282. 65 82 93 94 83283. 66 83 94 95 84284. 77 85 96 97 86285. 78 86 97 98 87286. 79 87 98 99 88287. 80 88 99 100 89288. 81 89 100 101 90289. 82 90 101 102 91290. 83 91 102 103 92291. 84 92 103 104 93292. 85 93 104 105 94293. 86 94 105 106 95294. 97 96 107 108 97295. 98 97 108 109 98296. 99 98 109 110 99297. 100 99 110 111 100298. 101 100 111 112 101299. 102 101 112 113 102



300. 103 102 113 114 103301. 104 103 114 115 104302. 105 104 115 116 105303. 106 105 116 117 106304. 117 107 118 119 108305. 118 108 119 120 109306. 119 109 120 121 110307. 120 110 121 122 111308. 121 111 122 123 112309. 122 112 123 124 113310. 123 113 124 125 114311. 124 114 125 126 115312. 125 115 126 127 116313. 126 116 127 128 117314. 137 118 129 130 119315. 138 119 130 131 120316. 139 120 131 132 121317. 140 121 132 133 122318. 141 122 133 134 123

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 7* FILE: PLATE15.STD319. 142 123 134 135 124320. 143 124 135 136 125321. 144 125 136 137 126322. 145 126 137 138 127323. 146 127 138 139 128324. 157 129 140 141 130325. 158 130 141 142 131326. 159 131 142 143 132327. 160 132 143 144 133328. 161 133 144 145 134329. 162 134 145 146 135330. 163 135 146 147 136331. 164 136 147 148 137332. 165 137 148 149 138333. 166 138 149 150 139334. 171 44 50 51 45335. 172 45 51 52 46336. 173 46 52 53 47337. 174 47 53 54 48338. 175 48 54 55 49339. 176 49 55 151 140340. 177 140 151 152 141341. 178 141 152 153 142342. 179 142 153 154 143343. 180 143 154 155 144344. 181 144 155 156 145345. 182 145 156 157 146346. 183 146 157 158 147347. 184 147 158 159 148348. 185 148 159 160 149349. 186 149 160 161 150350. 191 50 56 57 51351. 192 51 57 58 52352. 193 52 58 59 53353. 194 53 59 60 54354. 195 54 60 61 55355. 196 55 61 162 151356. 197 151 162 163 152357. 198 152 163 164 153358. 199 153 164 165 154359. 200 154 165 166 155360. 201 155 166 167 156361. 202 156 167 168 157362. 203 157 168 169 158363. 204 158 169 170 159

234 — STAAD.Pro


Static Element 15

364. 205 159 170 171 160365. 206 160 171 172 161366. 211 56 62 63 57367. 212 57 63 64 58368. 213 58 64 65 59369. 214 59 65 66 60370. 215 60 66 67 61371. 216 61 67 173 162372. 217 162 173 174 163373. 218 163 174 175 164374. 219 164 175 176 165

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 8* FILE: PLATE15.STD375. 220 165 176 177 166376. 221 166 177 178 167377. 222 167 178 179 168378. 223 168 179 180 169379. 224 169 180 181 170380. 225 170 181 182 171381. 226 171 182 183 172382. 231 62 68 69 63383. 232 63 69 70 64384. 233 64 70 71 65385. 234 65 71 72 66386. 235 66 72 73 67387. 236 67 73 184 173388. 237 173 184 185 174389. 238 174 185 186 175390. 239 175 186 187 176391. 240 176 187 188 177392. 241 177 188 189 178393. 242 178 189 190 179394. 243 179 190 191 180395. 244 180 191 192 181396. 245 181 192 193 182397. 246 182 193 194 183398. ELEMENT PROPERTY399. 1 TO 9 11 TO 19 21 TO 29 31 TO 66 77 TO 86 THICKNESS 0.1400. 97 TO 106 117 TO 126 137 TO 146 157 TO 166 171 TO 186 191 TO 205 -401. 206 THICKNESS 0.1402. 211 TO 226 231 TO 246 THICKNESS 0.1403. ELEMENT PLANE STRESS404. 1 TO 9 11 TO 19 21 TO 29 31 TO 66 77 TO 86 97 TO 106 117 TO 126 137 -405. 138 TO 146 157 TO 166 171 TO 186 191 TO 206 211 TO 226 231 TO 246406. CONSTANTS407. E 3E+007 ALL408. POISSON 0.3 ALL409. SUPPORTS410. 10 20 30 40 74 TO 84 FIXED BUT FX411. 1 11 21 31 44 50 56 62 68 FIXED BUT FY412. LOAD 1 TENSILE LOADWARNING : IT IS ADVISABLE TO ANALYZE THIS STRUCTUREUSING THE COMMAND STAAD SPACE INSTEAD OF STAAD PLANE.413. JOINT LOAD414. 84 FX -42.857415. 95 106 117 128 139 FX -85.714416. 150 FX -103.571417. 161 172 183 FX -121.428418. 194 FX -60.714419. PERFORM ANALYSIS PRINT STATIC CHECK

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 9* FILE: PLATE15.STD


NUMBER OF JOINTS 195 NUMBER OF MEMBERS 0



NUMBER OF PLATES 177 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 24




STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1TENSILE LOADCENTER OF FORCE BASED ON X FORCES ONLY (INCH).

(FORCES IN NON-GLOBAL DIRECTIONS WILL INVALIDATE RESULTS)X = -0.605000019E+01Y = 0.174999944E+01Z = 0.000000000E+00

TOTAL APPLIED LOAD 1***TOTAL APPLIED LOAD ( POUN INCH ) SUMMARY (LOADING 1 )

SUMMATION FORCE-X = -1000.00SUMMATION FORCE-Y = 0.00SUMMATION FORCE-Z = 0.00SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= 0.00 MY= 0.00 MZ= 1749.99

TOTAL REACTION LOAD 1***TOTAL REACTION LOAD( POUN INCH ) SUMMARY (LOADING 1 )

SUMMATION FORCE-X = 1000.00SUMMATION FORCE-Y = 0.00SUMMATION FORCE-Z = 0.00SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= 0.00 MY= 0.00 MZ= -1749.99

MAXIMUM DISPLACEMENTS ( INCH /RADIANS) (LOADING 1)MAXIMUMS AT NODE

X = -6.72293E-04 194Y = -1.83454E-04 68Z = 0.00000E+00 0RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= 1.14134E-03 194

************ END OF DATA FROM INTERNAL STORAGE ************420. PRINT JOINT DISP LIST 6 84JOINT DISP LIST 6




6 1 -0.00024 -0.00008 0.00000 0.00000 0.00000 -0.0002984 1 -0.00066 0.00000 0.00000 0.00000 0.00000 0.00000

************** END OF LATEST ANALYSIS RESULT **************421. PRINT ELEMENT JOINT STRESSES LIST 1ELEMENT JOINT STRESSES LIST

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 12* FILE: PLATE15.STDELEMENT STRESSES FORCE,LENGTH UNITS= POUN INCH----------------



1 1 0.00 0.00 0.00 0.00 0.007461.40 7461.40 650.49 7726.25 -439.787753.48 7753.48

TOP : SMAX= 7753.48 SMIN= 623.26 TMAX= 3565.11 ANGLE=-86.5BOTT: SMAX= 7753.48 SMIN= 623.26 TMAX= 3565.11 ANGLE=-86.5

236 — STAAD.Pro


Static Element 15

JOINT 0.00 0.00 0.00 0.00 0.001 9229.88 9229.88 751.63 9488.87 -757.04

TOP : SMAX= 9553.97 SMIN= 686.52 TMAX= 4433.73 ANGLE=-85.1BOTT: SMAX= 9553.97 SMIN= 686.52 TMAX= 4433.73 ANGLE=-85.1JOINT 0.00 0.00 0.00 0.00 0.0011 5912.86 5912.86 608.93 6174.80 -272.64

TOP : SMAX= 6188.12 SMIN= 595.61 TMAX= 2796.26 ANGLE=-87.2BOTT: SMAX= 6188.12 SMIN= 595.61 TMAX= 2796.26 ANGLE=-87.2JOINT 0.00 0.00 0.00 0.00 0.0012 5802.42 5802.42 548.98 6051.20 -154.55

TOP : SMAX= 6055.53 SMIN= 544.64 TMAX= 2755.45 ANGLE=-88.4BOTT: SMAX= 6055.53 SMIN= 544.64 TMAX= 2755.45 ANGLE=-88.4JOINT 0.00 0.00 0.00 0.00 0.00

2 8940.01 8940.01 666.87 9167.41 -719.10TOP : SMAX= 9227.81 SMIN= 606.47 TMAX= 4310.67 ANGLE=-85.2BOTT: SMAX= 9227.81 SMIN= 606.47 TMAX= 4310.67 ANGLE=-85.2


9.553974E+03 5.446443E+02 4.433728E+03 7.461401E+03 7.753480E+03PLATE NO. 1 1 1 1 1CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************422. FINISH

:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 13* FILE: PLATE15.STD:STRESS CONCENTRATION IN A PLATE -- PAGE NO. 14



Static Element 16ObjectiveTo find the normal stress on the edge of a circular hole in the center of a rectangular plate.

ReferenceYoung, W. C., Roark’s Formulas for Stress and Strain, McGraw-Hill Inc., 6th Edition, 1989, Page 429.

ProblemFind the normal stress on the edge of the circular hole for the plate shown, when an in-planeload causes tension. Use a one-quarter, doubly symmetric model.

E =10,000.0 ksi

Radius = 10 in, Thickness = 0.02 in



w = 0.1 psi

Figure 4-20: Model

Comparison


δ at node 1 (in) 2.133 2.161 1.4%

Moment at joint 1 (in-lbs) 0.813 0.830 2.6%


STAAD Input


STAAD SPACE :UNIFORM PRESSURE ON A FIXED CIRCULAR PLATE** FILE: PLATE16.STD** REFERENCE: "ROARK'S FORMULAS FOR STRESS AND STRAIN", WARREN C. YOUNG,* SIXTH EDITION, MCGRAW-HILL, PAGE 429.*UNIT POUND INCHJOINT COORDINATES CYLINDRICAL REVERSE1 0. 0. 0.2 1.0 0. 0. 37 1.0 0. 350.38 1.2916 0. 0. 73 1.2916 0. 350.74 1.6681 0. 0. 109 1.6681 0. 350.110 2.1544 0. 0. 145 2.1544 0. 350.146 2.7826 0. 0. 181 2.7826 0. 350.182 3.5938 0. 0. 217 3.5938 0. 350.218 4.6416 0. 0. 253 4.6416 0. 350.254 5.9948 0. 0. 289 5.9948 0. 350.290 7.7426 0. 0. 325 7.7426 0. 350.326 10. 0. 0. 361 10. 0. 350.ELEMENT INCIDENCES37 2 38 39 3 TO 71 1 172 37 73 38 2REPEAT ALL 8 36 361 1 2 32 1 3 43 1 4 54 1 5 65 1 6 76 1 7 87 1 8 9

238 — STAAD.Pro


Static Element 16

8 1 9 109 1 10 1110 1 11 1211 1 12 1312 1 13 1413 1 14 1514 1 15 1615 1 16 1716 1 17 1817 1 18 1918 1 19 2019 1 20 2120 1 21 2221 1 22 2322 1 23 2423 1 24 2524 1 25 2625 1 26 2726 1 27 2827 1 28 2928 1 29 3029 1 30 3130 1 31 3231 1 32 3332 1 33 3433 1 34 3534 1 35 3635 1 36 3736 1 37 2ELEMENT PROPERTY1 TO 360 TH 0.02CONSTANTSE 10000000 ALLPOISSON 0.3 ALLSUPPORT326 TO 361 FIXEDLOAD 1 UNIFORM PRESSUREELEMENT LOAD1 TO 360 PRE 0.1PERFORM ANALYSISPRINT JOINT DISPLACEMENT LIST 1PRINT ELEMENT JOINT STRESSES LIST 1PRINT SUPPORT REACTIONS LIST 326FINISH



1. STAAD SPACE :UNIFORM PRESSURE ON A FIXED CIRCULAR PLATEINPUT FILE: PLATE16.STD

2. *3. * FILE: PLATE16.STD4. *



5. * REFERENCE: "ROARK'S FORMULAS FOR STRESS AND STRAIN", WARREN C. YOUNG,6. * SIXTH EDITION, MCGRAW-HILL, PAGE 429.7. *8. UNIT POUND INCH9. JOINT COORDINATES CYLINDRICAL REVERSE10. 1 0. 0. 0.11. 2 1.0 0. 0. 37 1.0 0. 350.12. 38 1.2916 0. 0. 73 1.2916 0. 350.13. 74 1.6681 0. 0. 109 1.6681 0. 350.14. 110 2.1544 0. 0. 145 2.1544 0. 350.15. 146 2.7826 0. 0. 181 2.7826 0. 350.16. 182 3.5938 0. 0. 217 3.5938 0. 350.17. 218 4.6416 0. 0. 253 4.6416 0. 350.18. 254 5.9948 0. 0. 289 5.9948 0. 350.19. 290 7.7426 0. 0. 325 7.7426 0. 350.20. 326 10. 0. 0. 361 10. 0. 350.21. ELEMENT INCIDENCES22. 37 2 38 39 3 TO 71 1 123. 72 37 73 38 224. REPEAT ALL 8 36 3625. 1 1 2 326. 2 1 3 427. 3 1 4 528. 4 1 5 629. 5 1 6 730. 6 1 7 831. 7 1 8 932. 8 1 9 1033. 9 1 10 1134. 10 1 11 1235. 11 1 12 1336. 12 1 13 1437. 13 1 14 1538. 14 1 15 16:UNIFORM PRESSURE ON A FIXED CIRCULAR PLATE -- PAGE NO. 2

*39. 15 1 16 1740. 16 1 17 1841. 17 1 18 1942. 18 1 19 2043. 19 1 20 2144. 20 1 21 2245. 21 1 22 2346. 22 1 23 2447. 23 1 24 2548. 24 1 25 2649. 25 1 26 2750. 26 1 27 2851. 27 1 28 2952. 28 1 29 3053. 29 1 30 3154. 30 1 31 3255. 31 1 32 3356. 32 1 33 3457. 33 1 34 3558. 34 1 35 3659. 35 1 36 3760. 36 1 37 261. ELEMENT PROPERTY62. 1 TO 360 TH 0.0263. CONSTANTS64. E 10000000 ALL65. POISSON 0.3 ALL66. SUPPORT67. 326 TO 361 FIXED68. LOAD 1 UNIFORM PRESSURE

240 — STAAD.Pro


Static Element 16

69. ELEMENT LOAD70. 1 TO 360 PRE 0.171. PERFORM ANALYSIS





72. PRINT JOINT DISPLACEMENT LIST 1JOINT DISPLACE LIST 1

:UNIFORM PRESSURE ON A FIXED CIRCULAR PLATE -- PAGE NO. 3*



1 1 0.00000 2.16005 0.00000 0.00000 0.00000 0.00000************** END OF LATEST ANALYSIS RESULT **************73. PRINT ELEMENT JOINT STRESSES LIST 1

ELEMENT JOINT STRESSES LIST:UNIFORM PRESSURE ON A FIXED CIRCULAR PLATE -- PAGE NO. 4

*ELEMENT STRESSES FORCE,LENGTH UNITS= POUN INCH----------------



1 1 -1.48 -2.18 0.83 0.83 0.0012399.08 12399.08 0.00 0.00 0.0012399.08 12399.08

TOP : SMAX= 12399.08 SMIN= 12399.08 TMAX= 0.00 ANGLE= 90.0BOTT: SMAX= -12399.08 SMIN= -12399.08 TMAX= 0.00 ANGLE= 90.0JOINT -1.48 -2.18 0.85 0.83 0.00

1 12566.42 12566.42 0.00 0.00 0.00TOP : SMAX= 12692.08 SMIN= 12436.87 TMAX= 127.61 ANGLE= 0.0BOTT: SMAX= -12436.87 SMIN= -12692.08 TMAX= 127.61 ANGLE=-90.0JOINT -1.48 -2.18 0.82 0.83 0.00

2 12344.11 12344.11 0.00 0.00 0.00TOP : SMAX= 12436.87 SMIN= 12249.21 TMAX= 93.83 ANGLE= 90.0BOTT: SMAX= -12249.21 SMIN= -12436.87 TMAX= 93.83 ANGLE= 0.0JOINT -1.48 -2.18 0.82 0.82 0.00

3 12289.85 12289.85 0.00 0.00 0.00TOP : SMAX= 12323.49 SMIN= 12255.94 TMAX= 33.77 ANGLE= 90.0BOTT: SMAX= -12255.94 SMIN= -12323.49 TMAX= 33.77 ANGLE= 0.0


1.269208E+04 -1.269208E+04 1.276061E+02 1.239908E+04 1.239908E+04PLATE NO. 1 1 1 1 1CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************74. PRINT SUPPORT REACTIONS LIST 326

SUPPORT REACTION LIST 326:UNIFORM PRESSURE ON A FIXED CIRCULAR PLATE -- PAGE NO. 5

*

SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = SPACE



-----------------JOINT LOAD FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z

326 1 0.00 -0.87 0.00 -0.01 0.00 2.15************** END OF LATEST ANALYSIS RESULT **************75. FINISH:UNIFORM PRESSURE ON A FIXED CIRCULAR PLATE -- PAGE NO. 6



Static Element 17ObjectiveTo find the bending moments at various points on a wall fixed along three edges.

ReferenceYoung, W. C., Roark’s Formulas for Stress and Strain, McGraw-Hill Inc., 6th Edition, 1989.

ProblemFind the bending moment at the points circled in the figure for 2 load cases:

a. a uniform pressure over the entire wall

b. a hydrostatic pressure varying linearly from 0 at the top to maximum at the bottom.

E =3,150 ksi

Length, a = 60 ft

Height, b = 40 ft

242 — STAAD.Pro


Static Element 17

Figure 4-21: Model

Comparison


Bending moment at midpoint of bottomedge (ft-kip/ft)

193.9 393.25/2= 196.6

1.4%

Bending moment at midpoint of top edge(ft-kip/ft)

129 130.6 1.2%

Bending moment at corner of free edgeand fixed edge (ft-kip/ft)

286.1 294.0 2.8%

Table 4-18: Comparison of results uniform pressure load case


Bending moment at midpoint of bottomedge (ft-kip/ft)

327.6 673.0/2 =336.5

2.7%

Bending moment at corner of free edgeand fixed edge (ft-kip/ft)

227.7 212.0 6.9%

Table 4-19: Comparison of results linearly varying pressure load case

Hand Calculation

= = 1.5a

b

60ft

40ft

M =β q

6

i2

a. For uniform pressure (load case 1):

where



βi = value taken for Case 10a, Table 26, on p.469 of the reference (when a/b= 1.5):

= 0.727 for midpoint of bottom edge (moment about thehorizontal axis)

= 0.484 for midpoint of top edge (free edge; moment about thehorizontal axis)

= 1.073 for corner of the free edge and fixed edge (momentabout the vertical axis)

q = magnitude of the pressure, 1 ksf

b. For linearly varying pressure (load case 2):

Pressure varies from zero intensity at the top to maximum at the base.

where

βi = value taken for Case 10d, Table 26, on p.470 of the reference (when a/b= 1.5):

= 0.351 for midpoint of bottom edge (moment about thehorizontal axis)

= 0.244 for corner of the free edge and fixed edge (momentabout the vertical axis)

q = magnitude of the pressure at bottom, 3.5 ksf

STAAD Input


STAAD SPACE : A WALL FIXED ALONG 2 EDGES* FILE: PLATE17.STD** REFERENCE 'ROARK'S FORMULAS FOR STRESS AND STRAIN', WARREN YOUNG, 6TH ED.* CASES 10A & 10D, PP.469-470*UNIT FEET KIPJOINT COORDINATES1 0 0 0; 2 0 40 03 30 0 0 ; 4 30 40 05 60 0 0 ; 6 60 40 0*DEFINR MESHA JOINT 1B JOINT 2C JOINT 3D JOINT 4E JOINT 5F JOINT 6*GENERATE ELEMENT QUADMESH ABDC 20 15MESH CDFE 20 15*ELEMENT PROPERTY1 TO 600 THICKNESS 2*

244 — STAAD.Pro


Static Element 17

UNIT INCHCONSTANTSE 3150 ALLPOISSON 0.2 ALL*UNIT FTSUPPORTSXRA -1 1 FIXEDXRA 59 61 FIXEDYRA -1 1 FIXED*LOAD 1ELEMENT LOAD1 TO 600 PR 1*LOAD 2 HYDROSTATICELEMENT LOADYRA -1 3 TRAP X 3.5 3.325YRA 1 5 TRAP X 3.325 3.15YRA 3 7 TRAP X 3.15 2.975YRA 5 9 TRAP X 2.975 2.8YRA 7 11 TRAP X 2.8 2.625YRA 9 13 TRAP X 2.625 2.45YRA 11 15 TRAP X 2.45 2.275YRA 13 17 TRAP X 2.275 2.1YRA 15 19 TRAP X 2.1 1.925YRA 17 21 TRAP X 1.925 1.75YRA 19 23 TRAP X 1.75 1.575YRA 21 25 TRAP X 1.575 1.4YRA 23 27 TRAP X 1.4 1.225YRA 25 29 TRAP X 1.225 1.05YRA 27 31 TRAP X 1.05 0.875YRA 29 33 TRAP X 0.875 0.7YRA 31 35 TRAP X 0.7 0.525YRA 33 37 TRAP X 0.525 0.35YRA 35 39 TRAP X 0.35 0.175YRA 37 41 TRAP X 0.175 0*PERFORM ANALYSISPRINT SUPPORT REACTION LIST 2 3PRINT ELEMENT JOINT STRESSES LIST 300FINISH



1. STAAD SPACE : A WALL FIXED ALONG 2 EDGESINPUT FILE: PLATE17.STD

2. * FILE: PLATE17.STD3. *4. * REFERENCE 'ROARK'S FORMULAS FOR STRESS AND STRAIN', WARREN YOUNG, 6TH ED.5. * CASES 10A & 10D, PP.469-4706. *



7. UNIT FEET KIP8. JOINT COORDINATES9. 1 0 0 0; 2 0 40 010. 3 30 0 0 ; 4 30 40 011. 5 60 0 0 ; 6 60 40 012. *13. DEFINR MESH14. A JOINT 115. B JOINT 216. C JOINT 317. D JOINT 418. E JOINT 519. F JOINT 620. *21. GENERATE ELEMENT QUAD22. MESH ABDC 20 1523. MESH CDFE 20 1524. *25. ELEMENT PROPERTY26. 1 TO 600 THICKNESS 227. *28. UNIT INCH29. CONSTANTS30. E 3150 ALL31. POISSON 0.2 ALL32. *33. UNIT FT34. SUPPORTS35. XRA -1 1 FIXED36. XRA 59 61 FIXED37. YRA -1 1 FIXED38. *: A WALL FIXED ALONG 2 EDGES -- PAGE NO. 2

* FILE: PLATE17.STD39. LOAD 1

**WARNING, 1 or more joints are in multiple SUPPORT commands, First Joint 1The subsequent entries will add to support direction specs. See Tech Ref Manual.

40. ELEMENT LOAD41. 1 TO 600 PR 142. *43. LOAD 2 HYDROSTATIC44. ELEMENT LOAD45. YRA -1 3 TRAP X 3.5 3.32546. YRA 1 5 TRAP X 3.325 3.1547. YRA 3 7 TRAP X 3.15 2.97548. YRA 5 9 TRAP X 2.975 2.849. YRA 7 11 TRAP X 2.8 2.62550. YRA 9 13 TRAP X 2.625 2.4551. YRA 11 15 TRAP X 2.45 2.27552. YRA 13 17 TRAP X 2.275 2.153. YRA 15 19 TRAP X 2.1 1.92554. YRA 17 21 TRAP X 1.925 1.7555. YRA 19 23 TRAP X 1.75 1.57556. YRA 21 25 TRAP X 1.575 1.457. YRA 23 27 TRAP X 1.4 1.22558. YRA 25 29 TRAP X 1.225 1.0559. YRA 27 31 TRAP X 1.05 0.87560. YRA 29 33 TRAP X 0.875 0.761. YRA 31 35 TRAP X 0.7 0.52562. YRA 33 37 TRAP X 0.525 0.3563. YRA 35 39 TRAP X 0.35 0.17564. YRA 37 41 TRAP X 0.175 065. *66. PERFORM ANALYSIS


246 — STAAD.Pro


Static Element 17




67. PRINT SUPPORT REACTION LIST 2 3SUPPORT REACTION LIST 2

: A WALL FIXED ALONG 2 EDGES -- PAGE NO. 3* FILE: PLATE17.STD

SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = SPACE-----------------


2 1 0.00 0.00 24.50 -59.94 -293.96 0.002 0.00 0.00 -3.73 -42.71 -211.97 0.00

3 1 0.00 0.00 53.00 393.27 0.00 0.002 0.00 0.00 112.98 673.01 0.00 0.00

************** END OF LATEST ANALYSIS RESULT **************68. PRINT ELEMENT JOINT STRESSES LIST 300

ELEMENT JOINT STRESSES LIST: A WALL FIXED ALONG 2 EDGES -- PAGE NO. 4

* FILE: PLATE17.STDELEMENT STRESSES FORCE,LENGTH UNITS= KIP FEET----------------



300 1 -0.88 1.09 2.76 126.17 -2.01187.30 187.30 0.00 0.00 0.00189.31 189.31

TOP : SMAX= 189.31 SMIN= 4.09 TMAX= 92.61 ANGLE=-89.1BOTT: SMAX= -4.09 SMIN= -189.31 TMAX= 92.61 ANGLE= 0.9JOINT -0.92 0.26 4.26 125.10 -2.45318 184.65 184.65 0.00 0.00 0.00


TOP : SMAX= 186.13 SMIN= 1.29 TMAX= 92.42 ANGLE=-89.4BOTT: SMAX= -1.29 SMIN= -186.13 TMAX= 92.42 ANGLE= 0.6JOINT -0.84 1.92 1.43 130.57 -1.57

4 194.83 194.83 0.00 0.00 0.00TOP : SMAX= 195.88 SMIN= 2.11 TMAX= 96.88 ANGLE=-89.3BOTT: SMAX= -2.11 SMIN= -195.88 TMAX= 96.88 ANGLE= 0.7JOINT -0.84 0.26 4.47 124.94 -2.76338 184.30 184.30 0.00 0.00 0.00

TOP : SMAX= 187.51 SMIN= 6.61 TMAX= 90.45 ANGLE=-88.7BOTT: SMAX= -6.61 SMIN= -187.51 TMAX= 90.45 ANGLE= 1.3

2 -0.92 0.78 2.26 116.85 -1.13173.62 173.62 0.00 0.00 0.00175.29 175.29



TOP : SMAX= 172.85 SMIN= 0.93 TMAX= 85.96 ANGLE=-89.8



BOTT: SMAX= -0.93 SMIN= -172.85 TMAX= 85.96 ANGLE= 0.2JOINT -0.90 1.26 0.90 119.46 -1.05

4 178.54 178.54 0.00 0.00 0.00TOP : SMAX= 179.20 SMIN= 1.34 TMAX= 88.93 ANGLE=-89.5BOTT: SMAX= -1.34 SMIN= -179.20 TMAX= 88.93 ANGLE= 0.5JOINT -0.90 0.29 3.81 116.52 -1.88338 172.06 172.06 0.00 0.00 0.00

TOP : SMAX= 174.83 SMIN= 5.67 TMAX= 84.58 ANGLE=-89.0BOTT: SMAX= -5.67 SMIN= -174.83 TMAX= 84.58 ANGLE= 1.0: A WALL FIXED ALONG 2 EDGES -- PAGE NO. 5



1.958811E+02 -1.958811E+02 9.688407E+01 1.872972E+02 1.893074E+02PLATE NO. 300 300 300 300 300CASE NO. 1 1 1 1 1********************END OF ELEMENT FORCES********************69. FINISH: A WALL FIXED ALONG 2 EDGES -- PAGE NO. 6



248 — STAAD.Pro


Static Element 17

5Solid Elements

Static Solid 1 249

Static Solid 2 253

Static Solid 1ObjectiveTo find the displacement at the free end of a cantilever beam modeled with solid elements.

ReferenceHand calculation.

ProblemCalculate the maximum displacement of a cantilever beam due to a concentrated load at the freeend

Figure 5-1: Entire model


Figure 5-2: Free end section with node numbers

L = 10 in

A = 2 in2

P = 300 lb

l = 2/3 in.4

250 — STAAD.Pro

5 Solid Elements

Static Solid 1

E = 29,000 ksi

ν = 0.3

Hand Calculationδbend = PL3/(3EI) = 300(10)3/{3[29(10)6](2/3)} = 0.00517 in

δshear = 12/5*(1+ν)PL/AE = 12/5*(1+0.3)(300)(10)/[29(10)6(2)] = 0.00016 in

δ = δbend + δshear = 0.00517 + 0.00016 = 0.00533 in

Comparison


Deflection, δ, (in) 0.00533 0.00529 < 1.0%

Table 5-1: Comparison of results for static solid no. 1

STAAD InputSTAAD SPACE : A CANTILEVER BEAM WITH SOLID ELEMENTS* INPUT FILE: SOLID01.STD**INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0 0 0 21 10 0 0REPE 4 0 0 .25REPE ALL 4 0 .5 0ELEMENT INCIDENCES SOLID1 22 127 106 1 23 128 107 2 TO 20 1 1REPE 3 20 21REPE ALL 3 80 105CONSTANTE STEEL ALLPOISSON 0.3 ALLSUPPORT1 TO 421 BY 105 FIXED22 TO 442 BY 105 FIXED43 TO 463 BY 105 FIXED64 TO 484 BY 105 FIXED85 TO 505 BY 105 FIXEDLOAD 1JOINT LOAD21 105 441 525 FY -75.PERFORM ANALYSISPRINT JOINT DISP LIST 21 105 273 441 525FINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:30: 2 ** ** USER ID: Bentley Systems, Inc. *

5 Solid Elements


****************************************************

1. STAAD SPACE : A CANTILEVER BEAM WITH SOLID ELEMENTSINPUT FILE: SOLID01.STD

2. * INPUT FILE: SOLID01.STD3. *4. *5. INPUT WIDTH 726. UNIT INCHES POUND7. JOINT COORDINATES8. 1 0 0 0 21 10 0 09. REPE 4 0 0 .2510. REPE ALL 4 0 .5 011. ELEMENT INCIDENCES SOLID12. 1 22 127 106 1 23 128 107 2 TO 20 1 113. REPE 3 20 2114. REPE ALL 3 80 10515. CONSTANT16. E STEEL ALL17. POISSON 0.3 ALL18. SUPPORT19. 1 TO 421 BY 105 FIXED20. 22 TO 442 BY 105 FIXED21. 43 TO 463 BY 105 FIXED22. 64 TO 484 BY 105 FIXED23. 85 TO 505 BY 105 FIXED24. LOAD 125. JOINT LOAD26. 21 105 441 525 FY -75.27. PERFORM ANALYSIS: A CANTILEVER BEAM WITH SOLID ELEMENTS -- PAGE NO. 2

* INPUT FILE: SOLID01.STD





28. PRINT JOINT DISP LIST 21 105 273 441 525JOINT DISP LIST 21

: A CANTILEVER BEAM WITH SOLID ELEMENTS -- PAGE NO. 3* INPUT FILE: SOLID01.STD



21 1 -0.00078 -0.00529 0.00001 0.00000 0.00000 0.00000105 1 -0.00078 -0.00529 -0.00001 0.00000 0.00000 0.00000273 1 0.00000 -0.00525 0.00000 0.00000 0.00000 0.00000441 1 0.00078 -0.00529 -0.00001 0.00000 0.00000 0.00000525 1 0.00078 -0.00529 0.00001 0.00000 0.00000 0.00000************** END OF LATEST ANALYSIS RESULT **************29. FINISH



************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ *

252 — STAAD.Pro

5 Solid Elements

Static Solid 1

* ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Static Solid 2ObjectiveTo find the displacement at the free end and normal stresses at mid-span of a cantilever beammodeled with solid elements.

ReferenceHand calculation and STARDYNE Verification Manual problem 3.

Hand CalculationDisplacement due to Load 1:

δL1 = PL/(AE) = 1200(15)/[10(10)6](6)} = 0.0003 in

Rotate due to Load 2:

φL2 = TL/(c2ab3G)

where:

a = long side of the cross section = 3 in

b = short side of the cross section = 2 in

c2 = 0.1958 for a/b = 1.5

G = E/[2(1+ν)] = 10(10)3/(2(1+0.3)] = 3,846 ksi

φL2 = 2000(15)//[0.1958(3)(2)33.846(10)6] = 0.00166 rad

Displacement due to Load 3:

δL3 = ML2/(2EI) = 2500(15)2/[2(10)(10)7(4.5)] = 0.00625 in

Displacement due to Load 4:

δbend = PL3/(3EI) = 1000(15)3/{3[10(10)6](4.5)} = 0.025 in

δshear = 12/5*(1+ν)PL/AE = 12/5*(1+0.3)(1000)(15)/[(6)10(10)6] = 0.00078 in

δL4 = δbend + δshear = 0.025 + 0.00078 = 0.02578 in

Stress at midspan due to Load 1:

σa = P/A = 1200/6 = 200 psi


σb = My/I = 2500(1.5)/4.5 = 833.33 psi


5 Solid Elements


σb = My/I = 7.5(1000)(1.5)/4.5 = 2,500 psi

Comparison


Maximum Displacement, δ (in) LC1 0.00030 0.00029 3.4%

LC3 0.00625 0.00619 <1%

LC4 0.02578 0.02533 1.7%

Maximum Rotation, φ (rad) LC2 0.00166 0.00149 10.2%

Normal Stress at Midspan* (psi) LC1 200.0 200.004 none

LC3 833.3 833.325 none

LC4 2,500 2630.409 5.2%

Table 5-2: Comparison of results for static solid no. 2

Note: (*) Stresses computed at Node no. 32 of solid no. 10.

STAAD InputSTAAD SPACE : A CANTILEVER BEAM WITH SOLID ELEMENTS* INPUT FILE: SOLID02.STD**INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0 0 0 21 15 0 0REPE 4 0 0 .5REPE ALL 4 0 .75 0** SINCE SOLID-ONLY MODELS HAVE NO ROTATIONAL DOF AT THEIR NODES, ADD* DUMMY MEMBERS TO CREATE THOSE DEGREES OF FREEDOM.*MEMB INCI1001 525 2731002 105 2731003 21 2731004 441 273*ELEMENT INCIDENCES SOLID1 22 127 106 1 23 128 107 2 TO 20 1 1REPE 3 20 21REPE ALL 3 80 105*MEMB PROP1001 TO 1004 PRIS YD 0.2*CONSTANTE 10E6 ALLPOISSON 0.3 ALLSUPPORT1 TO 421 BY 105 PINNED22 TO 442 BY 105 PINNED43 TO 463 BY 105 PINNED64 TO 484 BY 105 PINNED

254 — STAAD.Pro

5 Solid Elements

Static Solid 2

85 TO 505 BY 105 PINNEDLOAD 1JOINT LOAD21 FX -4842 FX -4863 FX -4884 FX -48105 FX -48126 FX -48147 FX -48168 FX -48189 FX -48210 FX -48231 FX -48252 FX -48273 FX -48294 FX -48315 FX -48336 FX -48357 FX -48378 FX -48399 FX -48420 FX -48441 FX -48462 FX -48483 FX -48504 FX -48525 FX -48LOAD 2JOINT LOAD231 FY 1000315 FY -1000LOAD 3JOINT LOAD21 FX 133.3342 FX 133.3363 FX 133.3384 FX 133.33105 FX 133.33126 FX 66.67147 FX 66.67168 FX 66.67189 FX 66.67210 FX 66.67336 FX -66.67357 FX -66.67378 FX -66.67399 FX -66.67420 FX -66.67441 FX -133.33462 FX -133.33483 FX -133.33504 FX -133.33525 FX -133.33LOAD 4JOINT LOAD21 FY 4042 FY 4063 FY 4084 FY 40105 FY 40126 FY 40147 FY 40168 FY 40189 FY 40210 FY 40

5 Solid Elements


231 FY 40252 FY 40273 FY 40294 FY 40315 FY 40336 FY 40357 FY 40378 FY 40399 FY 40420 FY 40441 FY 40462 FY 40483 FY 40504 FY 40525 FY 40PERFORM ANALYSIS*LOAD LIST 1PRINT JOINT DISP LIST 21 TO 441 BY 105 42 TO 462 BY 105 -63 TO 483 BY 105 84 TO 504 BY 105 105 TO 525 BY 105*LOAD LIST 2PRINT JOINT DISPLACEMENTS LIST 525 105 21 441 273*LOAD LIST 3PRINT JOINT DISP LIST 21 TO 441 BY 105 42 TO 462 BY 105 -63 TO 483 BY 105 84 TO 504 BY 105 105 TO 525 BY 105*LOAD LIST 4PRINT JOINT DISP LIST 21 TO 441 BY 105 42 TO 462 BY 105 -63 TO 483 BY 105 84 TO 504 BY 105 105 TO 525 BY 105*LOAD LIST ALLPRINT ELEMENT JOINT STRESSES SOLID LIST 10*PRINT ELEMENT JOINT STRESSES SOLID LIST 10 TO 70 BY 20*PRINT ELEMENT JOINT STRESSES SOLID LIST 90 TO 150 BY 20*PRINT ELEMENT JOINT STRESSES SOLID LIST 170 TO 230 BY 20*PRINT ELEMENT JOINT STRESSES SOLID LIST 250 TO 310 BY 20FINISH



1. STAAD SPACE : A CANTILEVER BEAM WITH SOLID ELEMENTSINPUT FILE: SOLID02.STD

2. * INPUT FILE: SOLID02.STD3. *4. *5. INPUT WIDTH 726. UNIT INCHES POUND7. JOINT COORDINATES8. 1 0 0 0 21 15 0 09. REPE 4 0 0 .5

256 — STAAD.Pro

5 Solid Elements

Static Solid 2

10. REPE ALL 4 0 .75 011. *12. * SINCE SOLID-ONLY MODELS HAVE NO ROTATIONAL DOF AT THEIR NODES, ADD13. * DUMMY MEMBERS TO CREATE THOSE DEGREES OF FREEDOM.14. *15. MEMB INCI16. 1001 525 27317. 1002 105 27318. 1003 21 27319. 1004 441 27320. *21. ELEMENT INCIDENCES SOLID22. 1 22 127 106 1 23 128 107 2 TO 20 1 123. REPE 3 20 2124. REPE ALL 3 80 10525. *26. MEMB PROP27. 1001 TO 1004 PRIS YD 0.228. *29. CONSTANT30. E 10E6 ALL31. POISSON 0.3 ALL32. SUPPORT33. 1 TO 421 BY 105 PINNED34. 22 TO 442 BY 105 PINNED35. 43 TO 463 BY 105 PINNED36. 64 TO 484 BY 105 PINNED37. 85 TO 505 BY 105 PINNED38. LOAD 1: A CANTILEVER BEAM WITH SOLID ELEMENTS -- PAGE NO. 2

* INPUT FILE: SOLID02.STD39. JOINT LOAD40. 21 FX -4841. 42 FX -4842. 63 FX -4843. 84 FX -4844. 105 FX -4845. 126 FX -4846. 147 FX -4847. 168 FX -4848. 189 FX -4849. 210 FX -4850. 231 FX -4851. 252 FX -4852. 273 FX -4853. 294 FX -4854. 315 FX -4855. 336 FX -4856. 357 FX -4857. 378 FX -4858. 399 FX -4859. 420 FX -4860. 441 FX -4861. 462 FX -4862. 483 FX -4863. 504 FX -4864. 525 FX -4865. LOAD 266. JOINT LOAD67. 231 FY 100068. 315 FY -100069. LOAD 370. JOINT LOAD71. 21 FX 133.3372. 42 FX 133.3373. 63 FX 133.33

5 Solid Elements


74. 84 FX 133.3375. 105 FX 133.3376. 126 FX 66.6777. 147 FX 66.6778. 168 FX 66.6779. 189 FX 66.6780. 210 FX 66.6781. 336 FX -66.6782. 357 FX -66.6783. 378 FX -66.6784. 399 FX -66.6785. 420 FX -66.6786. 441 FX -133.3387. 462 FX -133.3388. 483 FX -133.3389. 504 FX -133.3390. 525 FX -133.3391. LOAD 492. JOINT LOAD93. 21 FY 4094. 42 FY 40: A CANTILEVER BEAM WITH SOLID ELEMENTS -- PAGE NO. 3

* INPUT FILE: SOLID02.STD95. 63 FY 4096. 84 FY 4097. 105 FY 4098. 126 FY 4099. 147 FY 40100. 168 FY 40101. 189 FY 40102. 210 FY 40103. 231 FY 40104. 252 FY 40105. 273 FY 40106. 294 FY 40107. 315 FY 40108. 336 FY 40109. 357 FY 40110. 378 FY 40111. 399 FY 40112. 420 FY 40113. 441 FY 40114. 462 FY 40115. 483 FY 40116. 504 FY 40117. 525 FY 40118. PERFORM ANALYSIS





119. *120. LOAD LIST 1121. PRINT JOINT DISP LIST 21 TO 441 BY 105 42 TO 462 BY 105 -JOINT DISP LIST 21122. 63 TO 483 BY 105 84 TO 504 BY 105 105 TO 525 BY 105


258 — STAAD.Pro

5 Solid Elements

Static Solid 2



21 1 -0.00033 -0.00002 -0.00001 0.00000 0.00002 -0.00003126 1 -0.00030 -0.00001 -0.00001 0.00000 0.00000 0.00000231 1 -0.00030 0.00000 -0.00001 0.00000 0.00000 0.00000336 1 -0.00030 0.00001 -0.00001 0.00000 0.00000 0.00000441 1 -0.00033 0.00002 -0.00001 0.00000 0.00002 0.0000342 1 -0.00031 -0.00002 -0.00001 0.00000 0.00000 0.00000147 1 -0.00029 -0.00001 0.00000 0.00000 0.00000 0.00000252 1 -0.00029 0.00000 0.00000 0.00000 0.00000 0.00000357 1 -0.00029 0.00001 0.00000 0.00000 0.00000 0.00000462 1 -0.00031 0.00002 -0.00001 0.00000 0.00000 0.0000063 1 -0.00031 -0.00002 0.00000 0.00000 0.00000 0.00000168 1 -0.00029 -0.00001 0.00000 0.00000 0.00000 0.00000273 1 -0.00029 0.00000 0.00000 0.00000 0.00000 0.00000378 1 -0.00029 0.00001 0.00000 0.00000 0.00000 0.00000483 1 -0.00031 0.00002 0.00000 0.00000 0.00000 0.0000084 1 -0.00031 -0.00002 0.00001 0.00000 0.00000 0.00000189 1 -0.00029 -0.00001 0.00000 0.00000 0.00000 0.00000294 1 -0.00029 0.00000 0.00000 0.00000 0.00000 0.00000399 1 -0.00029 0.00001 0.00000 0.00000 0.00000 0.00000504 1 -0.00031 0.00002 0.00001 0.00000 0.00000 0.00000105 1 -0.00033 -0.00002 0.00001 0.00000 -0.00002 -0.00003210 1 -0.00030 -0.00001 0.00001 0.00000 0.00000 0.00000315 1 -0.00030 0.00000 0.00001 0.00000 0.00000 0.00000420 1 -0.00030 0.00001 0.00001 0.00000 0.00000 0.00000525 1 -0.00033 0.00002 0.00001 0.00000 -0.00002 0.00003************** END OF LATEST ANALYSIS RESULT **************123. *124. LOAD LIST 2125. PRINT JOINT DISPLACEMENTS LIST 525 105 21 441 273JOINT DISPLACE LIST 525




525 2 -0.00002 -0.00149 0.00224 0.00149 -0.00001 0.00001105 2 0.00002 -0.00149 -0.00224 0.00149 0.00001 0.0000121 2 -0.00002 0.00149 -0.00224 0.00149 0.00001 -0.00001441 2 0.00002 0.00149 0.00224 0.00149 -0.00001 -0.00001273 2 0.00000 0.00000 0.00000 0.00149 0.00000 0.00000************** END OF LATEST ANALYSIS RESULT **************126. *127. LOAD LIST 3128. PRINT JOINT DISP LIST 21 TO 441 BY 105 42 TO 462 BY 105 -JOINT DISP LIST 21129. 63 TO 483 BY 105 84 TO 504 BY 105 105 TO 525 BY 105




21 3 0.00132 0.00621 0.00004 -0.00002 0.00000 0.00088126 3 0.00061 0.00619 0.00001 0.00000 0.00000 0.00000231 3 0.00000 0.00618 0.00000 0.00000 0.00000 0.00000336 3 -0.00061 0.00619 -0.00001 0.00000 0.00000 0.00000441 3 -0.00132 0.00621 -0.00004 -0.00002 0.00000 0.0008842 3 0.00125 0.00621 0.00002 0.00000 0.00000 0.00000147 3 0.00060 0.00619 0.00001 0.00000 0.00000 0.00000

5 Solid Elements


252 3 0.00000 0.00618 0.00000 0.00000 0.00000 0.00000357 3 -0.00060 0.00619 -0.00001 0.00000 0.00000 0.00000462 3 -0.00125 0.00621 -0.00002 0.00000 0.00000 0.0000063 3 0.00125 0.00621 0.00000 0.00000 0.00000 0.00000168 3 0.00060 0.00619 0.00000 0.00000 0.00000 0.00000273 3 0.00000 0.00619 0.00000 0.00000 0.00000 0.00088378 3 -0.00060 0.00619 0.00000 0.00000 0.00000 0.00000483 3 -0.00125 0.00621 0.00000 0.00000 0.00000 0.0000084 3 0.00125 0.00621 -0.00002 0.00000 0.00000 0.00000189 3 0.00060 0.00619 -0.00001 0.00000 0.00000 0.00000294 3 0.00000 0.00618 0.00000 0.00000 0.00000 0.00000399 3 -0.00060 0.00619 0.00001 0.00000 0.00000 0.00000504 3 -0.00125 0.00621 0.00002 0.00000 0.00000 0.00000105 3 0.00132 0.00621 -0.00004 0.00002 0.00000 0.00088210 3 0.00061 0.00619 -0.00001 0.00000 0.00000 0.00000315 3 0.00000 0.00618 0.00000 0.00000 0.00000 0.00000420 3 -0.00061 0.00619 0.00001 0.00000 0.00000 0.00000525 3 -0.00132 0.00621 0.00004 0.00002 0.00000 0.00088************** END OF LATEST ANALYSIS RESULT **************130. *131. LOAD LIST 4132. PRINT JOINT DISP LIST 21 TO 441 BY 105 42 TO 462 BY 105 -JOINT DISP LIST 21133. 63 TO 483 BY 105 84 TO 504 BY 105 105 TO 525 BY 105




21 4 0.00372 0.02537 -0.00001 0.00003 0.00000 0.00248126 4 0.00184 0.02535 0.00000 0.00000 0.00000 0.00000231 4 0.00000 0.02534 0.00000 0.00000 0.00000 0.00000336 4 -0.00184 0.02535 0.00000 0.00000 0.00000 0.00000441 4 -0.00372 0.02537 0.00001 0.00003 0.00000 0.0024842 4 0.00373 0.02536 -0.00001 0.00000 0.00000 0.00000147 4 0.00185 0.02534 0.00000 0.00000 0.00000 0.00000252 4 0.00000 0.02533 0.00000 0.00000 0.00000 0.00000357 4 -0.00185 0.02534 0.00000 0.00000 0.00000 0.00000462 4 -0.00373 0.02536 0.00001 0.00000 0.00000 0.0000063 4 0.00373 0.02535 0.00000 0.00000 0.00000 0.00000168 4 0.00185 0.02534 0.00000 0.00000 0.00000 0.00000273 4 0.00000 0.02533 0.00000 0.00000 0.00000 0.00248378 4 -0.00185 0.02534 0.00000 0.00000 0.00000 0.00000483 4 -0.00373 0.02535 0.00000 0.00000 0.00000 0.0000084 4 0.00373 0.02536 0.00001 0.00000 0.00000 0.00000189 4 0.00185 0.02534 0.00000 0.00000 0.00000 0.00000294 4 0.00000 0.02533 0.00000 0.00000 0.00000 0.00000399 4 -0.00185 0.02534 0.00000 0.00000 0.00000 0.00000504 4 -0.00373 0.02536 -0.00001 0.00000 0.00000 0.00000105 4 0.00372 0.02537 0.00001 -0.00003 0.00000 0.00248210 4 0.00184 0.02535 0.00000 0.00000 0.00000 0.00000315 4 0.00000 0.02534 0.00000 0.00000 0.00000 0.00000420 4 -0.00184 0.02535 0.00000 0.00000 0.00000 0.00000525 4 -0.00372 0.02537 -0.00001 -0.00003 0.00000 0.00248************** END OF LATEST ANALYSIS RESULT **************134. *135. LOAD LIST ALL136. PRINT ELEMENT JOINT STRESSES SOLID LIST 10ELEMENT JOINT STRESSES SOLID


ELEMENT STRESSES UNITS= POUNINCH-------------------------------------------------------------------------------

NODE/ NORMAL STRESSES SHEAR STRESSES

260 — STAAD.Pro

5 Solid Elements

Static Solid 2

ELEMENT LOAD CENTER SXX SYY SZZ SXY SYZ SZX-------------------------------------------------------------------------------

10 1 31 -200.005 -0.003 0.000 0.001 0.000 -0.00110 1 136 -199.999 -0.003 0.001 0.001 0.000 0.00010 1 115 -200.000 -0.003 0.002 0.001 0.000 0.00010 1 10 -200.007 -0.003 0.000 0.001 0.000 -0.00110 1 32 -200.004 -0.001 0.001 0.001 0.000 0.00010 1 137 -199.999 -0.001 0.000 0.001 0.000 -0.00110 1 116 -200.000 -0.002 0.000 0.001 0.000 0.00010 1 11 -200.007 -0.002 0.001 0.001 0.000 -0.001

10 1 CENTER -200.003 -0.002 0.001 0.001 0.000 0.000S1= 0.001 S2= -0.002 S3= -200.003 SE= 200.002DC= 0.000 -0.017 1.000 0.000 1.000 0.017

10 2 31 0.006 -0.006 -0.008 137.619 0.001 -279.91310 2 136 0.006 -0.004 -0.004 137.618 0.003 -53.16010 2 115 0.006 -0.009 -0.006 390.964 0.002 -53.15910 2 10 0.007 -0.010 -0.009 390.962 0.000 -279.91310 2 32 0.005 0.004 0.008 137.619 0.000 -279.91310 2 137 0.002 0.002 0.003 137.618 -0.002 -53.16010 2 116 0.006 0.007 0.005 390.963 -0.001 -53.15910 2 11 0.011 0.009 0.010 390.962 0.001 -279.914

10 2 CENTER 0.006 -0.001 0.000 264.291 0.001 -166.536S1= 312.387 S2= 0.000 S3= -312.382 SE= 541.066DC= 0.707 0.598 -0.377 0.000 0.533 0.846


ELEMENT STRESSES UNITS= POUNINCH-------------------------------------------------------------------------------

NODE/ NORMAL STRESSES SHEAR STRESSESELEMENT LOAD CENTER SXX SYY SZZ SXY SYZ SZX-------------------------------------------------------------------------------

10 3 31 833.325 -0.002 0.000 0.000 0.000 0.00010 3 136 416.662 -0.002 0.000 0.000 0.000 0.00010 3 115 416.662 -0.002 -0.001 0.000 0.000 0.00010 3 10 833.325 -0.002 0.000 0.000 0.000 0.00010 3 32 833.325 0.000 0.000 0.000 0.000 0.00010 3 137 416.662 0.001 0.000 0.000 0.000 0.00010 3 116 416.662 0.001 0.000 0.000 0.000 0.00010 3 11 833.325 0.001 0.000 0.000 0.000 0.000

10 3 CENTER 624.994 -0.001 0.000 0.000 0.000 0.000S1= 624.994 S2= 0.000 S3= -0.001 SE= 624.994DC= 1.000 0.000 0.000 0.000 0.046 0.999

10 4 31 2619.592 -45.597 -52.800 101.363 2.404 -4.54110 4 136 1317.907 -34.780 -27.561 101.362 2.404 -2.11010 4 115 1317.908 -34.781 -27.562 115.768 -2.403 2.69710 4 10 2619.594 -45.598 -52.801 115.768 -2.404 -9.34910 4 32 2630.409 45.589 52.800 101.363 -2.404 -4.54110 4 137 1307.089 34.772 27.558 101.363 -2.404 -2.11010 4 116 1307.091 34.773 27.559 115.768 2.404 2.69810 4 11 2630.412 45.590 52.800 115.767 2.404 -9.349

10 4 CENTER 1968.750 -0.004 -0.001 108.565 0.000 -3.326S1= 1974.724 S2= -0.001 S3= -5.978 SE= 1977.721DC= 0.998 0.055 -0.002 0.000 0.031 1.000

137. *PRINT ELEMENT JOINT STRESSES SOLID LIST 10 TO 70 BY 20138. *PRINT ELEMENT JOINT STRESSES SOLID LIST 90 TO 150 BY 20139. *PRINT ELEMENT JOINT STRESSES SOLID LIST 170 TO 230 BY 20140. *PRINT ELEMENT JOINT STRESSES SOLID LIST 250 TO 310 BY 20141. FINISH

5 Solid Elements





262 — STAAD.Pro

5 Solid Elements

Static Solid 2

6Nonlinear Static Analysis

Static Nonlinear 1ObjectiveTo verify P-Delta analysis for a Ten story plane frame.

ReferenceNaeim, F., The Seismic Design Handbook, Van Nostrand Reinhold, 1989.

ProblemFind the lateral displacement of the 10th story after two iterations of P-Delta analysis.

E = 29,000 ksi

Figure 6-1: Ten story, plane frame

Comparison


Displacement, δ (in) 8.508 8.65068 1.7%

Table 6-1: Comparison of displacements for the frame


STAAD InputSTAAD PLANE : 2-ITERATION PDELTA ANALYSIS OF A 10 STOREY PLANE FRAME* INPUT FILE: PROB211.STD*INPUT WIDTH 72UNIT FEET KIPJOINT COORDINATES1 0. 0. 0.; 2 20. 0. 0.; 3 40. 0. 0.; 4 60. 0. 0.; 5 0. 15. 0.6 20. 15. 0.; 7 40. 15. 0.; 8 60. 15. 0.; 9 0. 27. 0.; 10 20. 27. 0.11 40. 27. 0.; 12 60. 27. 0.; 13 0. 39. 0.; 14 20. 39. 0.; 15 40. 39. 0.16 60. 39. 0.; 17 0. 51. 0.; 18 20. 51. 0.; 19 40. 51. 0.; 20 60. 51. 0.21 0. 63. 0.; 22 20. 63. 0.; 23 40. 63. 0.; 24 60. 63. 0.; 25 0. 75. 0.26 20. 75. 0.; 27 40. 75. 0.; 28 60. 75. 0.; 29 0. 87. 0.; 30 20. 87. 0.31 40. 87. 0.; 32 60. 87. 0.; 33 0. 99. 0.; 34 20. 99. 0.; 35 40. 99. 0.36 60. 99. 0.; 37 0. 111. 0.; 38 20. 111. 0.; 39 40. 111. 0.40 60. 111. 0.; 41 0. 123. 0.; 42 20. 123. 0.; 43 40. 123. 0.44 60. 123. 0.MEMBER INCIDENCES1 1 5; 2 2 6; 3 3 7; 4 4 8; 5 5 6; 6 6 7; 7 7 8; 8 5 9; 9 6 10; 10 7 1111 8 12; 12 9 10; 13 10 11; 14 11 12; 15 9 13; 16 10 14; 17 11 1518 12 16; 19 13 14; 20 14 15; 21 15 16; 22 13 17; 23 14 18; 24 15 1925 16 20; 26 17 18; 27 18 19; 28 19 20; 29 17 21; 30 18 22; 31 19 2332 20 24; 33 21 22; 34 22 23; 35 23 24; 36 21 25; 37 22 26; 38 23 2739 24 28; 40 25 26; 41 26 27; 42 27 28; 43 25 29; 44 26 30; 45 27 3146 28 32; 47 29 30; 48 30 31; 49 31 32; 50 29 33; 51 30 34; 52 31 3553 32 36; 54 33 34; 55 34 35; 56 35 36; 57 33 37; 58 34 38; 59 35 3960 36 40; 61 37 38; 62 38 39; 63 39 40; 64 37 41; 65 38 42; 66 39 4367 40 44; 68 41 42; 69 42 43; 70 43 44MEMBER PROPERTY AMERICAN61 TO 63 68 TO 70 TABLE ST W16X4047 TO 49 54 TO 56 TABLE ST W21X4433 TO 35 40 TO 42 TABLE ST W21X505 TO 7 12 TO 14 19 TO 21 26 TO 28 TABLE ST W24X551 4 8 11 TABLE ST W14X10915 18 22 25 TABLE ST W14X8229 32 36 39 TABLE ST W14X6843 46 50 53 TABLE ST W14X5357 60 64 67 TABLE ST W14X432 3 9 10 TABLE ST W14X15916 17 23 24 TABLE ST W14X10930 31 37 38 TABLE ST W14X9044 45 51 52 TABLE ST W14X6858 59 65 66 TABLE ST W14X48UNIT INCHES KIPCONSTANTSE 29000. ALLDENSITY STEEL ALLPOISSON STEEL ALLSUPPORTS1 TO 4 FIXEDUNIT FEET KIPLOAD 1 LATERAL LOADSSELFWEIGHT Y -1.0JOINT LOAD5 FX 2.979 FX 5.3413 FX 7.7117 FX 10.0821 FX 12.4525 FX 14.8329 FX 17.233 FX 19.5737 FX 21.9441 FX 30.22

264 — STAAD.Pro

6 Nonlinear Static Analysis

Static Nonlinear 1

MEMBER LOAD68 TO 70 UNI GY -3.5 TO 7 12 TO 14 19 TO 21 26 TO 28 33 TO 35 40 TO 42 47 TO 49 -54 TO 56 61 TO 63 UNI GY -3.6PDELTA 2 ANALYSISPRINT SUPPORT REACTIONSPRINT JOINT DISPLACEMENTS LIST 5 9 13 17 21 25 29 33 37 41FINISH



1. STAAD PLANE : 2-ITERATION PDELTA ANALYSIS OF A 10 STOREY PLANE FRAMEINPUT FILE: PROB211.STD

2. * INPUT FILE: PROB211.STD3. *4. INPUT WIDTH 725. UNIT FEET KIP6. JOINT COORDINATES7. 1 0. 0. 0.; 2 20. 0. 0.; 3 40. 0. 0.; 4 60. 0. 0.; 5 0. 15. 0.8. 6 20. 15. 0.; 7 40. 15. 0.; 8 60. 15. 0.; 9 0. 27. 0.; 10 20. 27. 0.9. 11 40. 27. 0.; 12 60. 27. 0.; 13 0. 39. 0.; 14 20. 39. 0.; 15 40. 39. 0.10. 16 60. 39. 0.; 17 0. 51. 0.; 18 20. 51. 0.; 19 40. 51. 0.; 20 60. 51. 0.11. 21 0. 63. 0.; 22 20. 63. 0.; 23 40. 63. 0.; 24 60. 63. 0.; 25 0. 75. 0.12. 26 20. 75. 0.; 27 40. 75. 0.; 28 60. 75. 0.; 29 0. 87. 0.; 30 20. 87. 0.13. 31 40. 87. 0.; 32 60. 87. 0.; 33 0. 99. 0.; 34 20. 99. 0.; 35 40. 99. 0.14. 36 60. 99. 0.; 37 0. 111. 0.; 38 20. 111. 0.; 39 40. 111. 0.15. 40 60. 111. 0.; 41 0. 123. 0.; 42 20. 123. 0.; 43 40. 123. 0.16. 44 60. 123. 0.17. MEMBER INCIDENCES18. 1 1 5; 2 2 6; 3 3 7; 4 4 8; 5 5 6; 6 6 7; 7 7 8; 8 5 9; 9 6 10; 10 7 1119. 11 8 12; 12 9 10; 13 10 11; 14 11 12; 15 9 13; 16 10 14; 17 11 1520. 18 12 16; 19 13 14; 20 14 15; 21 15 16; 22 13 17; 23 14 18; 24 15 1921. 25 16 20; 26 17 18; 27 18 19; 28 19 20; 29 17 21; 30 18 22; 31 19 2322. 32 20 24; 33 21 22; 34 22 23; 35 23 24; 36 21 25; 37 22 26; 38 23 2723. 39 24 28; 40 25 26; 41 26 27; 42 27 28; 43 25 29; 44 26 30; 45 27 3124. 46 28 32; 47 29 30; 48 30 31; 49 31 32; 50 29 33; 51 30 34; 52 31 3525. 53 32 36; 54 33 34; 55 34 35; 56 35 36; 57 33 37; 58 34 38; 59 35 3926. 60 36 40; 61 37 38; 62 38 39; 63 39 40; 64 37 41; 65 38 42; 66 39 4327. 67 40 44; 68 41 42; 69 42 43; 70 43 4428. MEMBER PROPERTY AMERICAN29. 61 TO 63 68 TO 70 TABLE ST W16X4030. 47 TO 49 54 TO 56 TABLE ST W21X4431. 33 TO 35 40 TO 42 TABLE ST W21X5032. 5 TO 7 12 TO 14 19 TO 21 26 TO 28 TABLE ST W24X5533. 1 4 8 11 TABLE ST W14X10934. 15 18 22 25 TABLE ST W14X8235. 29 32 36 39 TABLE ST W14X6836. 43 46 50 53 TABLE ST W14X5337. 57 60 64 67 TABLE ST W14X4338. 2 3 9 10 TABLE ST W14X159: 2-ITERATION PDELTA ANALYSIS OF A 10 STOREY PLANE FRAME -- PAGE NO. 2

* INPUT FILE: PROB211.STD



39. 16 17 23 24 TABLE ST W14X10940. 30 31 37 38 TABLE ST W14X9041. 44 45 51 52 TABLE ST W14X6842. 58 59 65 66 TABLE ST W14X4843. UNIT INCHES KIP44. CONSTANTS45. E 29000. ALL46. DENSITY STEEL ALL47. POISSON STEEL ALL48. SUPPORTS49. 1 TO 4 FIXED50. UNIT FEET KIP51. LOAD 1 LATERAL LOADS52. SELFWEIGHT Y -1.053. JOINT LOAD54. 5 FX 2.9755. 9 FX 5.3456. 13 FX 7.7157. 17 FX 10.0858. 21 FX 12.4559. 25 FX 14.8360. 29 FX 17.261. 33 FX 19.5762. 37 FX 21.9463. 41 FX 30.2264. MEMBER LOAD65. 68 TO 70 UNI GY -3.66. 5 TO 7 12 TO 14 19 TO 21 26 TO 28 33 TO 35 40 TO 42 47 TO 49 -67. 54 TO 56 61 TO 63 UNI GY -3.668. PDELTA 2 ANALYSIS





++ Adjusting Displacements.++ Adjusting Displacements.69. PRINT SUPPORT REACTIONS

SUPPORT REACTION: 2-ITERATION PDELTA ANALYSIS OF A 10 STOREY PLANE FRAME -- PAGE NO. 3


SUPPORT REACTIONS -UNIT KIP FEET STRUCTURE TYPE = PLANE-----------------


1 1 -24.00 167.71 0.00 0.00 0.00 266.142 1 -44.43 728.93 0.00 0.00 0.00 450.673 1 -44.18 735.89 0.00 0.00 0.00 450.194 1 -29.70 562.08 0.00 0.00 0.00 299.73

************** END OF LATEST ANALYSIS RESULT **************70. PRINT JOINT DISPLACEMENTS LIST 5 9 13 17 21 25 29 33 37 41

JOINT DISPLACE LIST 5: 2-ITERATION PDELTA ANALYSIS OF A 10 STOREY PLANE FRAME -- PAGE NO. 4




266 — STAAD.Pro


Static Nonlinear 1

5 1 0.82897 -0.03237 0.00000 0.00000 0.00000 -0.004899 1 1.67625 -0.05713 0.00000 0.00000 0.00000 -0.0050513 1 2.62309 -0.08847 0.00000 0.00000 0.00000 -0.0052617 1 3.53869 -0.11799 0.00000 0.00000 0.00000 -0.0052621 1 4.53245 -0.15093 0.00000 0.00000 0.00000 -0.0059925 1 5.50658 -0.18017 0.00000 0.00000 0.00000 -0.0058329 1 6.48039 -0.21225 0.00000 0.00000 0.00000 -0.0057633 1 7.31800 -0.23765 0.00000 0.00000 0.00000 -0.0052637 1 8.09132 -0.25954 0.00000 0.00000 0.00000 -0.0051641 1 8.65068 -0.26980 0.00000 0.00000 0.00000 -0.00482



: 2-ITERATION PDELTA ANALYSIS OF A 10 STOREY PLANE FRAME -- PAGE NO. 5* INPUT FILE: PROB211.STD




268 — STAAD.Pro


Notes

7Dynamic Analysis

Dynamic Truss 1 269

Dynamic Beam 1 272

Dynamic Beam 2 276

Dynamic Beam 3 278

Dynamic Beam 4 281

Dynamic Beam 7 287

Dynamic Truss 1ObjectiveTo calculate the Natural frequency of vibration for a two story truss.

ReferenceHand calculation using known formula.

ProblemFind the natural frequency of vibration, f, of the truss.


E = 30,000 ksi

All members are L4x4x5/16


Lateral load at joints 3 and 6 equal to 10 kips, each

Hand CalculationCalculate average deflection at top:

δavg = (0.45255 in + 0.43535 in)/2 = 0.444 in

Stiffness of truss:

k = P/δavg = 20.0 kip/0.444 in = 45.5 k/in

Mass:

M = w/g = 20.0/386.4 = 0.05175 k-sec2/in

Frequency:

f Hz= = = 4.696k m

π π

/

2

45.05 / 0.05175

2

Comparison


Frequency, f (Hz) 4.696 4.693 none

Table 7-1: Comparison of frequency for dynamic analysis truss

STAAD InputSTAAD TRUSS : A TWO STORY TRUSS* INPUT FILE: PROB311.STD**UNIT FEET KIPJOINT COORD1 0 0 0 3 0 20 04 10 0 0 6 10 20 0MEMBER INCI1 1 2 23 4 5 45 1 4 78 2 4; 9 2 6MEMB PROPERTIES AMERICAN1 TO 9 TA ST L40405CONSTANTSE STEEL ALLDEN STEEL ALLPOIS STEEL ALLSUPPORTS1 PINNED4 FIXED BUT FX FZ MX MY MZCUT OFF MODE 1LOAD 1JOINT LOAD3 6 FX 10MODAL CALCULATIONPERFORM ANALYSISPRINT JOINT DISPLACEMENTS LIST 3 6FINI


270 — STAAD.Pro

7 Dynamic Analysis

Dynamic Truss 1


1. STAAD TRUSS : A TWO STORY TRUSSINPUT FILE: PROB311.STD

2. * INPUT FILE: PROB311.STD3. *4. *5. UNIT FEET KIP6. JOINT COORD7. 1 0 0 0 3 0 20 08. 4 10 0 0 6 10 20 09. MEMBER INCI10. 1 1 2 211. 3 4 5 412. 5 1 4 713. 8 2 4; 9 2 614. MEMB PROPERTIES AMERICAN15. 1 TO 9 TA ST L4040516. CONSTANTS17. E STEEL ALL18. DEN STEEL ALL19. POIS STEEL ALL20. SUPPORTS21. 1 PINNED22. 4 FIXED BUT FX FZ MX MY MZ23. CUT OFF MODE 124. LOAD 125. JOINT LOAD26. 3 6 FX 1027. MODAL CALCULATION28. PERFORM ANALYSIS: A TWO STORY TRUSS -- PAGE NO. 2






NUMBER OF MODES REQUESTED = 1NUMBER OF EXISTING MASSES IN THE MODEL = 2NUMBER OF MODES THAT WILL BE USED = 1

*** EIGENSOLUTION : ADVANCED METHOD ***: A TWO STORY TRUSS -- PAGE NO. 3

* INPUT FILE: PROB311.STDCALCULATED FREQUENCIES FOR LOAD CASE 1

MODE FREQUENCY(CYCLES/SEC) PERIOD(SEC)1 4.693 0.21310

MODAL WEIGHT (MODAL MASS TIMES g) IN KIP GENERALIZEDMODE X Y Z WEIGHT

7 Dynamic Analysis


1 1.999221E+01 0.000000E+00 0.000000E+00 1.924051E+01PARTICIPATION FACTORS

MASS PARTICIPATION FACTORS IN PERCENT--------------------------------------

MODE X Y Z SUMM-X SUMM-Y SUMM-Z1 99.96 0.00 0.00 99.961 0.000 0.000


: A TWO STORY TRUSS -- PAGE NO. 4* INPUT FILE: PROB311.STD



3 1 0.45255 0.06879 0.00000 0.00000 0.00000 0.000006 1 0.43535 -0.06879 0.00000 0.00000 0.00000 0.00000

************** END OF LATEST ANALYSIS RESULT **************30. FINI


: A TWO STORY TRUSS -- PAGE NO. 5* INPUT FILE: PROB311.STD


Dynamic Beam 1ObjectiveTo calculate the Natural frequency of vibration for a rectangular cantilever beam with a massat the free end.

ReferenceHand calculation using known formulas.

ProblemFind the natural frequency of vibration, ω, of the cantilever beam.

272 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 1

Figure 7-2: Model for dynamic beam no. 1

E = 30,000 ksi

h = 12.0 in, b = 6.0 in

W = 10.0 k

L = 120 in

Hand CalculationsStiffness at free end:

k = 3EI/L3 = 45 k/in

Mass

m = w/g = 10.0 k / (386.4 k-sec2/in) = 0.02588 k-sec2/in

Circular frequency:

ω = = = 41.7 rad/seck

m

45

0.02588

= 6.637 cycles/sec

Comparison



Table 7-2: Comparison of results for dynamic beam no. 1

STAAD InputSTAAD PLANE: A RECTANGULAR CANTILEVER BEAM WITH A MASS AT THE FREE END* FILE: DYNB01.STD** REFERENCE: CALCULATED EXPLICITLY USING KNOWN FORMULA*INPUT WIDTH 72SET SHEARUNIT FEETJOINT COORDINATES1 0.0 0.02 5.0 0.03 10.0 0.0*UNIT KIP INCHMEMBER INCIDENCES

7 Dynamic Analysis


1 1 2 2MEMBER PROPERTIES1 2 PRI YD 12 ZD 6CONSTANTSE 30000.0 ALL*SUPPORTS1 FIXEDCUT OFF MODE SHAPE 1*UNIT FTLOADING 1 VERTICAL LOADMEMBER LOAD2 CONC Y -10.0 5.01 2 UNI GY -.001MODAL CALCULATION*PERFORM ANALYSIS*PRINT MODE SHAPESFINISH



1. STAAD PLANE: A RECTANGULAR CANTILEVER BEAM WITH A MASS AT THE FREE ENDINPUT FILE: DYNB01.STD

2. * FILE: DYNB01.STD3. *4. * REFERENCE: CALCULATED EXPLICITLY USING KNOWN FORMULA5. *6. INPUT WIDTH 727. SET SHEAR8. UNIT FEET9. JOINT COORDINATES10. 1 0.0 0.011. 2 5.0 0.012. 3 10.0 0.013. *14. UNIT KIP INCH15. MEMBER INCIDENCES16. 1 1 2 217. MEMBER PROPERTIES18. 1 2 PRI YD 12 ZD 619. CONSTANTS20. E 30000.0 ALL21. *22. SUPPORTS23. 1 FIXED24. CUT OFF MODE SHAPE 125. *26. UNIT FT27. LOADING 1 VERTICAL LOAD28. MEMBER LOAD

274 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 1

29. 2 CONC Y -10.0 5.030. 1 2 UNI GY -.00131. MODAL CALCULATION32. *33. PERFORM ANALYSIS

A RECTANGULAR CANTILEVER BEAM WITH A MASS AT THE FREE EN -- PAGE NO. 2* FILE: DYNB01.STD







*** EIGENSOLUTION : ADVANCED METHOD ***A RECTANGULAR CANTILEVER BEAM WITH A MASS AT THE FREE EN -- PAGE NO. 3

* FILE: DYNB01.STDCALCULATED FREQUENCIES FOR LOAD CASE 1


MODAL WEIGHT (MODAL MASS TIMES g) IN KIP GENERALIZEDMODE X Y Z WEIGHT



MODE X Y Z SUMM-X SUMM-Y SUMM-Z1 0.00 99.98 0.00 0.000 99.976 0.000

34. *PRINT MODE SHAPES35. FINISH


A RECTANGULAR CANTILEVER BEAM WITH A MASS AT THE FREE EN -- PAGE NO. 4* FILE: DYNB01.STD


7 Dynamic Analysis


Dynamic Beam 2ObjectiveTo calculate the Natural frequency of vibration using the Rayleigh method for a light cantileverbeam with a mass at the free end.

ReferenceThomson, W.T., Vibration Theory and Applications, Prentice-Hall, Inc., 1965.

ProblemFind the natural frequency of vibration, f, of a mass, m, attached to the end of a light cantileverbeam of length, L, and flexural stiffness, EI.


E = 30,000 ksi

I = 1.3333 in4

m = 0.1 lb-sec2/in

L = 30 in

Comparison




STAAD InputSTAAD PLANE NATURAL FREQUENCY OF A CANTILEVERED MASS* FILE: DYNB02.STD** REFERENCE: THOMSON, W.T., "VIBRATION THEORY AND APPLICATIONS",* PRENTICE HALL INC., ENGLEWOODS, NEW JERSEY, 1965

276 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 2

*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 30. 0. 0.MEMBER INCIDENCES1 1 2MEMBER PROPERTY AMERICAN1 PRI IZ 1.333333333333CONSTANTSE 30000000. ALLSUPPORTS1 FIXEDLOAD 1 NATURAL FREQUENCYJOINT LOAD2 FY -38.64CALCULATE RAYLEIGH FREQUENCYPERFORM ANALYSISPRINT JOINT DISPFINISH



1. STAAD PLANE NATURAL FREQUENCY OF A CANTILEVERED MASSINPUT FILE: DYNB02.STD

2. * FILE: DYNB02.STD3. *4. * REFERENCE: THOMSON, W.T., "VIBRATION THEORY AND APPLICATIONS",5. * PRENTICE HALL INC., ENGLEWOODS, NEW JERSEY, 19656. *7. INPUT WIDTH 728. UNIT INCHES POUND9. JOINT COORDINATES10. 1 0. 0. 0.; 2 30. 0. 0.11. MEMBER INCIDENCES12. 1 1 213. MEMBER PROPERTY AMERICAN14. 1 PRI IZ 1.333333333333*WARNING* INSUFFICIENT DATA FOR PRISMATIC PROPERTIES.

CIRCULAR SECTION ASSUMED.15. CONSTANTS16. E 30000000. ALL17. SUPPORTS18. 1 FIXED19. LOAD 1 NATURAL FREQUENCY20. JOINT LOAD21. 2 FY -38.6422. CALCULATE RAYLEIGH FREQUENCY23. PERFORM ANALYSIS


7 Dynamic Analysis


NATURAL FREQUENCY OF A CANTILEVERED MASS -- PAGE NO. 2* FILE: DYNB02.STD





*********************************************************** ** RAYLEIGH FREQUENCY FOR LOADING 1 = 33.53650 CPS ** MAX DEFLECTION = 0.00870 INCH GLO Y, AT JOINT 2 ** ***********************************************************

24. PRINT JOINT DISPJOINT DISP




1 1 0.00000 0.00000 0.00000 0.00000 0.00000 0.000002 1 0.00000 -0.00870 0.00000 0.00000 0.00000 -0.00043





Dynamic Beam 3ObjectiveTo find the fundamental frequency of vibration for a simply supported beam with a uniformmass.

278 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 3

ReferenceThomson, W.T., Vibration Theory and Applications, Prentice-Hall, Inc., 1965. Also compared withANSYS® Finite Element Software.

ProblemFind the fundamental frequency, f, of a simply supported beam of uniform cross-section.


E = 30,000 ksi

I = 1.3333 in4

A = 4 in2

w = 1.124 lb/in

L = 80 in

Comparison

Result Type Theory ANSYS STAAD.Pro Difference

Frequency, f (Hz) 28.766 28.767 28.7438 (Rayleigh) none

28.761 (Eigensolution) none


STAAD InputSTAAD PLANE :FUNDAMENTAL FREQUENCY OF A SIMPLY SUPPORTED BEAM* FILE: DYNB03.STD** REFERENCE: THOMSON, W.T., "VIBRATION THEORY AND APPLICATIONS",* PRENTICE HALL INC., ENGLEWOODS, NEW JERSEY, 1965*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 20. 0. 0.; 3 40. 0. 0.; 4 60. 0. 0.; 5 80. 0. 0.MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4; 4 4 5MEMBER PROPERTY AMERICAN1 TO 4 PRI AX 4.0 IZ 1.333333333333CONSTANTSE 30000000. ALLSUPPORTS1 5 PINNEDCUT OFF FREQUENCY 100.CUT OFF MODE SHAPE 3LOAD 1 DYNAMIC ANALYSIS (NATURAL FREQUENCY)MEMBER LOAD

7 Dynamic Analysis


1 TO 4 UNI GY 1.124CALCULATE RAYLEIGH FREQUENCYMODAL CALCULATIONPERFORM ANALYSISFINISH



1. STAAD PLANE :FUNDAMENTAL FREQUENCY OF A SIMPLY SUPPORTED BEAMINPUT FILE: DYNB03.STD

2. * FILE: DYNB03.STD3. *4. * REFERENCE: THOMSON, W.T., "VIBRATION THEORY AND APPLICATIONS",5. * PRENTICE HALL INC., ENGLEWOODS, NEW JERSEY, 19656. *7. INPUT WIDTH 728. UNIT INCHES POUND9. JOINT COORDINATES10. 1 0. 0. 0.; 2 20. 0. 0.; 3 40. 0. 0.; 4 60. 0. 0.; 5 80. 0. 0.11. MEMBER INCIDENCES12. 1 1 2; 2 2 3; 3 3 4; 4 4 513. MEMBER PROPERTY AMERICAN14. 1 TO 4 PRI AX 4.0 IZ 1.33333333333315. CONSTANTS16. E 30000000. ALL17. SUPPORTS18. 1 5 PINNED19. CUT OFF FREQUENCY 100.20. CUT OFF MODE SHAPE 321. LOAD 1 DYNAMIC ANALYSIS (NATURAL FREQUENCY)22. MEMBER LOAD23. 1 TO 4 UNI GY 1.12424. CALCULATE RAYLEIGH FREQUENCY25. MODAL CALCULATION26. PERFORM ANALYSIS


:FUNDAMENTAL FREQUENCY OF A SIMPLY SUPPORTED BEAM -- PAGE NO. 2* FILE: DYNB03.STD





280 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 3


*** EIGENSOLUTION : ADVANCED METHOD ***:FUNDAMENTAL FREQUENCY OF A SIMPLY SUPPORTED BEAM -- PAGE NO. 3


MODE FREQUENCY(CYCLES/SEC) PERIOD(SEC)1 28.761 0.034772 114.242 0.008753 242.561 0.00412

MODAL WEIGHT (MODAL MASS TIMES g) IN POUN GENERALIZEDMODE X Y Z WEIGHT

1 0.000000E+00 6.551152E+01 0.000000E+00 4.496000E+012 0.000000E+00 1.370158E-30 0.000000E+00 4.496000E+013 0.000000E+00 1.928479E+00 0.000000E+00 4.496000E+01

PARTICIPATION FACTORSMASS PARTICIPATION FACTORS IN PERCENT--------------------------------------

MODE X Y Z SUMM-X SUMM-Y SUMM-Z1 0.00 97.14 0.00 0.000 97.140 0.0002 0.00 0.00 0.00 0.000 97.140 0.0003 0.00 2.86 0.00 0.000 100.000 0.000

*********************************************************** ** RAYLEIGH FREQUENCY FOR LOADING 1 = 28.74382 CPS ** MAX DEFLECTION = 0.01499 INCH GLO Y, AT JOINT 3 ** ***********************************************************

27. FINISH:FUNDAMENTAL FREQUENCY OF A SIMPLY SUPPORTED BEAM -- PAGE NO. 4

* FILE: DYNB03.STD*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:28:44 ****


Dynamic Beam 4ObjectiveTo find the first three natural frequencies of vibration for a cantilever beam with a uniformmass.

ReferenceThomson, W.T., Vibration Theory and Applications, Prentice-Hall, Inc., 1965. Also compared withANSYS® Finite Element software.

7 Dynamic Analysis


ProblemFind the first three natural frequencies, f1, f2 and f3 of the cantilever beam.


E = 30,000 ksi

I = 1.3333 in4

A = 4 in2

w = 1.124 lb/in

L = 80 in

Comparison

Result Type Theory ANSYS STAAD.Pro Difference

Frequency, f1 (Hz) 10.247 10.247 10.237 none

Frequency, f2 (Hz) 64.221 64.197 63.974 none

Frequency, f3 (Hz) 179.82 180.14 178.672 <1%


STAAD InputSTAAD PLANE : FREQUENCIES OF A CANTILEVERED BEAM* FILE: DYNB04.STD** REFERENCE: THOMSON, W.T., "VIBRATION THEORY AND APPLICATIONS",* PRENTICE HALL INC., ENGLEWOODS, NEW JERSEY, 1965*INPUT WIDTH 72UNIT INCHES POUNDJOINT COORDINATES1 0. 0. 0.; 2 4. 0. 0.; 3 8. 0. 0.; 4 12. 0. 0.; 5 16. 0. 0.6 20. 0. 0.; 7 24. 0. 0.; 8 28. 0. 0.; 9 32. 0. 0.; 10 36. 0. 0.11 40. 0. 0.; 12 44. 0. 0.; 13 48. 0. 0.; 14 52. 0. 0.; 15 56. 0. 0.16 60. 0. 0.; 17 64. 0. 0.; 18 68. 0. 0.; 19 72. 0. 0.; 20 76. 0. 0.21 80. 0. 0.MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8; 8 8 9; 9 9 10; 10 10 11

282 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 4

11 11 12; 12 12 13; 13 13 14; 14 14 15; 15 15 16; 16 16 17; 17 17 1818 18 19; 19 19 20; 20 20 21MEMBER PROPERTY AMERICAN1 TO 20 PRI AX 4. IZ 1.3333CONSTANTSE 30000000. ALLSUPPORTS1 FIXEDCUT OFF FREQUENCY 200.CUT OFF MODE SHAPE 3LOAD 1 UNIFORM MASS FOR MODAL ANALYSISMEMBER LOAD1 TO 20 UNI GY 1.124MODAL CALCULATION REQUESTEDPERFORM ANALYSISFINISH



1. STAAD PLANE : FREQUENCIES OF A CANTILEVERED BEAMINPUT FILE: DYNB04.STD

2. * FILE: DYNB04.STD3. *4. * REFERENCE: THOMSON, W.T., "VIBRATION THEORY AND APPLICATIONS",5. * PRENTICE HALL INC., ENGLEWOODS, NEW JERSEY, 19656. *7. INPUT WIDTH 728. UNIT INCHES POUND9. JOINT COORDINATES10. 1 0. 0. 0.; 2 4. 0. 0.; 3 8. 0. 0.; 4 12. 0. 0.; 5 16. 0. 0.11. 6 20. 0. 0.; 7 24. 0. 0.; 8 28. 0. 0.; 9 32. 0. 0.; 10 36. 0. 0.12. 11 40. 0. 0.; 12 44. 0. 0.; 13 48. 0. 0.; 14 52. 0. 0.; 15 56. 0. 0.13. 16 60. 0. 0.; 17 64. 0. 0.; 18 68. 0. 0.; 19 72. 0. 0.; 20 76. 0. 0.14. 21 80. 0. 0.15. MEMBER INCIDENCES16. 1 1 2; 2 2 3; 3 3 4; 4 4 5; 5 5 6; 6 6 7; 7 7 8; 8 8 9; 9 9 10; 10 10 1117. 11 11 12; 12 12 13; 13 13 14; 14 14 15; 15 15 16; 16 16 17; 17 17 1818. 18 18 19; 19 19 20; 20 20 2119. MEMBER PROPERTY AMERICAN20. 1 TO 20 PRI AX 4. IZ 1.333321. CONSTANTS22. E 30000000. ALL23. SUPPORTS24. 1 FIXED25. CUT OFF FREQUENCY 200.26. CUT OFF MODE SHAPE 327. LOAD 1 UNIFORM MASS FOR MODAL ANALYSIS28. MEMBER LOAD29. 1 TO 20 UNI GY 1.12430. MODAL CALCULATION REQUESTED31. PERFORM ANALYSIS

7 Dynamic Analysis



: FREQUENCIES OF A CANTILEVERED BEAM -- PAGE NO. 2* FILE: DYNB04.STD






*** EIGENSOLUTION : ADVANCED METHOD ***: FREQUENCIES OF A CANTILEVERED BEAM -- PAGE NO. 3


MODE FREQUENCY(CYCLES/SEC) PERIOD(SEC)1 10.237 0.097682 63.974 0.015633 178.672 0.00560


1 0.000000E+00 5.507472E+01 0.000000E+00 2.252359E+012 0.000000E+00 1.693755E+01 0.000000E+00 2.278794E+013 0.000000E+00 5.820203E+00 0.000000E+00 2.323735E+01


MODE X Y Z SUMM-X SUMM-Y SUMM-Z1 0.00 62.82 0.00 0.000 62.819 0.0002 0.00 19.32 0.00 0.000 82.138 0.0003 0.00 6.64 0.00 0.000 88.777 0.000

32. FINISH: FREQUENCIES OF A CANTILEVERED BEAM -- PAGE NO. 4



Natural Frequency CalculationObjectiveTo find the period of free vibration for a beam supported on two springs with a point mass.

284 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 4

ReferenceTimoshenko, S., Young, D., and Weaver, W., Vibration Problems in Engineering, John Wiley & Sons,4th edition, 1974. page 11, problem 1.1-3.

ProblemA simple beam is supported by two spring as shown in the figure. Neglecting the distributedmass of the beam, calculate the period of free vibration of the beam subjected to a load of W.

EI = 30,000.0 ksi

A = 7.0 ft

B = 3.0 ft.

W = 1,000 lbfK = 300.0 lb/in.

Figure 7-6: Beam supported on springs

Comparison



Period, sec 0.533 0.533 0.533

Table 7-6: Comparison of period, in sec., for verification problem no. 2

STAAD InputSTAAD PLANE VERIFICATION PROBLEM NO 2** REFERENCE 'VIBRATION PROBLEMS IN ENGINEERING' BY* TIMOSHENKO,YOUNG,WEAVER. (4TH EDITION, PAGE 11, PROB 1.1-3)* THE ANSWER IN THE BOOK IS T = 0.533 sec., viz., F = 1.876 CPS*UNIT POUND FEETJOINT COORD ; 1 0. 0. ; 2 7. 0. ; 3 10. 0.MEMB INCI ; 1 1 2 2UNIT INCHSUPPORT1 3 FIXED BUT MZ KFY 300.MEMB PROP ; 1 2 PRIS AX 1. IZ 1.CONSTANTE 30E6 ALLPOISSON STEEL ALLCUT OFF MODE SHAPE 1LOADING 1 1000 LB LOAD AT JOINT 2JOINT LOAD ; 2 FY -1000.MODAL CALCULATION

7 Dynamic Analysis


PERFORM ANALYSFINISH



1. STAAD PLANE VERIFICATION PROBLEM NO 2INPUT FILE: VER02.STD

2. *3. * REFERENCE 'VIBRATION PROBLEMS IN ENGINEERING' BY4. * TIMOSHENKO,YOUNG,WEAVER. (4TH EDITION, PAGE 11, PROB 1.1-3)5. * THE ANSWER IN THE BOOK IS T = 0.533 SEC., VIZ., F = 1.876 CPS6. *7. UNIT POUND FEET8. JOINT COORD ; 1 0. 0. ; 2 7. 0. ; 3 10. 0.9. MEMB INCI ; 1 1 2 210. UNIT INCH11. SUPPORT12. 1 3 FIXED BUT MZ KFY 300.13. MEMB PROP ; 1 2 PRIS AX 1. IZ 1.14. CONSTANT15. E 30E6 ALL16. POISSON STEEL ALL17. CUT OFF MODE SHAPE 118. LOADING 1 1000 LB LOAD AT JOINT 219. JOINT LOAD ; 2 FY -1000.20. MODAL CALCULATION21. PERFORM ANALYS




TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 7VERIFICATION PROBLEM NO 2 -- PAGE NO. 2

*


*** EIGENSOLUTION : ADVANCED METHOD ***VERIFICATION PROBLEM NO 2 -- PAGE NO. 3

*CALCULATED FREQUENCIES FOR LOAD CASE 1



286 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 4



MODE X Y Z SUMM-X SUMM-Y SUMM-Z1 0.00100.00 0.00 0.000 100.000 0.000

22. FINISH*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:30:37 ****



Dynamic Beam 7ObjectiveTo find the natural frequencies of vibration for a simply supported beam.

ReferenceRoark’s Formulas for Stress and Strain, Warren C. Young, McGraw Hill, 6th edition.

ProblemFind the first five flexural natural frequencies of the simple beam. Neglect shear deformation androtary inertia.


E = 10,000 ksi

density = 0.1 lb/in3

Ax = 2.0 in2

Ix = 0.6667 in4

L = 20 in

Hand CalculationsWeight

wweight = Ax * density = 2.0 (0.1) = 0.2 lb/in

7 Dynamic Analysis


wmass = 0.2 /(386.4) = 0.000518

From Table 36, Item 1b of the reference:

⋅( )

f k= = = 45.16n

k

π

EI

wl

k

π n2 2

10(10) 0.6667

0.000518(20)

n n

4

6

4

Mode kc Frequency (Hz)

1 9.87 445.7

2 39.5 1,783.7

3 88.8 4,010.0

4 158 7,134.9

5 247 11,154

Table 7-7: Modal stiffness and natural frequencies

Comparison


Frequency, f1 (Hz) 445.7 445.495 none

Frequency, f2 (Hz) 1,783.7 1,781.968 none



Frequency, f5 (Hz) 11,154 11,133.978 none


STAAD InputSTAAD PLANE : NATURAL FREQUENCIES OF A S.SUPPORTED BEAM* FILE: DYNB07.STD** REFERENCE: W.C.YOUNG., "ROARK'S FORMULAS FOR STRESS & STRAIN", 6TH ED.* CASE 1B, TABLE 36, PAGE 714*UNIT POUNDS INCHJOINR COORD1 0 0 0 21 20 0 0MEMBER INCIDENCES1 1 2 20CONSTANTSE 10E6 ALLDEN .1 ALLMEMBER PROPERTIES1 TO 20 PRIS AX 2 IZ .666667SUPPORT1 21 FIXED BUT MZ2 TO 20 FIXED BUT FY MZCUT OFF MODE 6CUT OFF FREQUENCY 12000LOAD 1

288 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 7

SELF Y -1MODAL CALCULATION REQUESTEDPERFORM ANALYSISFINISH



1. STAAD PLANE : NATURAL FREQUENCIES OF A S.SUPPORTED BEAMINPUT FILE: DYNB07.STD

2. * FILE: DYNB07.STD3. *4. * REFERENCE: W.C.YOUNG., "ROARK'S FORMULAS FOR STRESS &AMP; STRAIN", 6TH ED.5. * CASE 1B, TABLE 36, PAGE 7146. *7. UNIT POUNDS INCH8. JOINR COORD9. 1 0 0 0 21 20 0 010. MEMBER INCIDENCES11. 1 1 2 2012. CONSTANTS13. E 10E6 ALL14. DEN .1 ALL15. MEMBER PROPERTIES16. 1 TO 20 PRIS AX 2 IZ .66666717. SUPPORT18. 1 21 FIXED BUT MZ19. 2 TO 20 FIXED BUT FY MZ20. CUT OFF MODE 621. CUT OFF FREQUENCY 1200022. LOAD 123. SELF Y -124. MODAL CALCULATION REQUESTED25. PERFORM ANALYSIS


: NATURAL FREQUENCIES OF A S.SUPPORTED BEAM -- PAGE NO. 2* FILE: DYNB07.STD





NUMBER OF MODES REQUESTED = 6NUMBER OF EXISTING MASSES IN THE MODEL = 19

7 Dynamic Analysis


NUMBER OF MODES THAT WILL BE USED = 6

*** EIGENSOLUTION : ADVANCED METHOD ***: NATURAL FREQUENCIES OF A S.SUPPORTED BEAM -- PAGE NO. 3


MODE FREQUENCY(CYCLES/SEC) PERIOD(SEC)1 445.495 0.002242 1781.968 0.000563 4009.310 0.000254 7127.074 0.000145 11133.978 0.00009


1 0.000000E+00 3.228953E+00 0.000000E+00 2.000000E+002 0.000000E+00 1.116193E-28 0.000000E+00 2.000000E+003 0.000000E+00 3.469944E-01 0.000000E+00 2.000000E+004 0.000000E+00 1.934716E-31 0.000000E+00 2.211146E+005 0.000000E+00 1.165685E-01 0.000000E+00 2.000000E+00


MODE X Y Z SUMM-X SUMM-Y SUMM-Z1 0.00 84.97 0.00 0.000 84.972 0.0002 0.00 0.00 0.00 0.000 84.972 0.0003 0.00 9.13 0.00 0.000 94.104 0.0004 0.00 0.00 0.00 0.000 94.104 0.0005 0.00 3.07 0.00 0.000 97.171 0.000

26. FINISH: NATURAL FREQUENCIES OF A S.SUPPORTED BEAM -- PAGE NO. 4



290 — STAAD.Pro

7 Dynamic Analysis

Dynamic Beam 7

8Concrete Design - ACI 318





Concrete Design per ACI 318 1ObjectiveTo determine the reinforced steel quantity for a rectangular beam per the ACI 318 code.

ReferenceNotes on ACI 318-02 Building Code Requirements for Structural Concrete, Example 7.1, p7-24, Designof Rectangular Beam with Tension Reinforcement Only

Notes on ACI 318-99 Building Code Requirements for Structural Concrete, Example 10.1, p10-10,Design of Rectangular Beam with Tension Reinforcement Only

ProblemDead Load moment (service) = 56 fit-kips

Live Load moment (service) = 35 ft-kips

f'c = 4,000 psi

fy = 60,000 psi

Comparison

Result Type ACI Notes STAAD.Pro Difference

Required steel area(in2)

per ACI318-99

2.78 2.793 none

per ACI 2.40 2.44 1.7%

Table 8-1: Comparison of results forconcrete beam designed per ACI 318-02



318-02

Provided steel area(in2)

per ACI318-02

2.40 (2 - #8 & 1-#9)

(2- #10)2.45

1.7%

Note: The assumed NSF of 0.72 is comparable to the term Ae/Ag which comes out to be5.11/7.08.

NotesSTAAD reports that it is unable to find a suitable bar arrangement to satisfy the reinforcementrequirement per ACI 318-99. However, this does not mean that it is impossible to come up witha bar arrangement. When STAAD looks for a bar arrangement, it uses only bars of the samesize. It begins with the bar size corresponding to the parameter MINMAIN. If an arrangement isnot possible with that bar, it tries with the next larger bar size. If all the permissible bar sizesare exhausted, the program reports that it could not come up with a bar arrangement.However, the user may be able to satisfy the requirement by mixing bars of various diameters.For example, 3 # 11 bars and 2 # 10 bars may satisfy the requirement. The program is notequipped with facilities to come up with such combinations of bar sizes.

In fact, in the reference mentioned for the 1999 edition of ACI 318, the bar arrangement chosenis 2 # 9 and 1 # 8. It proves the point that finding bars of the same diameter is not possible forthe 1999 edition based solution.

STAAD InputSTAAD PLANE RECTANGULAR CONCRETE BEAM DESIGN PER ACI 318** INPUT FILE: ACI318_FLEX1.STD** REFERENCE : NOTES ON ACI 318-02 BUILDING CODE REQUIREMENTS* FOR STRUCUTURAL CONCRETE EXAMPLE 7.1 (PAGE # 7-24)* AND* NOTES ON ACI 318-99 BUILDING CODE REQUIREMENTS* FOR STRUCUTURAL CONCRETE EXAMPLE 10.1 (PAGE # 10-10)** OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A* RECTANGULAR BEAM PER THE ACI 318 CODE**INPUT WIDTH 79UNIT FEET KIPJOINT COORDINATES1 0 0 0; 2 10 0 0MEMBER INCIDENCES1 1 2UNIT INCHMEMB PROP1 PRIS YD 16.0 ZD 10.0CONSTANTSE CONCRETE ALLPOI CONCRETE ALLSUPPORT1 2 PINNEDUNIT FEETLOAD 1 DEAD LOADMEMBER LOAD

292 — STAAD.Pro

8 Concrete Design - ACI 318

Concrete Design per ACI 318 1

1 UNI GY -4.48LOAD 2 LIVE LOADMEMBER LOAD1 UNI GY -2.8LOAD COMBINATION 3 ACI 318R-991 1.4 2 1.7LOAD COMBINATION 4 ACI 318R-021 1.2 2 1.6PERF ANALUNIT INCH*** CONCRETE DESIGN AS PER ACI 318R-99*LOAD LIST 3START CONCRETE DESIGNCODE ACI 1999FC 4 ALLFYMAIN 60 ALLTRACK 1 ALLDESIGN BEAM ALLEND CONCRETE DESIGN*** CONCRETE DESIGN AS PER ACI 318R-02*LOAD LIST 4START CONCRETE DESIGNCODE ACI 2002FC 4 ALLFYMAIN 60 ALLTRACK 1 ALLDESIGN BEAM ALLEND CONCRETE DESIGNFINISH



1. STAAD PLANE RECTANGULAR CONCRETE BEAM DESIGN PER ACI 318INPUT FILE: ACI318_FLEX1.STD

2. *3. * INPUT FILE: ACI318_FLEX1.STD4. *5. * REFERENCE : NOTES ON ACI 318-02 BUILDING CODE REQUIREMENTS6. * FOR STRUCUTURAL CONCRETE EXAMPLE 7.1 (PAGE # 7-24)7. * AND8. * NOTES ON ACI 318-99 BUILDING CODE REQUIREMENTS9. * FOR STRUCUTURAL CONCRETE EXAMPLE 10.1 (PAGE # 10-10)10. *11. * OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A12. * RECTANGULAR BEAM PER THE ACI 318 CODE13. *14. *15. INPUT WIDTH 79



16. UNIT FEET KIP17. JOINT COORDINATES18. 1 0 0 0; 2 10 0 019. MEMBER INCIDENCES20. 1 1 221. UNIT INCH22. MEMB PROP23. 1 PRIS YD 16.0 ZD 10.024. CONSTANTS25. E CONCRETE ALL26. POI CONCRETE ALL27. SUPPORT28. 1 2 PINNED29. UNIT FEET30. LOAD 1 DEAD LOAD31. MEMBER LOAD32. 1 UNI GY -4.4833. LOAD 2 LIVE LOAD34. MEMBER LOAD35. 1 UNI GY -2.836. LOAD COMBINATION 3 ACI 318R-9937. 1 1.4 2 1.738. LOAD COMBINATION 4 ACI 318R-02RECTANGULAR CONCRETE BEAM DESIGN PER ACI 318 -- PAGE NO. 2

*39. 1 1.2 2 1.640. PERF ANAL





41. UNIT INCH42. *43. ** CONCRETE DESIGN AS PER ACI 318R-9944. *45. LOAD LIST 346. START CONCRETE DESIGN

CONCRETE DESIGN47. CODE ACI 199948. FC 4 ALL49. FYMAIN 60 ALL50. TRACK 1 ALL51. DESIGN BEAM ALLRECTANGULAR CONCRETE BEAM DESIGN PER ACI 318 -- PAGE NO. 3

*

=====================================================================BEAM NO. 1 DESIGN RESULTS - FLEXURE PER CODE ACI 318-99

LEN - 10.00FT. FY - 60000. FC - 4000. SIZE - 10.00 X 16.00 INCHESLEVEL HEIGHT BAR INFO FROM TO ANCHOR

FT. IN. FT. IN. FT. IN. STA END_____________________________________________________________________

*** A SUITABLE BAR ARRANGEMENT COULD NOT BE DETERMINED.REQD. STEEL = 2.793 IN2, MAX. STEEL PERMISSIBLE = 2.873 IN2MAX POS MOMENT = 137.90 KIP-FT, LOADING 3

___ 1J____________________ 120.X 10.X 16_____________________ 2J____| |

294 — STAAD.Pro



| || || || || || ||___________________________________________________________________________|_________ _________ _________ _________ _________ _________| | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | ||_________| |_________| |_________| |_________| |_________| |_________|********************END OF BEAM DESIGN**************************52. END CONCRETE DESIGN53. *54. ** CONCRETE DESIGN AS PER ACI 318R-0255. *56. LOAD LIST 457. START CONCRETE DESIGN

CONCRETE DESIGN58. CODE ACI 200259. FC 4 ALL60. FYMAIN 60 ALL61. TRACK 1 ALL62. DESIGN BEAM ALLRECTANGULAR CONCRETE BEAM DESIGN PER ACI 318 -- PAGE NO. 4

*

=====================================================================BEAM NO. 1 DESIGN RESULTS - FLEXURE PER CODE ACI 318-02

LEN - 10.00FT. FY - 60000. FC - 4000. SIZE - 10.00 X 16.00 INCHESLEVEL HEIGHT BAR INFO FROM TO ANCHOR

FT. IN. FT. IN. FT. IN. STA END_____________________________________________________________________

1 0 + 2-3/4 2-NUM.10 0 + 0-0/0 10 + 0-0/0 YES YES|----------------------------------------------------------------|| CRITICAL POS MOMENT= 123.20 KIP-FT AT 5.00 FT, LOAD 4|| REQD STEEL= 2.44 IN2, RHO=0.0183, RHOMX=0.0214 RHOMN=0.0033 || MAX/MIN/ACTUAL BAR SPACING= 10.00/ 2.54/ 4.73 INCH || REQD. DEVELOPMENT LENGTH = 48.52 INCH ||----------------------------------------------------------------|Cracked Moment of Inertia Iz at above location = 1817.34 inch^4

B E A M N O. 1 D E S I G N R E S U L T S - SHEAR

AT START SUPPORT - Vu= 38.19 KIP Vc= 21.42 KIP Vs= 29.50 KIPTu= 0.00 KIP-FT Tc= 1.95 KIP-FT Ts= 0.00 KIP-FT LOAD 4NO STIRRUPS ARE REQUIRED FOR TORSION.REINFORCEMENT IS REQUIRED FOR SHEAR.PROVIDE NUM. 4 2-LEGGED STIRRUPS AT 6.7 IN. C/C FOR 46. IN.

AT END SUPPORT - Vu= 38.19 KIP Vc= 21.42 KIP Vs= 29.50 KIPTu= 0.00 KIP-FT Tc= 1.95 KIP-FT Ts= 0.00 KIP-FT LOAD 4NO STIRRUPS ARE REQUIRED FOR TORSION.REINFORCEMENT IS REQUIRED FOR SHEAR.PROVIDE NUM. 4 2-LEGGED STIRRUPS AT 6.7 IN. C/C FOR 46. IN.

RECTANGULAR CONCRETE BEAM DESIGN PER ACI 318 -- PAGE NO. 5*

___ 1J____________________ 120.X 10.X 16_____________________ 2J____



| || || || 8#4 C/C 7 8#4 C/C 7 || 2#10H 3. 0.TO 120. |||=========================================================================||| ||___________________________________________________________________________|_________ _________ _________ _________ _________ _________| | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | || | | | | | | | | | | || 2#10 | | 2#10 | | 2#10 | | 2#10 | | 2#10 | | 2#10 || OO | | OO | | OO | | OO | | OO | | OO || | | | | | | | | | | ||_________| |_________| |_________| |_________| |_________| |_________|********************END OF BEAM DESIGN**************************63. END CONCRETE DESIGN64. FINISH


RECTANGULAR CONCRETE BEAM DESIGN PER ACI 318 -- PAGE NO. 6*


Concrete Design per ACI 318 3ObjectiveTo determine the reinforced steel quantity for a square column per ACI 318-02.

ReferenceNotes on ACI 318-02 Building Code Requirements for Structural Concrete, Example 7.8, p7-46,Design of Square Column for Biaxial loading.

ProblemP = 1,200 kips

Muz = 300 ft-kips

Muy = 125 ft-kips

f'c = 5,000 psi

fy = 60,000 psi

296 — STAAD.Pro



Comparison


Provided steel area per ACI 318-02(in2)

5.93 (4-#11)

5.93 (4-#11)

none

Table 8-2: Comparison of results for concrete beam-column designed per ACI318-02

STAAD InputSTAAD SPACE SQUARE COLUMN DESIGN PER ACI 318-02** INPUT FILE: ACI318_COL1.STD** REFERENCE : NOTES ON ACI 318-02 BUILDING CODE REQUIREMENTS* FOR STRUCUTURAL CONCRETE EXAMPLE 7.8 (PAGE # 7-46)** OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A* SQUARE COLUMN PER THE ACI 318-02 CODE**UNIT FEET KIPJOINT COORDINATES1 0 0 0; 2 0 12 0MEMBER INCIDENCES1 1 2UNIT INCHES KIPMEMBER PROPERTY AMERICAN1 PRIS YD 24 ZD 24CONSTANTSE CONCRETE ALLPOISSON CONCRETE ALLSUPPORTS1 FIXEDUNIT FEET KIPLOAD 1JOINT LOAD2 FY -12002 MZ 3002 MX 125PERFORM ANALYSISSTART CONCRETE DESIGNCODE ACIUNIT INCHES KIPFC 5 ALLMINMAIN 11 ALLMAXMAIN 11 ALLTRACK 2 ALLDESIGN COLUMN ALLEND CONCRETE DESIGNFINISH





* Date= DEC 13, 2013 ** Time= 12:24: 1 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE SQUARE COLUMN DESIGN PER ACI 318-02INPUT FILE: ACI318_COL1.STD

2. *3. * INPUT FILE: ACI318_COL1.STD4. *5. * REFERENCE : NOTES ON ACI 318-02 BUILDING CODE REQUIREMENTS6. * FOR STRUCUTURAL CONCRETE EXAMPLE 7.8 (PAGE # 7-46)7. *8. * OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A9. * SQUARE COLUMN PER THE ACI 318-02 CODE10. *11. *12. UNIT FEET KIP13. JOINT COORDINATES14. 1 0 0 0; 2 0 12 015. MEMBER INCIDENCES16. 1 1 217. UNIT INCHES KIP18. MEMBER PROPERTY AMERICAN19. 1 PRIS YD 24 ZD 2420. CONSTANTS21. E CONCRETE ALL22. POISSON CONCRETE ALL23. SUPPORTS24. 1 FIXED25. UNIT FEET KIP26. LOAD 127. JOINT LOAD28. 2 FY -120029. 2 MZ 30030. 2 MX 12531. PERFORM ANALYSISSQUARE COLUMN DESIGN PER ACI 318-02 -- PAGE NO. 2

*





32. START CONCRETE DESIGNCONCRETE DESIGN

33. CODE ACI34. UNIT INCHES KIP35. FC 5 ALL36. MINMAIN 11 ALL37. MAXMAIN 11 ALL38. TRACK 2 ALL39. DESIGN COLUMN ALLSQUARE COLUMN DESIGN PER ACI 318-02 -- PAGE NO. 3

*

====================================================================COLUMN NO. 1 DESIGN PER ACI 318-08 - AXIAL + BENDING

298 — STAAD.Pro



FY - 60000 FC - 5000 PSI, SQRE SIZE - 24.00 X 24.00 INCHES, TIEDONLY MINIMUM STEEL IS REQUIRED.AREA OF STEEL REQUIRED = 5.760 SQ. IN.

BAR CONFIGURATION REINF PCT. LOAD LOCATION PHI----------------------------------------------------------4 - NUMBER 11 1.083 1 END 0.650

(PROVIDE EQUAL NUMBER OF BARS ON EACH FACE)TIE BAR NUMBER 4 SPACING 22.56 IN

COLUMN INTERACTION: MOMENT ABOUT Z -AXIS (KIP-FT)--------------------------------------------------------P0 Pn max P-bal. M-bal. e-bal.(inch)

2795.88 2236.70 1039.31 894.77 10.33M0 P-tens. Des.Pn Des.Mn e/h

325.52 -374.40 1846.15 461.54 0.02083--------------------------------------------------------

COLUMN INTERACTION: MOMENT ABOUT Y -AXIS (KIP-FT)--------------------------------------------------------P0 Pn max P-bal. M-bal. e-bal.(inch)

2795.88 2236.70 1039.31 894.77 10.33M0 P-tens. Des.Pn Des.Mn e/h

325.52 -374.40 1846.15 192.31 0.00868--------------------------------------------------------

Pn Mn Pn Mn (@ Z )| 2064.65 571.73 1032.32 893.78

P0 |* 1892.60 657.35 860.27 856.61| * 1720.54 729.78 688.22 795.25

Pn,max|__* 1548.49 787.54 516.16 707.98| * 1376.43 832.65 344.11 595.12

Pn | * 1204.38 867.74 172.05 465.20NOMINAL| * Pn Mn Pn Mn (@ Y )AXIAL| * 2064.65 571.73 1032.32 893.78

COMPRESSION| * 1892.60 657.35 860.27 856.61Pb|-------*Mb 1720.54 729.78 688.22 795.25| * 1548.49 787.54 516.16 707.98

___________|____*_______ 1376.43 832.65 344.11 595.12| * M0 Mn, 1204.38 867.74 172.05 465.20| * BENDING

P-tens|* MOMENT|

********************END OF COLUMN DESIGN RESULTS********************SQUARE COLUMN DESIGN PER ACI 318-02 -- PAGE NO. 4

*40. END CONCRETE DESIGN41. FINISH





Concrete Design per ACI 318 4ObjectiveTo determine the reinforced steel quantity for the square column as per ACI 318-99.

ReferenceChu-Kia Wang and Charles G.Slamon, Reinforced Concrete Design, 5th Edition, Examples problem13.21.1, p509 .

ProblemPu = 144 kips

Muz = 120 ft-kips

Muy = 54 ft-kips

f'c = 3,000 psi

fy = 60,000 psi

Comparison

Result Type Reference STAAD.Pro Difference

Provided steel area per ACI 318-99(in2)

8.0 (8-#9)

9.0 (4-#14)

none


Note: In the reference book, the axial capacity provided is 141 kips, which is less than therequirement of 144 kips. In the STAAD implementation of the code, any reinforcementarrangement which yields less capacity than the required value is considered un-acceptable.This is why STAAD reports a higher required steel than the reference book.

STAAD InputSTAAD SPACE SQUARE COLUMN DESIGN ACI 318-99** INPUT FILE: ACI318_COL2.STD** REFERENCE : REINFORCED CONCRETE DESIGN 5TH EDITION BY CHU-KIA WANG* AND CHARLES G.SALMON EX.13.21.1 PAGE 509.** OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A* SQUARE COLUMN PER THE ACI 318-99 CODE*UNIT FEET KIPJOINT COORDINATES1 0 0 0; 2 0 12 0MEMBER INCIDENCES1 1 2UNIT INCHES KIPMEMBER PROPERTY AMERICAN1 PRIS YD 16 ZD 16

300 — STAAD.Pro



CONSTANTSE CONCRETE ALLPOISSON CONCRETE ALLSUPPORTS1 FIXEDUNIT FEET KIPLOAD 1JOINT LOAD2 FY -1442 MZ 1202 MX 54PERFORM ANALYSISUNIT INCHES KIPSTART CONCRETE DESIGNCODE ACI 1999FC 3 ALLFYMAIN 40 ALLFYSEC 40 ALLMINMAIN 9 ALLTRACK 2 ALLDESIGN COLUMN ALLEND CONCRETE DESIGNFINISH



1. STAAD SPACE SQUARE COLUMN DESIGN ACI 318-99INPUT FILE: ACI318_COL2.STD

2. *3. * INPUT FILE: ACI318_COL2.STD4. *5. * REFERENCE : REINFORCED CONCRETE DESIGN 5TH EDITION BY CHU-KIA WANG6. * AND CHARLES G.SALMON EX.13.21.1 PAGE 509.7. *8. * OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A9. * SQUARE COLUMN PER THE ACI 318-99 CODE10. *11. UNIT FEET KIP12. JOINT COORDINATES13. 1 0 0 0; 2 0 12 014. MEMBER INCIDENCES15. 1 1 216. UNIT INCHES KIP17. MEMBER PROPERTY AMERICAN18. 1 PRIS YD 16 ZD 1619. CONSTANTS20. E CONCRETE ALL21. POISSON CONCRETE ALL22. SUPPORTS23. 1 FIXED24. UNIT FEET KIP25. LOAD 1



26. JOINT LOAD27. 2 FY -14428. 2 MZ 12029. 2 MX 5430. PERFORM ANALYSISSQUARE COLUMN DESIGN ACI 318-99 -- PAGE NO. 2

*





31. UNIT INCHES KIP32. START CONCRETE DESIGN

CONCRETE DESIGN33. CODE ACI 199934. FC 3 ALL35. FYMAIN 40 ALL36. FYSEC 40 ALL37. MINMAIN 9 ALL38. TRACK 2 ALL39. DESIGN COLUMN ALLSQUARE COLUMN DESIGN ACI 318-99 -- PAGE NO. 3

*


FY - 40000 FC - 3000 PSI, SQRE SIZE - 16.00 X 16.00 INCHES, TIEDAREA OF STEEL REQUIRED = 8.474 SQ. IN.

BAR CONFIGURATION REINF PCT. LOAD LOCATION PHI----------------------------------------------------------4 - NUMBER 14 3.516 1 END 0.700

(PROVIDE EQUAL NUMBER OF BARS ON EACH FACE)TIE BAR NUMBER 4 SPACING 16.00 IN

COLUMN INTERACTION: MOMENT ABOUT Z -AXIS (KIP-FT)--------------------------------------------------------P0 Pn max P-bal. M-bal. e-bal.(inch)989.85 791.88 312.89 272.99 10.47M0 P-tens. Des.Pn Des.Mn e/h

178.88 -360.00 205.71 171.43 0.06944--------------------------------------------------------

COLUMN INTERACTION: MOMENT ABOUT Y -AXIS (KIP-FT)--------------------------------------------------------P0 Pn max P-bal. M-bal. e-bal.(inch)989.85 791.88 312.89 272.99 10.47M0 P-tens. Des.Pn Des.Mn e/h

178.88 -360.00 205.71 77.14 0.03125--------------------------------------------------------

Pn Mn Pn Mn (@ Z )| 730.97 130.65 365.48 257.30

P0 |* 670.05 156.21 304.57 272.89| * 609.14 178.28 243.66 267.81

Pn,max|__* 548.22 199.53 182.74 255.16| * 487.31 219.54 121.83 234.02

Pn | * 426.40 238.93 60.91 206.79NOMINAL| * Pn Mn Pn Mn (@ Y )AXIAL| * 730.97 130.65 365.48 257.30

COMPRESSION| * 670.05 156.21 304.57 272.89Pb|-------*Mb 609.14 178.28 243.66 267.81

302 — STAAD.Pro



| * 548.22 199.53 182.74 255.16___________|____*_______ 487.31 219.54 121.83 234.02

| * M0 Mn, 426.40 238.93 60.91 206.79| * BENDING

P-tens|* MOMENT|

********************END OF COLUMN DESIGN RESULTS********************40. END CONCRETE DESIGNSQUARE COLUMN DESIGN ACI 318-99 -- PAGE NO. 4

*41. FINISH



Concrete Design per ACI 318 5ObjectiveTo determine the reinforced steel quantity for a circular column per ACI 318-99.

ReferenceChu-Kia Wang and Charles G.Salmon, Reinforced Concrete Design, 5th Edition, Examples problem13.15.1, p481 .

ProblemPu = 1,050 kips

Muz = Muy = 0 ft-kips

f'c = 4,000 psi

fy = 60,000 psi

Spiral lateral reinforcement used.

Comparison


Required steel area (in2) 10.45 10.505 none

Provided steel area (in2) 10.82 (7- #11) 10.82 (18- #7) none


Note: STAAD reports a more economical bar arrangement than the reference book.



STAAD InputSTAAD SPACE CIRCULAR CONCRETE COLUMN DESIGN PER ACI 318-99** INPUT FILE: ACI318_COL3.STD** REFERENCE : REINFORCED CONCRETE DESIGN, 5TH EDITION BY CHU-KIA WANG* AND CHARLES G.SALMON, EX.13.15.1 PAGE 481** OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A* CIRCULAR COLUMN PER THE ACI 318-99 CODE*UNIT KIP FEETJOINT COOR1 0.0 0.02 0.0 12.0MEMB INCI1 1 2UNIT INCHMEMB PROP1 PRIS YD 20.0CONSTANTSE CONCRETE ALLPOI CONCRETE ALLSUPPORT1 FIXEDLOAD 1JOINT LOAD2 FY -1060PERF ANALSTART CONCRETE DESIGNCODE ACI 1999REINF 1.0 ALLDESIGN COLUMN ALLEND CONCRETE DESIGNFINISH



1. STAAD SPACE CIRCULAR CONCRETE COLUMN DESIGN PER ACI 318-99INPUT FILE: ACI318_COL3.STD

2. *3. * INPUT FILE: ACI318_COL3.STD4. *5. * REFERENCE : REINFORCED CONCRETE DESIGN, 5TH EDITION BY CHU-KIA WANG6. * AND CHARLES G.SALMON, EX.13.15.1 PAGE 4817. *8. * OBJECTIVE : TO DETERMINE THE REINFORCED STEEL QUANTITY FOR A9. * CIRCULAR COLUMN PER THE ACI 318-99 CODE10. *11. UNIT KIP FEET

304 — STAAD.Pro



12. JOINT COOR13. 1 0.0 0.014. 2 0.0 12.015. MEMB INCI16. 1 1 217. UNIT INCH18. MEMB PROP19. 1 PRIS YD 20.020. CONSTANTS21. E CONCRETE ALL22. POI CONCRETE ALL23. SUPPORT24. 1 FIXED25. LOAD 126. JOINT LOAD27. 2 FY -106028. PERF ANALCIRCULAR CONCRETE COLUMN DESIGN PER ACI 318-99 -- PAGE NO. 2

*





29. START CONCRETE DESIGNCONCRETE DESIGN

30. CODE ACI 199931. REINF 1.0 ALL32. DESIGN COLUMN ALLCIRCULAR CONCRETE COLUMN DESIGN PER ACI 318-99 -- PAGE NO. 3

*


FY - 60000 FC - 4000 PSI, CIRC SIZE 20.00 INCHES DIAMETER SPIRAREA OF STEEL REQUIRED = 10.505 SQ. IN.

BAR CONFIGURATION REINF PCT. LOAD LOCATION PHI----------------------------------------------------------18 - NUMBER 7 3.438 1 END 0.750(EQUALLY SPACED)TIE BAR NUMBER 4 SPACING 2.00 IN********************END OF COLUMN DESIGN RESULTS********************33. END CONCRETE DESIGN34. FINISH


CIRCULAR CONCRETE COLUMN DESIGN PER ACI 318-99 -- PAGE NO. 4*




306 — STAAD.Pro


Notes

9Steel Design - AISC 360-10

Steel Design per AISC 360-10 - Example E-2 307

Steel Design per AISC 360-10 - Example G-6 313

Steel Design per AISC 360-10 - Example D-2 319

Steel Design per AISC 360-10 - Example F.2-2 326

Steel Design per AISC 360-10 - Example H.1B 332

Steel Design per AISC 360-10 - Example E.5 339

Steel Design per AISC 360-10 - Example F.1-3B 345

Steel Design per AISC 360-10 - Example E-2ObjectiveFrom the reference:

Verify that a built-up, ASTM A572 Grade 50 column with PL 1 in. × 8 in. flanges anda PL 4 in. × 15 in. web is sufficient to carry a dead load of 70 kips and live load of210 kips in axial compression. The column length is 15 ft and the ends are pinned inboth axes.

Refer to the reference for calculations.

ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page E-11.

Note: This reference is freely available for download from theAISC website:http://www.aisc.org/WorkArea/showcontent.aspx?id=29596

Comparison


φcPn (kips) [LRFD] 508 506.862 none

Pn/Ωc (kips) [ASD] 338 337.233 none

Table 9-1: Comparison of compressive strength results for a built-up column


http://www.aisc.org/WorkArea/showcontent.aspx?id=29596

STAAD Input


STAAD PLANESTART JOB INFORMATIONENGINEER DATE 31-Oct-12END JOB INFORMATIONINPUT WIDTH 79UNIT FEET KIPJOINT COORDINATES1 0 0 0; 2 0 15 0;MEMBER INCIDENCES1 1 2;START USER TABLE*TABLE 1*UNIT INCHES KIP*ISECTION*I1*17 0.25 17 8 1 8 1 0 0 0TABLE 2UNIT INCHES KIPWIDE FLANGEI19.75 17 0.25 8 1 1095.65 85.3529 5.41146 4.25 10.6667 8 1ENDUNIT inch KIPDEFINE MATERIAL STARTISOTROPIC STEELE 29732.7POISSON 0.3DENSITY 0.000283ALPHA 1.2e-005DAMP 0.03TYPE STEELSTRENGTH FY 50 FU 65 RY 1.5 RT 1.2END DEFINE MATERIALUNIT INCHES KIPCONSTANTSMATERIAL STEEL ALLMEMBER PROPERTY AMERICAN1 UPTABLE 2 IUNIT FEET KIPSUPPORTS1 PINNED2 FIXED BUT FY MX MY MZLOAD 1 LOADTYPE Dead TITLE LOAD CASE 1JOINT LOAD2 FY -70LOAD 2 LOADTYPE Live TITLE LOAD CASE 2JOINT LOAD2 FY -210UNIT INCHES KIPLOAD COMB 3 COMBINATION LOAD CASE 31 1.2 2 1.6LOAD COMB 4 COMBINATION LOAD CASE 41 1.0 2 1.0PERFORM ANALYSISLOAD LIST 3PARAMETER 1CODE AISC UNIFIED 2010FU 65 ALLFYLD 50 ALLMETHOD LRFD

308 — STAAD.Pro

9 Steel Design - AISC 360-10

Steel Design per AISC 360-10 - Example E-2

TRACK 2 ALLCHECK CODE ALLLOAD LIST 4PARAMETER 2CODE AISC UNIFIED 2010FU 65 ALLFYLD 50 ALLMETHOD ASDTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD PLANEINPUT FILE: AISC360-10_Comp1.STD

2. START JOB INFORMATION3. ENGINEER DATE 31-OCT-124. END JOB INFORMATION5. INPUT WIDTH 796. UNIT FEET KIP7. JOINT COORDINATES8. 1 0 0 0; 2 0 15 09. MEMBER INCIDENCES10. 1 1 211. START USER TABLE12. *TABLE 113. *UNIT INCHES KIP14. *ISECTION15. *I116. *17 0.25 17 8 1 8 1 0 0 017. TABLE 218. UNIT INCHES KIP19. WIDE FLANGE20. I21. 19.75 17 0.25 8 1 1095.65 85.3529 5.41146 4.25 10.6667 8 122. END23. UNIT INCH KIP24. DEFINE MATERIAL START25. ISOTROPIC STEEL26. E 29732.727. POISSON 0.328. DENSITY 0.00028329. ALPHA 1.2E-00530. DAMP 0.0331. TYPE STEEL32. STRENGTH FY 50 FU 65 RY 1.5 RT 1.233. END DEFINE MATERIAL34. UNIT INCHES KIP35. CONSTANTS36. MATERIAL STEEL ALL37. MEMBER PROPERTY AMERICAN



38. 1 UPTABLE 2 ISTAAD PLANE -- PAGE NO. 2

39. UNIT FEET KIP40. SUPPORTS41. 1 PINNED42. 2 FIXED BUT FY MX MY MZ43. LOAD 1 LOADTYPE DEAD TITLE LOAD CASE 144. JOINT LOAD45. 2 FY -7046. LOAD 2 LOADTYPE LIVE TITLE LOAD CASE 247. JOINT LOAD48. 2 FY -21049. UNIT INCHES KIP50. LOAD COMB 3 COMBINATION LOAD CASE 351. 1 1.2 2 1.652. LOAD COMB 4 COMBINATION LOAD CASE 453. 1 1.0 2 1.054. PERFORM ANALYSIS





55. LOAD LIST 356. PARAMETER 157. CODE AISC UNIFIED 201058. FU 65 ALL59. FYLD 50 ALL60. METHOD LRFD61. TRACK 2 ALL62. CHECK CODE ALL

STEEL DESIGN

STAAD PLANE -- PAGE NO. 3

STAAD.PRO CODE CHECKING - (AISC-360-10-LRFD) v1.3********************************************

ALL UNITS ARE - KIP INCH (UNLESS OTHERWISE Noted)

-------------------- START OF DESIGN OUTPUT OF MEMBER 1 --------------------

MEMBER NO: 1 CRITICAL RATIO: 0.819(PASS) LOAD: 3LOCATION (ft): 0.00 CONDITION: Sec. E1SECTION: ST I (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.819(PASS) LOAD CASE: 3 LOCATION (ft): 0.00 CONDITION: Sec. E1

DESIGN FORCES: Fx: 420.00(C) Fy: 0.00 Fz: 0.00Mx: 0.00E+00 My: 0.00E+00 Mz: 0.00E+00

SECTION PROPERTIES: AZZ: 10.667 AYY: 4.250 CW: 5462.585SZZ: 128.900 SYY: 21.338IZZ: 1095.650 IYY: 85.353

MATERIAL PROPERTIES: FYLD: 50.000 FU: 65.000ACTUAL MEMBER LENGTH(ft): 14.999

310 — STAAD.Pro



PARAMETERS: KX: 1.000 KY: 1.000 NSF: 1.000 SLF: 1.000 CSP: 1.000SLENDERNESS: ACTUAL SLENDERNESS RATIO: 86.586 LOAD: 3 LOC.(ft): 1.250

ALLOWABLE SLENDERNESS RATIO: 200.000SECTION CLASS: FLANGE:/ l : l p: l r:

WEB:COMPRESSION: Non-Slender 4.000 13.656 N/A

Slender 60.000 36.334 N/AFLEXURE: Compact 4.000 9.267 24.386

Compact 60.000 91.690 138.998TENSION: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):YIELDING: 0.000 888.750 0.000 Eq. D2-1 3 0.000RUPTURE: 0.000 962.812 0.000 Eq. Sec. D2 3 0.000




COMPRESSION: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 420.000 803.402 0.523 Sec. E1 3 0.000MINOR: 420.000 512.919 0.819 Sec. E1 3 0.000INTERMEDIATE: Ag: KL/r: Fcr: Fe: Pn:MAJOR: 18.566 24.167 45.198 502.451 892.669MINOR: 19.133 86.586 28.856 39.142 569.910FLEX TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):

420.000 683.874 0.614 Sec. E4 3 0.000INTERMEDIATE: Ag: Fcr: Pn:

18.765 38.474 759.860SHEAR: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.000 288.001 0.000 Eq. G2-1 3 0.000MINOR: 0.000 114.713 0.000 Eq. G2-1 3 0.000INTERMEDIATE: Aw: Cv: Kv: h/tw: Vn:MAJOR: 10.667 1.000 1.200 4.000 320.001MINOR: 4.250 1.000 5.000 60.000 127.458

UNIT: KIP FEET

YIELDING: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 5.33E+02 0.000 Sec. F1 3 0.000MINOR: 0.00E+00 1.21E+02 0.000 Sec. F1 3 0.000INTERMEDIATE: Mnr: My: Cb: Lp: Lr: Lb:MAJOR: 5.92E+02 0.00E+00 1.000 7.435 25.919 14.999MINOR: 1.34E+02 0.00E+00 1.000 7.435 25.919 14.999

UNIT: KIP FEET

LAT TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 4.53E+02 0.000 Sec. F1 3 0.000INTERMEDIATE: Mn: Me: Cb: Lp: Lr: Lb:MAJOR: 5.04E+02 0.00E+00 1.000 7.435 25.919 14.999

UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.819 Eq. H1-1a 3 0.000FLEXURE TENS: 0.000 Eq. H1-1b 3 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 4.53E+02 1.21E+02 0.00E+00 0.00E+00 512.919 420.000FLEXURE TENS: 4.53E+02 1.21E+02 0.00E+00 0.00E+00 888.750 0.000

-------------------- END OF DESIGN OUTPUT OF MEMBER 1 --------------------

63. LOAD LIST 4STAAD PLANE -- PAGE NO. 5



64. PARAMETER 265. CODE AISC UNIFIED 201066. FU 65 ALL67. FYLD 50 ALL68. METHOD ASD69. TRACK 2 ALL70. CHECK CODE ALL

STEEL DESIGN


STAAD.PRO CODE CHECKING - ( AISC-360-10-ASD) v1.3********************************************



MEMBER NO: 1 CRITICAL RATIO: 0.546(PASS) LOAD: 4LOCATION (ft): 0.00 CONDITION: Sec. E1SECTION: ST I (AISC SECTIONS)

UNIT: KIP FEET




MATERIAL PROPERTIES: FYLD: 50.000 FU: 65.000ACTUAL MEMBER LENGTH(ft): 14.999PARAMETERS: KX: 1.000 KY: 1.000 NSF: 1.000 SLF: 1.000 CSP: 1.000SLENDERNESS: ACTUAL SLENDERNESS RATIO: 86.586 LOAD: 4 LOC.(ft): 1.250










18.765 38.474 759.860

312 — STAAD.Pro



SHEAR: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.000 288.001 0.000 Eq. G2-1 4 0.000MINOR: 0.000 114.713 0.000 Eq. G2-1 4 0.000INTERMEDIATE: Aw: Cv: Kv: h/tw: Vn:MAJOR: 10.667 1.000 1.200 4.000 320.001MINOR: 4.250 1.000 5.000 60.000 127.458

UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET



71. FINISHSTAAD PLANE -- PAGE NO. 8



Steel Design per AISC 360-10 - Example G-6ObjectiveFrom the reference:

Verify the available shear strength and adequacy of a W21×48 ASTM A992 beamwith end shears of 20.0 kips from dead load and 60.0 kips from live load in theweak direction.




ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page G-13.

Note: This reference is freely available for download from theAISC website:http://www.aisc.org/WorkArea/showcontent.aspx?id=29596

Comparison


φvVn (kips) [LRFD] 189 189.011 none

Vn/Ωv (kips) [ASD] 126 125.756 none

Table 9-2: Comparison of results for beam shear

STAAD Input


STAAD SPACESTART JOB INFORMATIONENGINEER DATE 25-Oct-12END JOB INFORMATIONINPUT WIDTH 79UNIT FEET KIPJOINT COORDINATES1 0 0 0; 2 8 0 0;MEMBER INCIDENCES1 1 2;DEFINE MATERIAL STARTISOTROPIC STEELE 4.28151e+006POISSON 0.3DENSITY 0.489024ALPHA 1.2e-005DAMP 0.03TYPE STEELSTRENGTH FY 7200 FU 9360 RY 1.5 RT 1.2END DEFINE MATERIALCONSTANTSMATERIAL STEEL ALLMEMBER PROPERTY AMERICAN1 TABLE ST W21X48SUPPORTS2 PINNED1 FIXED BUT FZ MX MY MZLOAD 1 LOADTYPE Dead TITLE LOAD CASE 1JOINT LOAD1 FZ -20LOAD 2 LOADTYPE Live TITLE LOAD CASE 2JOINT LOAD1 FZ -60LOAD COMB 3 COMBINATION LOAD CASE 31 1.2 2 1.6LOAD COMB 4 COMBINATION LOAD CASE 41 1.0 2 1.0PERFORM ANALYSISLOAD LIST 3PARAMETER 1CODE AISC UNIFIED 2010

314 — STAAD.Pro


Steel Design per AISC 360-10 - Example G-6


METHOD LRFDTRACK 2 ALLCHECK CODE ALLLOAD LIST 4PARAMETER 2CODE AISC UNIFIED 2010METHOD ASDTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: AISC360-10_Shear1.STD

2. START JOB INFORMATION3. ENGINEER DATE 25-OCT-124. END JOB INFORMATION5. INPUT WIDTH 796. UNIT FEET KIP7. JOINT COORDINATES8. 1 0 0 0; 2 8 0 09. MEMBER INCIDENCES10. 1 1 211. DEFINE MATERIAL START12. ISOTROPIC STEEL13. E 4.28151E+00614. POISSON 0.315. DENSITY 0.48902416. ALPHA 1.2E-00517. DAMP 0.0318. TYPE STEEL19. STRENGTH FY 7200 FU 9360 RY 1.5 RT 1.220. END DEFINE MATERIAL21. CONSTANTS22. MATERIAL STEEL ALL23. MEMBER PROPERTY AMERICAN24. 1 TABLE ST W21X4825. SUPPORTS26. 2 PINNED27. 1 FIXED BUT FZ MX MY MZ28. LOAD 1 LOADTYPE DEAD TITLE LOAD CASE 129. JOINT LOAD30. 1 FZ -2031. LOAD 2 LOADTYPE LIVE TITLE LOAD CASE 232. JOINT LOAD33. 1 FZ -6034. LOAD COMB 3 COMBINATION LOAD CASE 335. 1 1.2 2 1.636. LOAD COMB 4 COMBINATION LOAD CASE 437. 1 1.0 2 1.038. PERFORM ANALYSIS



STAAD SPACE -- PAGE NO. 2





***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MXPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 9.5654508E+01 L-MATRIX DIAG= 2.8421709E-14 EQN NO 5***NOTE - VERY WEAK SPRING ADDED FOR STABILITY***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MYPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 4.6962079E+04 L-MATRIX DIAG= 3.6379788E-11 EQN NO 6***NOTE - VERY WEAK SPRING ADDED FOR STABILITY39. LOAD LIST 340. PARAMETER 141. CODE AISC UNIFIED 201042. METHOD LRFD43. TRACK 2 ALL44. CHECK CODE ALL

STEEL DESIGN





*MEMBER NO: 1 CRITICAL RATIO: 23.863(FAIL) LOAD: 3LOCATION (ft): 8.00 CONDITION: Sec. F1SECTION: ST W21X48 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 23.863(FAIL) LOAD CASE: 3 LOCATION (ft): 8.00 CONDITION: Sec. F1

DESIGN FORCES: Fx: 0.00(T) Fy: 0.00 Fz: -120.00Mx: 0.00E+00 My: -9.60E+02 Mz: 0.00E+00






Compact 56.471 108.057 163.810TENSION: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):YIELDING: 0.000 456.840 0.000 Eq. D2-1 3 0.000

316 — STAAD.Pro



RUPTURE: 0.000 613.350 0.000 Eq. Sec. D2 3 0.000STAAD SPACE -- PAGE NO. 4






UNIT: KIP FEET

YIELDING: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 2.89E+02 0.000 Sec. F1 3 0.000MINOR: -9.60E+02 4.02E+01 23.863 Sec. F1 3 8.000INTERMEDIATE: Mnr: My: Cb: Lp: Lr: Lb:MAJOR: 3.21E+02 0.00E+00 1.000 6.983 20.316 8.000MINOR: 4.47E+01 0.00E+00 1.000 6.983 20.316 8.000

UNIT: KIP FEET


UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 23.863 Eq. H1-1b 3 8.000FLEXURE TENS: 23.863 Eq. H1-1b 3 8.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 2.80E+02 4.02E+01 0.00E+00 -9.60E+02 363.019 0.000FLEXURE TENS: 2.80E+02 4.02E+01 0.00E+00 -9.60E+02 456.840 0.000


45. LOAD LIST 4STAAD SPACE -- PAGE NO. 5

46. PARAMETER 247. CODE AISC UNIFIED 201048. METHOD ASD49. TRACK 2 ALL50. CHECK CODE ALL

STEEL DESIGN







*MEMBER NO: 1 CRITICAL RATIO: 15.909(FAIL) LOAD: 4LOCATION (ft): 8.00 CONDITION: Sec. F1SECTION: ST W21X48 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 15.909(FAIL) LOAD CASE: 4 LOCATION (ft): 8.00 CONDITION: Sec. F1

DESIGN FORCES: Fx: 0.00(T) Fy: 0.00 Fz: -80.00Mx: 0.00E+00 My: -6.40E+02 Mz: 0.00E+00













UNIT: KIP FEET

YIELDING: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 2.89E+02 0.000 Sec. F1 4 0.000MINOR: -6.40E+02 4.02E+01 15.909 Sec. F1 4 8.000INTERMEDIATE: Mnr: My: Cb: Lp: Lr: Lb:

318 — STAAD.Pro



MAJOR: 3.21E+02 0.00E+00 1.000 6.983 20.316 8.000MINOR: 4.47E+01 0.00E+00 1.000 6.983 20.316 8.000

UNIT: KIP FEET


UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 15.909 Eq. H1-1b 4 8.000FLEXURE TENS: 15.909 Eq. H1-1b 4 8.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 2.80E+02 4.02E+01 0.00E+00 -6.40E+02 363.019 0.000FLEXURE TENS: 2.80E+02 4.02E+01 0.00E+00 -6.40E+02 456.840 0.000


51. FINISHSTAAD SPACE -- PAGE NO. 8



Steel Design per AISC 360-10 - Example D-2ObjectiveFrom the reference:

Verify, by both ASD and LRFD, the tensile strength of an L4×4×1/2, ASTM A36 […].The member carries a dead load of 20 kips and a live load of 60 kips in tension.Calculate at what length this tension member would cease to satisfy therecommended slenderness limit. Assume that connection limit states do not govern.


ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page D-5.

Note: This reference is freely available for download from the AISC website:http://www.aisc.org/WorkArea/showcontent.aspx?id=29596




Comparison


φtPn (kips) [LRFD] 122 121.5 none

Pn/Ωt (kips) [ASD] 80.8 80.838 none

Lambda for L = 19.4 ft 300 297.698 <1%

Table 9-3: Comparison of results for a angle in tension

STAAD Input


STAAD SPACESTART JOB INFORMATIONENGINEER DATE 25-Oct-12END JOB INFORMATIONINPUT WIDTH 79UNIT INCHES KIPJOINT COORDINATES1 0 0 0; 2 6 0 0;MEMBER INCIDENCES1 1 2;DEFINE MATERIAL STARTISOTROPIC STEELE 29732.7POISSON 0.3DENSITY 0.000283ALPHA 1.2e-005DAMP 0.03TYPE STEELSTRENGTH FY 36.7236 FU 59.1464 RY 1.5 RT 1.2END DEFINE MATERIALMEMBER PROPERTY AMERICAN1 TABLE ST L40408CONSTANTSMATERIAL STEEL ALLSUPPORTS1 FIXEDLOAD 1 LOADTYPE Dead TITLE LOAD CASE 1JOINT LOAD2 FX 20LOAD 2 LOADTYPE Live TITLE LOAD CASE 2JOINT LOAD2 FX 60LOAD COMB 3 COMBINATION LOAD CASE 31 1.2 2 1.6LOAD COMB 4 COMBINATION LOAD CASE 41 1.0 2 1.0PERFORM ANALYSISload list 3PARAMETER 1CODE AISC UNIFIED 2010method LRFDTRACK 2 ALLCHECK CODE ALLload list 4PARAMETER 2CODE AISC UNIFIED 2010

320 — STAAD.Pro


Steel Design per AISC 360-10 - Example D-2

method ASDTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: AISC360-10_Ten1.STD

2. START JOB INFORMATION3. ENGINEER DATE 25-OCT-124. END JOB INFORMATION5. INPUT WIDTH 796. UNIT INCHES KIP7. JOINT COORDINATES8. 1 0 0 0; 2 6 0 09. MEMBER INCIDENCES10. 1 1 211. DEFINE MATERIAL START12. ISOTROPIC STEEL13. E 29732.714. POISSON 0.315. DENSITY 0.00028316. ALPHA 1.2E-00517. DAMP 0.0318. TYPE STEEL19. STRENGTH FY 36.7236 FU 59.1464 RY 1.5 RT 1.220. END DEFINE MATERIAL21. MEMBER PROPERTY AMERICAN22. 1 TABLE ST L4040823. CONSTANTS24. MATERIAL STEEL ALL25. SUPPORTS26. 1 FIXED27. LOAD 1 LOADTYPE DEAD TITLE LOAD CASE 128. JOINT LOAD29. 2 FX 2030. LOAD 2 LOADTYPE LIVE TITLE LOAD CASE 231. JOINT LOAD32. 2 FX 6033. LOAD COMB 3 COMBINATION LOAD CASE 334. 1 1.2 2 1.635. LOAD COMB 4 COMBINATION LOAD CASE 436. 1 1.0 2 1.037. PERFORM ANALYSISSTAAD SPACE -- PAGE NO. 2







38. LOAD LIST 339. PARAMETER 140. CODE AISC UNIFIED 201041. METHOD LRFD42. TRACK 2 ALL43. CHECK CODE ALL

STEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.988(PASS) LOAD: 3LOCATION (ft): 0.00 CONDITION: Eq. Sec. D2SECTION: ST L40408 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.988(PASS) LOAD CASE: 3 LOCATION (ft): 0.00 CONDITION: Eq. Sec. D

2DESIGN FORCES: Fx: 120.00(T) Fy: 0.00 Fz: 0.00

Mx: 0.00E+00 My: 0.00E+00 Mz: 0.00E+00SECTION PROPERTIES: AZZ: 2.000 AYY: 2.000 CW: 0.366

SZZ: 4.700 SYY: 4.700IZZ: 5.561 IYY: 5.561




Non-Slender 8.000 12.932 N/AFLEXURE: Compact 8.000 15.519 26.152





COMPRESSION: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.000 121.405 0.000 Sec. E1 3 0.000MINOR: 0.000 121.133 0.000 Sec. E1 3 0.000INTERMEDIATE: Ag: KL/r: Fcr: Fe: Pn:MAJOR: 3.750 3.910 35.972 19193.153 134.894MINOR: 3.750 7.673 35.891 4984.770 134.593

322 — STAAD.Pro



FLEX TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):0.000 116.534 0.000 Sec. E4 3 0.000

INTERMEDIATE: Ag: Fcr: Pn:3.750 34.528 129.482

SHEAR: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.000 38.880 0.000 Eq. G2-1 3 0.000MINOR: 0.000 38.880 0.000 Eq. G2-1 3 0.000INTERMEDIATE: Aw: Cv: Kv: h/tw: Vn:MAJOR: 2.000 1.000 1.200 8.000 43.200MINOR: 2.000 1.000 1.200 8.000 43.200

UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.000 Eq. H1-1b 3 0.000FLEXURE TENS: 0.988 Eq. H1-1a 3 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 1.26E+01 5.55E+00 0.00E+00 0.00E+00 116.534 0.000FLEXURE TENS: 1.26E+01 5.55E+00 0.00E+00 0.00E+00 121.500 120.000




UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft): STRESS:SHEAR: 0.000 Eq. H3-8 3 0.000 19.440

GEOMETRIC AXIS DESIGN

UNIT: KIP FEET


UNIT: KIP FEET

LAT TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 6.40E+00 0.000 Sec. F1 3 0.000MINOR: 0.00E+00 6.40E+00 0.000 Sec. F1 3 0.000



INTERMEDIATE: Mn: Me: Cb: Lp: Lr: Lb:MAJOR: 7.11E+00 1.17E+04 1.000 0.000 0.000 0.500MINOR: 7.11E+00 1.17E+04 1.000 0.000 0.000 0.500

UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.000 Eq. H1-1b 3 0.000FLEXURE TENS: 0.988 Eq. H1-1a 3 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 6.40E+00 6.40E+00 0.00E+00 0.00E+00 116.534 0.000FLEXURE COMP: 6.40E+00 6.40E+00 0.00E+00 0.00E+00 116.534 0.000


44. LOAD LIST 445. PARAMETER 246. CODE AISC UNIFIED 201047. METHOD ASD48. TRACK 2 ALL49. CHECK CODE ALL

STEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.658(PASS) LOAD: 4LOCATION (ft): 0.00 CONDITION: Eq. Sec. D2SECTION: ST L40408 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.658(PASS) LOAD CASE: 4 LOCATION (ft): 0.00 CONDITION: Eq. Sec. D

2DESIGN FORCES: Fx: 80.00(T) Fy: 0.00 Fz: 0.00

Mx: 0.00E+00 My: 0.00E+00 Mz: 0.00E+00SECTION PROPERTIES: AZZ: 2.000 AYY: 2.000 CW: 0.366

SZZ: 4.700 SYY: 4.700IZZ: 5.561 IYY: 5.561








324 — STAAD.Pro







UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.000 Eq. H1-1b 4 0.000FLEXURE TENS: 0.658 Eq. H1-1a 4 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 1.26E+01 5.55E+00 0.00E+00 0.00E+00 116.534 0.000FLEXURE TENS: 1.26E+01 5.55E+00 0.00E+00 0.00E+00 121.500 80.000




UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft): STRESS:SHEAR: 0.000 Eq. H3-8 4 0.000 19.440

GEOMETRIC AXIS DESIGN

UNIT: KIP FEET

YIELDING: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 8.00E+00 0.000 Sec. F1 4 0.000



MINOR: 0.00E+00 8.00E+00 0.000 Sec. F1 4 0.000INTERMEDIATE: Mnr: My: Cb: Lp: Lr: Lb:MAJOR: 8.88E+00 5.92E+00 1.000 0.000 0.000 0.500MINOR: 8.88E+00 5.92E+00 1.000 0.000 0.000 0.500

UNIT: KIP FEET

LAT TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 0.00E+00 6.40E+00 0.000 Sec. F1 4 0.000MINOR: 0.00E+00 6.40E+00 0.000 Sec. F1 4 0.000INTERMEDIATE: Mn: Me: Cb: Lp: Lr: Lb:MAJOR: 7.11E+00 1.17E+04 1.000 0.000 0.000 0.500MINOR: 7.11E+00 1.17E+04 1.000 0.000 0.000 0.500

UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.000 Eq. H1-1b 4 0.000FLEXURE TENS: 0.658 Eq. H1-1a 4 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 6.40E+00 6.40E+00 0.00E+00 0.00E+00 116.534 0.000FLEXURE COMP: 6.40E+00 6.40E+00 0.00E+00 0.00E+00 116.534 0.000





Steel Design per AISC 360-10 - Example F.2-2ObjectiveCheck an C15x33.9 channel of ASTM A36 steel which serves as a roof edge beam. The simplespan is 25 ft. The nominal loads on the member are a dead load 0.23 kip/ft and a uniform liveload of 0.69 kip/ft. The beam is braced at fifth points and at ends.

Refer to Example F.2-2B in the reference for calculations.

ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page F-20.


326 — STAAD.Pro


Steel Design per AISC 360-10 - Example F.2-2


Comparison


φbMn (kips) [LRFD] 131 130 <1%

Mn/Ωb (kips) [ASD] 86.8 86.2 <1%

Delta maximum, limit 0.833 0.833 none

Delta maximum, actual 0.664 .660 <1%

Table 9-4: Comparison of results for a flexure member

STAAD Input


STAAD SPACESTART JOB INFORMATIONENGINEER DATE 02-Nov-12END JOB INFORMATIONINPUT WIDTH 79UNIT FEET KIPJOINT COORDINATES1 0 5 0; 2 25 5 0;MEMBER INCIDENCES1 1 2;DEFINE MATERIAL STARTISOTROPIC STEELE 4.176e+006POISSON 0.3DENSITY 0.489024ALPHA 6e-006DAMP 0.03TYPE STEELSTRENGTH FY 5184 FU 8352 RY 1.5 RT 1.2END DEFINE MATERIALMEMBER PROPERTY AMERICAN1 TABLE ST C15X33CONSTANTSMATERIAL STEEL ALLSUPPORTS1 PINNED2 FIXED BUT FX MZLOAD 1 LOADTYPE None TITLE LOAD CASE 1MEMBER LOAD1 UNI GY -0.23LOAD 2 LOADTYPE None TITLE LOAD CASE 2MEMBER LOAD1 UNI GY -0.69LOAD COMB 3 COMBINATION LOAD CASE 31 1.2 2 1.6LOAD COMB 4 COMBINATION LOAD CASE 41 1.0 2 1.0PERFORM ANALYSISLOAD LIST 3PARAMETER 1CODE AISC UNIFIED 2010METHOD LRFDunt 5TRACK 2 ALL



CHECK CODE ALLLOAD LIST 4PARAMETER 1CODE AISC UNIFIED 2010METHOD asdunt 5TRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: AISC360-10_Flex1.STD

2. START JOB INFORMATION3. ENGINEER DATE 02-NOV-124. END JOB INFORMATION5. INPUT WIDTH 796. UNIT FEET KIP7. JOINT COORDINATES8. 1 0 5 0; 2 25 5 09. MEMBER INCIDENCES10. 1 1 211. DEFINE MATERIAL START12. ISOTROPIC STEEL13. E 4.176E+00614. POISSON 0.315. DENSITY 0.48902416. ALPHA 6E-00617. DAMP 0.0318. TYPE STEEL19. STRENGTH FY 5184 FU 8352 RY 1.5 RT 1.220. END DEFINE MATERIAL21. MEMBER PROPERTY AMERICAN22. 1 TABLE ST C15X3323. CONSTANTS24. MATERIAL STEEL ALL25. SUPPORTS26. 1 PINNED27. 2 FIXED BUT FX MZ28. LOAD 1 LOADTYPE NONE TITLE LOAD CASE 129. MEMBER LOAD30. 1 UNI GY -0.2331. LOAD 2 LOADTYPE NONE TITLE LOAD CASE 232. MEMBER LOAD33. 1 UNI GY -0.6934. LOAD COMB 3 COMBINATION LOAD CASE 335. 1 1.2 2 1.636. LOAD COMB 4 COMBINATION LOAD CASE 437. 1 1.0 2 1.038. PERFORM ANALYSISSTAAD SPACE -- PAGE NO. 2

328 — STAAD.Pro







39. LOAD LIST 340. PARAMETER 141. CODE AISC UNIFIED 201042. METHOD LRFD43. UNT 544. TRACK 2 ALL45. CHECK CODE ALL

STEEL DESIGN





*MEMBER NO: 1 CRITICAL RATIO: 1.107(FAIL) LOAD: 3LOCATION (ft): 2.08 CONDITION: SLENDERNESSSECTION: ST C15X33 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 1.107(FAIL) LOAD CASE: 3 LOCATION (ft): 2.08 CONDITION: SLENDERNESS

DESIGN FORCES: Fx: 0.00(T) Fy: 14.38 Fz: 0.00Mx: 0.00E+00 My: 0.00E+00 Mz: -3.29E+01















UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.832 Eq. H1-1b 3 12.499FLEXURE TENS: 0.832 Eq. H1-1b 3 12.499INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 1.30E+02 1.39E+01 1.08E+02 0.00E+00 20.407 0.000FLEXURE TENS: 1.30E+02 1.39E+01 1.08E+02 0.00E+00 322.704 0.000



47. PARAMETER 148. CODE AISC UNIFIED 201049. METHOD ASD50. UNT 551. TRACK 2 ALL52. CHECK CODE ALL

STEEL DESIGN





330 — STAAD.Pro



*MEMBER NO: 1 CRITICAL RATIO: 1.107(FAIL) LOAD: 4LOCATION (ft): 2.08 CONDITION: SLENDERNESSSECTION: ST C15X33 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 1.107(FAIL) LOAD CASE: 4 LOCATION (ft): 2.08 CONDITION: SLENDERNESS














UNIT: KIP FEET


UNIT: KIP FEET

LAT TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: 7.19E+01 1.30E+02 0.555 Sec. F1 4 12.499



INTERMEDIATE: Mn: Me: Cb: Lp: Lr: Lb:MAJOR: 1.44E+02 0.00E+00 1.000 3.761 14.542 5.000

UNIT: KIP FEET






Steel Design per AISC 360-10 - Example H.1BObjectiveFrom the reference:

Using AISC Manual tables to determine the available compressive and flexuralstrengths, determine if an ASTM A992 W14×99 has sufficient available strength tosupport the axial forces and moments listed as follows, obtained from a second-order analysis that includes P-δ effects. The unbraced length is 14 ft and themember has pinned ends. KLx = KLy = Lb = 14.0 ft.


Note: A static analysis is used in STAAD.Pro as the reference supplies only the resultingforces from an assumed P-δ analysis.

ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page H-4.


332 — STAAD.Pro


Steel Design per AISC 360-10 - Example H.1B


Comparison


LRFD Interaction Ratio 0.928 0.929 none

φMnx (kip-ft) 642 642 none

φMny (kip-ft) 311 311 none

φcPn (kips) 1,130 1,127.791 none

ASD Interaction Ratio 0.931 0.932 none

Mnx/Ω (kip-ft) 428 427 none

Mny/Ω (kip-ft) 207 207 none

Compression (kips) 750 750.36 none

Table 9-5: Comparison of results for a member with interacting loads

STAAD Input


STAAD SPACESTART JOB INFORMATIONENGINEER DATE 19-Nov-12END JOB INFORMATIONINPUT WIDTH 79UNIT FEET KIPJOINT COORDINATES1 0 14 0; 2 0 0 0;MEMBER INCIDENCES1 1 2;DEFINE MATERIAL STARTISOTROPIC STEELE 4.176e+006POISSON 0.3DENSITY 0.489024ALPHA 6e-006DAMP 0.03TYPE STEELSTRENGTH FY 5184 FU 8352 RY 1.5 RT 1.2END DEFINE MATERIALMEMBER PROPERTY AMERICAN1 TABLE ST W14X99CONSTANTSMATERIAL STEEL ALLSUPPORTS2 PINNEDLOAD 1 LOADTYPE None TITLE LOAD CASE 1JOINT LOAD1 FY -400 MX 80 MZ 250LOAD 2 LOADTYPE None TITLE LOAD CASE 2JOINT LOAD1 FY -267 MX 53.3 MZ 167PERFORM ANALYSISLOAD LIST 1PARAMETER 1



CODE AISC UNIFIED 2010METHOD LRFDFYLD 7200 allFU 9360 allLz 14 allLy 14 allTRACK 2 ALLCHECK CODE ALLLOAD LIST 2PARAMETER 2CODE AISC UNIFIED 2010METHOD ASDFYLD 7200 allFU 9360 allLz 14 allLy 14 allTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: AISC360-10_Comb1.STD

2. START JOB INFORMATION3. ENGINEER DATE 19-NOV-124. END JOB INFORMATION5. INPUT WIDTH 796. UNIT FEET KIP7. JOINT COORDINATES8. 1 0 14 0; 2 0 0 09. MEMBER INCIDENCES10. 1 1 211. DEFINE MATERIAL START12. ISOTROPIC STEEL13. E 4.176E+00614. POISSON 0.315. DENSITY 0.48902416. ALPHA 6E-00617. DAMP 0.0318. TYPE STEEL19. STRENGTH FY 5184 FU 8352 RY 1.5 RT 1.220. END DEFINE MATERIAL21. MEMBER PROPERTY AMERICAN22. 1 TABLE ST W14X9923. CONSTANTS24. MATERIAL STEEL ALL25. SUPPORTS26. 2 PINNED27. LOAD 1 LOADTYPE NONE TITLE LOAD CASE 128. JOINT LOAD29. 1 FY -400 MX 80 MZ 250

334 — STAAD.Pro



30. LOAD 2 LOADTYPE NONE TITLE LOAD CASE 231. JOINT LOAD32. 1 FY -267 MX 53.3 MZ 16733. PERFORM ANALYSISSTAAD SPACE -- PAGE NO. 2





***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MXPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 2.7163798E+05 L-MATRIX DIAG= -5.8207661E-11 EQN NO 7***NOTE - VERY WEAK SPRING ADDED FOR STABILITY***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MYPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 3.5652471E+02 L-MATRIX DIAG= 0.0000000E+00 EQN NO 8***NOTE - VERY WEAK SPRING ADDED FOR STABILITY***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MZPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 6.7929322E+05 L-MATRIX DIAG= -3.4924597E-10 EQN NO 9***NOTE - VERY WEAK SPRING ADDED FOR STABILITY34. LOAD LIST 135. PARAMETER 136. CODE AISC UNIFIED 201037. METHOD LRFD38. FYLD 7200 ALL39. FU 9360 ALL40. LZ 14 ALL41. LY 14 ALL42. TRACK 2 ALL43. CHECK CODE ALL

STEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.929(PASS) LOAD: 1LOCATION (ft): 0.00 CONDITION: Eq. H1-1aSECTION: ST W14X99 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.929(PASS) LOAD CASE: 1 LOCATION (ft): 0.00 CONDITION: Eq. H1-1a



MATERIAL PROPERTIES: FYLD: 50.000 FU: 65.000



ACTUAL MEMBER LENGTH(ft): 13.999PARAMETERS: KX: 1.000 KY: 1.000 NSF: 1.000 SLF: 1.000 CSP: 1.000SLENDERNESS: ACTUAL SLENDERNESS RATIO: 45.200 LOAD: 1 LOC.(ft): 1.167



Non-Slender 25.979 35.884 N/AFLEXURE: Non-Compact 9.337 9.152 24.083








UNIT: KIP FEET

YIELDING: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: -2.50E+02 6.49E+02 0.385 Sec. F1 1 0.000MINOR: 8.00E+01 3.13E+02 0.255 Sec. F1 1 0.000INTERMEDIATE: Mnr: My: Cb: Lp: Lr: Lb:MAJOR: 7.21E+02 0.00E+00 1.000 13.128 45.335 13.999MINOR: 3.48E+02 0.00E+00 1.000 13.128 45.335 13.999

UNIT: KIP FEET

LAT TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: -2.50E+02 6.42E+02 0.389 Sec. F1 1 0.000INTERMEDIATE: Mn: Me: Cb: Lp: Lr: Lb:MAJOR: 7.14E+02 0.00E+00 1.000 13.128 45.335 13.999

UNIT: KIP FEET

FLANGE LOC BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: -2.50E+02 6.46E+02 0.387 Sec. F1 1 0.000MINOR: 8.00E+01 3.11E+02 0.257 Sec. F1 1 0.000INTERMEDIATE: Mn: Fcr: Cb: Lp: Lr: Lb:MAJOR: 7.18E+02 0.000 1.000 13.128 45.335 13.999MINOR: 3.46E+02 0.000 1.000 13.128 45.335 13.999



336 — STAAD.Pro




UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.929 Eq. H1-1a 1 0.000FLEXURE TENS: 0.646 Eq. H1-1b 1 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 6.42E+02 3.11E+02 -2.50E+02 8.00E+01 1127.791 400.000FLEXURE TENS: 6.42E+02 3.11E+02 -2.50E+02 8.00E+01 1309.500 0.000


44. LOAD LIST 245. PARAMETER 246. CODE AISC UNIFIED 201047. METHOD ASD48. FYLD 7200 ALL49. FU 9360 ALL50. LZ 14 ALL51. LY 14 ALL52. TRACK 2 ALL53. CHECK CODE ALL

STEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.620(PASS) LOAD: 2LOCATION (ft): 0.00 CONDITION: Eq. H1-1aSECTION: ST W14X99 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.620(PASS) LOAD CASE: 2 LOCATION (ft): 0.00 CONDITION: Eq. H1-1a






Non-Slender 25.979 35.884 N/AFLEXURE: Non-Compact 9.337 9.152 24.083

Compact 25.979 90.553 137.274TENSION: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):YIELDING: 0.000 1309.500 0.000 Eq. D2-1 2 0.000



RUPTURE: 0.000 1418.625 0.000 Eq. Sec. D2 2 0.000STAAD SPACE -- PAGE NO. 7






UNIT: KIP FEET

YIELDING: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: -1.67E+02 6.49E+02 0.257 Sec. F1 2 0.000MINOR: 5.33E+01 3.13E+02 0.170 Sec. F1 2 0.000INTERMEDIATE: Mnr: My: Cb: Lp: Lr: Lb:MAJOR: 7.21E+02 0.00E+00 1.000 13.128 45.335 13.999MINOR: 3.48E+02 0.00E+00 1.000 13.128 45.335 13.999

UNIT: KIP FEET

LAT TOR BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: -1.67E+02 6.42E+02 0.260 Sec. F1 2 0.000INTERMEDIATE: Mn: Me: Cb: Lp: Lr: Lb:MAJOR: 7.14E+02 0.00E+00 1.000 13.128 45.335 13.999

UNIT: KIP FEET

FLANGE LOC BUCK: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):MAJOR: -1.67E+02 6.46E+02 0.259 Sec. F1 2 0.000MINOR: 5.33E+01 3.11E+02 0.171 Sec. F1 2 0.000INTERMEDIATE: Mn: Fcr: Cb: Lp: Lr: Lb:MAJOR: 7.18E+02 0.000 1.000 13.128 45.335 13.999MINOR: 3.46E+02 0.000 1.000 13.128 45.335 13.999




UNIT: KIP FEET

INTERACTION: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):FLEXURE COMP: 0.620 Eq. H1-1a 2 0.000FLEXURE TENS: 0.431 Eq. H1-1b 2 0.000INTERMEDIATE: Mcx: Mcy: Mrx: Mry: Pc: Pr:FLEXURE COMP: 6.42E+02 3.11E+02 -1.67E+02 5.33E+01 1127.791 267.000

338 — STAAD.Pro



FLEXURE TENS: 6.42E+02 3.11E+02 -1.67E+02 5.33E+01 1309.500 0.000


54. FINISH*********** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:24:25 ****

STAAD SPACE -- PAGE NO. 9************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Steel Design per AISC 360-10 - Example E.5ObjectiveFrom the reference:

Verify the strength of a 2L 4×3-1/2×3/4 LLBB (3/8-in. separation) strut, ASTM A36,with a length of 8 ft and pinned ends carrying an axial dead load of 20 kips and liveload of 60 kips.


ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page E-26.


Comparison


φcPn (kips) [LRFD] 128 126.929 1%

Pn/Ωc (kips) [ASD] 85.0 84.450 <1%

Table 9-6: Comparison of results for a double-angle column

NotesSTAAD.Pro does not perform design per Section E6 of the specification. It is assumed thatsufficient intermediate connectors of an appropriate type are present. It is left to the engineer toverify the intermediate connector design.




STAAD Input


STAAD SPACESTART JOB INFORMATIONENGINEER DATE 5-Dec-12END JOB INFORMATIONINPUT WIDTH 79UNIT FEET KIPJOINT COORDINATES1 0 8 0; 2 0 0 0;MEMBER INCIDENCES1 1 2;MEMBER PROPERTY AMERICAN1 TABLE LD L40356 SP 0.0625UNIT INCHES KIPDEFINE MATERIAL STARTISOTROPIC MATERIAL1E 29000POISSON 0.3ISOTROPIC STEELE 29000POISSON 0.3DENSITY 0.000283ALPHA 6e-006DAMP 0.03TYPE STEELSTRENGTH FY 36 FU 58 RY 1.5 RT 1.2END DEFINE MATERIALUNIT FEET KIPCONSTANTSMATERIAL STEEL ALLSUPPORTS2 PINNEDLOAD 1 LOADTYPE None TITLE LOAD CASE 1JOINT LOAD1 FY -20LOAD 2 LOADTYPE None TITLE LOAD CASE 2JOINT LOAD1 FY -60LOAD COMB 3 Ultimate Loads1 1.2 2 1.6LOAD COMB 4 Service Loads1 1.0 2 1.0PERFORM ANALYSISUNIT IN KIPLOAD LIST 3PARAMETER 1CODE AISC UNIFIED 2010METHOD LRFDFYLD 36 ALLFU 58 ALLLX 56 ALLTRACK 2 ALLCHECK CODE ALLLOAD LIST 4PARAMETER 2CODE AISC UNIFIED 2010METHOD ASDFYLD 36 ALLFU 58 ALLLX 56 ALLTRACK 2 ALL

340 — STAAD.Pro


Steel Design per AISC 360-10 - Example E.5

CHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: AISC360-10_Comp2.STD

2. START JOB INFORMATION3. ENGINEER DATE 5-DEC-124. END JOB INFORMATION5. INPUT WIDTH 796. UNIT FEET KIP7. JOINT COORDINATES8. 1 0 8 0; 2 0 0 09. MEMBER INCIDENCES10. 1 1 211. MEMBER PROPERTY AMERICAN12. 1 TABLE LD L40356 SP 0.062513. UNIT INCHES KIP14. DEFINE MATERIAL START15. ISOTROPIC MATERIAL116. E 2900017. POISSON 0.318. ISOTROPIC STEEL19. E 2900020. POISSON 0.321. DENSITY 0.00028322. ALPHA 6E-00623. DAMP 0.0324. TYPE STEEL25. STRENGTH FY 36 FU 58 RY 1.5 RT 1.226. END DEFINE MATERIAL27. UNIT FEET KIP28. CONSTANTS29. MATERIAL STEEL ALL30. SUPPORTS31. 2 PINNED32. LOAD 1 LOADTYPE NONE TITLE LOAD CASE 133. JOINT LOAD34. 1 FY -2035. LOAD 2 LOADTYPE NONE TITLE LOAD CASE 236. JOINT LOAD37. 1 FY -6038. LOAD COMB 3 ULTIMATE LOADSSTAAD SPACE -- PAGE NO. 2

39. 1 1.2 2 1.640. LOAD COMB 4 SERVICE LOADS41. 1 1.0 2 1.042. PERFORM ANALYSIS







***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MXPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 1.8233613E+04 L-MATRIX DIAG= 1.8189894E-11 EQN NO 7***NOTE - VERY WEAK SPRING ADDED FOR STABILITY***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MYPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 2.9104566E+01 L-MATRIX DIAG= 7.1054274E-15 EQN NO 8***NOTE - VERY WEAK SPRING ADDED FOR STABILITY***WARNING - INSTABILITY AT JOINT 2 DIRECTION = MZPROBABLE CAUSE SINGULAR-ADDING WEAK SPRINGK-MATRIX DIAG= 9.9841646E+03 L-MATRIX DIAG= -1.0913936E-11 EQN NO 9***NOTE - VERY WEAK SPRING ADDED FOR STABILITY43. UNIT IN KIP44. LOAD LIST 345. PARAMETER 146. CODE AISC UNIFIED 201047. METHOD LRFD48. FYLD 36 ALL49. FU 58 ALL50. LX 56 ALL51. TRACK 2 ALL52. CHECK CODE ALL

STEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.945(PASS) LOAD: 3LOCATION (ft): 0.00 CONDITION: Sec. E1SECTION: LD L40356 (AISC SECTIONS)

UNIT: KIP FEET







Non-Slender 10.667 12.772 N/A

342 — STAAD.Pro



FLEXURE: Compact 9.333 15.326 25.828Compact 10.667 15.326 25.828

TENSION: FORCE: CAPACITY: RATIO: CRITERIA: LOAD CASE: LOCATION(ft):YIELDING: 0.000 173.146 0.000 Eq. D2-1 3 0.000RUPTURE: 0.000 232.464 0.000 Eq. Sec. D2 3 0.000







UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET




54. PARAMETER 255. CODE AISC UNIFIED 201056. METHOD ASD57. FYLD 36 ALL58. FU 58 ALL59. LX 56 ALL60. TRACK 2 ALL



61. CHECK CODE ALLSTEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.630(PASS) LOAD: 4LOCATION (ft): 0.00 CONDITION: Sec. E1SECTION: LD L40356 (AISC SECTIONS)

UNIT: KIP FEET















344 — STAAD.Pro



UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET






Steel Design per AISC 360-10 - Example F.1-3BObjectiveVerify the available flexural strength of a W18x50, ASTM A992 beam. The span is 35 ft and thebeam is braced at both ends and at the center. The dead load is 0.45 kip/ft and the live load is0.75 kip/ft.

ReferenceDesign Examples, Version 14.0, American Institute of Steel Construction, 2011, page F-14.





Comparison


φbMn (kips) [LRFD] 289 288 none

Mn/Ωb (kips) [ASD] 191 192 <1%


STAAD Input


STAAD SPACESTART JOB INFORMATIONENGINEER DATE 25-OCT-12JOB NAME AISC 360-10 ValidationJOB CLIENT BentleyJOB NO 7END JOB INFORMATION************************************************************* AISC Example F.1-3* W-SHAPE FLEXURAL MEMBERDESIGN IN STRONG-AXIS BENDING,* BRACED AT MIDSPAN* (1 analytical member with 2 unbraced segment)************************************************************INPUT WIDTH 79UNIT INCHES KIPJOINT COORDINATES1 0 0 0; 2 420 0 0;MEMBER INCIDENCES1 1 2;***************************************************DEFINE MATERIAL STARTISOTROPIC STEELE 29000POISSON 0.3DENSITY 0.000283ALPHA 1.2e-005DAMP 0.03TYPE STEELSTRENGTH FY 36 FU 59 RY 1.5 RT 1.2END DEFINE MATERIAL***************************************************MEMBER PROPERTY AMERICAN1 TABLE ST W18x50***************************************************CONSTANTSMATERIAL STEEL ALL***************************************************SUPPORTS1 FIXED BUT MZ2 FIXED BUT FX MZ***************************************************LOAD 1 LOADTYPE Dead TITLE LOAD CASE 1MEMBER LOAD1 UNI GY -0.0375**LOAD 2 LOADTYPE Live TITLE LOAD CASE 2MEMBER LOAD1 UNI GY -0.0625**

346 — STAAD.Pro


Steel Design per AISC 360-10 - Example F.1-3B

LOAD COMB 3 COMBINATION LOAD CASE 31 1.2 2 1.6**LOAD COMB 4 COMBINATION LOAD CASE 41 1.0 2 1.0***************************************************PERFORM ANALYSIS**LOAD LIST 3PARAMETER 1CODE AISC UNIFIED 2010METHOD LRFD** ASTM A992FYLD 50 ALLFU 65 ALL*CB 0 ALLCB 1.3 ALL*LX 210 ALLUNT 210 ALLUNB 210 ALL*MAIN 1 ALL*TRACK 2 ALLCHECK CODE ALL***************************************************LOAD LIST 4PARAMETER 2CODE AISC UNIFIED 2010METHOD ASD** ASTM A992FYLD 50 ALLFU 65 ALL*CB 0 ALLCB 1.3 ALL*LX 210 ALLUNT 210 ALLUNB 210 ALL*TRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: AISC360-10_Flex2.STD

2. START JOB INFORMATION



3. ENGINEER DATE 25-OCT-124. JOB NAME AISC 360-10 VALIDATION5. JOB CLIENT BENTLEY6. JOB NO 77. END JOB INFORMATION8. ************************************************************9. * AISC EXAMPLE F.1-310. * W-SHAPE FLEXURAL MEMBERDESIGN IN STRONG-AXIS BENDING,11. * BRACED AT MIDSPAN12. * (1 ANALYTICAL MEMBER WITH 2 UNBRACED SEGMENT)13. ************************************************************14. INPUT WIDTH 7915. UNIT INCHES KIP16. JOINT COORDINATES17. 1 0 0 0; 2 420 0 018. MEMBER INCIDENCES19. 1 1 220. ***************************************************21. DEFINE MATERIAL START22. ISOTROPIC STEEL23. E 2900024. POISSON 0.325. DENSITY 0.00028326. ALPHA 1.2E-00527. DAMP 0.0328. TYPE STEEL29. STRENGTH FY 36 FU 59 RY 1.5 RT 1.230. END DEFINE MATERIAL31. ***************************************************32. MEMBER PROPERTY AMERICAN33. 1 TABLE ST W18X5034. ***************************************************35. CONSTANTS36. MATERIAL STEEL ALL37. ***************************************************38. SUPPORTSSTAAD SPACE -- PAGE NO. 2

39. 1 FIXED BUT MZ40. 2 FIXED BUT FX MZ41. ***************************************************42. LOAD 1 LOADTYPE DEAD TITLE LOAD CASE 143. MEMBER LOAD44. 1 UNI GY -0.037545. **46. LOAD 2 LOADTYPE LIVE TITLE LOAD CASE 247. MEMBER LOAD48. 1 UNI GY -0.062549. **50. LOAD COMB 3 COMBINATION LOAD CASE 351. 1 1.2 2 1.652. **53. LOAD COMB 4 COMBINATION LOAD CASE 454. 1 1.0 2 1.055. ***************************************************56. PERFORM ANALYSIS





348 — STAAD.Pro



57. **58. LOAD LIST 359. PARAMETER 160. CODE AISC UNIFIED 201061. METHOD LRFD62. *63. * ASTM A99264. FYLD 50 ALL65. FU 65 ALL66. *CB 0 ALL67. CB 1.3 ALL68. *69. LX 210 ALL70. UNT 210 ALL71. UNB 210 ALL72. *73. MAIN 1 ALL74. *STAAD SPACE -- PAGE NO. 3

75. TRACK 2 ALL76. CHECK CODE ALL

STEEL DESIGN





MEMBER NO: 1 CRITICAL RATIO: 0.924(PASS) LOAD: 3LOCATION (ft):17.50 CONDITION: Sec. F1SECTION: ST W18X50 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.924(PASS) LOAD CASE: 3 LOCATION (ft):17.50 CONDITION: Sec. F1
















UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET



77. ***************************************************STAAD SPACE -- PAGE NO. 6

78. LOAD LIST 479. PARAMETER 280. CODE AISC UNIFIED 201081. METHOD ASD82. *83. * ASTM A99284. FYLD 50 ALL85. FU 65 ALL86. *CB 0 ALL87. CB 1.3 ALL88. *89. LX 210 ALL90. UNT 210 ALL91. UNB 210 ALL92. *93. TRACK 2 ALL

350 — STAAD.Pro








MEMBER NO: 1 CRITICAL RATIO: 0.637(PASS) LOAD: 4LOCATION (ft):17.50 CONDITION: Sec. F1SECTION: ST W18X50 (AISC SECTIONS)

UNIT: KIP FEET

STRENGTH CHECKS:CRITICAL RATIO: 0.637(PASS) LOAD CASE: 4 LOCATION (ft):17.50 CONDITION: Sec. F1
















UNIT: KIP FEET


UNIT: KIP FEET


UNIT: KIP FEET






352 — STAAD.Pro



10Steel Design per AISC ASD



















Steel Design per AISC ASD 1ObjectiveTo determine the axial compression capacity of a W14X132 column.

ReferenceAISC Allowable Stress Design, 9th Edition, Example 1, page 3-4.


ProblemFy =36 ksi

KyLy =16ft

KzLz = 31ft

ComparisonValue obtained by multiplying FA times AX from the STAAD output.


Allowable load (kips) 679 679 none

Table 10-1: Comparison of results for ASD column no. 1

STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 1. FA SHOULD BE 679/38.8 =* 17.5 KSI. RATIO SHOULD BE APPROXIMATELY 670/679 = 0.987UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 31 0MEMB INCI1 1 2MEMB PROP1 TA ST W14X132CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -670PERF ANALYUNIT INCHPARAMCODE AISCFYLD 36 ALLLY 192 ALLTRACK 2 ALLCHECK CODE ALLFINISH



354 — STAAD.Pro

10 Steel Design per AISC ASD

Steel Design per AISC ASD 1

1. STAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.INPUT FILE: AISC_ASD_COL1.STD

2. * PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 1. FA SHOULD BE 679/38.8 =3. * 17.5 KSI. RATIO SHOULD BE APPROXIMATELY 670/679 = 0.9874. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 31 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W14X13211. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -67020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 1. F21. UNIT INCH22. PARAM23. CODE AISC24. FYLD 36 ALL25. LY 192 ALL26. TRACK 2 ALL27. CHECK CODE ALL

STEEL DESIGNAISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 3

* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 1. F

STAAD.PRO CODE CHECKING - (AISC 9TH EDITION) v1.0********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 38.80 || * | ST W14X132 | | --Z AY = 8.50 ||DESIGN CODE * | | | AZ = 20.26 || AISC-1989 * =============================== ===|=== SY = 74.43 || * SZ = 208.73 || * |<---LENGTH (FT)= 31.00 --->| RY = 3.76 ||************* RZ = 6.28 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 51.09 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 17.50 || KL/R-Z= 59.24 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 17.27 |



| UNL = 372.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 21.60 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 21.60 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 27.00 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 27.00 || FYLD = 36.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 57.21 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 42.55 || (KL/R)max = 59.24 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 670.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.987 1 || 670.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 1. F

ALL UNITS ARE - KIP INCH (UNLESS OTHERWISE Noted)MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/

FX MY MZ LOCATION=======================================================================

|--------------------------------------------------------------------------|AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 5

* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 1. F28. FINISH



356 — STAAD.Pro





ProblemFy =36 ksi

KyLy =11ft

KzLz = 22ft

ComparisonValue obtained by multiplying FA times AX from the STAAD output = 18.50(31.20) = 577.2.


Allowable load (kips) 577 577.2 none


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 2.* RATIO SHOULD BE APPROXIMATELY 540/577 = 0.936UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 11 0MEMB INCI1 1 2MEMB PROP1 TA ST W12X106CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -540PERF ANALYUNIT INCHPARAMCODE AISCFYLD 36 ALLTRACK 2 ALLKZ 2 ALLCHECK CODE ALLFINISH






2. * PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 2.3. * RATIO SHOULD BE APPROXIMATELY 540/577 = 0.9364. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 11 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W12X10611. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -54020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 2.21. UNIT INCH22. PARAM23. CODE AISC24. FYLD 36 ALL25. TRACK 2 ALL26. KZ 2 ALL27. CHECK CODE ALL


* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 2.


|--------------------------------------------------------------------------|

358 — STAAD.Pro



| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 31.20 || * | ST W12X106 | | --Z AY = 7.02 ||DESIGN CODE * | | | AZ = 16.17 || AISC-1989 * =============================== ===|=== SY = 49.26 || * SZ = 144.76 || * |<---LENGTH (FT)= 11.00 --->| RY = 3.11 ||************* RZ = 5.47 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 42.50 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 18.50 || KL/R-Z= 48.28 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 17.31 || UNL = 132.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 23.76 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 23.76 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 27.00 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 27.00 || FYLD = 36.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 82.68 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 64.07 || (KL/R)max = 48.28 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 540.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.936 1 || 540.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 2.


FX MY MZ LOCATION=======================================================================


* PAGE 3-4 OF 9TH ED. AISC-ASD. EXAMPLE 2.28. FINISH







ReferenceAISC Allowable Stress Design, 9th Edition, tables on page 3-28.

ProblemFy =36 ksi

KyLy = KzLz = 16ft



Axial capacity (kips) 154 154.1 none


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-28 OF 9TH ED. AISC-ASD. W12X40, 16 FT LONG.* FA SHOULD BE APPROXIMATELY 154/11.80 = 13.05 KSIUNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 16 0MEMB INCI1 1 2MEMB PROP1 TA ST W12X40CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -150PERF ANALYUNIT INCHPARAMCODE AISC

360 — STAAD.Pro



FYLD 36 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * PAGE 3-28 OF 9TH ED. AISC-ASD. W12X40, 16 FT LONG.3. * FA SHOULD BE APPROXIMATELY 154/11.80 = 13.05 KSI4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 16 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W12X4011. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -15020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-28 OF 9TH ED. AISC-ASD. W12X40, 1621. UNIT INCH22. PARAM23. CODE AISC24. FYLD 36 ALL25. TRACK 2 ALL26. CHECK CODE ALL


* PAGE 3-28 OF 9TH ED. AISC-ASD. W12X40, 16

STAAD.PRO CODE CHECKING - (AISC 9TH EDITION) v1.0



********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 11.80 || * | ST W12X40 | | --Z AY = 3.27 ||DESIGN CODE * | | | AZ = 5.51 || AISC-1989 * =============================== ===|=== SY = 11.02 || * SZ = 51.93 || * |<---LENGTH (FT)= 16.00 --->| RY = 1.93 ||************* RZ = 5.13 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 99.32 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 13.06 || KL/R-Z= 37.46 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 12.71 || UNL = 192.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 21.58 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 21.60 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 27.00 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 27.00 || FYLD = 36.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 15.14 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 106.42 || (KL/R)max = 99.32 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 150.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.973 1 || 150.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-28 OF 9TH ED. AISC-ASD. W12X40, 16


FX MY MZ LOCATION=======================================================================


* PAGE 3-28 OF 9TH ED. AISC-ASD. W12X40, 1627. FINISH


362 — STAAD.Pro



**** DATE= DEC 13,2013 TIME= 12:25: 2 ***************************************************************** For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Steel Design per AISC ASD 4ObjectiveTo determine the axial compression capacity of an extra strong pipe of nominal diameter 12 in.


ProblemFy =36 ksi

KyLy = KzLz = 21ft



Axial capacity (kips) 337 338.1 <1%


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-37 OF 9TH ED. AISC-ASD. EXTRA STRONG PIPE WITH NOMINAL* DIA OF 12, 21 FT LONG. FA SHOULD BE APPROX. 337/19.20 = 17.55 KSIUNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 21 0MEMB INCI1 1 2MEMB PROP1 TA ST PIPX120CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -330PERF ANALY



UNIT INCHPARAMCODE AISCFYLD 36 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * PAGE 3-37 OF 9TH ED. AISC-ASD. EXTRA STRONG PIPE WITH NOMINAL3. * DIA OF 12, 21 FT LONG. FA SHOULD BE APPROX. 337/19.20 = 17.55 KSI4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 21 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST PIPX12011. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -33020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-37 OF 9TH ED. AISC-ASD. EXTRA STRON21. UNIT INCH22. PARAM23. CODE AISC24. FYLD 36 ALL25. TRACK 2 ALL26. CHECK CODE ALL


364 — STAAD.Pro



* PAGE 3-37 OF 9TH ED. AISC-ASD. EXTRA STRON


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ==| |== ------------ ||MEMBER 1 * | AISC SECTIONS | | | AX = 17.90 || * | ST PIPX120 | | | --Z AY = 8.98 ||DESIGN CODE * | | | | AZ = 8.98 || AISC-1989 * =============================== ==| |== SY = 53.18 || * SZ = 53.18 || * |<---LENGTH (FT)= 21.00 --->| RY = 4.35 ||************* RZ = 4.35 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 57.91 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 17.63 || KL/R-Z= 57.91 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 18.44 || UNL = 252.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 23.76 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 23.76 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 23.76 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 23.76 || FYLD = 36.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 44.53 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 44.53 || (KL/R)max = 57.91 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 330.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || FAIL AISC- H1-1 1.046 1 || 330.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-37 OF 9TH ED. AISC-ASD. EXTRA STRON


FX MY MZ LOCATION=======================================================================




* PAGE 3-37 OF 9TH ED. AISC-ASD. EXTRA STRON27. FINISH



Steel Design per AISC ASD 5ObjectiveTo determine the axial compression capacity of an square (8x8x5/8) structural tube.


ProblemFy =46 ksi

KyLy = KzLz = 25ft





STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-41 OF 9TH ED. AISC-ASD. SQUARE TUBE 8X8X5/8, 25 FT LONG.* FA SHOULD BE APPROX. 247/17.40 = 14.20 KSIUNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 25 0MEMB INCI1 1 2MEMB PROP1 TA ST TUB808010CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1

366 — STAAD.Pro



JOINT LOAD2 FY -240PERF ANALYUNIT INCHPARAMCODE AISCFYLD 46 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * PAGE 3-41 OF 9TH ED. AISC-ASD. SQUARE TUBE 8X8X5/8, 25 FT LONG.3. * FA SHOULD BE APPROX. 247/17.40 = 14.20 KSI4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 25 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST TUB80801011. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -24020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-41 OF 9TH ED. AISC-ASD. SQUARE TUBE21. UNIT INCH22. PARAM23. CODE AISC24. FYLD 46 ALL25. TRACK 2 ALL




AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 3* PAGE 3-41 OF 9TH ED. AISC-ASD. SQUARE TUBE


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| |=====| ------------ ||MEMBER 1 * | AISC SECTIONS | | | AX = 17.40 || * | ST TUB808010 | | |--Z AY = 7.48 ||DESIGN CODE * | | | | AZ = 7.48 || AISC-1989 * =============================== |=====| SY = 38.25 || * SZ = 38.25 || * |<---LENGTH (FT)= 25.00 --->| RY = 2.97 ||************* RZ = 2.97 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 101.17 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 14.15 || KL/R-Z= 101.17 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 13.79 || UNL = 300.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 27.60 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 27.60 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 27.60 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 27.60 || FYLD = 46.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 14.59 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 14.59 || (KL/R)max = 101.17 (WITH LOAD NO.) FV = 18.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 240.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.975 1 || 240.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-41 OF 9TH ED. AISC-ASD. SQUARE TUBE


FX MY MZ LOCATION=======================================================================

368 — STAAD.Pro




* PAGE 3-41 OF 9TH ED. AISC-ASD. SQUARE TUBE27. FINISH



Steel Design per AISC ASD 6ObjectiveTo determine the axial compression capacity of an rectangular (7x5x3/8) structural tube.


ProblemFy =46 ksi

KyLy = KzLz = 25ft





STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-49 OF 9TH ED. AISC-ASD. RECTANGULAR TUBE 7X5X3/8, 25 FT LONG.* FA SHOULD BE APPROX. 51/8.08 = 6.31 KSIUNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 25 0MEMB INCI1 1 2MEMB PROP1 TA ST TUB70506CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALL



SUPP1 FIXEDLOAD 1JOINT LOAD2 FY -50PERF ANALYUNIT INCHPARAMCODE AISCFYLD 46 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * PAGE 3-49 OF 9TH ED. AISC-ASD. RECTANGULAR TUBE 7X5X3/8, 25 FT LONG.3. * FA SHOULD BE APPROX. 51/8.08 = 6.31 KSI4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 25 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST TUB7050611. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -5020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-49 OF 9TH ED. AISC-ASD. RECTANGULAR21. UNIT INCH22. PARAM

370 — STAAD.Pro



23. CODE AISC24. FYLD 46 ALL25. TRACK 2 ALL26. CHECK CODE ALL


* PAGE 3-49 OF 9TH ED. AISC-ASD. RECTANGULAR


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| |=====| ------------ ||MEMBER 1 * | AISC SECTIONS | | | AX = 8.08 || * | ST TUB70506 | | |--Z AY = 3.97 ||DESIGN CODE * | | | | AZ = 2.98 || AISC-1989 * =============================== |=====| SY = 12.32 || * SZ = 14.91 || * |<---LENGTH (FT)= 25.00 --->| RY = 1.95 ||************* RZ = 2.54 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 153.66 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 6.32 || KL/R-Z= 118.03 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 6.19 || UNL = 300.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 27.60 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 27.60 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 27.60 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 27.60 || FYLD = 46.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 6.32 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 10.72 || (KL/R)max = 153.66 (WITH LOAD NO.) FV = 18.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 50.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.978 1 || 50.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-49 OF 9TH ED. AISC-ASD. RECTANGULAR




MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/FX MY MZ LOCATION

=======================================================================


* PAGE 3-49 OF 9TH ED. AISC-ASD. RECTANGULAR27. FINISH



Steel Design per AISC ASD 7ObjectiveTo determine the axial compression capacity of a long legs back-to-back double angle(L8x6x3/4) with 3/8in. spacing and fully restrained torsionally.


ProblemFy =36 ksi

KyLy = KzLz = 16ft



Axial capacity (kips) 300 310.9 3.6%


Note: The calculations in the AISC manual are approximate due to rounding off of KL/r values

STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-54 OF 9TH ED. AISC-ASD. DOUBLE ANGLES 8X6X3/4,* 40 FT LONG, 16FT UNBRACED LENGTH FOR BOTH AXES. FA SHOULD BE APPROX. 300/19.8UNIT KIP FEETJOINT COORD1 0 0 0 ; 2 0 40 0MEMB INCI

372 — STAAD.Pro



1 1 2UNIT INCHMEMB PROP1 TA LD L806012 SP 0.375CONSTE STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -300PERF ANALYUNIT INCHPARAMCODE AISCLY 192 ALLLZ 192 ALL* FULLY RESTRAINED TORSIONALLY. SET LX TO 0.1 INCHESLX 0.1 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * PAGE 3-54 OF 9TH ED. AISC-ASD. DOUBLE ANGLES 8X6X3/4,3. * 40 FT LONG, 16FT UNBRACED LENGTH FOR BOTH AXES. FA SHOULD BE APPROX. 300/19.84. UNIT KIP FEET5. JOINT COORD6. 1 0 0 0 ; 2 0 40 07. MEMB INCI8. 1 1 29. UNIT INCH10. MEMB PROP11. 1 TA LD L806012 SP 0.37512. CONST13. E STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -30020. PERF ANALY





NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 1



AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-54 OF 9TH ED. AISC-ASD. DOUBLE ANGL21. UNIT INCH22. PARAM23. CODE AISC24. LY 192 ALL25. LZ 192 ALL26. * FULLY RESTRAINED TORSIONALLY. SET LX TO 0.1 INCHES27. LX 0.1 ALL28. TRACK 2 ALL29. CHECK CODE ALL


* PAGE 3-54 OF 9TH ED. AISC-ASD. DOUBLE ANGL


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ==||== ------------ ||MEMBER 1 * | AISC SECTIONS | || AX = 19.88 || * | LD L806012 | || --Z AY = 5.62 ||DESIGN CODE * | | || AZ = 8.88 || AISC-1989 * |-----------------------------| || SY = 19.78 || * SZ = 23.33 || * |<---LENGTH (FT)= 40.00 --->| RY = 2.48 ||************* RZ = 2.53 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 77.37 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 15.64 || KL/R-Z= 76.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 15.09 || UNL = 480.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 21.60 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 21.60 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 21.60 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 21.60 || FYLD = 36.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 24.94 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 25.85 || (KL/R)max = 77.37 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 300.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *|

374 — STAAD.Pro



|* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.965 1 || 300.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-54 OF 9TH ED. AISC-ASD. DOUBLE ANGL


FX MY MZ LOCATION=======================================================================


* PAGE 3-54 OF 9TH ED. AISC-ASD. DOUBLE ANGL30. FINISH



Steel Design per AISC ASD 8ObjectiveTo determine the axial compression capacity of a WT10.5x25.


ProblemFy =36 ksi

KyLy = 5ft

KzLz = 30ft

ComparisonValue obtained by multiplying FA times AX from the STAAD output =10.09(7.35) = 74.16.






STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY.* PAGE 3-93 OF 9TH ED. AISC-ASD. TEE SHAPE WT10.5X25, KL Z-AXIS = 30 FT* KL Y-AXIS = 5 FT, FA SHOULD BE APPROX. 74/7.35 = 10.07 KSIUNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 10 0MEMB INCI1 1 2MEMB PROP1 TA T W21X50CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -70PERF ANALYUNIT INCHPARAMCODE AISCFYLD 36 ALLLZ 360 ALLLY 60 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * PAGE 3-93 OF 9TH ED. AISC-ASD. TEE SHAPE WT10.5X25, KL Z-AXIS = 30 FT3. * KL Y-AXIS = 5 FT, FA SHOULD BE APPROX. 74/7.35 = 10.07 KSI4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 10 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA T W21X5011. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED

376 — STAAD.Pro



17. LOAD 118. JOINT LOAD19. 2 FY -7020. PERF ANALY





AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 2* PAGE 3-93 OF 9TH ED. AISC-ASD. TEE SHAPE W21. UNIT INCH22. PARAM23. CODE AISC24. FYLD 36 ALL25. LZ 360 ALL26. LY 60 ALL27. TRACK 2 ALL28. CHECK CODE ALL


* PAGE 3-93 OF 9TH ED. AISC-ASD. TEE SHAPE W


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 7.35 || * | T W21X50 | | --Z AY = 2.84 ||DESIGN CODE * | | | AZ = 2.63 || AISC-1989 * |-----------------------------| | SY = 3.81 || * SZ = 10.65 || * |<---LENGTH (FT)= 10.00 --->| RY = 1.30 ||************* RZ = 3.29 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 STRESSES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 85.93 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FA = 10.09 || KL/R-Z= 109.32 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fa = 9.52 || UNL = 120.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCZ = 15.82 || CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTZ = 21.60 || CMY = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FCY = 27.00 || CMZ = 0.85 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 FTY = 27.00 || FYLD = 36.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 0.0 Fey = 20.22 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 12.50 || (KL/R)max = 109.32 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || |



| VALUE 70.0 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.944 1 || 70.00 C 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION CAPACITY -- PAGE NO. 4* PAGE 3-93 OF 9TH ED. AISC-ASD. TEE SHAPE W


FX MY MZ LOCATION=======================================================================


* PAGE 3-93 OF 9TH ED. AISC-ASD. TEE SHAPE W29. FINISH



Steel Design per AISC ASD 9ObjectiveTo determine the bending (transverse load carrying) capacity of a W10X45 shape.


ProblemFy =36 ksi

Lu = 6ft

378 — STAAD.Pro



ComparisonValue obtained by dividing the applied load (using the table capacity) by the reported STAADcritical ratio = 17/1.002 = 16.97.


Allowable uniform load (kips/ft) 17 16.97 <1%

Table 10-9: Comparison of results for ASD beam no. 9

STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-34 OF* 9TH ED. AISC-ASD EXAMPLE 5. GOVERNING CONDIION IS SHEAR.* RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 6 0 0MEMB INCI1 1 2MEMB PROP1 TA ST W10X45CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMB LOAD1 UNI GY -17.0PERF ANALYUNIT INCHPARAMCODE AISCMAIN 1.0 ALLBEAM 1.0 ALLFYLD 36 ALLTRACK 2 ALLSHE 1 ALLCHECK CODE ALLFINISH



1. STAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-34 OFINPUT FILE: AISC_ASD_FLEX9.STD

2. * 9TH ED. AISC-ASD EXAMPLE 5. GOVERNING CONDIION IS SHEAR.3. * RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT



5. JOINT COORD6. 1 0 0 0 ; 2 6 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W10X4511. CONST12. E STEEL ALL13. POISS STEEL ALL14. SUPP15. 1 PINNED16. 2 FIXED BUT MZ17. LOAD 118. MEMB LOAD19. 1 UNI GY -17.020. PERF ANALY





AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 2* 9TH ED. AISC-ASD EXAMPLE 5. GOVERNING COND21. UNIT INCH22. PARAM23. CODE AISC24. MAIN 1.0 ALL25. BEAM 1.0 ALL26. FYLD 36 ALL27. TRACK 2 ALL28. SHE 1 ALL29. CHECK CODE ALL

STEEL DESIGNAISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 3

* 9TH ED. AISC-ASD EXAMPLE 5. GOVERNING COND


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 13.30 || * | ST W10X45 | | --Z AY = 3.54 ||DESIGN CODE * | | | AZ = 9.94 || AISC-1989 * =============================== ===|=== SY = 13.32 || * SZ = 49.11 || * |<---LENGTH (FT)= 6.00 --->| RY = 2.00 ||************* RZ = 4.32 || || 76.5 (KIP-FEET) ||PARAMETER | L1 L1 L1 STRESSES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 35.93 | FA = 19.51 || KL/R-Z= 16.67 + L1 L1 fa = 0.00 || UNL = 72.00 | FCZ = 23.76 || CB = 1.00 + L1 L1 FTZ = 23.76 || CMY = 0.85 | FCY = 27.00 |

380 — STAAD.Pro



| CMZ = 0.85 + FTY = 27.00 || FYLD = 36.00 |L0 L0 fbz = 0.00 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -4.2 Fey = 115.66 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 537.14 || (KL/R)max = 35.93 (WITH LOAD NO.) FV = 14.40 || fv = 14.43 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 51.0 0.0 0.0 76.5 || LOCATION 0.0 0.0 0.0 0.0 3.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || FAIL SHEAR -Y 1.002 1 || 0.00 T 0.00 0.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 4* 9TH ED. AISC-ASD EXAMPLE 5. GOVERNING COND


FX MY MZ LOCATION=======================================================================

|--------------------------------------------------------------------------|AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 5

* 9TH ED. AISC-ASD EXAMPLE 5. GOVERNING COND30. FINISH



Steel Design per AISC ASD 10ObjectiveTo determine the bending (transverse load carrying) capacity of a W16x40 shape.



ReferenceAISC Allowable Stress Design, 9th Edition, Example1, page 2-5.

ProblemFy =36 ksi

Lu = 6ft

ComparisonValue obtained by multiplying the FCZ and SZ values from the STAAD output = 23.76(64.71) =1,537.5 in-kip = 128.1.


Bending capacity (ft-kips) 128 128.1 none


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-5 OF* 9TH ED. AISC-ASD CODE EXAMPLE 1. RATIO SHOULD BE A LITTLE UNDER 1.0.* CAPACITY SHOULD BE 128 KIP-FT. (SZ*FCZ SHOULD BE 128 KIP-FT).UNIT KIP FTJOINT COORD1 0 0 0 ; 2 10 0 0MEMB INCI1 1 2MEMB PROP1 TA ST W16X40CONSTE STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY 12.5PERF ANALYUNIT INCHPARAMCODE AISCMAIN 1.0 ALLFYLD 36 ALLUNL 72.0 ALLTRACK 2 ALLCHECK CODE ALLFINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:25:25 ** *

382 — STAAD.Pro



* USER ID: Bentley Systems, Inc. *****************************************************


2. * 9TH ED. AISC-ASD CODE EXAMPLE 1. RATIO SHOULD BE A LITTLE UNDER 1.0.3. * CAPACITY SHOULD BE 128 KIP-FT. (SZ*FCZ SHOULD BE 128 KIP-FT).4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 10 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W16X4011. CONST12. E STEEL ALL13. POISS STEEL ALL14. SUPP15. 1 FIXED16. LOAD 117. JOINT LOAD18. 2 FY 12.519. PERF ANALY





AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-5 -- PAGE NO. 2* 9TH ED. AISC-ASD CODE EXAMPLE 1. RATIO SHO20. UNIT INCH21. PARAM22. CODE AISC23. MAIN 1.0 ALL24. FYLD 36 ALL25. UNL 72.0 ALL26. TRACK 2 ALL27. CHECK CODE ALL


* 9TH ED. AISC-ASD CODE EXAMPLE 1. RATIO SHO


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 11.80 || * | ST W16X40 | | --Z AY = 4.39 ||DESIGN CODE * | | | AZ = 4.73 || AISC-1989 * =============================== ===|=== SY = 8.26 || * SZ = 64.71 || * |<---LENGTH (FT)= 10.00 --->| RY = 1.56 ||************* RZ = 6.63 || || 125.0 (KIP-FEET) ||PARAMETER |L1 STRESSES ||IN KIP INCH | L1 IN KIP INCH |



|--------------- + L1 L1 -------------|| KL/R-Y= 76.68 | L1 FA = 15.56 || KL/R-Z= 18.11 + L1 fa = 0.00 || UNL = 72.00 | L1 FCZ = 23.76 || CB = 1.00 + FTZ = 23.76 || CMY = 0.85 | L1 L1 FCY = 27.00 || CMZ = 0.85 + L1 FTY = 27.00 || FYLD = 36.00 | L0 fbz = 23.18 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -6.9 Fey = 25.40 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 455.24 || (KL/R)max = 76.68 (WITH LOAD NO.) FV = 14.40 || fv = 2.85 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 12.5 0.0 0.0 125.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-3 0.976 1 || 0.00 T 0.00 -125.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-5 -- PAGE NO. 4* 9TH ED. AISC-ASD CODE EXAMPLE 1. RATIO SHO


FX MY MZ LOCATION=======================================================================


* 9TH ED. AISC-ASD CODE EXAMPLE 1. RATIO SHO28. FINISH



384 — STAAD.Pro




ReferenceAISC Allowable Stress Design, 9th Edition, Example1, page 2-5.

ProblemFy =36 ksi

Luc = 9ft (Unbraced length of compression flange)

ComparisonValue obtained by multiplying the FCZ and SZ values from the STAAD output = 21.60(64.71) =1397.7 in-kip = 116.5 ft-kips


Bending capacity (ft-kips) 116.5 116.5 none


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-6 OF* 9TH ED. AISC-ASD CODE EXAMPLE 2.* CAPACITY SHOULD BE 116.5 KIP-FT. (SZ*FCZ SHOULD BE 116.5 KIP-FT).UNIT KIP FTJOINT COORD1 0 0 0 ; 2 9 0 0MEMB INCI1 1 2MEMB PROP1 TA ST W16X40CONSTE STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY 12.94PERF ANALYUNIT INCHPARAMCODE AISCMAIN 1.0 ALLFYLD 36 ALLTRACK 2 ALLCHECK CODE ALLFINISH






2. * 9TH ED. AISC-ASD CODE EXAMPLE 2.3. * CAPACITY SHOULD BE 116.5 KIP-FT. (SZ*FCZ SHOULD BE 116.5 KIP-FT).4. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 9 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W16X4011. CONST12. E STEEL ALL13. POISS STEEL ALL14. SUPP15. 1 FIXED16. LOAD 117. JOINT LOAD18. 2 FY 12.9419. PERF ANALY





AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-6 -- PAGE NO. 2* 9TH ED. AISC-ASD CODE EXAMPLE 2.20. UNIT INCH21. PARAM22. CODE AISC23. MAIN 1.0 ALL24. FYLD 36 ALL25. TRACK 2 ALL26. CHECK CODE ALL


* 9TH ED. AISC-ASD CODE EXAMPLE 2.


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 11.80 || * | ST W16X40 | | --Z AY = 4.39 ||DESIGN CODE * | | | AZ = 4.73 |

386 — STAAD.Pro



| AISC-1989 * =============================== ===|=== SY = 8.26 || * SZ = 64.71 || * |<---LENGTH (FT)= 9.00 --->| RY = 1.56 ||************* RZ = 6.63 || || 116.5 (KIP-FEET) ||PARAMETER |L1 STRESSES ||IN KIP INCH | L1 IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 69.01 | L1 FA = 16.30 || KL/R-Z= 16.30 + fa = 0.00 || UNL = 108.00 | L1 L1 FCZ = 21.60 || CB = 1.00 + FTZ = 21.60 || CMY = 0.85 | L1 FCY = 27.00 || CMZ = 0.85 + L1 L1 FTY = 27.00 || FYLD = 36.00 | L0 fbz = 21.60 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -6.5 Fey = 31.36 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 562.02 || (KL/R)max = 69.01 (WITH LOAD NO.) FV = 14.40 || fv = 2.95 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 12.9 0.0 0.0 116.5 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-3 1.000 1 || 0.00 T 0.00 -116.46 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-6 -- PAGE NO. 4* 9TH ED. AISC-ASD CODE EXAMPLE 2.


FX MY MZ LOCATION=======================================================================


* 9TH ED. AISC-ASD CODE EXAMPLE 2.27. FINISH






Steel Design per AISC ASD 12ObjectiveTo determine the bending (transverse load carrying) capacity of an MC18x58 channel. The beamis laterally supported along its entire length.

ReferenceAISC Allowable Stress Design, 9th Edition, tables, page 2-80.

ProblemFy =36 ksi

L = 25ft

ComparisonValue obtained by dividing the applied load (using the table capacity) by the reported STAADcritical ratio =43/0.904 = 47.57.


Total allowable uniform load (kips/ft) 43 47.57 10.6%


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-80 OF* 9TH ED. AISC-ASD. LATERALLY SUPPORTED MC18X58 CHANNEL, 25FT LONG* LOAD CAPACITY = 43 KIPS. RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 25 0 0MEMB INCI1 1 2MEMB PROP1 TA ST MC18X58CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMB LOAD* LOAD INTENSITY = 43/25 = 1.72 KIP/FT1 UNI GY -1.72PERF ANALYUNIT INCHPARAMCODE AISCMAIN 1.0 ALLBEAM 1.0 ALLFYLD 36 ALL

388 — STAAD.Pro



UNL 1.0 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. * 9TH ED. AISC-ASD. LATERALLY SUPPORTED MC18X58 CHANNEL, 25FT LONG3. * LOAD CAPACITY = 43 KIPS. RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 25 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST MC18X5811. CONST12. E STEEL ALL13. POISS STEEL ALL14. SUPP15. 1 PINNED16. 2 FIXED BUT MZ17. LOAD 118. MEMB LOAD19. * LOAD INTENSITY = 43/25 = 1.72 KIP/FT20. 1 UNI GY -1.7221. PERF ANALY




TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 4AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-8 -- PAGE NO. 2

* 9TH ED. AISC-ASD. LATERALLY SUPPORTED MC18

22. UNIT INCH23. PARAM24. CODE AISC25. MAIN 1.0 ALL26. BEAM 1.0 ALL27. FYLD 36 ALL28. UNL 1.0 ALL29. TRACK 2 ALL30. CHECK CODE ALL

STEEL DESIGN



AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-8 -- PAGE NO. 3* 9TH ED. AISC-ASD. LATERALLY SUPPORTED MC18


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| |=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 17.10 || * | ST MC18X58 | | --Z AY = 9.99 ||DESIGN CODE * | | | AZ = 3.24 || AISC-1989 * =============================== |=== SY = 5.37 || * SZ = 75.11 || * |<---LENGTH (FT)= 25.00 --->| RY = 1.02 ||************* RZ = 6.29 || || 134.4 (KIP-FEET) ||PARAMETER | L1 L1 L1 STRESSES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 294.04 | FA = 1.73 || KL/R-Z= 47.71 + L1 L1 fa = 0.00 || UNL = 1.00 | FCZ = 21.60 || CB = 1.00 + L1 L1 FTZ = 21.60 || CMY = 0.85 | FCY = 21.60 || CMZ = 0.85 + FTY = 21.60 || FYLD = 36.00 |L0 L0 fbz = 21.47 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -7.5 Fey = 1.73 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 65.59 || (KL/R)max = 294.04 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 21.5 0.0 0.0 134.4 || LOCATION 0.0 0.0 0.0 0.0 12.5 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-3 0.994 1 || 0.00 T 0.00 -134.38 12.50 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-8 -- PAGE NO. 4* 9TH ED. AISC-ASD. LATERALLY SUPPORTED MC18


FX MY MZ LOCATION=======================================================================

|--------------------------------------------------------------------------|

390 — STAAD.Pro



AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-8 -- PAGE NO. 5* 9TH ED. AISC-ASD. LATERALLY SUPPORTED MC1831. FINISH




ReferenceAISC Allowable Stress Design, 9th Edition, tables, page 2-80.

ProblemFy =36 ksi

L =20ft

Luc = 5ft (Unbraced length of compression flange)

ComparisonValue obtained by dividing the applied load (using the table capacity) by the reported STAADcritical ratio =58/1.008 = 57.54.


Total allowable uniform load (kips) 58 57.54 <1%


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-34 OF* 9TH ED. AISC-ASD EXAMPLE 4.* RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 20 0 0MEMB INCI1 1 2MEMB PROP1 TA ST W16X45CONSTE STEEL ALLPOISS STEEL ALL



SUPP1 PINNED2 FIXED BUT MZLOAD 1MEMB LOAD1 UNI GY -2.9PERF ANALYUNIT INCHPARAMCODE AISCMAIN 1.0 ALLBEAM 1.0 ALLFYLD 36 ALLTRACK 2 ALLUNL 60.0 ALLCHECK CODE ALLFINISH




2. * 9TH ED. AISC-ASD EXAMPLE 4.3. * RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 20 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W16X4511. CONST12. E STEEL ALL13. POISS STEEL ALL14. SUPP15. 1 PINNED16. 2 FIXED BUT MZ17. LOAD 118. MEMB LOAD19. 1 UNI GY -2.920. PERF ANALY





392 — STAAD.Pro



AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 2* 9TH ED. AISC-ASD EXAMPLE 4.21. UNIT INCH22. PARAM23. CODE AISC24. MAIN 1.0 ALL25. BEAM 1.0 ALL26. FYLD 36 ALL27. TRACK 2 ALL28. UNL 60.0 ALL29. CHECK CODE ALL


* 9TH ED. AISC-ASD EXAMPLE 4.


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 13.30 || * | ST W16X45 | | --Z AY = 4.98 ||DESIGN CODE * | | | AZ = 5.31 || AISC-1989 * =============================== ===|=== SY = 9.32 || * SZ = 72.66 || * |<---LENGTH (FT)= 20.00 --->| RY = 1.57 ||************* RZ = 6.64 || || 145.0 (KIP-FEET) ||PARAMETER | L1 L1 L1 STRESSES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 152.83 | FA = 6.39 || KL/R-Z= 36.16 + L1 L1 fa = 0.00 || UNL = 60.00 | FCZ = 23.76 || CB = 1.00 + L1 L1 FTZ = 23.76 || CMY = 0.85 | FCY = 27.00 || CMZ = 0.85 + FTY = 27.00 || FYLD = 36.00 |L0 L0 fbz = 23.95 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -8.1 Fey = 6.39 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 114.23 || (KL/R)max = 152.83 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 29.0 0.0 0.0 145.0 || LOCATION 0.0 0.0 0.0 0.0 10.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || FAIL AISC- H1-3 1.008 1 || 0.00 T 0.00 -145.00 10.00 |



|* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 4* 9TH ED. AISC-ASD EXAMPLE 4.


FX MY MZ LOCATION=======================================================================


* 9TH ED. AISC-ASD EXAMPLE 4.30. FINISH



Steel Design per AISC ASD 14ObjectiveTo find the optimum W shape that spans 30 ft, and is braced at 7.5 ft intervals.

ReferenceAISC Allowable Stress Design, 9th Edition,Example 6, page 2-35.

ProblemThree concentrated loads of 20 kips each at quarter span points. Desired beam depth of 18 in.

Fy =36 ksi

Comparison


Selected section W18x86 W18x86 none


STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-35 OF* 9TH ED. AISC-ASD EXAMPLE 6.* RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 30 0 0

394 — STAAD.Pro



MEMB INCI1 1 2MEMB PROP1 TA ST W18X35CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMB LOAD1 CON GY -20.0 7.51 CON GY -20.0 15.01 CON GY -20.0 22.5PERF ANALYUNIT INCHPARAMCODE AISCDMAX 19 ALLMAIN 1 ALLBEAM 1 ALLFYLD 36 ALLUNL 90 ALLTRACK 2 ALLSELECT OPTIMIZEDFINISH




2. * 9TH ED. AISC-ASD EXAMPLE 6.3. * RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 30 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W18X3511. CONST12. E STEEL ALL13. POISS STEEL ALL14. SUPP15. 1 PINNED16. 2 FIXED BUT MZ17. LOAD 118. MEMB LOAD19. 1 CON GY -20.0 7.520. 1 CON GY -20.0 15.021. 1 CON GY -20.0 22.5



22. PERF ANALY




AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 2* 9TH ED. AISC-ASD EXAMPLE 6.TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 4

23. UNIT INCH24. PARAM25. CODE AISC26. DMAX 19 ALL27. MAIN 1 ALL28. BEAM 1 ALL29. FYLD 36 ALL30. UNL 90 ALL31. TRACK 2 ALL32. SELECT OPTIMIZED

STEEL DESIGNSTEEL DESIGNSTEEL DESIGN


STAAD.PRO MEMBER SELECTION - (AISC 9TH EDITION) v1.0***********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 25.30 || * | ST W18X86 | | --Z AY = 7.96 ||DESIGN CODE * | | | AZ = 11.40 || AISC-1989 * =============================== ===|=== SY = 31.56 || * SZ = 166.39 || * |<---LENGTH (FT)= 30.00 --->| RY = 2.63 ||************* RZ = 7.78 || || 300.0 (KIP-FEET) ||PARAMETER | L1 STRESSES ||IN KIP INCH | L1 L1 IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 136.88 | FA = 7.97 || KL/R-Z= 46.29 + fa = 0.00 || UNL = 90.00 | L1 L1 FCZ = 23.76 || CB = 1.00 + FTZ = 23.76 || CMY = 0.85 | L1 L1 FCY = 27.00 || CMZ = 0.85 + FTY = 27.00 || FYLD = 36.00 |L0 L0 fbz = 21.64 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -16.7 Fey = 7.97 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 69.68 || (KL/R)max = 136.88 (WITH LOAD NO.) FV = 14.40 || fv = 1.26 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z |

396 — STAAD.Pro



| || VALUE 0.0 30.0 0.0 0.0 300.0 || LOCATION 0.0 0.0 0.0 0.0 15.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-3 0.911 1 || 0.00 T 0.00 -300.00 15.00 ||* *||**************************************************************************|| |



FX MY MZ LOCATION=======================================================================


* 9TH ED. AISC-ASD EXAMPLE 6.33. FINISH******************************************************************************WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.

IN THE POST PROCESSOR, MEMBER QUERIES WILL USE THE LASTANALYSIS FORCES WITH THE UPDATED MEMBER SIZES.TO CORRECT THIS INCONSISTENCY, PLEASE DO ONE MORE ANALYSIS.FROM THE UPPER MENU, PRESS RESULTS, UPDATE PROPERTIES, THENFILE SAVE; THEN ANALYZE AGAIN WITHOUT THE GROUP OR SELECTCOMMANDS.

*************************************************************************************** END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:25:42 ****



Steel Design per AISC ASD 15ObjectiveTo find a 14in deep section to carry a load of 1 kip/ft over a span of 25 ft.




ProblemThe beam is laterally supported throughout its length.

Fy =36 ksi

Comparison




STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-35 OF* 9TH ED. AISC-ASD EXAMPLE 7. LATERALLY SUPPORTED BEAM.* RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 25 0 0MEMB INCI1 1 2MEMB PROP* TRIAL SECTION SIZE:1 TA ST W14X22CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMB LOAD1 UNI GY -1.0PERF ANALYUNIT INCHPARAMCODE AISCDMAX 15 ALLMAIN 1.0 ALLBEAM 1.0 ALLFYLD 36 ALLUNL 1.0 ALLTRACK 2 ALL*CHECK CODE ALLSELECT OPTIMIZEDFINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 *

398 — STAAD.Pro



* Time= 12:25:42 ** ** USER ID: Bentley Systems, Inc. *****************************************************


2. * 9TH ED. AISC-ASD EXAMPLE 7. LATERALLY SUPPORTED BEAM.3. * RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 25 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. * TRIAL SECTION SIZE:11. 1 TA ST W14X2212. CONST13. E STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 PINNED17. 2 FIXED BUT MZ18. LOAD 119. MEMB LOAD20. 1 UNI GY -1.021. PERF ANALY




TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 4AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 2

* 9TH ED. AISC-ASD EXAMPLE 7. LATERALLY SUPP

22. UNIT INCH23. PARAM24. CODE AISC25. DMAX 15 ALL26. MAIN 1.0 ALL27. BEAM 1.0 ALL28. FYLD 36 ALL29. UNL 1.0 ALL30. TRACK 2 ALL31. *CHECK CODE ALL32. SELECT OPTIMIZED


AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-3 -- PAGE NO. 3* 9TH ED. AISC-ASD EXAMPLE 7. LATERALLY SUPP


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 8.85 || * | ST W14X30 | | --Z AY = 3.39 |



|DESIGN CODE * | | | AZ = 3.47 || AISC-1989 * =============================== ===|=== SY = 5.82 || * SZ = 42.05 || * |<---LENGTH (FT)= 25.00 --->| RY = 1.49 ||************* RZ = 5.73 || || 78.1 (KIP-FEET) ||PARAMETER | L1 L1 L1 STRESSES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 201.59 | FA = 3.67 || KL/R-Z= 52.32 + L1 L1 fa = 0.00 || UNL = 1.00 | FCZ = 23.76 || CB = 1.00 + L1 L1 FTZ = 23.76 || CMY = 0.85 | FCY = 27.00 || CMZ = 0.85 + FTY = 27.00 || FYLD = 36.00 |L0 L0 fbz = 22.29 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -4.3 Fey = 3.67 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 54.56 || (KL/R)max = 201.59 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 12.5 0.0 0.0 78.1 || LOCATION 0.0 0.0 0.0 0.0 12.5 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-3 0.938 1 || 0.00 T 0.00 -78.12 12.50 ||* *||**************************************************************************|| |



FX MY MZ LOCATION=======================================================================


* 9TH ED. AISC-ASD EXAMPLE 7. LATERALLY SUPP33. FINISH******************************************************************************WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.


****************************************************************************

400 — STAAD.Pro






Steel Design per AISC ASD 16ObjectiveTo find an optimum section to carry a moment of 220 ft-kips plus its selfweight and spanning 35ft between supports.


ProblemFy =36 ksi

Cb = 1.0

Maximum unbraced length of compression flange is 15 ft.

Comparison




STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-147* OF 9TH ED. AISC-ASD. EXAMPLE 10.* RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 35 0 0MEMB INCI1 1 2MEMB PROP*TRIAL SECTION1 TA ST W18X35CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP



1 PINNED2 FIXED BUT MZLOAD 1SELF Y -1.0MEMB LOAD1 CON GY -22 101 CON GY -22 25PERF ANALYUNIT INCHPARAMCODE AISCMAIN 1.0 ALLBEAM 1.0 ALLFYLD 36 ALLUNL 180 ALLTRACK 2 ALL*CHECK CODE ALLSELECT OPTIMIZEDFINISH



1. STAAD SPACE AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-147INPUT FILE: AISC_ASD_FLEX16.STD

2. * OF 9TH ED. AISC-ASD. EXAMPLE 10.3. * RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 35 0 07. MEMB INCI8. 1 1 29. MEMB PROP10. *TRIAL SECTION11. 1 TA ST W18X3512. CONST13. E STEEL ALL14. DENS STEEL ALL15. POISS STEEL ALL16. SUPP17. 1 PINNED18. 2 FIXED BUT MZ19. LOAD 120. SELF Y -1.021. MEMB LOAD22. 1 CON GY -22 1023. 1 CON GY -22 2524. PERF ANALY



402 — STAAD.Pro



NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-1 -- PAGE NO. 2

* OF 9TH ED. AISC-ASD. EXAMPLE 10.



25. UNIT INCH26. PARAM27. CODE AISC28. MAIN 1.0 ALL29. BEAM 1.0 ALL30. FYLD 36 ALL31. UNL 180 ALL32. TRACK 2 ALL33. *CHECK CODE ALL34. SELECT OPTIMIZED


AISC VERIFICATION PROBLEM FOR BENDING CAPACITY. PAGE 2-1 -- PAGE NO. 3* OF 9TH ED. AISC-ASD. EXAMPLE 10.


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 20.10 || * | ST W24X68 | | --Z AY = 8.72 ||DESIGN CODE * | | | AZ = 7.02 || AISC-1989 * =============================== ===|=== SY = 15.71 || * SZ = 154.24 || * |<---LENGTH (FT)= 35.00 --->| RY = 1.87 ||************* RZ = 9.54 || || 232.6 (KIP-FEET) ||PARAMETER | L1 L1 L1 STRESSES ||IN KIP INCH | L1 L1 IN KIP INCH ||--------------- + -------------|| KL/R-Y= 224.42 | FA = 2.97 || KL/R-Z= 44.02 + L1 L1 fa = 0.00 || UNL = 180.00 | FCZ = 18.59 || CB = 1.00 + L1 L1 FTZ = 21.60 || CMY = 0.85 | FCY = 27.00 || CMZ = 0.85 + FTY = 27.00 || FYLD = 36.00 |L0 L0 fbz = 18.10 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 0.00 || DFF = 0.00 -12.9 Fey = 2.97 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 77.07 || (KL/R)max = 224.42 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 23.4 0.0 0.0 232.6 || LOCATION 0.0 0.0 0.0 0.0 17.5 || LOADING 0 1 0 0 1 || ||**************************************************************************|



|* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-3 0.974 1 || 0.00 T 0.00 -232.64 17.50 ||* *||**************************************************************************|| |



FX MY MZ LOCATION=======================================================================


* OF 9TH ED. AISC-ASD. EXAMPLE 10.35. FINISH******************************************************************************WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.





Steel Design per AISC ASD 17ObjectiveTo determine the suitability of a W14x109 shape to resist axial compression and biaxialbending.


404 — STAAD.Pro



ProblemP =200 kips

Mz = 120 ft-kips (strong axis)

My = 40 ft-kips (weak axis)

KL = 14 ft

Cm= 0.85


Comparison


Selected section OK OK (stress ratio = 0.93) none

Table 10-17: Comparison of results for ASD beam-column no. 17

STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING.* PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.* RATIO SHOULD BE APPROXIMATELY 1.0UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 14 0MEMB INCI1 1 2MEMB PROP1 TA ST W14X109CONSTE STEEL ALLDENS STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -2002 MZ 1202 MX 40PERF ANALYUNIT INCHPARAMCODE AISCFYLD 36 ALLTRACK 2 ALLCHECK CODE ALLUNIT INCHPARAMCODE AISCFYLD 36 ALLTRACK 2 ALLCHECK CODE ALL


***************************************************** *



* STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:25:19 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING.INPUT FILE: AISC_ASD_COMB17.STD

2. * PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.3. * RATIO SHOULD BE APPROXIMATELY 1.04. UNIT KIP FT5. JOINT COORD6. 1 0 0 0 ; 2 0 14 07. MEMB INCI8. 1 1 29. MEMB PROP10. 1 TA ST W14X10911. CONST12. E STEEL ALL13. DENS STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -20020. 2 MZ 12021. 2 MX 4022. PERF ANALY




AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 2* PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 6

23. UNIT INCH24. PARAM25. CODE AISC26. FYLD 36 ALL27. TRACK 2 ALL28. CHECK CODE ALL

STEEL DESIGNAISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 3



|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 32.00 || * | ST W14X109 | | --Z AY = 6.86 ||DESIGN CODE * | | | AZ = 16.79 |

406 — STAAD.Pro



| AISC-1989 * =============================== ===|=== SY = 61.21 || * SZ = 173.18 || * |<---LENGTH (FT)= 14.00 --->| RY = 3.74 ||************* RZ = 6.22 || || 120.0 (KIP-FEET) ||PARAMETER |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 STRESSES ||IN KIP INCH |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 IN KIP INCH ||--------------- +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 -------------|| KL/R-Y= 44.95 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FA = 18.78 || KL/R-Z= 26.99 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 fa = 6.25 || UNL = 168.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FCZ = 23.76 || CB = 1.00 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FTZ = 23.76 || CMY = 0.85 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FCY = 27.00 || CMZ = 0.85 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FTY = 27.00 || FYLD = 36.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 fbz = 8.31 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 7.84 || DFF = 0.00 120.0 Fey = 73.91 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 205.02 || (KL/R)max = 44.95 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 200.0 0.0 0.0 40.0 120.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 1 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-2 0.930 1 || 200.00 C 40.00 -120.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 4* PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.


FX MY MZ LOCATION=======================================================================

|--------------------------------------------------------------------------|AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 5

* PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.29. UNIT INCH30. PARAM31. CODE AISC32. FYLD 36 ALL33. TRACK 2 ALL34. CHECK CODE ALL

STEEL DESIGNAISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 6


STAAD.PRO CODE CHECKING - (AISC 9TH EDITION) v1.0



********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX = 32.00 || * | ST W14X109 | | --Z AY = 6.86 ||DESIGN CODE * | | | AZ = 16.79 || AISC-1989 * =============================== ===|=== SY = 61.21 || * SZ = 173.18 || * |<---LENGTH (FT)= 14.00 --->| RY = 3.74 ||************* RZ = 6.22 || || 120.0 (KIP-FEET) ||PARAMETER |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 STRESSES ||IN KIP INCH |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 IN KIP INCH ||--------------- +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 -------------|| KL/R-Y= 44.95 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FA = 18.78 || KL/R-Z= 26.99 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 fa = 6.25 || UNL = 168.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FCZ = 23.76 || CB = 1.00 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FTZ = 23.76 || CMY = 0.85 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FCY = 27.00 || CMZ = 0.85 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FTY = 27.00 || FYLD = 36.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 fbz = 8.31 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 7.84 || DFF = 0.00 120.0 Fey = 73.91 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 205.02 || (KL/R)max = 44.95 (WITH LOAD NO.) FV = 14.40 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 200.0 0.0 0.0 40.0 120.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 1 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-2 0.930 1 || 200.00 C 40.00 -120.00 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 7* PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.


FX MY MZ LOCATION=======================================================================

|--------------------------------------------------------------------------|AISC VERIFICATION PROBLEM FOR COMBINED AXIAL + BENDING. -- PAGE NO. 8

* PAGE 3-11 OF 9TH ED. AISC-ASD. EXAMPLE 4.**WARNING- NO END OR FINISH STATEMENT FOUND. FINISH ADDED.


408 — STAAD.Pro



**** DATE= DEC 13,2013 TIME= 12:25:22 ***************************************************************** For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Steel Design per AISC ASD 18ObjectiveTo determine the allowable compressive load on a single L2x2x1/4 loaded by a gusset plateattached to one leg with eccentricities from the centroid along both axes.


ProblemP =200 kips

ez = 0.277in

ey = 0.854in

KL = 40 ft

Cm= 0.85


Comparison


Allowable compressiveload (kips)

4.5 Using a P of 4.5 kip yields aratio of 0.898

none

Table 10-18: Comparison of results for ASD beam-column no. 18

STAAD InputSTAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION + BIAXIAL BENDING* PAGE 3-55 OF 9TH ED. AISC-ASD. SINGLE ANGLE 2X2X1/4* UNBRACED LENGTH IS 40 INCHES.UNIT KIP FEETJOINT COORD1 0 0 0 ; 2 0 5 0MEMB INCI1 1 2UNIT INCHMEMB PROP AMERICAN1 TA ST L20204CONST



E STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY -4.5* MZ = P * 0.277 = 1.2465 KIP-INCH* MX = P * 0.854 = 3.843 KIP-INCH2 MZ 1.24652 MX -3.843PERF ANALYUNIT INCHPARAMCODE AISCFYLD 50 ALLUNT 40 ALLUNB 40 ALLLY 40 ALLLZ 40 ALLTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACE AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION + BIAXIAL BENDINGINPUT FILE: AISC_ASD_COMB18.STD

2. * PAGE 3-55 OF 9TH ED. AISC-ASD. SINGLE ANGLE 2X2X1/43. * UNBRACED LENGTH IS 40 INCHES.4. UNIT KIP FEET5. JOINT COORD6. 1 0 0 0 ; 2 0 5 07. MEMB INCI8. 1 1 29. UNIT INCH10. MEMB PROP AMERICAN11. 1 TA ST L2020412. CONST13. E STEEL ALL14. POISS STEEL ALL15. SUPP16. 1 FIXED17. LOAD 118. JOINT LOAD19. 2 FY -4.520. * MZ = P * 0.277 = 1.2465 KIP-INCH21. * MX = P * 0.854 = 3.843 KIP-INCH22. 2 MZ 1.246523. 2 MX -3.84324. PERF ANALY

410 — STAAD.Pro




NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 1AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION + BIAXIA -- PAGE NO. 2

* PAGE 3-55 OF 9TH ED. AISC-ASD. SINGLE ANGL



25. UNIT INCH26. PARAM27. CODE AISC28. FYLD 50 ALL29. UNT 40 ALL30. UNB 40 ALL31. LY 40 ALL32. LZ 40 ALL33. TRACK 2 ALL34. CHECK CODE ALL

STEEL DESIGNAISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION + BIAXIA -- PAGE NO. 3

* PAGE 3-55 OF 9TH ED. AISC-ASD. SINGLE ANGL


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ==| |== ------------ ||MEMBER 1 * | AISC SECTIONS | | | AX = 0.94 || * | ST L20204 | | | --Z AY = 0.33 ||DESIGN CODE * | | | | AZ = 0.33 || AISC-1989 * =============================== ==| |== SY = 0.39 || * SZ = 0.17 || * |<---LENGTH (FT)= 5.00 --->| RY = 0.77 ||************* RZ = 0.39 || || 0.1 (KIP-FEET) ||PARAMETER |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 STRESSES ||IN KIP INCH |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 IN KIP INCH ||--------------- +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 -------------|| KL/R-Y= 52.15 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FA = 14.17 || KL/R-Z= 102.30 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 fa = 4.80 || UNL = 40.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FCZ = 33.00 || CB = 1.00 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FTZ = 33.00 || CMY = 0.85 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FCY = 33.00 || CMZ = 0.85 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 FTY = 33.00 || FYLD = 50.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 fbz = 7.26 || NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| fby = 9.85 || DFF = 0.00 0.1 Fey = 54.90 || dff= 0.00 ABSOLUTE MZ ENVELOPE Fez = 14.27 || (KL/R)max = 102.30 (WITH LOAD NO.) FV = 20.00 || fv = 0.00 || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 4.5 0.0 0.0 0.3 0.1 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 1 1 |



| ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS AISC- H1-1 0.898 1 || 4.50 C -0.32 -0.10 0.00 ||* *||**************************************************************************|| |

AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION + BIAXIA -- PAGE NO. 4* PAGE 3-55 OF 9TH ED. AISC-ASD. SINGLE ANGL


FX MY MZ LOCATION=======================================================================

|--------------------------------------------------------------------------|AISC VERIFICATION PROBLEM FOR AXIAL COMPRESSION + BIAXIA -- PAGE NO. 5

* PAGE 3-55 OF 9TH ED. AISC-ASD. SINGLE ANGL35. FINISH



412 — STAAD.Pro



11Steel Design per AISC LRFD




























Steel Design per AISC LRFD 1ObjectiveTo check the adequacy of a W8X24 American section to carry a tensile design load of 245 Kips.Assume the reduction in area due to bolt holes to be equivalent to a net section factor of 0.72.


AISC Load Factor Resistance Design, 3rd Edition, Example 3.1, case (a), page 3-5.

ProblemFy =50 ksi

L =10ft

ComparisonValue based on the term PNT in the STAAD output.


Design strength (kips) 248.5 248.51 none

Table 11-1: Comparison of results for beam no. 1


Hand CalculationNet section = 0.72(7.08in.2) = 5.11 in.2

( )( )

( )( )ϕP

ϕ F A ksi in k

ϕ F A ksi in k=

= 0.9 50 7.08 . = 318.6

= 0.75 65 5.11 . = 248.5n

t y g

t u e

2

2

STAAD InputSTAAD SPACE TENSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_TEN1.STD** OBJECTIVE : CHECKING THE DESIGN AXIAL TENSILE STRENGTH OF A* W8X24 AMERICAN SECTION. CAPACITY SHOULD BE 245 KIPS ACCORDING TO* EXAMPLE 3-1 ON PAGE 3-5 OF 3RD EDITION LRFD CODE.*UNIT KIP FEETJOINT COORD1 0 0 0 ; 2 10 0 0MEMBER INCIDENCES1 1 2MEMBER PROPERTY AMERICAN1 TA ST W8X24CONSTANT

414 — STAAD.Pro

11 Steel Design per AISC LRFD

Steel Design per AISC LRFD 1

E STEEL ALLPOISSON STEEL ALLSUPPORT1 FIXEDLOAD 1JOINT LOAD2 FX 245PERFORM ANALYSISUNIT KIP INCHPARAMETERCODE LRFD* NSF = 5.11/7.08 = 0.72NSF 0.72 ALLFYLD 50 ALLFU 65 ALLTRACK 1 ALLCHECK CODE ALLFINISH



1. STAAD SPACE TENSION CAPACITY PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_TEN1.STD

2. *3. * INPUT FILE: AISC_LRFD_TEN1.STD4. *5. * OBJECTIVE : CHECKING THE DESIGN AXIAL TENSILE STRENGTH OF A6. * W8X24 AMERICAN SECTION. CAPACITY SHOULD BE 245 KIPS ACCORDING TO7. * EXAMPLE 3-1 ON PAGE 3-5 OF 3RD EDITION LRFD CODE.8. *9. UNIT KIP FEET10. JOINT COORD11. 1 0 0 0 ; 2 10 0 012. MEMBER INCIDENCES13. 1 1 214. MEMBER PROPERTY AMERICAN15. 1 TA ST W8X2416. CONSTANT17. E STEEL ALL18. POISSON STEEL ALL19. SUPPORT20. 1 FIXED21. LOAD 122. JOINT LOAD23. 2 FX 24524. PERFORM ANALYSIS





TENSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2*



25. UNIT KIP INCH26. PARAMETER27. CODE LRFD28. * NSF = 5.11/7.08 = 0.7229. NSF 0.72 ALL30. FYLD 50 ALL31. FU 65 ALL32. TRACK 1 ALL33. CHECK CODE ALL

STEEL DESIGNTENSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 3

*

STAAD.Pro CODE CHECKING - (LRFD 3RD EDITION) v1.0***********************


FX MY MZ LOCATION=======================================================================

1 ST W8X24 (AISC SECTIONS)PASS LRFD-H1-1A-T 0.986 1

245.00 T 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 200.22 PNT= 248.51 MNZ= 934.08 MNY= 380.37 VN= 52.46 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************34. FINISH




Steel Design per AISC LRFD 2ObjectiveTo check the adequacy of a L4X4X1/2 American single angle to carry a tensile design load of120 Kips. Assume the reduction in area due to bolt holes to be equivalent to a net section factorof 0.795.

416 — STAAD.Pro





ProblemFy =36 ksi



Design strength (kips) 121.5 121.5 none

Table 11-2: Comparison of results for beam no. 2


Hand CalculationNet section = 0.795(3.75 in.2) = 2.98 in.2

( )( )

( )( )ϕP

ϕ F A ksi in k

ϕ F A ksi in k=

= 0.9 36 3.75 . = 121.5

= 0.75 58 2.98 . = 129.6n

t y g

t u e

2

2

STAAD InputSTAAD SPACE TENSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_TEN2.STD** OBJECTIVE : CHECKING THE DESIGN AXIAL TENSILE STRENGTH OF A* L4X4X1/2 AMERICAN SECTION. CAPACITY SHOULD BE 122 KIPS ACCORDING TO* EXAMPLE 3-2 ON PAGE 3-7 OF 3RD EDITION LRFD CODE.*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 10 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST L40408CONSTE STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY 120PERF ANALYUNIT INCHPARAMCODE LRFDFU 58 ALL* NSF = 2.98/3.75 = 0.795



NSF 0.795 ALLTRACK 1 ALLCHECK CODE ALLFINISH



1. STAAD SPACE TENSION CAPACITY PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_TEN2.STD

2. *3. * INPUT FILE: AISC_LRFD_TEN2.STD4. *5. * OBJECTIVE : CHECKING THE DESIGN AXIAL TENSILE STRENGTH OF A6. * L4X4X1/2 AMERICAN SECTION. CAPACITY SHOULD BE 122 KIPS ACCORDING TO7. * EXAMPLE 3-2 ON PAGE 3-7 OF 3RD EDITION LRFD CODE.8. *9. UNIT KIP FT10. JOINT COORD11. 1 0 0 0 ; 2 0 10 012. MEMB INCI13. 1 1 214. MEMB PROP AMERICAN15. 1 TA ST L4040816. CONST17. E STEEL ALL18. POISS STEEL ALL19. SUPP20. 1 FIXED21. LOAD 122. JOINT LOAD23. 2 FY 12024. PERF ANALY


NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 1TENSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. UNIT INCH26. PARAM27. CODE LRFD28. FU 58 ALL29. * NSF = 2.98/3.75 = 0.79530. NSF 0.795 ALL31. TRACK 1 ALL

418 — STAAD.Pro







FX MY MZ LOCATION=======================================================================

1 ST L40408 (AISC SECTIONS)PASS LRFD-H1-1A-T 0.988 1

120.00 T 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 34.95 PNT= 121.50 MNZ= 96.57 MNY= 134.69 VN= 25.92 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************33. FINISH




Steel Design per AISC LRFD 3ObjectiveTo determine the capacity of W14X132 column in axial compression. The column is braced at itsends for both axes.



ProblemFy =50 ksi

Length = 30 ft





Design strength (kips) 844 843.02 none

Table 11-3: Comparison of results for column no. 3


STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP1.STD** EXAMPLE PROBLEM 4.1, CASE (A), PAGE 4-7, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 844 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 30 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W14X132CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -840PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 50 ALLTRACK 1 ALLCHECK CODE ALLFINISH



1. STAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_CMP1.STD

2. *3. * INPUT FILE: AISC_LRFD_CMP1.STD4. *

420 — STAAD.Pro



5. * EXAMPLE PROBLEM 4.1, CASE (A), PAGE 4-7, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 844 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 30 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W14X13215. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT FY MX MZ21. LOAD 122. JOINT LOAD23. 2 FY -84024. PERF ANALY


NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. UNIT INCH26. PARAM27. CODE LRFD28. FYLD 50 ALL29. TRACK 1 ALL30. CHECK CODE ALL

STEEL DESIGNAXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 3

*



FX MY MZ LOCATION=======================================================================

1 ST W14X132 (AISC SECTIONS)PASS LRFD-H1-1A-C 0.996 1

840.00 C 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 843.02 PNT= 1746.00 MNZ= 9143.11 MNY= 5024.11 VN= 255.30 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************31. FINISH


AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 4*

************************************************************



* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Steel Design per AISC LRFD 4ObjectiveTo determine the capacity of W14X132 column in axial compression. The column is braced at itsends for its major axis, and at ends and mid-height for the minor axis.


AISC Load Factor Resistance Design, 3rd Edition, Example 4.1, case (b), page 4-7.

ProblemFy =50 ksi

Length = 30 ft



Design strength (kips) 1,300 1,296.75 none



STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP2.STD** EXAMPLE PROBLEM 4.1, CASE (B), PAGE 4-7, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 1300 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 30 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W14X132CONST

422 — STAAD.Pro



E STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -840PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 50 ALLLY 15 ALLTRACK 1 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_CMP2.STD4. *5. * EXAMPLE PROBLEM 4.1, CASE (B), PAGE 4-7, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 1300 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 30 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W14X13215. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT FY MX MZ21. LOAD 122. JOINT LOAD23. 2 FY -84024. PERF ANALY





*



25. UNIT INCH26. PARAM27. CODE LRFD28. FYLD 50 ALL29. LY 15 ALL30. TRACK 1 ALL31. CHECK CODE ALL


*



FX MY MZ LOCATION=======================================================================

1 ST W14X132 (AISC SECTIONS)PASS LRFD-H1-1A-C 0.648 1





Steel Design per AISC LRFD 5ObjectiveTo determine the design strength of an 8ft long single angle L4X3.5X5/16 in axial compression.Column is pinned at its ends and no intermediate bracing.


424 — STAAD.Pro



AISC Load Factor Resistance Design, 3rd Edition, Example 4.3, page 4-12.

ProblemFy =36 ksi

Length = 8 ft



Design strength (kips) 28.7 29.32 2.2%


STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP3.STD** EXAMPLE PROBLEM 4.3, PAGE 4-12, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 28.7 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 8 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST L40355CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -25PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 36 ALLTRACK 1 ALLCHECK CODE ALLFINISH





****************************************************


2. *3. * INPUT FILE: AISC_LRFD_CMP3.STD4. *5. * EXAMPLE PROBLEM 4.3, PAGE 4-12, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 28.7 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 8 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST L4035515. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT FY MX MZ21. LOAD 122. JOINT LOAD23. 2 FY -2524. PERF ANALY



*





*



FX MY MZ LOCATION=======================================================================

1 ST L40355 (AISC SECTIONS)PASS LRFD-H1-1A-C 0.853 1

25.00 C 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 29.32 PNT= 72.90 MNZ= 60.87 MNY= 67.97 VN= 16.23 |+---------------------------------------------------------------------+

426 — STAAD.Pro



************** END OF TABULATED RESULT OF DESIGN **************31. FINISH




Steel Design per AISC LRFD 6ObjectiveTo find a suitable American T-section with an axial compressive strength of 100 Kips. Member is20ft long. Ends are pinned, and the member is braced at the ends only for both axes.



ProblemFy = 50 ksi

Length = 20 ft

ComparisonValue based on the term PNC in the STAAD output.




STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP4.STD** EXAMPLE PROBLEM 4.4, PAGE 4-13, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 102 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 20 0MEMB INCI1 1 2



MEMB PROP AMERICAN1 TA T W12X26CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -100PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 50 ALLTRACK 1 ALLSELECT ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_CMP4.STD4. *5. * EXAMPLE PROBLEM 4.4, PAGE 4-13, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 102 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 20 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA T W12X2615. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT FY MX MZ21. LOAD 122. JOINT LOAD23. 2 FY -10024. PERF ANALY



428 — STAAD.Pro



NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. UNIT INCH26. PARAM27. CODE LRFD28. FYLD 50 ALL29. TRACK 1 ALL30. SELECT ALL


*

STAAD.Pro MEMBER SELECTION - (LRFD 3RD EDITION) v1.0**************************


FX MY MZ LOCATION=======================================================================

1 T W14X53 (AISC SECTIONS)PASS LRFD-H1-1A-C 0.981 1

100.00 C 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 101.98 PNT= 351.00 MNZ= 210.21 MNY= 322.15 VN= 69.53 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************31. FINISH******************************************************************************WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.


****************************************************************************AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 4





Steel Design per AISC LRFD 7ObjectiveTo validate that an American ASTM A500 grade B HSS12X10X1/2 compression member has adesign compressive strength of over 500 kips.


AISC Load Factor Resistance Design, 3rd Edition, Example 4.8, page 4-13 & Table 4-6, Page 4-50.

ProblemFy = 46 ksi

Length = 20 ft

KY = KZ = 0.8



Design strength in Axial Compression(kips)

634(*)

634.26 none

Table 11-7: Comparison of results for AISC LRFD 7

Note:* In the solved example, on page 4-14, the capacity is reported as Phi*Pn = 580 kips. Lookingat Table 4-6 on page 4-50, this happens to be the capacity for a 20 ft effective length, not a 16ft effective length. As per the table, the capacity corresponding to a 16ft effective length is634 kips.

STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP5.STD** EXAMPLE PROBLEM 4.5, PAGE 4-13, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 634 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 20 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST HSST12X10X0.5CONSTE STEEL ALLPOISS STEEL ALLSUPP

430 — STAAD.Pro



1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -500PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 46 ALLKY 0.8 ALLKZ 0.8 ALLTRACK 1 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_CMP5.STD4. *5. * EXAMPLE PROBLEM 4.5, PAGE 4-13, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 634 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 20 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST HSST12X10X0.515. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT FY MX MZ21. LOAD 122. JOINT LOAD23. 2 FY -50024. PERF ANALY



*





25. UNIT INCH26. PARAM27. CODE LRFD28. FYLD 46 ALL29. KY 0.8 ALL30. KZ 0.8 ALL31. TRACK 1 ALL32. CHECK CODE ALL


*



FX MY MZ LOCATION=======================================================================

1 ST HSST12X10X0.5 (AISC SECTIONS)PASS HSS COMPRESS 0.788 1

500.00 C 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 634.26 PNT= 786.60 MNZ= 3262.32 MNY= 2881.44 || VNZ= 231.01 VNY= 277.21 TN= 2533.68 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************33. FINISH




Steel Design per AISC LRFD 8ObjectiveTo find a suitable American ASTM A53 grade B steel pipe section with an axial compressivestrength of 200 Kips. Member is 30ft long. Ends are pinned. Unbraced length should be assumedas the distance between ends.

432 — STAAD.Pro





ProblemFy = 35 ksi

Length = 30 ft



Design strength (kips) 216 202.79 (1) 6.1%


STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP6.STD** EXAMPLE PROBLEM 4.6, PAGE 4-14, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 216 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 30 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST PIPS100CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -200PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 35 ALLTRACK 1 ALLCHECK CODE ALLFINISH







2. *3. * INPUT FILE: AISC_LRFD_CMP6.STD4. *5. * EXAMPLE PROBLEM 4.6, PAGE 4-14, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 216 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 30 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST PIPS10015. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT FY MX MZ21. LOAD 122. JOINT LOAD23. 2 FY -20024. PERF ANALY



*





*



FX MY MZ LOCATION=======================================================================

1 ST PIPS100 (AISC SECTIONS)PASS LRFD-H1-1A-C 0.986 1

434 — STAAD.Pro







Steel Design per AISC LRFD 9ObjectiveTo determine the design compressive strength of a long-leg-back-to-back double angle made ofAmerican L4X3.5X1/2 angles with 3/4-in. separation. Member is 8 ft long. Ends are pinned.Unbraced length should be assumed as the distance between ends.



ProblemFy = 36 ksi

Length = 30 ft





STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP7.STD** EXAMPLE PROBLEM 4.7, PAGE 4-14, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 101 KIPS



*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 8 0MEMB INCI1 1 2UNIT INCHMEMB PROP AMERICAN1 TA LD L40355 SP 0.75CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -100PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 36 ALLTRACK 1 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_CMP7.STD4. *5. * EXAMPLE PROBLEM 4.7, PAGE 4-14, AISC LRFD 3RD ED.6. * CAPACITY (PNC) SHOULD BE ABOUT 101 KIPS7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 8 011. MEMB INCI12. 1 1 213. UNIT INCH14. MEMB PROP AMERICAN15. 1 TA LD L40355 SP 0.7516. CONST17. E STEEL ALL18. POISS STEEL ALL19. SUPP20. 1 PINNED21. 2 FIXED BUT FY MX MZ22. LOAD 1

436 — STAAD.Pro



23. JOINT LOAD24. 2 FY -10025. PERF ANALY



*





*



FX MY MZ LOCATION=======================================================================

1 LD L40355 (AISC SECTIONS)PASS LRFD-H1-1A-C 0.988 1







Steel Design per AISC LRFD 10ObjectiveTo validate that an American Round HSS 10.000X0.5 compression member has a designcompressive strength of about 364 kips.


AISC Load Factor Resistance Design, 3rd Edition, Table 4-7, Page 4-68.

ProblemFy = 42 ksi

Length = 20 ft





STAAD InputSTAAD SPACE AXIAL COMPRESSION CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_CMP8.STD** DESIGN COMPRESSIVE STRENGTH OF A ROUND HSS 10.000X0.5* TABLE 4-7, PAGE 4-68, AISC LRFD 3RD ED.* CAPACITY (PNC) SHOULD BE ABOUT 364 KIPS*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 20 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST HSSP10X0.5CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT FY MX MZLOAD 1JOINT LOAD2 FY -350PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 42 ALL

438 — STAAD.Pro



TRACK 1 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_CMP8.STD4. *5. * DESIGN COMPRESSIVE STRENGTH OF A ROUND HSS 10.000X0.56. * TABLE 4-7, PAGE 4-68, AISC LRFD 3RD ED.7. * CAPACITY (PNC) SHOULD BE ABOUT 364 KIPS8. *9. UNIT KIP FT10. JOINT COORD11. 1 0 0 0 ; 2 0 20 012. MEMB INCI13. 1 1 214. MEMB PROP AMERICAN15. 1 TA ST HSSP10X0.516. CONST17. E STEEL ALL18. POISS STEEL ALL19. SUPP20. 1 PINNED21. 2 FIXED BUT FY MX MZ22. LOAD 123. JOINT LOAD24. 2 FY -35025. PERF ANALY



*




STEEL DESIGN






FX MY MZ LOCATION=======================================================================

1 ST HSSP10X0.5 (AISC SECTIONS)PASS HSS COMPRESS 0.961 1

350.00 C 0.00 0.00 0.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 364.22 PNT= 525.42 MNZ= 1598.94 MNY= 1598.94 || VNZ= 157.63 VNY= 157.63 TN= 1440.18 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************32. FINISH




Steel Design per AISC LRFD 11ObjectiveTo determine the design flexural strength of an ASTM A992 W18X40 bent about its strong axison a 35-ft span with a uniformly distributed load. The beam is braced such that Lb=2ft. Thedeflection at mid-span due to a uniformly distributed service load of 1 kip/ft is also to becalculated.


AISC Load Factor Resistance Design, 3rd Edition, Example 5.1, Case (a), page 5-12.

ProblemFy = 50 ksi

Length = 35 ft

440 — STAAD.Pro



ComparisonValue based on the term MNZ in the STAAD output.


Deflection (in) 1.90 1.8918 none

Design flexural strength (ft-kips) 294 294

(3,528 in-kips)

none


STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN1.STD** EXAMPLE PROBLEM 5.1, CASE (A), PAGE 5-12, AISC LRFD 3RD ED.* CAPACITY (MNZ) SHOULD BE ABOUT 294 KIP-FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 35 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W18X40CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -1.0LOAD COMB 21 1.8PERF ANALYLOAD LIST 1SECTION 0.5 ALLPRINT SECTION DISPLOAD LIST 2UNIT FEETPARAMCODE LRFDMAIN 1.0 ALLFYLD 7200 ALLUNT 2 ALLTRACK 1 ALLCHECK CODE ALLFINISH






1. STAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_BEN1.STD

2. *3. * INPUT FILE: AISC_LRFD_BEN1.STD4. *5. * EXAMPLE PROBLEM 5.1, CASE (A), PAGE 5-12, AISC LRFD 3RD ED.6. * CAPACITY (MNZ) SHOULD BE ABOUT 294 KIP-FT7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 35 0 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W18X4015. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT MZ21. LOAD 122. MEMBER LOAD23. 1 UNI GY -1.024. LOAD COMB 225. 1 1.826. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*





27. LOAD LIST 128. SECTION 0.5 ALL29. PRINT SECTION DISP

SECTION DISPBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 3

*MEMBER SECTION DISPLACEMENTS----------------------------UNITS ARE - INCHMEMB LOAD GLOBAL X,Y,Z DISPL FROM START TO END JOINTS AT 1/12TH PTS1 1 0.0000 0.0000 0.0000 0.0000 -0.4973 0.0000

0.0000 -0.9571 0.0000 0.0000 -1.3475 0.00000.0000 -1.6441 0.0000 0.0000 -1.8290 0.00000.0000 -1.8918 0.0000 0.0000 -1.8290 0.00000.0000 -1.6441 0.0000 0.0000 -1.3475 0.00000.0000 -0.9571 0.0000 0.0000 -0.4973 0.00000.0000 0.0000 0.0000

MAX LOCAL DISP = 1.89185 AT 210.00 LOAD 1 L/DISP= 222************ END OF SECT DISPL RESULTS ***********

442 — STAAD.Pro



30. LOAD LIST 231. UNIT FEET32. PARAM33. CODE LRFD34. MAIN 1.0 ALL35. FYLD 7200 ALL36. UNT 2 ALL37. TRACK 1 ALL38. CHECK CODE ALL

STEEL DESIGNBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 4

*


ALL UNITS ARE - KIP FEET (UNLESS OTHERWISE Noted)MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/

FX MY MZ LOCATION=======================================================================

1 ST W18X40 (AISC SECTIONS)PASS LRFD-H1-1B-C 0.938 2

0.00 C 0.00 -275.62 17.50+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 23.10 PNT= 531.00 MNZ= 3528.00 MNY= 428.68 VN= 152.24 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************39. FINISH


BENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 5*


Steel Design per AISC LRFD 12ObjectiveTo determine the design flexural strength of an ASTM A992 W18X40 bent about its strong axis ona 35-ft span with a uniformly distributed load. The beam is braced at the ends and at third pointssuch that Lb = 11.7ft.


AISC Load Factor Resistance Design, 3rd Edition, Example 5.1, Case (b), page 5-12.



ProblemFy = 50 ksi

Length = 35 ft



Design flexural strength (ft-kips) 211 209.5

(2,514 in-kips)

<1%


Note: The STAAD.Pro result is based on a Cb of 1.0, while the theoretical solution is based ona Cb of 1.01

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN2.STD** EXAMPLE PROBLEM 5.1, CASE (B), PAGE 5-12, AISC LRFD 3RD ED.* CAPACITY (MNZ) SHOULD BE ABOUT 211 KIP-FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 35 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W18X40CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -1.3PERF ANALYPARAMCODE LRFDMAIN 1.0 ALLCB 1.00 ALLFYLD 7200 ALLUNT 11.7 ALLTRACK 2 ALLCHECK CODE ALLFINISH



444 — STAAD.Pro



* Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:26: 7 ** ** USER ID: Bentley Systems, Inc. *****************************************************


2. *3. * INPUT FILE: AISC_LRFD_BEN2.STD4. *5. * EXAMPLE PROBLEM 5.1, CASE (B), PAGE 5-12, AISC LRFD 3RD ED.6. * CAPACITY (MNZ) SHOULD BE ABOUT 211 KIP-FT7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 35 0 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W18X4015. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT MZ21. LOAD 122. MEMBER LOAD23. 1 UNI GY -1.324. PERF ANALY


NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2BENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. PARAM26. CODE LRFD27. MAIN 1.0 ALL28. CB 1.00 ALL29. FYLD 7200 ALL30. UNT 11.7 ALL31. TRACK 2 ALL32. CHECK CODE ALL


*

STAAD.PRO CODE CHECKING - (LRFD 3RD EDITION) v1.0********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ |



|MEMBER 1 * | AISC SECTIONS | | AX=0.1180E+2 || * | ST W18X40 | | --Z AY=0.5638E+1 ||DESIGN CODE * | | | AZ=0.4210E+1 || LRFD 2001 * =============================== ===|=== PY=0.1000E+2 || * PZ=0.7840E+2 || * |<---LENGTH (FT)= 35.00 --->| RY=0.1272E+1 ||************* RZ=0.7202E+1 || || 199.1 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 330.12 | PNC=0.2310E+2|| KL/R-Z= 58.32 + L1 L1 pnc=0.0000E+0|| UNL = 140.40 | PNT=0.5310E+3|| CB = 1.00 + L1 L1 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.2514E+4|| PHIB = 0.90 + mnz=0.2389E+4|| FYLD = 50.00 |L0 L0 MNY=0.4287E+3|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -11.1 VN =0.1522E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 22.7 0.0 0.0 199.1 || LOCATION 0.0 0.0 0.0 0.0 17.5 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1B-C 0.950 1 || 0.00 C 0.00 -199.06 17.50 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************33. FINISH



446 — STAAD.Pro



Steel Design per AISC LRFD 13ObjectiveTo determine the design flexural strength of an ASTM A992 W18X40 bent about its strong axis ona 35-ft span with a uniformly distributed load. The beam is braced at the ends and so, Lb = 35 ft.


AISC Load Factor Resistance Design, 3rd Edition, Example 5.1, Case (c), page 5-12.

ProblemFy = 50 ksi

Length = 35 ft



Design flexural strength (ft-kips) 50.8 50.6

(607.2 in-kips)

<1%


Note: The Cb of 1.14 calculated by STAAD.Pro precisely matches the value used in thereference hand calculation.

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN3.STD** EXAMPLE PROBLEM 5.1, CASE (C), PAGE 5-12, AISC LRFD 3RD ED.* CAPACITY (MNZ) SHOULD BE ABOUT 50.8 KIP-FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 35 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W18X40CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -0.3



PERF ANALYPARAMCODE LRFDMAIN 1.0 ALLCB 0.0 ALLFYLD 7200 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_BEN3.STD4. *5. * EXAMPLE PROBLEM 5.1, CASE (C), PAGE 5-12, AISC LRFD 3RD ED.6. * CAPACITY (MNZ) SHOULD BE ABOUT 50.8 KIP-FT7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 35 0 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W18X4015. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 PINNED20. 2 FIXED BUT MZ21. LOAD 122. MEMBER LOAD23. 1 UNI GY -0.324. PERF ANALY


NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2BENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. PARAM26. CODE LRFD

448 — STAAD.Pro



27. MAIN 1.0 ALL28. CB 0.0 ALL29. FYLD 7200 ALL30. TRACK 2 ALL31. CHECK CODE ALL


*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.1180E+2 || * | ST W18X40 | | --Z AY=0.5638E+1 ||DESIGN CODE * | | | AZ=0.4210E+1 || LRFD 2001 * =============================== ===|=== PY=0.1000E+2 || * PZ=0.7840E+2 || * |<---LENGTH (FT)= 35.00 --->| RY=0.1272E+1 ||************* RZ=0.7202E+1 || || 45.9 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 330.12 | PNC=0.2310E+2|| KL/R-Z= 58.32 + L1 L1 pnc=0.0000E+0|| UNL = 420.00 | PNT=0.5310E+3|| CB = 1.14 + L1 L1 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.6072E+3|| PHIB = 0.90 + mnz=0.5512E+3|| FYLD = 50.00 |L0 L0 MNY=0.4287E+3|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -2.6 VN =0.1522E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 5.2 0.0 0.0 45.9 || LOCATION 0.0 0.0 0.0 0.0 17.5 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1B-C 0.908 1 || 0.00 C 0.00 -45.94 17.50 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************32. FINISH




**** DATE= DEC 13,2013 TIME= 12:26:14 ***************************************************************** For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Steel Design per AISC LRFD 14ObjectiveTo select the optimum ASTM A992 W-shape with a design flexural strength of 500 kip-ft. Beamis bent about its strong axis, and is continuously braced.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Table 5.2, , page 5-50.

ProblemFy = 50 ksi

Length = 30 ft

w = 4.44 kip/ft (equiv. of 500 ft-kip design moment)

Comparison


Optimum section W24x55 W24x55 none

Design strength, ϕbMz (ft-kips) 506 502.5 (*) <1%


* Calculated as MZ envelope value divided by the MZ ratio:

499.95 ft-kips/0.995 = 502.5 ft-kips

Note: Fully braced condition can be achieved by setting the UNT parameter equal to 1.0 inch.

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN4.STD** TABLE 5.2, PAGE 5-40, AISC LRFD 3RD ED.* OBJECTIVE : TO SELECT THE MOST OPTIMUM SECTION WITH A DESIGN* FLEXURAL STRENGTH OF 500 KIP-FT.* FOR A FULLY BRACED BEAM, PER ABOVE REFERENCE, IT SHOULD BE* A W24X55*

450 — STAAD.Pro



* 500 KIP-FT IS EQUAL TO AN APPLIED LOAD OF 4.444 KIP/FT ON* A SIMPLY SUPPORTED BEAM*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 30 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W12X26CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -4.444PERF ANALYUNIT INCHPARAMCODE LRFD* FULLY BRACED CONDITION IS ACHIEVED WITH A UNT OF 1.0 INCHUNT 1.0 ALLMAIN 1.0 ALLFYLD 50 ALLCB 0.0 ALLTRACK 2 ALLSELECT ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_BEN4.STD4. *5. * TABLE 5.2, PAGE 5-40, AISC LRFD 3RD ED.6. * OBJECTIVE : TO SELECT THE MOST OPTIMUM SECTION WITH A DESIGN7. * FLEXURAL STRENGTH OF 500 KIP-FT.8. * FOR A FULLY BRACED BEAM, PER ABOVE REFERENCE, IT SHOULD BE9. * A W24X5510. *11. * 500 KIP-FT IS EQUAL TO AN APPLIED LOAD OF 4.444 KIP/FT ON12. * A SIMPLY SUPPORTED BEAM13. *14. UNIT KIP FT15. JOINT COORD16. 1 0 0 0 ; 2 30 0 017. MEMB INCI



18. 1 1 219. MEMB PROP AMERICAN20. 1 TA ST W12X2621. CONST22. E STEEL ALL23. POISS STEEL ALL24. SUPP25. 1 PINNED26. 2 FIXED BUT MZ27. LOAD 128. MEMBER LOAD29. 1 UNI GY -4.44430. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*





31. UNIT INCH32. PARAM33. CODE LRFD34. * FULLY BRACED CONDITION IS ACHIEVED WITH A UNT OF 1.0 INCH35. UNT 1.0 ALL36. MAIN 1.0 ALL37. FYLD 50 ALL38. CB 0.0 ALL39. TRACK 2 ALL40. SELECT ALL


*

STAAD.PRO MEMBER SELECTION - (LRFD 3RD EDITION) v1.0***********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.1620E+2 || * | ST W24X55 | | --Z AY=0.9310E+1 ||DESIGN CODE * | | | AZ=0.4717E+1 || LRFD 2001 * =============================== ===|=== PY=0.1330E+2 || * PZ=0.1340E+3 || * |<---LENGTH (FT)= 30.00 --->| RY=0.1340E+1 ||************* RZ=0.9129E+1 || || 499.9 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 268.60 | PNC=0.4791E+2|| KL/R-Z= 39.44 + L1 L1 pnc=0.0000E+0|| UNL = 1.00 | PNT=0.7290E+3|| CB = 1.14 + L1 L1 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.6030E+4|| PHIB = 0.90 + mnz=0.5999E+4|| FYLD = 50.00 |L0 L0 MNY=0.5608E+3|

452 — STAAD.Pro



| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -27.8 VN =0.2514E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 66.7 0.0 0.0 499.9 || LOCATION 0.0 0.0 0.0 0.0 15.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1B-C 0.995 1 || 0.00 C 0.00 -499.95 15.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************41. FINISH******************************************************************************WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.





Steel Design per AISC LRFD 15ObjectiveTo check the adequacy of a non-compact fully braced W shape to carry a uniformly distributedload of 5.5 kips/ft. Beam is bent about its strong axis.




ProblemW14x90 shape

Fy = 50 ksi

Length = 30 ft



Maximum total Factored Load, W (kips) 154 153.1 <1%

ϕbWc 4,610 4,605 none



Hand CalculationMNZ = 6,908 in-kips = wl2/8

⋅

w = = = 0.426kips/inM

l

8 8(6, 908)

(30 12)2 2

W = 0.426 kips/in(30ft)(12 in/ft) = 153.1 kips

ϕbWc = 153.1 kips (30 ft) = 4,605 ft-kips

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN5.STD** TABLE 5-4, PAGE 5-65, AISC LRFD 3RD ED.* OBJECTIVE : TO CHECK THE ADEQUACY OF A NON-COMPACT W SHAPE.** BEAM IS FULLY BRACED. ACCORDING TO ABOVE REFERENCE,* CAPACITY OF A 30 FT LONG W14X90 IS 154/30=5.133 KIP/FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 30 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W14X90CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1

454 — STAAD.Pro



MEMBER LOAD1 UNI GY -5.5PERF ANALYUNIT INCHPARAMCODE LRFDMAIN 1.0 ALL* FULLY BRACED CONDITION IS ACHIEVED WITH A UNT OF 1.0 INCHUNT 1 ALLFYLD 50 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_BEN5.STD4. *5. * TABLE 5-4, PAGE 5-65, AISC LRFD 3RD ED.6. * OBJECTIVE : TO CHECK THE ADEQUACY OF A NON-COMPACT W SHAPE.7. *8. * BEAM IS FULLY BRACED. ACCORDING TO ABOVE REFERENCE,9. * CAPACITY OF A 30 FT LONG W14X90 IS 154/30=5.133 KIP/FT10. *11. UNIT KIP FT12. JOINT COORD13. 1 0 0 0 ; 2 30 0 014. MEMB INCI15. 1 1 216. MEMB PROP AMERICAN17. 1 TA ST W14X9018. CONST19. E STEEL ALL20. POISS STEEL ALL21. SUPP22. 1 PINNED23. 2 FIXED BUT MZ24. LOAD 125. MEMBER LOAD26. 1 UNI GY -5.527. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*







28. UNIT INCH29. PARAM30. CODE LRFD31. MAIN 1.0 ALL32. * FULLY BRACED CONDITION IS ACHIEVED WITH A UNT OF 1.0 INCH33. UNT 1 ALL34. FYLD 50 ALL35. TRACK 2 ALL36. CHECK CODE ALL


*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.2650E+2 || * | ST W14X90 | | --Z AY=0.6169E+1 ||DESIGN CODE * | | | AZ=0.1375E+2 || LRFD 2001 * =============================== ===|=== PY=0.7560E+2 || * PZ=0.1570E+3 || * |<---LENGTH (FT)= 30.00 --->| RY=0.3696E+1 ||************* RZ=0.6140E+1 || || 618.8 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 97.40 | PNC=0.5628E+3|| KL/R-Z= 58.63 + L1 L1 pnc=0.0000E+0|| UNL = 1.00 | PNT=0.1192E+4|| CB = 1.00 + L1 L1 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.6908E+4|| PHIB = 0.90 + mnz=0.7425E+4|| FYLD = 50.00 |L0 L0 MNY=0.3274E+4|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -34.4 VN =0.1666E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 82.5 0.0 0.0 618.8 || LOCATION 0.0 0.0 0.0 0.0 15.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== |

456 — STAAD.Pro



| FAIL LRFD-H1-1B-C 1.075 1 || 0.00 C 0.00 -618.75 15.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************37. FINISH



Steel Design per AISC LRFD 16ObjectiveTo check the adequacy of a fully braced C shape to carry a uniformly distributed load of 1.5kips/ft. Beam is bent about its strong axis.


ProblemC12x25 shape

Fy = 50 ksi

Length = 20 ft



Maximum total Factored Load, W (kips) 31.8 31.5 <1%

ϕbMc 635 630.7 <1%



Hand CalculationMNZ =946.1 in-kips = wl2/8



⋅

w = = = 0.131kips/inM

l

8 8(946.1)

(20 12)2 2


ϕbWc = 31.5 kips (20 ft) = 630.7 ft-kips

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN6.STD** TABLE 5-9, PAGE 5-120, AISC LRFD 3RD ED.* OBJECTIVE : TO CHECK THE ADEQUACY OF A C SHAPE.** BEAM IS FULLY BRACED. ACCORDING TO ABOVE REFERENCE,* CAPACITY OF A 20 FT LONG C12X25 IS 31.8/20=1.59 KIP/FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 20 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST C12X25CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -1.50PERF ANALYUNIT INCHPARAMCODE LRFDMAIN 1.0 ALL* FULLY BRACED CONDITION IS ACHIEVED WITH A UNT OF 1.0 INCHUNT 1 ALLFYLD 36 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. *

458 — STAAD.Pro



3. * INPUT FILE: AISC_LRFD_BEN6.STD4. *5. * TABLE 5-9, PAGE 5-120, AISC LRFD 3RD ED.6. * OBJECTIVE : TO CHECK THE ADEQUACY OF A C SHAPE.7. *8. * BEAM IS FULLY BRACED. ACCORDING TO ABOVE REFERENCE,9. * CAPACITY OF A 20 FT LONG C12X25 IS 31.8/20=1.59 KIP/FT10. *11. UNIT KIP FT12. JOINT COORD13. 1 0 0 0 ; 2 20 0 014. MEMB INCI15. 1 1 216. MEMB PROP AMERICAN17. 1 TA ST C12X2518. CONST19. E STEEL ALL20. POISS STEEL ALL21. SUPP22. 1 PINNED23. 2 FIXED BUT MZ24. LOAD 125. MEMBER LOAD26. 1 UNI GY -1.5027. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*







*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| |=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.7350E+1 || * | ST C12X25 | | --Z AY=0.4644E+1 ||DESIGN CODE * | | | AZ=0.2035E+1 || LRFD 2001 * =============================== |=== PY=0.3800E+1 || * PZ=0.2920E+2 || * |<---LENGTH (FT)= 20.00 --->| RY=0.7798E+0 ||************* RZ=0.4426E+1 || |



| 75.0 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 307.75 | PNC=0.1642E+2|| KL/R-Z= 54.22 + L1 L1 pnc=0.0000E+0|| UNL = 1.00 | PNT=0.2381E+3|| CB = 1.00 + L1 L1 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.9461E+3|| PHIB = 0.90 + mnz=0.9000E+3|| FYLD = 36.00 |L0 L0 MNY=0.9139E+2|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -4.2 VN =0.9028E+2|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 15.0 0.0 0.0 75.0 || LOCATION 0.0 0.0 0.0 0.0 10.0 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1B-C 0.951 1 || 0.00 C 0.00 -75.00 10.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************37. FINISH



Steel Design per AISC LRFD 17ObjectiveTo check the adequacy of a fully braced MC shape to carry a uniformly distributed load of 1.34kips/ft. Beam is bent about its strong axis.

460 — STAAD.Pro



ReferenceAISC Load Factor Resistance Design, 3rd Edition, Table 5.10 , page 5-124.

ProblemMC10x41.1 shape

Fy = 50 ksi

Length = 25 ft



Maximum total Factored Load, W (kips) 34 33.6 1.2%

ϕbWc 849 840 1.1%



Hand CalculationMNZ = 1,260 in-kips = wl2/8

⋅

w = = = 0.112kips/inM

l

8 8(1, 260)

(25 12)2 2


ϕbWc = 33.6 kips (25 ft) = 840 ft-kips

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN7.STD** TABLE 5-10, PAGE 5-124, AISC LRFD 3RD ED.* OBJECTIVE : TO CHECK THE ADEQUACY OF AN MC SHAPE.** BEAM IS FULLY BRACED. ACCORDING TO ABOVE REFERENCE,* CAPACITY OF A 25 FT LONG MC10X41 IS APPROX. 34/25=1.36 KIP/FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 25 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST MC10X41CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1



MEMBER LOAD1 UNI GY -1.34PERF ANALYUNIT INCHPARAMCODE LRFDMAIN 1.0 ALL* FULLY BRACED CONDITION IS ACHIEVED WITH A UNT OF 1.0 INCHUNT 1 ALLFYLD 36 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. *3. * INPUT FILE: AISC_LRFD_BEN7.STD4. *5. * TABLE 5-10, PAGE 5-124, AISC LRFD 3RD ED.6. * OBJECTIVE : TO CHECK THE ADEQUACY OF AN MC SHAPE.7. *8. * BEAM IS FULLY BRACED. ACCORDING TO ABOVE REFERENCE,9. * CAPACITY OF A 25 FT LONG MC10X41 IS APPROX. 34/25=1.36 KIP/FT10. *11. UNIT KIP FT12. JOINT COORD13. 1 0 0 0 ; 2 25 0 014. MEMB INCI15. 1 1 216. MEMB PROP AMERICAN17. 1 TA ST MC10X4118. CONST19. E STEEL ALL20. POISS STEEL ALL21. SUPP22. 1 PINNED23. 2 FIXED BUT MZ24. LOAD 125. MEMBER LOAD26. 1 UNI GY -1.3427. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*



462 — STAAD.Pro







*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| |=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.1210E+2 || * | ST MC10X41 | | --Z AY=0.7960E+1 ||DESIGN CODE * | | | AZ=0.3313E+1 || LRFD 2001 * =============================== |=== PY=0.8700E+1 || * PZ=0.3890E+2 || * |<---LENGTH (FT)= 25.00 --->| RY=0.1143E+1 ||************* RZ=0.3614E+1 || || 104.7 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 262.53 | PNC=0.3715E+2|| KL/R-Z= 83.02 + L1 L1 pnc=0.0000E+0|| UNL = 1.00 | PNT=0.3920E+3|| CB = 1.00 + L1 L1 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.1260E+4|| PHIB = 0.90 + mnz=0.1256E+4|| FYLD = 36.00 |L0 L0 MNY=0.2377E+3|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -5.8 VN =0.1547E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 16.8 0.0 0.0 104.7 || LOCATION 0.0 0.0 0.0 0.0 12.5 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== |



| PASS LRFD-H1-1B-C 0.997 1 || 0.00 C 0.00 -104.69 12.50 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************37. FINISH



Steel Design per AISC LRFD 18ObjectiveTo determine the design bending strength of a non-compact American wide flange section bentabout its strong axis. The deflection at mid-span due to 2 concentrated loads acting at the thirdpoints along the beam is also to be calculated.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Example 5.2, case (a), page 5-16.

ProblemW21x48 shape

Fy = 50 ksi

Length = 40 ft

Lb = 5 ft



Deflection (in) 1.41 1.41 none

Design bending strength, ϕbMn 398 398.3

(4,780.1 in-kips)

none



464 — STAAD.Pro



STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN8.STD** EXAMPLE PROBLEM 5.2, CASE (A), PAGE 5-16, AISC LRFD 3RD ED.* CAPACITY (MNZ) SHOULD BE ABOUT 398 KIP-FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 40 0 0*MEMB INCI1 1 2*MEMB PROP AMERICAN1 TA ST W21X48*CONSTE STEEL ALLPOISS STEEL ALL*SUPP1 PINNED2 FIXED BUT MZ*LOAD 1MEMBER LOAD1 CON GY -10 13.3331 CON GY -10 26.667*PERF ANALY*SECTION 0.5 ALLPRINT SECTION DISPLACEMENTS*PARAMCODE LRFDMAIN 1.0 ALLFYLD 7200 ALLUNT 5 ALLTRACK 1 ALLCHECK CODE ALLFINISH




2. *



3. * INPUT FILE: AISC_LRFD_BEN8.STD4. *5. * EXAMPLE PROBLEM 5.2, CASE (A), PAGE 5-16, AISC LRFD 3RD ED.6. * CAPACITY (MNZ) SHOULD BE ABOUT 398 KIP-FT7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 40 0 011. *12. MEMB INCI13. 1 1 214. *15. MEMB PROP AMERICAN16. 1 TA ST W21X4817. *18. CONST19. E STEEL ALL20. POISS STEEL ALL21. *22. SUPP23. 1 PINNED24. 2 FIXED BUT MZ25. *26. LOAD 127. MEMBER LOAD28. 1 CON GY -10 13.33329. 1 CON GY -10 26.66730. *31. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*





32. *33. SECTION 0.5 ALL34. PRINT SECTION DISPLACEMENTS

SECTION DISPLACEBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 3


0.0000 -0.7057 0.0000 0.0000 -1.0010 0.00000.0000 -1.2273 0.0000 0.0000 -1.3654 0.00000.0000 -1.4114 0.0000 0.0000 -1.3654 0.00000.0000 -1.2273 0.0000 0.0000 -1.0010 0.00000.0000 -0.7057 0.0000 0.0000 -0.3644 0.00000.0000 0.0000 0.0000


35. *36. PARAM37. CODE LRFD38. MAIN 1.0 ALL39. FYLD 7200 ALL

466 — STAAD.Pro



40. UNT 5 ALL41. TRACK 1 ALL42. CHECK CODE ALL


*



FX MY MZ LOCATION=======================================================================






Steel Design per AISC LRFD 19ObjectiveTo determine the design bending strength of a non-compact American wide flange section bentabout its strong axis.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Example 5.2, case (b), page 5-16.

ProblemW21x48 shape

Fy = 50 ksi

Length = 40 ft

Lb = 13.3 ft






(3,657.6 in-kips)

<1%


STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN9.STD** EXAMPLE PROBLEM 5.2, CASE (B), PAGE 5-16, AISC LRFD 3RD ED.* CAPACITY (MNZ) SHOULD BE ABOUT 306 KIP-FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 40 0 0*MEMB INCI1 1 2*MEMB PROP AMERICAN1 TA ST W21X48*CONSTE STEEL ALLPOISS STEEL ALL*SUPP1 PINNED2 FIXED BUT MZ*LOAD 1MEMBER LOAD1 CON GY -10 13.3331 CON GY -10 26.667*PERF ANALY*PARAMCODE LRFDMAIN 1.0 ALLFYLD 7200 ALLUNT 13.333 ALLTRACK 1 ALLCHECK CODE ALLFINISH



468 — STAAD.Pro





2. *3. * INPUT FILE: AISC_LRFD_BEN9.STD4. *5. * EXAMPLE PROBLEM 5.2, CASE (B), PAGE 5-16, AISC LRFD 3RD ED.6. * CAPACITY (MNZ) SHOULD BE ABOUT 306 KIP-FT7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 40 0 011. *12. MEMB INCI13. 1 1 214. *15. MEMB PROP AMERICAN16. 1 TA ST W21X4817. *18. CONST19. E STEEL ALL20. POISS STEEL ALL21. *22. SUPP23. 1 PINNED24. 2 FIXED BUT MZ25. *26. LOAD 127. MEMBER LOAD28. 1 CON GY -10 13.33329. 1 CON GY -10 26.66730. *31. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*





32. *33. PARAM34. CODE LRFD35. MAIN 1.0 ALL36. FYLD 7200 ALL37. UNT 13.333 ALL38. TRACK 1 ALL39. CHECK CODE ALL


*





FX MY MZ LOCATION=======================================================================






Steel Design per AISC LRFD 20ObjectiveTo determine the design bending strength of a non-compact American wide flange section bentabout its strong axis.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Example 5.2, case (c), page 5-16.

ProblemW21x48 shape

Fy = 50 ksi

Length = 40 ft

Lb = 40 ft (braced at end points only)


470 — STAAD.Pro




Design bending strength, ϕbMn 70.2 69.57

(834.8 in-kips)

<1%


Note: The Cb of 1.14 calculated by STAAD.Pro precisely matches the value used in thereference hand calculation.

STAAD InputSTAAD SPACE BENDING CAPACITY PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN10.STD** EXAMPLE PROBLEM 5.2, CASE (C), PAGE 5-16, AISC LRFD 3RD ED.* CAPACITY (MNZ) SHOULD BE ABOUT 70.2 KIP-FT*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 40 0 0*MEMB INCI1 1 2*MEMB PROP AMERICAN1 TA ST W21X48*CONSTE STEEL ALLPOISS STEEL ALL*SUPP1 PINNED2 FIXED BUT MZ*LOAD 1MEMBER LOAD1 CON GY -10 13.3331 CON GY -10 26.667*PERF ANALY*PARAMCODE LRFDMAIN 1.0 ALLFYLD 7200 ALLCB 0.0 ALLTRACK 2 ALLCHECK CODE ALLFINISH







2. *3. * INPUT FILE: AISC_LRFD_BEN10.STD4. *5. * EXAMPLE PROBLEM 5.2, CASE (C), PAGE 5-16, AISC LRFD 3RD ED.6. * CAPACITY (MNZ) SHOULD BE ABOUT 70.2 KIP-FT7. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 40 0 011. *12. MEMB INCI13. 1 1 214. *15. MEMB PROP AMERICAN16. 1 TA ST W21X4817. *18. CONST19. E STEEL ALL20. POISS STEEL ALL21. *22. SUPP23. 1 PINNED24. 2 FIXED BUT MZ25. *26. LOAD 127. MEMBER LOAD28. 1 CON GY -10 13.33329. 1 CON GY -10 26.66730. *31. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*





32. *33. PARAM34. CODE LRFD35. MAIN 1.0 ALL36. FYLD 7200 ALL37. CB 0.0 ALL38. TRACK 2 ALL39. CHECK CODE ALL


*


472 — STAAD.Pro



|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.1410E+2 || * | ST W21X48 | | --Z AY=0.7219E+1 ||DESIGN CODE * | | | AZ=0.4667E+1 || LRFD 2001 * =============================== ===|=== PY=0.1490E+2 || * PZ=0.1070E+3 || * |<---LENGTH (FT)= 40.00 --->| RY=0.1657E+1 ||************* RZ=0.8247E+1 || || 133.3 (KIP-FEET) ||PARAMETER | L1 L1 L1 CAPACITIES ||IN KIP INCH | IN KIP INCH ||--------------- + L1 L1 -------------|| KL/R-Y= 289.73 | PNC=0.3584E+2|| KL/R-Z= 58.20 + L1 L1 pnc=0.0000E+0|| UNL = 480.00 | PNT=0.6345E+3|| CB = 1.14 + pnt=0.0000E+0|| PHIC = 0.85 | L1 L1 MNZ=0.8348E+3|| PHIB = 0.90 + mnz=0.1600E+4|| FYLD = 50.00 |L0 L0 MNY=0.6367E+3|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 -7.4 VN =0.1949E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.1000E+2|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 0.0 10.0 0.0 0.0 133.3 || LOCATION 0.0 0.0 0.0 0.0 13.3 || LOADING 0 1 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || FAIL LRFD-H1-1B-C 1.917 1 || 0.00 C 0.00 -133.33 13.33 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************40. FINISH





Steel Design per AISC LRFD 21ObjectiveTo find the optimum W shape with a flexural design strength of 150 ft-kips. Beam is braced atends and at mid-span point. The beam should also satisfy a deflection limit of 1.0 inches underservice load.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Example 5.4, page 5-21.

ProblemFy = 50 ksi

Length = 20 ft

Lb = 10 ft

Service load of 2.0 kip/ft. Deflection limit under service load = 1.0 in.



Optimum Section W16x31 W16x31 none


(1,802 in-kips)

none

Maximum permissible deflection (in) 1.0 0.658 N/A


STAAD InputSTAAD SPACE BENDING PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN11.STD** EXAMPLE 5.4, PAGE 5-21, AISC LRFD 3RD ED.* OBJECTIVE : TO FIND THE OPTIMUM W SHAPE WITH A FLEXURAL* DESIGN STRENGTH OF 150 KIP-FT.** ACCORDING TO ABOVE REFERENCE, THE SECTION SHOULD BE W16X31*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 20 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W12X26CONSTE STEEL ALLPOISS STEEL ALL

474 — STAAD.Pro



SUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -2.0LOAD COMB 21 1.5PERF ANALYLOAD LIST 2UNIT INCHPARAMCODE LRFDMAIN 1.0 ALLUNT 120 ALLFYLD 50 ALLTRACK 1 ALLSELECT ALLLOAD LIST ALLPERFORM ANALYSISLOAD LIST 1SECTION 0.5 ALLPRINT SECTION DISPLOAD LIST 2CHECK CODE ALLFINISH



1. STAAD SPACE BENDING PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_BEN11.STD

2. *3. * INPUT FILE: AISC_LRFD_BEN11.STD4. *5. * EXAMPLE 5.4, PAGE 5-21, AISC LRFD 3RD ED.6. * OBJECTIVE : TO FIND THE OPTIMUM W SHAPE WITH A FLEXURAL7. * DESIGN STRENGTH OF 150 KIP-FT.8. *9. * ACCORDING TO ABOVE REFERENCE, THE SECTION SHOULD BE W16X3110. *11. UNIT KIP FT12. JOINT COORD13. 1 0 0 0 ; 2 20 0 014. MEMB INCI15. 1 1 216. MEMB PROP AMERICAN17. 1 TA ST W12X2618. CONST19. E STEEL ALL20. POISS STEEL ALL21. SUPP22. 1 PINNED



23. 2 FIXED BUT MZ24. LOAD 125. MEMBER LOAD26. 1 UNI GY -2.027. LOAD COMB 228. 1 1.529. PERF ANALYBENDING PER AISC LRFD 3RD ED -- PAGE NO. 2

*





30. LOAD LIST 231. UNIT INCH32. PARAM33. CODE LRFD34. MAIN 1.0 ALL35. UNT 120 ALL36. FYLD 50 ALL37. TRACK 1 ALL38. SELECT ALL

STEEL DESIGNBENDING PER AISC LRFD 3RD ED -- PAGE NO. 3

*

STAAD.Pro MEMBER SELECTION - (LRFD 3RD EDITION) v1.0**************************


FX MY MZ LOCATION=======================================================================


0.00 C 0.00 -1800.00 120.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 45.93 PNT= 410.40 MNZ= 1802.06 MNY= 302.99 VN= 117.91 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************39. LOAD LIST ALL40. PERFORM ANALYSIS41. LOAD LIST 142. SECTION 0.5 ALL43. PRINT SECTION DISP

SECTION DISPBENDING PER AISC LRFD 3RD ED -- PAGE NO. 4


0.0000 -0.3331 0.0000 0.0000 -0.4690 0.00000.0000 -0.5722 0.0000 0.0000 -0.6365 0.00000.0000 -0.6584 0.0000 0.0000 -0.6365 0.0000

476 — STAAD.Pro



0.0000 -0.5722 0.0000 0.0000 -0.4690 0.00000.0000 -0.3331 0.0000 0.0000 -0.1731 0.00000.0000 0.0000 0.0000


44. LOAD LIST 245. CHECK CODE ALL

STEEL DESIGNBENDING PER AISC LRFD 3RD ED -- PAGE NO. 5

*



FX MY MZ LOCATION=======================================================================




BENDING PER AISC LRFD 3RD ED -- PAGE NO. 6*


Steel Design per AISC LRFD 22ObjectiveTo find the design flexural strength capacity of 3 beams of different spans using the data in Table5-4 of AISC LRFD 3rd edition. All beams are fully braced.


ProblemW21x62

Fy = 50 ksi



40 ft, 30 ft, and 8 ft spans are investigated.

ComparisonValue based on the ratio of MNZ in the STAAD output.


Utilization ratio, 30 ft span 1.0 1.0 none




STAAD InputSTAAD SPACE BENDING PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_BEN11.STD** EXAMPLE 5.4, PAGE 5-21, AISC LRFD 3RD ED.* OBJECTIVE : TO FIND THE OPTIMUM W SHAPE WITH A FLEXURAL* DESIGN STRENGTH OF 150 KIP-FT.** ACCORDING TO ABOVE REFERENCE, THE SECTION SHOULD BE W16X31*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 20 0 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W12X26CONSTE STEEL ALLPOISS STEEL ALLSUPP1 PINNED2 FIXED BUT MZLOAD 1MEMBER LOAD1 UNI GY -2.0LOAD COMB 21 1.5PERF ANALYLOAD LIST 2UNIT INCHPARAMCODE LRFDMAIN 1.0 ALLUNT 120 ALLFYLD 50 ALLTRACK 1 ALLSELECT ALLLOAD LIST ALLPERFORM ANALYSISLOAD LIST 1SECTION 0.5 ALLPRINT SECTION DISPLOAD LIST 2CHECK CODE ALLFINISH

478 — STAAD.Pro






2. *3. * INPUT FILE: AISC_LRFD_BEN12.STD4. *5. * OBJECTIVE : TO DETERMINE THE MAXIMUM UNIFORMLY6. * DISTRIBUTED LOAD CARRYING CAPACITY OF 3 BEAMS.7. *8. * EXAMPLE PROBLEM 5.5 PAGE 5-21, AISC LRFD 3RD ED.9. *10. UNIT KIP FT11. JOINT COORD12. 1 0 0 0 ; 2 40 0 013. 3 0 10 0 ; 4 30 10 014. 5 0 20 0 ; 6 8 20 015. MEMB INCI16. 1 1 2 ; 2 3 4 ; 3 5 617. MEMB PROP AMERICAN18. 1 2 3 TA ST W21X6219. CONST20. E STEEL ALL21. POISS STEEL ALL22. SUPP23. 1 3 5 PINNED24. 2 4 6 FIXED BUT MZ25. *26. LOAD 1**WARNING- THIS STRUCTURE IS DISJOINTED. IGNORE IF

MASTER/SLAVE OR IF UNCONNECTED JOINTS.27. MEMBER LOAD28. * ON MEMBER 1, W=108/40=2.729. 1 UNI GY -2.730. * ON MEMBER 2, W=144/3031. 2 UNI GY -4.832. * ON MEMBER 3, W=454/833. 3 UNI GY -56.7534. *35. PERF ANALYBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 2

*







36. PARAM37. CODE LRFD38. MAIN 1.0 ALL39. FYLD 7200 ALL40. * FULLY BRACED CONDITION CAN BE ACHIEVED BY SETTING UNT TO 1.0 INCH41. UNT 0.1 ALL42. TRACK 1 ALL43. CHECK CODE ALL


*



FX MY MZ LOCATION=======================================================================

* 1 ST W21X62 (AISC SECTIONS)FAIL LRFD-H1-1B-C 1.000 1

0.00 C 0.00 -540.00 20.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 1 UNITS - KIP IN || PNC= 53.25 PNT= 823.50 MNZ= 6480.00 MNY= 942.05 VN= 226.69 |+---------------------------------------------------------------------+


0.00 C 0.00 -540.00 15.00+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 2 UNITS - KIP IN || PNC= 94.66 PNT= 823.50 MNZ= 6480.00 MNY= 942.05 VN= 226.69 |+---------------------------------------------------------------------+* 3 ST W21X62 (AISC SECTIONS)

FAIL SHEAR-Y 1.001 10.00 C 0.00 0.00 0.00

+---------------------------------------------------------------------+| DESIGN STRENGTHS FOR MEMBER 3 UNITS - KIP IN || PNC= 608.25 PNT= 823.50 MNZ= 6161.12 MNY= 942.05 VN= 226.69 |+---------------------------------------------------------------------+************** END OF TABULATED RESULT OF DESIGN **************44. FINISHBENDING CAPACITY PER AISC LRFD 3RD ED -- PAGE NO. 4

************ END OF THE STAAD.Pro RUN *************** DATE= DEC 13,2013 TIME= 12:26: 7 ****


480 — STAAD.Pro



Steel Design per AISC LRFD 23ObjectiveTo check the adequacy of an ASTM A992 W10X22 subject to axial tension and flexure about theweak axis.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Example 6.1 case(a), page 6-5.

ProblemW10x22

Fy = 50 ksi

Fu = 65 ksi

Pu = 55 kips

Muy = 20 ft-kips, Muz = 0

ComparisonValue based on the terms PNT and MNY in the STAAD output.


Design tensile strength, ϕtPn (kips) 292.0 292 none

Design bending strength, ϕbMny (ft-kips)

22.9 22.31

(267.7 in-kips)

2.6%

Utilization ratio 0.967 0.991 2.5%



Hand CalculationsAccording to page 16.1 - 97 of the LRFD 3rd ed. code,

Mp = Fy · Z ≤ 1.5Fy · S

For a W10X22,

0.9 (1.5Fy · S) = 0.9 [1.5 (50)(3.97)] = 268 kip-in = 22.33 kip-ft,

which is lower than (0.9 Fy . Z) = 22.9. Hence, STAAD.Pro uses this limit state.

STAAD InputSTAAD SPACE COMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_COMB1.STD*



* EXAMPLE PROBLEM 6.1, CASE (A), PAGE 6-5, AISC LRFD 3RD ED.* INTERACTION RATIO SHOULD BE ABOUT 0.967*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 10 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W10X22CONSTE STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY 552 MX 20.0PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 50 ALLFU 65 ALLUNT 1 ALLUNB 1 ALLTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACE COMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_COMB1.STD

2. *3. * INPUT FILE: AISC_LRFD_COMB1.STD4. *5. * EXAMPLE PROBLEM 6.1, CASE (A), PAGE 6-5, AISC LRFD 3RD ED.6. * INTERACTION RATIO SHOULD BE ABOUT 0.9677. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 10 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W10X2215. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP

482 — STAAD.Pro



19. 1 FIXED20. LOAD 121. JOINT LOAD22. 2 FY 5523. 2 MX 20.024. PERF ANALY


NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 1COMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. UNIT INCH26. PARAM27. CODE LRFD28. FYLD 50 ALL29. FU 65 ALL30. UNT 1 ALL31. UNB 1 ALL32. TRACK 2 ALL33. CHECK CODE ALL

STEEL DESIGNCOMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD ED -- PAGE NO. 3

*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.6490E+1 || * | ST W10X22 | | --Z AY=0.2441E+1 ||DESIGN CODE * | | | AZ=0.2760E+1 || LRFD 2001 * =============================== ===|=== PY=0.6100E+1 || * PZ=0.2600E+2 || * |<---LENGTH (FT)= 10.00 --->| RY=0.1325E+1 ||************* RZ=0.4264E+1 || || 0.0 (KIP-FEET) ||PARAMETER |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 CAPACITIES ||IN KIP INCH |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 IN KIP INCH ||--------------- +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 -------------|| KL/R-Y= 90.54 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 PNC=0.1515E+3|| KL/R-Z= 28.14 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 pnc=0.0000E+0|| UNL = 1.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 PNT=0.2920E+3|| CB = 1.00 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 pnt=0.5500E+2|| PHIC = 0.85 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 MNZ=0.1170E+4|| PHIB = 0.90 +L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 mnz=0.0000E+0|| FYLD = 50.00 |L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 L0 MNY=0.2677E+3|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.2400E+3|| DFF = 0.00 0.0 VN =0.6590E+2|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || |



| AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE -55.0 0.0 0.0 20.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 1 0 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1B-T 0.991 1 || 55.00 T 20.00 0.00 0.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************34. FINISH



Steel Design per AISC LRFD 24ObjectiveTo check the adequacy of an ASTM A992 W10X22 subject to axial tension and flexure about thestrong axis.

ReferenceAISC Load Factor Resistance Design, 3rd Edition, Example 6.1 case(b), page 6-5.

ProblemW10x22

Fy = 50 ksi

Fu = 65 ksi

Pu = 55 kips

Muy = 0, Muz = 55 ft-kips

Lb = 4 ft

484 — STAAD.Pro



ComparisonValue based on the terms PNT and MNZ in the STAAD output.


Design tensile strength, ϕtPn (kips) 292.0 292 none


97.5 97.5

(1,170 in-kips)

none

Utilization ratio 0.98 0.98 none



STAAD InputSTAAD SPACE COMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_COMB2.STD** EXAMPLE PROBLEM 6.1, CASE (B), PAGE 6-5, AISC LRFD 3RD ED.* INTERACTION RATIO SHOULD BE ABOUT 0.98*UNIT KIP FTJOINT COORD1 0 0 0 ; 2 0 10 0MEMB INCI1 1 2MEMB PROP AMERICAN1 TA ST W10X22CONSTE STEEL ALLPOISS STEEL ALLSUPP1 FIXEDLOAD 1JOINT LOAD2 FY 1402 MZ 55.0PERF ANALYUNIT INCHPARAMCODE LRFDFYLD 50 ALLFU 65 ALLUNT 48 ALLUNB 48 ALLTRACK 2 ALLCHECK CODE ALLFINISH





* Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:27: 1 ** ** USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE COMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_COMB2.STD

2. *3. * INPUT FILE: AISC_LRFD_COMB2.STD4. *5. * EXAMPLE PROBLEM 6.1, CASE (B), PAGE 6-5, AISC LRFD 3RD ED.6. * INTERACTION RATIO SHOULD BE ABOUT 0.987. *8. UNIT KIP FT9. JOINT COORD10. 1 0 0 0 ; 2 0 10 011. MEMB INCI12. 1 1 213. MEMB PROP AMERICAN14. 1 TA ST W10X2215. CONST16. E STEEL ALL17. POISS STEEL ALL18. SUPP19. 1 FIXED20. LOAD 121. JOINT LOAD22. 2 FY 14023. 2 MZ 55.024. PERF ANALY


NUMBER OF JOINTS 2 NUMBER OF MEMBERS 1NUMBER OF PLATES 0 NUMBER OF SOLIDS 0NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 1COMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD ED -- PAGE NO. 2

*



25. UNIT INCH26. PARAM27. CODE LRFD28. FYLD 50 ALL29. FU 65 ALL30. UNT 48 ALL31. UNB 48 ALL32. TRACK 2 ALL33. CHECK CODE ALL

STEEL DESIGNCOMBINED AXIAL TENSION + FLEXURE PER AISC LRFD 3RD ED -- PAGE NO. 3

*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT |

486 — STAAD.Pro



| * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.6490E+1 || * | ST W10X22 | | --Z AY=0.2441E+1 ||DESIGN CODE * | | | AZ=0.2760E+1 || LRFD 2001 * =============================== ===|=== PY=0.6100E+1 || * PZ=0.2600E+2 || * |<---LENGTH (FT)= 10.00 --->| RY=0.1325E+1 ||************* RZ=0.4264E+1 || || 55.0 (KIP-FEET) ||PARAMETER |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 CAPACITIES ||IN KIP INCH |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 IN KIP INCH ||--------------- +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 -------------|| KL/R-Y= 90.54 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 PNC=0.1515E+3|| KL/R-Z= 28.14 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 pnc=0.0000E+0|| UNL = 48.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 PNT=0.2920E+3|| CB = 1.00 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 pnt=0.1400E+3|| PHIC = 0.85 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 MNZ=0.1170E+4|| PHIB = 0.90 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 mnz=0.6600E+3|| FYLD = 50.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 MNY=0.2677E+3|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.0000E+0|| DFF = 0.00 55.0 VN =0.6590E+2|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE -140.0 0.0 0.0 0.0 55.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1A-T 0.980 1 || 140.00 T 0.00 -55.00 0.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************34. FINISH





Steel Design per AISC LRFD 25ObjectiveTo check the adequacy of an ASTM A992 W14X176 beam subject to axial compression andbiaxial bending.


ProblemW14x176

Fy = 50 ksi

Pu = 1,400 kips

Muy = 70 ft-kips, Muz = 200 ft-kips

Lb = 14 ft

Reverse curvature bending with equal end moments for both axis.

ComparisonValue based on the terms PNT, MNY, and MNZ in the STAAD output.


Design tensile strength, ϕtPn (kips) 1,940 1,938 none


611 602.4

(7,229 in-kips)

1.4%

Design bending strength, ϕbMnz (ft-kips)

1,200 1,200

(14,400 in-kips)

none

Utilization ratio 0.973 0.974 none


Hand CalculationsAccording to page 16.1 - 97 of the LRFD 3rd ed. code,

Mp = Fy · Z ≤ 1.5Fy · S

For a W14x176,

0.9 (1.5Fy · S) = 0.9 [1.5 (50)(107)] = 7,222 kip-in = 601.8 kip-ft,

which is lower than (0.9 Fy . Z) = 611. Hence, STAAD.Pro uses this limit state.

STAAD InputSTAAD SPACE AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED

488 — STAAD.Pro



** INPUT FILE: AISC_LRFD_COMB3.STD** EXAMPLE PROBLEM 6.2, PAGE 6-6, AISC LRFD 3RD ED.* INTERACTION RATIO SHOULD BE ABOUT 0.973*UNIT KIP FTJOINT COORDINATES1 0 0 0 ; 2 14 0*MEMBER INCIDENCES1 1 2*MEMB PROP AMERICAN1 TA ST W14X176*CONSTE STEEL ALLPOISS STEEL ALL*SUPPORT1 FIXED BUT FX MX MY MZ2 FIXED BUT MY MZ*LOAD 1JOINT LOAD1 FX 1400*LOAD 2JOINT LOAD1 MZ 2002 MZ 200*LOAD 3JOINT LOAD1 MY 702 MY 70*LOAD COMB 41 1 2 1 3 1*PERF ANALYLOAD LIST 4PRINT MEMB FORCE*PARAMETERCODE LRFDFYLD 7200 ALLTRACK 2 ALLCHECK CODE ALL*FINISH


***************************************************** ** STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:27: 5 ** *



* USER ID: Bentley Systems, Inc. *****************************************************

1. STAAD SPACE AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_COMB3.STD

2. *3. * INPUT FILE: AISC_LRFD_COMB3.STD4. *5. * EXAMPLE PROBLEM 6.2, PAGE 6-6, AISC LRFD 3RD ED.6. * INTERACTION RATIO SHOULD BE ABOUT 0.9737. *8. UNIT KIP FT9. JOINT COORDINATES10. 1 0 0 0 ; 2 14 011. *12. MEMBER INCIDENCES13. 1 1 214. *15. MEMB PROP AMERICAN16. 1 TA ST W14X17617. *18. CONST19. E STEEL ALL20. POISS STEEL ALL21. *22. SUPPORT23. 1 FIXED BUT FX MX MY MZ24. 2 FIXED BUT MY MZ25. *26. LOAD 127. JOINT LOAD28. 1 FX 140029. *30. LOAD 231. JOINT LOAD32. 1 MZ 20033. 2 MZ 20034. *35. LOAD 336. JOINT LOAD37. 1 MY 7038. 2 MY 70AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 2

*39. *40. LOAD COMB 441. 1 1 2 1 3 142. *43. PERF ANALY





44. LOAD LIST 445. PRINT MEMB FORCE

MEMB FORCEAXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 3

*

490 — STAAD.Pro



MEMBER END FORCES STRUCTURE TYPE = SPACE-----------------ALL UNITS ARE -- KIP FEET (LOCAL )MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z

1 4 1 1400.00 28.57 -10.00 0.00 70.00 200.002 -1400.00 -28.57 10.00 0.00 70.00 200.00

************** END OF LATEST ANALYSIS RESULT **************46. *47. PARAMETER48. CODE LRFD49. FYLD 7200 ALL50. TRACK 2 ALL51. CHECK CODE ALL

STEEL DESIGNAXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 4

*


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.5180E+2 || * | ST W14X176 | | --Z AY=0.1263E+2 ||DESIGN CODE * | | | AZ=0.2733E+2 || LRFD 2001 * =============================== ===|=== PY=0.1630E+3 || * PZ=0.3200E+3 || * |<---LENGTH (FT)= 14.00 --->| RY=0.4022E+1 ||************* RZ=0.6427E+1 || || 200.0 (KIP-FEET) ||PARAMETER |L4 L4 CAPACITIES ||IN KIP INCH | L4 L4 IN KIP INCH ||--------------- + -------------|| KL/R-Y= 41.77 | L4 L4 PNC=0.1938E+4|| KL/R-Z= 26.14 + pnc=0.1400E+4|| UNL = 168.00 | L4 L4 PNT=0.2331E+4|| CB = 1.00 + L4 L4 pnt=0.0000E+0|| PHIC = 0.85 | MNZ=0.1440E+5|| PHIB = 0.90 + mnz=0.2400E+4|| FYLD = 50.00 | L4 MNY=0.7229E+4|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.8400E+3|| DFF = 0.00 -11.1 VN =0.3411E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.2857E+2|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 1400.0 28.6 10.0 70.0 200.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 4 4 4 4 4 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== |



| PASS LRFD-H1-1A-C 0.974 4 || 1400.00 C 70.00 200.00 0.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************52. *53. FINISH


AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 5*


Steel Design per AISC LRFD 26ObjectiveTo select the lightest ASTM A992 W14 section capable of carrying an axial compression plusbiaxial bending.


ProblemFy = 50 ksi

Pu = 400 kips

Muy = 80 ft-kips, Muz = 250 ft-kips

Lb = 14 ft

Reverse curvature bending with equal end moments for both axis.

Comparison


Selection section W14x99 W14x99 none


STAAD InputSTAAD SPACE AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED** INPUT FILE: AISC_LRFD_COMB4.STD

492 — STAAD.Pro



** EXAMPLE PROBLEM 6.4, PAGE 6-9, AISC LRFD 3RD ED.* THE LIGHTEST SUITABLE SECTION SHOULD BE A W14X99*UNIT KIP FTJOINT COORDINATES1 0 0 0 ; 2 14 0*MEMBER INCIDENCES1 1 2*MEMB PROP AMERICAN1 TA ST W14X90*CONSTE STEEL ALLPOISS STEEL ALL*SUPPORT1 FIXED*LOAD 1JOINT LOAD2 FX -4002 MZ 2502 MY 80*PERF ANALY*PARAMETERCODE LRFDFYLD 7200 ALLTRACK 2 ALLSELECT ALL*FINISH



1. STAAD SPACE AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD EDINPUT FILE: AISC_LRFD_COMB4.STD

2. *3. * INPUT FILE: AISC_LRFD_COMB4.STD4. *5. * EXAMPLE PROBLEM 6.4, PAGE 6-9, AISC LRFD 3RD ED.6. * THE LIGHTEST SUITABLE SECTION SHOULD BE A W14X997. *8. UNIT KIP FT9. JOINT COORDINATES10. 1 0 0 0 ; 2 14 011. *12. MEMBER INCIDENCES



13. 1 1 214. *15. MEMB PROP AMERICAN16. 1 TA ST W14X9017. *18. CONST19. E STEEL ALL20. POISS STEEL ALL21. *22. SUPPORT23. 1 FIXED24. *25. LOAD 126. JOINT LOAD27. 2 FX -40028. 2 MZ 25029. 2 MY 8030. *31. PERF ANALYAXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 2

*





32. *33. PARAMETER34. CODE LRFD35. FYLD 7200 ALL36. TRACK 2 ALL37. SELECT ALL

STEEL DESIGNAXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 3

*

STAAD.PRO MEMBER SELECTION - (LRFD 3RD EDITION) v1.0***********************************************

|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN INCH UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AISC SECTIONS | | AX=0.2910E+2 || * | ST W14X99 | | --Z AY=0.6868E+1 ||DESIGN CODE * | | | AZ=0.1515E+2 || LRFD 2001 * =============================== ===|=== PY=0.8360E+2 || * PZ=0.1730E+3 || * |<---LENGTH (FT)= 14.00 --->| RY=0.3717E+1 ||************* RZ=0.6176E+1 || || 250.0 (KIP-FEET) ||PARAMETER |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 CAPACITIES ||IN KIP INCH |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 IN KIP INCH ||--------------- +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 -------------|| KL/R-Y= 45.20 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 PNC=0.1065E+4|| KL/R-Z= 27.20 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 pnc=0.4000E+3|| UNL = 168.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 PNT=0.1310E+4|| CB = 1.00 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 pnt=0.0000E+0|| PHIC = 0.85 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 MNZ=0.7717E+4|

494 — STAAD.Pro



| PHIB = 0.90 +L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 mnz=0.3000E+4|| FYLD = 50.00 |L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 L1 MNY=0.3709E+4|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| mny=0.9600E+3|| DFF = 0.00 250.0 VN =0.1854E+3|| dff = 0.00 ABSOLUTE MZ ENVELOPE vn =0.0000E+0|| (WITH LOAD NO.) || || MAX FORCE/ MOMENT SUMMARY (KIP-FEET) || ------------------------- || || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || || VALUE 400.0 0.0 0.0 80.0 250.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 1 1 || ||**************************************************************************||* *||* DESIGN SUMMARY (KIP-FEET) *||* -------------- *||* *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *|| FX MY MZ LOCATION || ====================================================== || PASS LRFD-H1-1A-C 0.951 1 || 400.00 C -80.00 -250.00 0.00 ||* *||**************************************************************************|| ||--------------------------------------------------------------------------|************** END OF TABULATED RESULT OF DESIGN **************38. *39. FINISH******************************************************************************WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.



AXIAL COMPRESSION + BIAXIAL BENDING PER AISC LRFD 3RD ED -- PAGE NO. 4*




496 — STAAD.Pro


Notes

12Steel Design per AS 4100-1998





Steel Design per AS 4100-1998 1ObjectiveTo check the bending capacity of the UB shape per AS4100-1998.

ReferenceB.Gorenc, R.Tinyou and A.Syam, Steel Designer's Handbook, 6th edition, UNSW Press, problem 5.3,page 115.


ProblemFigure 12-1: Beam with load cases as shown

Comparison


Bending capacity, Msz (kN-m) 209.4 209.9 none

Bending moment (kN-m) 124.6 124.6 none


The reference book does not compute the ratio. STAAD computes the ratio per the firstequation of clause 8.3.4 as 0.617.

STAAD Input


STAAD PLANE BENDING CAPACITY PER AS4100 1998** INPUT FILE: AS4100_BEN1.STD** REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,* 6TH EDITION, EXAMPLE PROBLEM 5.3, PAGE 115** OBJECTIVE : TO DETERMINE THE ADEQUACY OF A UB SHAPE IN BENDING PER* THE AS4100-1998 CODE**INPUT WIDTH 79UNIT METER KN

498 — STAAD.Pro

12 Steel Design per AS 4100-1998

Steel Design per AS 4100-1998 1

JOINT COORDINATES1 0 0 0; 2 8 0 0MEMBER INCIDENCES1 1 2DEFINE MATERIAL STARTISOTROPIC STEELE 1.99947E+008POISSON 0.3DENSITY 76.8191ALPHA 6.5E-006DAMP 0.03END DEFINE MATERIAL*MEMBER PROPERTY AUSTRALIAN1 TABLE ST UB360X50.7*CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 2 PINNEDLOAD 1 DEAD LOADMEMBER LOAD1 UNI GY -3.7LOAD 2 LIVE LOADMEMBER LOAD1 UNI GY -4.81 CON GY -10LOAD COMBINATION 31 1.25 2 1.5PERFORM ANALYSISUNIT NEWTON MMPARAMETERCODE AUSTRALIANFYLD 260 ALLALM 1.41 ALLUNT 4000 ALLLZ 5880 ALLLY 5880 ALLTRACK 2.0 ALLCHECK CODE MEMB 1FINISH



1. STAAD PLANE BENDING CAPACITY PER AS4100 1998INPUT FILE: AS4100_BEN1.STD

2. *3. * INPUT FILE: AS4100_BEN1.STD4. *5. * REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,6. * 6TH EDITION, EXAMPLE PROBLEM 5.3, PAGE 1157. *



8. * OBJECTIVE : TO DETERMINE THE ADEQUACY OF A UB SHAPE IN BENDING PER9. * THE AS4100-1998 CODE10. *11. *12. INPUT WIDTH 7913. UNIT METER KN14. JOINT COORDINATES15. 1 0 0 0; 2 8 0 016. MEMBER INCIDENCES17. 1 1 218. DEFINE MATERIAL START19. ISOTROPIC STEEL20. E 1.99947E+00821. POISSON 0.322. DENSITY 76.819123. ALPHA 6.5E-00624. DAMP 0.0325. END DEFINE MATERIAL26. *27. MEMBER PROPERTY AUSTRALIAN28. 1 TABLE ST UB360X50.729. *30. CONSTANTS31. MATERIAL STEEL MEMB 132. SUPPORTS33. 1 2 PINNED34. LOAD 1 DEAD LOAD35. MEMBER LOAD36. 1 UNI GY -3.737. LOAD 2 LIVE LOAD38. MEMBER LOADBENDING CAPACITY PER AS4100 1998 -- PAGE NO. 2

*39. 1 UNI GY -4.840. 1 CON GY -1041. LOAD COMBINATION 342. 1 1.25 2 1.543. PERFORM ANALYSIS





44. UNIT NEWTON MM45. PARAMETER46. CODE AUSTRALIAN47. FYLD 260 ALL48. ALM 1.41 ALL49. UNT 4000 ALL50. LZ 5880 ALL51. LY 5880 ALL52. TRACK 2.0 ALL53. CHECK CODE MEMB 1

STEEL DESIGNBENDING CAPACITY PER AS4100 1998 -- PAGE NO. 3

*STAAD.Pro CODE CHECKING - ( AS4100-1998 ) V2.3****************************************************

|--------------------------------------------------------------------------|| Y PROPERTIES |

500 — STAAD.Pro



|************* | IN CM UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AUSTRALIAN SECTIONS | | AX=0.6470E+2 || * | ST UB360X50.7 | | --Z AY=0.2599E+2 ||DESIGN CODE * | | | AZ=0.2622E+2 ||AS4100 1998 * =============================== ===|=== PY=0.1730E+3 || * PZ=0.8970E+3 || * |<---LENGTH (ME= 8.00 --->| RY=0.3852E+1 ||************* RZ=0.1481E+2 || Iw=0.2848E+6 || 124.6( KN-METR) ||PARAMETER | 3 FORCE/MOMENT ||IN NEWTON MM | 3 3 IN KN METRE ||--------------- + -------------|| KL/R-Y= 152.6 | 3 3 PNC=0.4162E+3|| KL/R-Z= 39.7 + 3 3 PNT=0.1514E+4|| UNL = 4000.0 | pn =0.0000E+0|| MAIN = 0.0 + MNZ=0.1850E+3|| PHI = 0.90 | 3 3 mnz=-.1246E+3|| FULT = 440.0 + MNY=0.3941E+2|| FYLD = 260.0 | 0 0 mny=0.0000E+0|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| VZ =0.3681E+3|| SKT = 1.00 -6.9 vz =0.0000E+0|| SKL = 1.00 ABSOLUTE MZ ENVELOPE VY =0.3649E+3|| SKR = 1.00 (WITH LOAD NO.) vy =0.7500E+1|| || Section Type: Compact - about Z axis; Compact - about Y axis || || Parameters used to calculate RATIO || ---------------------------------- || Ns=0.1662E+4 Msz=0.2332E+3 Msy=0.4379E+2 Mbz=0.2056E+3 Mby=0.4379E+2 || Miz=0.2332E+3 Miy=0.4379E+2 Moz=0.2056E+3 Moy=0.4379E+2 || Nciz=0.1502E+4 Nciy=0.4624E+3 Ncz=0.1502E+4 Ncy=0.4624E+3 || ALPHA,M= 1.410 ALPHA,B= 0.000 ALPHA,SZ= 0.625 ALPHA,SY= 0.941 || || MAX FORCE/ MOMENT SUMMARY ( KN-METR) || ------------------------- || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || VALUE 0.0 54.8 0.0 0.0 124.6 || LOCATION 0.0 0.0 0.0 0.0 4.0 || LOADING 0 3 0 0 3 ||**************************************************************************||* DESIGN SUMMARY ( KN-METR) *||* -------------- *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *||* FX MY MZ LOCATION *||* ====================================================== *||* PASS AS-8.4.4.1 0.674 3 *||* 0.00 C 0.0 -124.6 4.00 *||**************************************************************************||--------------------------------------------------------------------------|

BENDING CAPACITY PER AS4100 1998 -- PAGE NO. 4*************** END OF TABULATED RESULT OF DESIGN **************54. FINISH


************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.



* http://www.bentley.com *************************************************************

Steel Design per AS 4100-1998 2ObjectiveTo check the capacity of a member in axial compression plus bending per AS4100-1998.


ProblemDescription

Problem values

502 — STAAD.Pro



Figure 12-2: Compression member designed per AS 4100

Comparison


Ratio 0.86 0.919 6.9%


Clause 8.3.4 has two equations for checking the ratio of the applied load and moment to sectioncapacity. STAAD.Pro considers only the first of those 2 equations. The reference book uses thesecond equation to compute the ratio



STAAD Input


STAAD SPACE COMPRESSION+BENDING PER AS4100 1998** INPUT FILE: AS4100_BEN2.STD** REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,* 6TH EDITION, EXAMPLE PROBLEM 6.3, PAGE 160** OBJECTIVE : TO DETERMINE THE ADEQUACY OF A UC SHAPE IN COMPRESSION* PLUS BENDING PER THE AS4100-1998 CODE*INPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 0 4 0MEMBER INCIDENCES1 1 2DEFINE MATERIAL STARTISOTROPIC STEELE 1.99947E+008POISSON 0.3DENSITY 76.8191ALPHA 6.5E-006DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY AUSTRALIAN1 TABLE ST UC150X30.0CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 FIXEDLOAD 1 DEAD LOADJOINT LOAD2 FY -124.12 MZ 352 MX 3.76PERFORM ANALYSISUNIT NEWTON MMPARAMETERCODE AUSTRALIANKZ 1.16 ALLKY 0.85 ALLNSF 1.0 ALLALM 2.5 ALLTRACK 2 MEMB 1CHECK CODE MEMB 1FINISH



504 — STAAD.Pro



****************************************************

1. STAAD SPACE COMPRESSION+BENDING PER AS4100 1998INPUT FILE: AS4100_BEN2.STD

2. *3. * INPUT FILE: AS4100_BEN2.STD4. *5. * REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,6. * 6TH EDITION, EXAMPLE PROBLEM 6.3, PAGE 1607. *8. * OBJECTIVE : TO DETERMINE THE ADEQUACY OF A UC SHAPE IN COMPRESSION9. * PLUS BENDING PER THE AS4100-1998 CODE10. *11. INPUT WIDTH 7912. UNIT METER KN13. JOINT COORDINATES14. 1 0 0 0; 2 0 4 015. MEMBER INCIDENCES16. 1 1 217. DEFINE MATERIAL START18. ISOTROPIC STEEL19. E 1.99947E+00820. POISSON 0.321. DENSITY 76.819122. ALPHA 6.5E-00623. DAMP 0.0324. END DEFINE MATERIAL25. MEMBER PROPERTY AUSTRALIAN26. 1 TABLE ST UC150X30.027. CONSTANTS28. MATERIAL STEEL MEMB 129. SUPPORTS30. 1 FIXED31. LOAD 1 DEAD LOAD32. JOINT LOAD33. 2 FY -124.134. 2 MZ 3535. 2 MX 3.7636. PERFORM ANALYSISCOMPRESSION+BENDING PER AS4100 1998 -- PAGE NO. 2

*





37. UNIT NEWTON MM38. PARAMETER39. CODE AUSTRALIAN40. KZ 1.16 ALL41. KY 0.85 ALL42. NSF 1.0 ALL43. ALM 2.5 ALL44. TRACK 2 MEMB 145. CHECK CODE MEMB 1

STEEL DESIGNCOMPRESSION+BENDING PER AS4100 1998 -- PAGE NO. 3




|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN CM UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AUSTRALIAN SECTIONS | | AX=0.3860E+2 || * | ST UC150X30.0 | | --Z AY=0.1043E+2 ||DESIGN CODE * | | | AZ=0.1918E+2 ||AS4100 1998 * =============================== ===|=== PY=0.1120E+3 || * PZ=0.2500E+3 || * |<---LENGTH (ME= 4.00 --->| RY=0.3816E+1 ||************* RZ=0.6752E+1 || Iw=0.3103E+5 || 35.0( KN-METR) ||PARAMETER | 1 1 1 1 1 1 1 1 1 1 1 FORCE/MOMENT ||IN NEWTON MM | 1 1 1 1 1 1 1 1 1 1 1 IN KN METRE ||--------------- + 1 1 1 1 1 1 1 1 1 1 1 -------------|| KL/R-Y= 89.1 | 1 1 1 1 1 1 1 1 1 1 1 PNC=0.5953E+3|| KL/R-Z= 68.7 + 1 1 1 1 1 1 1 1 1 1 1 PNT=0.1112E+4|| UNL = 4000.0 | 1 1 1 1 1 1 1 1 1 1 1 pn =0.1241E+3|| MAIN = 0.0 + 1 1 1 1 1 1 1 1 1 1 1 MNZ=0.7200E+2|| PHI = 0.90 | 1 1 1 1 1 1 1 1 1 1 1 mnz=-.3500E+2|| FULT = 440.0 + 1 1 1 1 1 1 1 1 1 1 1 MNY=0.3174E+2|| FYLD = 320.0 | 1 1 1 1 1 1 1 1 1 1 1 mny=0.3760E+1|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| VZ =0.3314E+3|| SKT = 1.00 35.0 vz =0.0000E+0|| SKL = 1.00 ABSOLUTE MZ ENVELOPE VY =0.1802E+3|| SKR = 1.00 (WITH LOAD NO.) vy =0.0000E+0|| || Section Type: Compact - about Z axis; Compact - about Y axis || || Parameters used to calculate RATIO || ---------------------------------- || Ns=0.1235E+4 Msz=0.8000E+2 Msy=0.3526E+2 Mbz=0.8000E+2 Mby=0.3526E+2 || Miz=0.6836E+2 Miy=0.2791E+2 Moz=0.6332E+2 Moy=0.2961E+2 || Nciz=0.9475E+3 Nciy=0.6614E+3 Ncz=0.8602E+3 Ncy=0.6614E+3 || ALPHA,M= 2.500 ALPHA,B= 0.000 ALPHA,SZ= 0.645 ALPHA,SY= 0.837 || || MAX FORCE/ MOMENT SUMMARY ( KN-METR) || ------------------------- || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || VALUE 124.1 0.0 0.0 3.8 35.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 1 1 ||**************************************************************************||* DESIGN SUMMARY ( KN-METR) *||* -------------- *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *||* FX MY MZ LOCATION *||* ====================================================== *||* PASS AS-8.3.4 0.984 1 *||* 124.10 C 3.8 -35.0 0.00 *||**************************************************************************||--------------------------------------------------------------------------|

COMPRESSION+BENDING PER AS4100 1998 -- PAGE NO. 4*************** END OF TABULATED RESULT OF DESIGN **************46. FINISH



506 — STAAD.Pro




Steel Design per AS 4100-1998 3ObjectiveTo check the tensile capacity of a single angle per AS4100-1998.


ProblemFigure 12-3: Tension member designed per AS 4100

Comparison


Tensile capacity (kN) φ475.0 427.4 see note (a)

Applied tensile load (kN) 300.3 300.3 none

Ratio 0.703a 0.703 none


a. The reference book reports that the tensile capacity should be the product of φ and 475.0.If we use a φ of 0.9, the tensile capacity is ( φ475.0)= (0.9 * 475.0)= 427.4 KN. The STAADvalue then compares well with the textbook solution.

STAAD Input


STAAD SPACE AXIAL TENSILE CAPACITY PER AS4100 1998** INPUT FILE: AS4100_TEN1.STD** REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,* 6TH EDITION, EXAMPLE PROBLEM 7.2, PAGE 186** OBJECTIVE : TO DETERMINE THE CAPACITY OF A SINGLE ANGLE IN TENSION* PER THE AS4100-1998 CODE*INPUT WIDTH 79UNIT METER KN



JOINT COORDINATES1 0 0 0; 2 4 0 0MEMBER INCIDENCES1 1 2DEFINE MATERIAL STARTISOTROPIC STEELE 1.99947E+008POISSON 0.3DENSITY 76.8191ALPHA 6.5E-006DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY AUSTRALIAN1 TABLE ST A125X125X8CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 FIXEDLOAD 1 DEAD LOADJOINT LOAD2 FX 300.3PERFORM ANALYSISUNIT MMS NEWTONPARAMETERCODE AUSTRALIANTRACK 2.0 ALLCHECK CODE MEMB 1FINISH



1. STAAD SPACE AXIAL TENSILE CAPACITY PER AS4100 1998INPUT FILE: AS4100_TEN1.STD

2. *3. * INPUT FILE: AS4100_TEN1.STD4. *5. * REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,6. * 6TH EDITION, EXAMPLE PROBLEM 7.2, PAGE 1867. *8. * OBJECTIVE : TO DETERMINE THE CAPACITY OF A SINGLE ANGLE IN TENSION9. * PER THE AS4100-1998 CODE10. *11. INPUT WIDTH 7912. UNIT METER KN13. JOINT COORDINATES14. 1 0 0 0; 2 4 0 015. MEMBER INCIDENCES16. 1 1 217. DEFINE MATERIAL START18. ISOTROPIC STEEL19. E 1.99947E+00820. POISSON 0.3

508 — STAAD.Pro



21. DENSITY 76.819122. ALPHA 6.5E-00623. DAMP 0.0324. END DEFINE MATERIAL25. MEMBER PROPERTY AUSTRALIAN26. 1 TABLE ST A125X125X827. CONSTANTS28. MATERIAL STEEL MEMB 129. SUPPORTS30. 1 FIXED31. LOAD 1 DEAD LOAD32. JOINT LOAD33. 2 FX 300.334. PERFORM ANALYSISAXIAL TENSILE CAPACITY PER AS4100 1998 -- PAGE NO. 2

*





35. UNIT MMS NEWTON36. PARAMETER37. CODE AUSTRALIAN38. TRACK 2.0 ALL39. CHECK CODE MEMB 1

STEEL DESIGNAXIAL TENSILE CAPACITY PER AS4100 1998 -- PAGE NO. 3


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN CM UNIT || * |=============================| ==| |== ------------ ||MEMBER 1 * | AUSTRALIAN SECTIONS | | | AX=0.1900E+2 || * | ST A125X125X8 | | | --Z AY=0.6500E+1 ||DESIGN CODE * | | | | AZ=0.6500E+1 ||AS4100 1998 * =============================== ==| |== PY=0.9409E+2 || * PZ=0.4381E+2 || * |<---LENGTH (ME= 4.00 --->| RY=0.4931E+1 ||************* RZ=0.2480E+1 || Iw=0.0000E+0 || 0.0( KN-METR) ||PARAMETER | 0 0 0 0 0 0 0 0 0 0 0 FORCE/MOMENT ||IN NEWTON MM | 0 0 0 0 0 0 0 0 0 0 0 IN KN METRE ||--------------- + 0 0 0 0 0 0 0 0 0 0 0 -------------|| KL/R-Y= 81.1 | 0 0 0 0 0 0 0 0 0 0 0 PNC=0.1024E+3|| KL/R-Z= 161.3 + 0 0 0 0 0 0 0 0 0 0 0 PNT=0.5472E+3|| UNL = 4000.0 | 0 0 0 0 0 0 0 0 0 0 0 pn =-.3003E+3|| MAIN = 0.0 + 0 0 0 0 0 0 0 0 0 0 0 MNZ=0.7201E+1|| PHI = 0.90 | 0 0 0 0 0 0 0 0 0 0 0 mnz=0.0000E+0|| FULT = 440.0 + 0 0 0 0 0 0 0 0 0 0 0 MNY=0.1156E+2|| FYLD = 320.0 | 0 0 0 0 0 0 0 0 0 0 0 mny=0.0000E+0|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| VZ =0.1123E+3|| SKT = 1.00 0.0 vz =0.0000E+0|| SKL = 1.00 ABSOLUTE MZ ENVELOPE VY =0.1123E+3|| SKR = 1.00 (WITH LOAD NO.) vy =0.0000E+0|| || Section Type: Noncompact - about Z axis; Noncompact - about Y axis |



| || Parameters used to calculate RATIO || ---------------------------------- || Ns=0.6045E+3 Msz=0.1013E+2 Msy=0.2174E+2 Mbz=0.8001E+1 Mby=0.1284E+2 || Miz=0.0000E+0 Miy=0.0000E+0 Moz=0.0000E+0 Moy=0.0000E+0 || Nciz=0.1138E+3 Nciy=0.2897E+3 Ncz=0.1138E+3 Ncy=0.2897E+3 || ALPHA,M= 1.000 ALPHA,B= 1.000 ALPHA,SZ= 0.790 ALPHA,SY= 0.591 || || MAX FORCE/ MOMENT SUMMARY ( KN-METR) || ------------------------- || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || VALUE -300.3 0.0 0.0 0.0 0.0 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 0 ||**************************************************************************||* DESIGN SUMMARY ( KN-METR) *||* -------------- *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *||* FX MY MZ LOCATION *||* ====================================================== *||* PASS TENSION 0.549 1 *||* 300.30 T 0.0 0.0 0.00 *||**************************************************************************||--------------------------------------------------------------------------|

AXIAL TENSILE CAPACITY PER AS4100 1998 -- PAGE NO. 4*************** END OF TABULATED RESULT OF DESIGN **************40. FINISH



Steel Design per AS 4100-1998 4ObjectiveTo check the capacity of a member in tension plus bending per AS4100-1998.


510 — STAAD.Pro



ProblemFigure 12-4: Member under combined stress designed per AS 4100

Comparison


Ratio 0.814 0.803 1.4%


STAAD Input


STAAD SPACE TENSION+BENDING PER AS4100 1998** INPUT FILE: AS4100_BEN3.STD** REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,* 6TH EDITION, EXAMPLE PROBLEM 7.1, PAGE 184** OBJECTIVE : TO DETERMINE THE CAPACITY OF A UC SHAPE IN TENSION* PLUS BENDING PER THE AS4100-1998 CODE*INPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 4 0 0MEMBER INCIDENCES1 1 2DEFINE MATERIAL STARTISOTROPIC STEELE 1.99947E+008POISSON 0.3DENSITY 76.8191ALPHA 6.5E-006DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY AUSTRALIAN1 TABLE ST UC250X89.5CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 FIXEDLOAD 1 DEAD LOADJOINT LOAD2 FX 433.72 MZ 175.4PERFORM ANALYSISUNIT MMS NEWTONPARAMETER



CODE AUSTRALIANNSF 1 ALLTRACK 2 MEMB 1CHECK CODE MEMB 1FINISH



1. STAAD SPACE TENSION+BENDING PER AS4100 1998INPUT FILE: AS4100_BEN3.STD

2. *3. * INPUT FILE: AS4100_BEN3.STD4. *5. * REFERENCE : STEEL DESIGNER'S HANDBOOK, B.GORENC, R.TINYOU AND A.SYAM,6. * 6TH EDITION, EXAMPLE PROBLEM 7.1, PAGE 1847. *8. * OBJECTIVE : TO DETERMINE THE CAPACITY OF A UC SHAPE IN TENSION9. * PLUS BENDING PER THE AS4100-1998 CODE10. *11. INPUT WIDTH 7912. UNIT METER KN13. JOINT COORDINATES14. 1 0 0 0; 2 4 0 015. MEMBER INCIDENCES16. 1 1 217. DEFINE MATERIAL START18. ISOTROPIC STEEL19. E 1.99947E+00820. POISSON 0.321. DENSITY 76.819122. ALPHA 6.5E-00623. DAMP 0.0324. END DEFINE MATERIAL25. MEMBER PROPERTY AUSTRALIAN26. 1 TABLE ST UC250X89.527. CONSTANTS28. MATERIAL STEEL MEMB 129. SUPPORTS30. 1 FIXED31. LOAD 1 DEAD LOAD32. JOINT LOAD33. 2 FX 433.734. 2 MZ 175.435. PERFORM ANALYSISTENSION+BENDING PER AS4100 1998 -- PAGE NO. 2

*



512 — STAAD.Pro





36. UNIT MMS NEWTON37. PARAMETER38. CODE AUSTRALIAN39. NSF 1 ALL40. TRACK 2 MEMB 141. CHECK CODE MEMB 1

STEEL DESIGNTENSION+BENDING PER AS4100 1998 -- PAGE NO. 3


|--------------------------------------------------------------------------|| Y PROPERTIES ||************* | IN CM UNIT || * |=============================| ===|=== ------------ ||MEMBER 1 * | AUSTRALIAN SECTIONS | | AX=0.1140E+3 || * | ST UC250X89.5 | | --Z AY=0.2730E+2 ||DESIGN CODE * | | | AZ=0.5905E+2 ||AS4100 1998 * =============================== ===|=== PY=0.5750E+3 || * PZ=0.1230E+4 || * |<---LENGTH (ME= 4.00 --->| RY=0.6516E+1 ||************* RZ=0.1120E+2 || Iw=0.7127E+6 || 175.4( KN-METR) ||PARAMETER | 1 1 1 1 1 1 1 1 1 1 1 FORCE/MOMENT ||IN NEWTON MM | 1 1 1 1 1 1 1 1 1 1 1 IN KN METRE ||--------------- + 1 1 1 1 1 1 1 1 1 1 1 -------------|| KL/R-Y= 61.4 | 1 1 1 1 1 1 1 1 1 1 1 PNC=0.2240E+4|| KL/R-Z= 35.7 + 1 1 1 1 1 1 1 1 1 1 1 PNT=0.2873E+4|| UNL = 4000.0 | 1 1 1 1 1 1 1 1 1 1 1 pn =-.4337E+3|| MAIN = 0.0 + 1 1 1 1 1 1 1 1 1 1 1 MNZ=0.2600E+3|| PHI = 0.90 | 1 1 1 1 1 1 1 1 1 1 1 mnz=-.1754E+3|| FULT = 440.0 + 1 1 1 1 1 1 1 1 1 1 1 MNY=0.1332E+3|| FYLD = 280.0 | 1 1 1 1 1 1 1 1 1 1 1 mny=0.0000E+0|| NSF = 1.00 +---+---+---+---+---+---+---+---+---+---| VZ =0.1020E+4|| SKT = 1.00 175.4 vz =0.0000E+0|| SKL = 1.00 ABSOLUTE MZ ENVELOPE VY =0.4717E+3|| SKR = 1.00 (WITH LOAD NO.) vy =0.0000E+0|| || Section Type: Compact - about Z axis; Compact - about Y axis || || Parameters used to calculate RATIO || ---------------------------------- || Ns=0.3192E+4 Msz=0.3444E+3 Msy=0.1588E+3 Mbz=0.2889E+3 Mby=0.1480E+3 || Mrz=0.3055E+3 Mry=0.1409E+3 Moz=0.3366E+3 Moy=0.1766E+3 || Nciz=0.2917E+4 Nciy=0.2489E+4 Ncz=0.2917E+4 Ncy=0.2489E+4 || ALPHA,M= 0.981 ALPHA,B= 0.000 ALPHA,SZ= 0.855 ALPHA,SY= 0.949 || || MAX FORCE/ MOMENT SUMMARY ( KN-METR) || ------------------------- || AXIAL SHEAR-Y SHEAR-Z MOMENT-Y MOMENT-Z || VALUE -433.7 0.0 0.0 0.0 175.4 || LOCATION 0.0 0.0 0.0 0.0 0.0 || LOADING 1 0 0 0 1 ||**************************************************************************||* DESIGN SUMMARY ( KN-METR) *||* -------------- *||* RESULT/ CRITICAL COND/ RATIO/ LOADING/ *||* FX MY MZ LOCATION *||* ====================================================== *||* PASS AS-5.1 0.675 1 *|



|* 433.70 T 0.0 -175.4 0.00 *||**************************************************************************||--------------------------------------------------------------------------|

TENSION+BENDING PER AS4100 1998 -- PAGE NO. 4*************** END OF TABULATED RESULT OF DESIGN **************42. FINISH



514 — STAAD.Pro



13Steel Design per BS 5950-1:2000








Steel Design per BS 5950-1:2000 1ObjectiveA 6.5 m, simply-supported beam is fully restrained along its length. The beam is designed in S275steel for the loading described.

ReferenceSteelwork Design Guide to BS 5950-1:2000, Volume 2, Worked Examples, SCI publication P326,Example 2, The Steel Construction Institute.

ProblemDead Loads, γfd = 1.4:

l Distributed load (including s/w) wd = 15 kN/m

l Point Load Wd = 40 kN

Imposed Loads, γfi = 1.6:

l Distributed load Wi = 30 kN/m

l Point Load Wi = 50 kN


Comparison


Shear capacity, Pv(kN) 888 888.4 none

Moment capacity, Mcx (kN-m) 649 649 none

Total deflection, δ (mm) 8.69 9.25a 6.4%

Deflection limit (mm) 18.1 18.056 none

Table 13-1: Comparison of results for BS 5950 beam 1

a. STAAD.Pro includes effects of shear deformation, resulting in a higher calculatedmaximum deflection.

STAAD InputTRACK 2 ALL

Maximum detail output

UNI 0 ALL

Identifies the beam as fully restrained

DEF 360 ALL

Limiting ratio of beam length to maximum deflection

DJ1 1 ALL

Identifies starting joint of "physical member" for deflection check

DJ2 3 ALL

Identifies ending joint of "physical member" for deflection check


STAAD SPACESTART JOB INFORMATIONJOB NAME Example no. 2JOB CLIENT The Steel Construction InstituteJOB COMMENT Simply supported restrained beamENGINEER DATE Jun-2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KN*********************************************JOINT COORDINATES1 0 0 0; 2 3.25 0 0; 3 6.5 0 0;MEMBER INCIDENCES1 1 2; 2 2 3;DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03END DEFINE MATERIAL

516 — STAAD.Pro

13 Steel Design per BS 5950-1:2000

Steel Design per BS 5950-1:2000 1

MEMBER PROPERTY BRITISH1 2 TABLE ST UB533X210X92CONSTANTSMATERIAL STEEL MEMB 1 2SUPPORTS1 3 FIXED BUT MZ********************************************** LoadingLOAD 1 DEADJOINT LOAD2 FY -40MEMBER LOAD1 2 UNI GY -15*********************************************LOAD 2 LIVEJOINT LOAD2 FY -50MEMBER LOAD1 2 UNI GY -30*********************************************LOAD COMB 100 COMBINATION LOAD CASE 31 1.4 2 1.6PERFORM ANALYSIS PRINT STATICS CHECK********************************************** First check the forcesPARAMETERCODE BS5950TRACK 2 ALLUNL 0 ALLCHECK CODE ALL********************************************** Second check the displacementsUNIT MMS KNLOAD LIST 2PARAMETERCODE BS5950DFF 360 ALLDJ1 1 ALLDJ2 3 ALLTRACK 4 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: BS5950_Beam1.STD

2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 24. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE5. JOB COMMENT SIMPLY SUPPORTED RESTRAINED BEAM6. ENGINEER DATE JUN-2003



7. END JOB INFORMATION8. INPUT WIDTH 799. UNIT METER KN10. *********************************************11. JOINT COORDINATES12. 1 0 0 0; 2 3.25 0 0; 3 6.5 0 013. MEMBER INCIDENCES14. 1 1 2; 2 2 315. DEFINE MATERIAL START16. ISOTROPIC STEEL17. E 2.05E+00818. POISSON 0.319. DENSITY 76.819520. ALPHA 1.2E-00521. DAMP 0.0322. END DEFINE MATERIAL23. MEMBER PROPERTY BRITISH24. 1 2 TABLE ST UB533X210X9225. CONSTANTS26. MATERIAL STEEL MEMB 1 227. SUPPORTS28. 1 3 FIXED BUT MZ29. *********************************************30. * LOADING31. LOAD 1 DEAD32. JOINT LOAD33. 2 FY -4034. MEMBER LOAD35. 1 2 UNI GY -1536. *********************************************37. LOAD 2 LIVE38. JOINT LOADSTAAD SPACE -- PAGE NO. 2

39. 2 FY -5040. MEMBER LOAD41. 1 2 UNI GY -3042. *********************************************43. LOAD COMB 100 COMBINATION LOAD CASE 344. 1 1.4 2 1.645. PERFORM ANALYSIS PRINT STATICS CHECK





STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1DEADCENTER OF FORCE BASED ON Y FORCES ONLY (METE).

(FORCES IN NON-GLOBAL DIRECTIONS WILL INVALIDATE RESULTS)X = 0.325000003E+01Y = 0.000000000E+00Z = 0.000000000E+00

TOTAL APPLIED LOAD 1***TOTAL APPLIED LOAD ( KN METE ) SUMMARY (LOADING 1 )

SUMMATION FORCE-X = 0.00SUMMATION FORCE-Y = -137.50SUMMATION FORCE-Z = 0.00SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= 0.00 MY= 0.00 MZ= -446.88

518 — STAAD.Pro



TOTAL REACTION LOAD 1***TOTAL REACTION LOAD( KN METE ) SUMMARY (LOADING 1 )

SUMMATION FORCE-X = 0.00SUMMATION FORCE-Y = 137.50SUMMATION FORCE-Z = 0.00SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= 0.00 MY= 0.00 MZ= 446.87

MAXIMUM DISPLACEMENTS ( CM /RADIANS) (LOADING 1)MAXIMUMS AT NODE

X = 0.00000E+00 0Y = -5.44310E-01 2Z = 0.00000E+00 0RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= -2.45021E-03 1

STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 2LIVECENTER OF FORCE BASED ON Y FORCES ONLY (METE).


STAAD SPACE -- PAGE NO. 4TOTAL APPLIED LOAD 2***TOTAL APPLIED LOAD ( KN METE ) SUMMARY (LOADING 2 )





X = 0.00000E+00 0Y = -9.25457E-01 2Z = 0.00000E+00 0RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= 4.20036E-03 3

************ END OF DATA FROM INTERNAL STORAGE ************46. *********************************************47. * FIRST CHECK THE FORCES48. PARAMETER49. CODE BS595050. TRACK 2 ALL51. UNL 0 ALL52. CHECK CODE ALL

STEEL DESIGNSTAAD.Pro CODE CHECKING - (BSI )***********************

PROGRAM CODE REVISION V2.13_5950-1_2000STAAD SPACE -- PAGE NO. 5

ALL UNITS ARE - KN METE (UNLESS OTHERWISE Noted)MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/

FX MY MZ LOCATION=======================================================================

1 ST UB533X210X92 PASS BS-4.3.6 0.902 1000.00 0.00 585.41 0.00



=======================================================================MATERIAL DATA

Grade of steel = S 275Modulus of elasticity = 205 kN/mm2Design Strength (py) = 275 N/mm2

SECTION PROPERTIES (units - cm)Member Length = 325.00Gross Area = 117.00 Net Area = 117.00 Eff. Area = 117.00

z-z axis y-y axisMoment of inertia : 55200.004 2390.000Plastic modulus : 2360.000 355.000Elastic modulus : 2070.906 228.380Effective modulus : 2360.000 355.000Shear Area : 58.771 53.843

DESIGN DATA (units - kN,m) BS5950-1/2000Section Class : PLASTIC

z-z axis y-y axisMoment Capacity : 649.0 94.2Reduced Moment Capacity : 649.0 94.2Shear Capacity : 969.7 888.4

BUCKLING CALCULATIONS (units - kN,m)(axis nomenclature as per design code)

LTB Moment Capacity (kNm) and LTB Length (m): 649.00, 0.000LTB Coefficients & Associated Moments (kNm):mLT = 1.00 : mx = 0.00 : my = 0.00 : myx = 0.00Mlt = 585.41 : Mx = 0.00 : My = 0.00 : My = 0.00

CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):CLAUSE RATIO LOAD FX VY VZ MZ MYBS-4.2.3-(Y) 0.329 100 - 292.3 - - -BS-4.3.6 0.902 100 - 292.3 - 585.4 -Torsion and deflections have not been considered in the design.

_________________________STAAD SPACE -- PAGE NO. 6


FX MY MZ LOCATION=======================================================================

2 ST UB533X210X92 PASS BS-4.3.6 0.902 1000.00 0.00 585.41 0.00

=======================================================================MATERIAL DATA







LTB Moment Capacity (kNm) and LTB Length (m): 649.00, 0.000LTB Coefficients & Associated Moments (kNm):mLT = 1.00 : mx = 0.00 : my = 0.00 : myx = 0.00

520 — STAAD.Pro



Mlt = 585.41 : Mx = 0.00 : My = 0.00 : My = 0.00CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):CLAUSE RATIO LOAD FX VY VZ MZ MYBS-4.2.3-(Y) 0.329 100 - 292.3 - - -BS-4.3.6 0.902 100 - 68.0 - 585.4 -Torsion and deflections have not been considered in the design.


************** END OF TABULATED RESULT OF DESIGN **************53. *********************************************54. * SECOND CHECK THE DISPLACEMENTS55. UNIT MMS KN56. LOAD LIST 257. PARAMETER58. CODE BS595059. DFF 360 ALL60. DJ1 1 ALL61. DJ2 3 ALL62. TRACK 4 ALL63. CHECK CODE ALL



CLAUSE BS-2.5.1 CHECKSLENGTH UNITS - MMSMEMBER TABLE RESULT ACTUAL DEFL. DEFL.LEN/ LOAD/

DEFL. LIMIT DFF LOCATION=======================================================================

1 ST UB533X210X92 PASS 9.255 18.056 6500.000 2360.000 3249.67

2 ST UB533X210X92 PASS 9.255 18.056 6500.000 2360.000 0.00



STAAD SPACE -- PAGE NO. 9************************************************************* For technical assistance on STAAD.Pro, please visit ** http://selectservices.bentley.com/en-US/ ** ** Details about additional assistance from ** Bentley and Partners can be found at program menu ** Help->Technical Support ** ** Copyright © 1997-2013 Bentley Systems, Inc.* http://www.bentley.com *************************************************************

Steel Design per BS 5950-1:2000 2ObjectiveDesign of a 9 m, unrestrained beam with end moments. Intermediate point loads are applied tothe bottom flange. These do not provide restraint against lateral-torsional buckling. The beam isdesigned in S275 steel.





l Selfweight ws = 3 kN/m

l Point Load W1d = 40 kN



l Point Load W1i = 60 kN


Comparison


Shear capacity, Pv (kN) 636 635.9 none

Moment capacity, Mcx (kN-m) 404 404.5 none

Lateral-torsional buckling capacity, Mb(kN-m)

150 150.26 none

Table 13-2: Comparison of results for BS 5950 Beam 2



MLT 0.46ALL

Specifies the mLT value to use in the lateral-torsional buckling calculations

UNI 6.3 ALL

Specifies the lateral-torsional buckling length to be used


STAAD SPACESTART JOB INFORMATIONJOB NAME Example no. 3JOB CLIENT The Steel Construction InstituteJOB COMMENT Unrestrained beam with end momentsENGINEER DATE Jun-2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 3 0 0; 3 6 0 0; 4 9 0 0;MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4;

522 — STAAD.Pro



*************************************DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY BRITISH1 TO 3 TABLE ST UB457X191X67CONSTANTSMATERIAL STEEL MEMB 1 TO 3SUPPORTS1 4 FIXED*************************************LOAD 1 DEADJOINT LOAD2 FY -40MEMBER LOAD1 TO 3 UNI GY -3UNIT MMS KNJOINT LOAD3 FY -20UNIT METER KNLOAD 2 LIVEJOINT LOAD2 FY -60UNIT MMS KNJOINT LOAD3 FY -30UNIT METER KNLOAD COMB 100 COMBINATION LOAD CASE 31 1.4 2 1.6PERFORM ANALYSIS PRINT STATICS CHECK***************************************PARAMETERCODE BS5950TRACK 2 ALLMLT 0.46 ALLUNL 6.3 ALLCHECK CODE ALLFINISH***************************************




2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 34. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE



5. JOB COMMENT UNRESTRAINED BEAM WITH END MOMENTS6. ENGINEER DATE JUN-20037. END JOB INFORMATION8. INPUT WIDTH 799. UNIT METER KN10. JOINT COORDINATES11. 1 0 0 0; 2 3 0 0; 3 6 0 0; 4 9 0 012. MEMBER INCIDENCES13. 1 1 2; 2 2 3; 3 3 414. *************************************15. DEFINE MATERIAL START16. ISOTROPIC STEEL17. E 2.05E+00818. POISSON 0.319. DENSITY 76.819520. ALPHA 1.2E-00521. DAMP 0.0322. END DEFINE MATERIAL23. MEMBER PROPERTY BRITISH24. 1 TO 3 TABLE ST UB457X191X6725. CONSTANTS26. MATERIAL STEEL MEMB 1 TO 327. SUPPORTS28. 1 4 FIXED29. *************************************30. LOAD 1 DEAD31. JOINT LOAD32. 2 FY -4033. MEMBER LOAD34. 1 TO 3 UNI GY -335. UNIT MMS KN36. JOINT LOAD37. 3 FY -2038. UNIT METER KNSTAAD SPACE -- PAGE NO. 2

39. LOAD 2 LIVE40. JOINT LOAD41. 2 FY -6042. UNIT MMS KN43. JOINT LOAD44. 3 FY -3045. UNIT METER KN46. LOAD COMB 100 COMBINATION LOAD CASE 347. 1 1.4 2 1.648. PERFORM ANALYSIS PRINT STATICS CHECK





STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1DEADCENTER OF FORCE BASED ON Y FORCES ONLY (METE).



524 — STAAD.Pro








STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 2LIVECENTER OF FORCE BASED ON Y FORCES ONLY (METE).


STAAD SPACE -- PAGE NO. 4TOTAL APPLIED LOAD 2***TOTAL APPLIED LOAD ( KN METE ) SUMMARY (LOADING 2 )






************ END OF DATA FROM INTERNAL STORAGE ************49. ***************************************50. PARAMETER51. CODE BS595052. TRACK 2 ALL53. MLT 0.46 ALL54. UNL 6.3 ALL55. CHECK CODE ALL






FX MY MZ LOCATION=======================================================================

1 ST UB457X191X67 PASS BS-4.3.6 0.861 1000.00 0.00 280.96 0.00

=======================================================================MATERIAL DATA











FX MY MZ LOCATION=======================================================================

2 ST UB457X191X67 PASS BS-4.3.6 0.470 1000.00 0.00 153.25 0.00

=======================================================================MATERIAL DATA






526 — STAAD.Pro








FX MY MZ LOCATION=======================================================================

3 ST UB457X191X67 PASS BS-4.3.6 0.710 1000.00 0.00 231.74 0.00

=======================================================================MATERIAL DATA
















Steel Design per BS 5950-1:2000 3ObjectiveDesign of a simply-supported, 9m beam, which is laterally restrained at the ends and at thepoints of load application only.



l Selfweight ws = 3 kN/m






Comparison




Lateral-torsional bucking moment, Mb (kN-m)

397 396.6 none

Table 13-3: Comparison of results for BS 5950 beam 3



MLT _MAIN J1 U2 U3 J4

Specifies that mLT is to be calculated with the end joints fully restrained and theintermediate joints restraining the upper flange


STAAD SPACE

528 — STAAD.Pro



START JOB INFORMATIONJOB NAME Example no. 4JOB CLIENT The Steel Construction InstituteJOB COMMENT Simply supported beam with lateral restraint pointsENGINEER DATE Jun-2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 3 0 0; 3 6 0 0; 4 9 0 0;MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4;*************************************START GROUP DEFINITIONMEMBER_MAIN 1 TO 3END GROUP DEFINITION*************************************DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY BRITISH1 TO 3 TABLE ST UB457X191X82CONSTANTSMATERIAL STEEL MEMB 1 TO 3SUPPORTS1 4 FIXED BUT MZ*************************************LOAD 1 DEADJOINT LOAD2 FY -40MEMBER LOAD1 TO 3 UNI GY -3UNIT MMS KNJOINT LOAD3 FY -20UNIT METER KNLOAD 2 LIVEJOINT LOAD2 FY -60UNIT MMS KNJOINT LOAD3 FY -30LOAD COMB 100 COMBINATION LOAD CASE 31 1.4 2 1.6PERFORM ANALYSIS PRINT STATICS CHECK***************************************PARAMETERCODE BS5950TRACK 2 ALLMLT _MAIN J1 U2 U3 J4CHECK CODE ALLFINISH***************************************


***************************************************** *



* STAAD.Pro V8i SELECTseries5 ** Version 20.07.10.41 ** Proprietary Program of ** Bentley Systems, Inc. ** Date= DEC 13, 2013 ** Time= 12:28:18 ** ** USER ID: Bentley Systems, Inc. *****************************************************


2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 44. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE5. JOB COMMENT SIMPLY SUPPORTED BEAM WITH LATERAL RESTRAINT POINTS6. ENGINEER DATE JUN-20037. END JOB INFORMATION8. INPUT WIDTH 799. UNIT METER KN10. JOINT COORDINATES11. 1 0 0 0; 2 3 0 0; 3 6 0 0; 4 9 0 012. MEMBER INCIDENCES13. 1 1 2; 2 2 3; 3 3 414. *************************************15. START GROUP DEFINITION16. MEMBER17. _MAIN 1 TO 318. END GROUP DEFINITION19. *************************************20. DEFINE MATERIAL START21. ISOTROPIC STEEL22. E 2.05E+00823. POISSON 0.324. DENSITY 76.819525. ALPHA 1.2E-00526. DAMP 0.0327. END DEFINE MATERIAL28. MEMBER PROPERTY BRITISH29. 1 TO 3 TABLE ST UB457X191X8230. CONSTANTS31. MATERIAL STEEL MEMB 1 TO 332. SUPPORTS33. 1 4 FIXED BUT MZ34. *************************************35. LOAD 1 DEAD36. JOINT LOAD37. 2 FY -4038. MEMBER LOADSTAAD SPACE -- PAGE NO. 2

39. 1 TO 3 UNI GY -340. UNIT MMS KN41. JOINT LOAD42. 3 FY -2043. UNIT METER KN44. LOAD 2 LIVE45. JOINT LOAD46. 2 FY -6047. UNIT MMS KN48. JOINT LOAD49. 3 FY -3050. LOAD COMB 100 COMBINATION LOAD CASE 351. 1 1.4 2 1.652. PERFORM ANALYSIS PRINT STATICS CHECK


530 — STAAD.Pro






STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1DEADCENTER OF FORCE BASED ON Y FORCES ONLY (MMS ).


TOTAL APPLIED LOAD 1***TOTAL APPLIED LOAD ( KN MMS ) SUMMARY (LOADING 1 )


TOTAL REACTION LOAD 1***TOTAL REACTION LOAD( KN MMS ) SUMMARY (LOADING 1 )



X = 0.00000E+00 0Y = -1.23549E+00 2Z = 0.00000E+00 0RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= -4.87969E-03 1

STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 2LIVECENTER OF FORCE BASED ON Y FORCES ONLY (MMS ).


STAAD SPACE -- PAGE NO. 4TOTAL APPLIED LOAD 2***TOTAL APPLIED LOAD ( KN MMS ) SUMMARY (LOADING 2 )


TOTAL REACTION LOAD 2***TOTAL REACTION LOAD( KN MMS ) SUMMARY (LOADING 2 )



X = 0.00000E+00 0Y = -1.40263E+00 2Z = 0.00000E+00 0



RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= -5.52232E-03 1

************ END OF DATA FROM INTERNAL STORAGE ************53. ***************************************54. PARAMETER55. CODE BS595056. TRACK 2 ALL57. MLT _MAIN J1 U2 U3 J458. CHECK CODE ALL



ALL UNITS ARE - KN MMS (UNLESS OTHERWISE Noted)MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/

FX MY MZ LOCATION=======================================================================

1 ST UB457X191X82 PASS BS-4.3.6 0.830 1000.00 0.00 417800.00 0.00

=======================================================================MATERIAL DATA











FX MY MZ LOCATION=======================================================================

2 ST UB457X191X82 PASS BS-4.3.6 0.986 1000.00 0.00 417800.00 0.00

=======================================================================MATERIAL DATA

532 — STAAD.Pro













FX MY MZ LOCATION=======================================================================

3 ST UB457X191X82 PASS BS-4.3.6 0.679 1000.00 0.00 341800.03 0.00

=======================================================================MATERIAL DATA








CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):



CLAUSE RATIO LOAD FX VY VZ MZ MYBS-4.2.3-(Y) 0.160 100 - 120.2 - - -BS-4.3.6 0.679 100 - 107.6 - 341.8 -Torsion and deflections have not been considered in the design.





Steel Design per BS 5950-1:2000 4ObjectiveDesign of a simply-supported, 9m beam, which is laterally restrained at the ends and at thepoints of load application only. The beam is a universal column from S355 steel.


ProblemLoads:

l Selfweight ws' = 3.4 kN/m

l Point Load W1' = 122 kN

l Point Load W2' = 61 kN

Comparison




Lateral-torsional buckling moment, Mb(kN-m)

333 332.17 none

Table 13-4: Comparison of results for BS 5950-1 beam 4

534 — STAAD.Pro



STAAD InputSGR 1 ALL

Specifies the use of Grade S355 steel

TRACK 2 ALL


MLT _MAIN J1 U2 U3 J4

Specifies that mLT is to be calculated with the end joints fully restrained and theintermediate joints restraining the upper flange


STAAD SPACESTART JOB INFORMATIONJOB NAME Example no. 5JOB CLIENT The Steel Construction InstituteJOB COMMENT Simply supported beam with lateral restraintJOB COMMENT at load application points using a class 3JOB COMMENT UC.ENGINEER DATE Jun-2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 3 0 0; 3 6 0 0; 4 9 0 0;MEMBER INCIDENCES1 1 2; 2 2 3; 3 3 4;*************************************START GROUP DEFINITIONMEMBER_MAIN 1 TO 3END GROUP DEFINITION*************************************DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY BRITISH1 TO 3 TABLE ST UC254X254X73CONSTANTSMATERIAL STEEL MEMB 1 TO 3SUPPORTS1 4 FIXED BUT MZ*************************************LOAD 100 FACTOREDJOINT LOAD2 FY -1223 FY -61MEMBER LOAD1 TO 3 UNI GY -3.4PERFORM ANALYSIS PRINT STATICS CHECK***************************************PARAMETERCODE BS5950SGR 1 ALLTRACK 2 ALL



MLT _MAIN J1 U2 U3 J4CHECK CODE ALLFINISH




2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 54. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE5. JOB COMMENT SIMPLY SUPPORTED BEAM WITH LATERAL RESTRAINT6. JOB COMMENT AT LOAD APPLICATION POINTS USING A CLASS 37. JOB COMMENT UC.8. ENGINEER DATE JUN-20039. END JOB INFORMATION10. INPUT WIDTH 7911. UNIT METER KN12. JOINT COORDINATES13. 1 0 0 0; 2 3 0 0; 3 6 0 0; 4 9 0 014. MEMBER INCIDENCES15. 1 1 2; 2 2 3; 3 3 416. *************************************17. START GROUP DEFINITION18. MEMBER19. _MAIN 1 TO 320. END GROUP DEFINITION21. *************************************22. DEFINE MATERIAL START23. ISOTROPIC STEEL24. E 2.05E+00825. POISSON 0.326. DENSITY 76.819527. ALPHA 1.2E-00528. DAMP 0.0329. END DEFINE MATERIAL30. MEMBER PROPERTY BRITISH31. 1 TO 3 TABLE ST UC254X254X7332. CONSTANTS33. MATERIAL STEEL MEMB 1 TO 334. SUPPORTS35. 1 4 FIXED BUT MZ36. *************************************37. LOAD 100 FACTORED38. JOINT LOADSTAAD SPACE -- PAGE NO. 2

39. 2 FY -12240. 3 FY -6141. MEMBER LOAD42. 1 TO 3 UNI GY -3.443. PERFORM ANALYSIS PRINT STATICS CHECK

536 — STAAD.Pro







STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 100FACTOREDCENTER OF FORCE BASED ON Y FORCES ONLY (METE).







X = 0.00000E+00 0Y = -1.02801E+01 2Z = 0.00000E+00 0RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= -4.09617E-02 1

************ END OF DATA FROM INTERNAL STORAGE ************44. ***************************************45. PARAMETER46. CODE BS595047. SGR 1 ALL48. TRACK 2 ALL49. MLT _MAIN J1 U2 U3 J450. CHECK CODE ALL

STEEL DESIGNSTAAD SPACE -- PAGE NO. 4

STAAD.Pro CODE CHECKING - (BSI )***********************



FX MY MZ LOCATION=======================================================================

1 ST UC254X254X73 PASS BS-4.3.6 0.958 1000.00 0.00 335.60 0.00

=======================================================================MATERIAL DATA

Grade of steel = S 355Modulus of elasticity = 205 kN/mm2



Design Strength (py) = 355 N/mm2SECTION PROPERTIES (units - cm)

Member Length = 300.00Gross Area = 93.10 Net Area = 93.10 Eff. Area = 93.10


DESIGN DATA (units - kN,m) BS5950-1/2000Section Class : SEMI-COMPACT







FX MY MZ LOCATION=======================================================================

2 ST UC254X254X73 PASS BS-4.3.6 0.958 1000.00 0.00 335.60 0.00

=======================================================================MATERIAL DATA








CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):CLAUSE RATIO LOAD FX VY VZ MZ MYBS-4.2.3-(Y) 0.055 100 - 25.4 - - -

538 — STAAD.Pro



BS-4.3.6 0.958 100 - 15.2 - 335.6 -Torsion and deflections have not been considered in the design.



FX MY MZ LOCATION=======================================================================

3 ST UC254X254X73 PASS BS-4.3.6 0.784 1000.00 0.00 274.60 0.00

=======================================================================MATERIAL DATA















Steel Design per BS 5950-1:2000 5ObjectiveA 6.0 m column is pin ended about both axes and has no intermediate restraints. The column isdesigned in S275 steel for the factored loading.


ProblemPoint load, Fc = 2,500 kN

Comparison


Slenderness about strong axis, λx 38.5 38.299 none

Slenderness about weak axis, λy 63.6 63.569 none

Compression capacity, Pc (kN) 3,100 3,090 none




SGR 0 ALL

Identifies steel grade as S275


STAAD SPACESTART JOB INFORMATIONJOB NAME Example no. 10JOB CLIENT The Steel Construction InstituteJOB COMMENT Pinned column using a non-slender UC.ENGINEER DATE Jun-2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 0 6 0;MEMBER INCIDENCES1 1 2;*************************************DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3

540 — STAAD.Pro



DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY BRITISH1 TABLE ST UC356X368X129CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 FIXED*************************************LOAD 1 AXIAL LOADJOINT LOAD2 FY -2500PERFORM ANALYSIS PRINT STATICS CHECK***************************************PARAMETERCODE BS5950SGR 0 ALLTRACK 2 ALLCHECK CODE ALLFINISH



1. STAAD SPACEINPUT FILE: BS5950_Col1.STD

2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 104. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE5. JOB COMMENT PINNED COLUMN USING A NON-SLENDER UC.6. ENGINEER DATE JUN-20037. END JOB INFORMATION8. INPUT WIDTH 799. UNIT METER KN10. JOINT COORDINATES11. 1 0 0 0; 2 0 6 012. MEMBER INCIDENCES13. 1 1 214. *************************************15. DEFINE MATERIAL START16. ISOTROPIC STEEL17. E 2.05E+00818. POISSON 0.319. DENSITY 76.819520. ALPHA 1.2E-00521. DAMP 0.0322. END DEFINE MATERIAL23. MEMBER PROPERTY BRITISH24. 1 TABLE ST UC356X368X12925. CONSTANTS26. MATERIAL STEEL MEMB 1



27. SUPPORTS28. 1 FIXED29. *************************************30. LOAD 1 AXIAL LOAD31. JOINT LOAD32. 2 FY -250033. PERFORM ANALYSIS PRINT STATICS CHECKSTAAD SPACE -- PAGE NO. 2





STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1AXIAL LOADCENTER OF FORCE BASED ON Y FORCES ONLY (METE).



SUMMATION FORCE-X = 0.00SUMMATION FORCE-Y = -2500.00SUMMATION FORCE-Z = 0.00SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= 0.0000000E+00 MY= 0.0000000E+00 MZ= 0.0000000E+00


SUMMATION FORCE-X = 0.00SUMMATION FORCE-Y = 2500.00SUMMATION FORCE-Z = 0.00SUMMATION OF MOMENTS AROUND THE ORIGIN-MX= 0.0000000E+00 MY= 0.0000000E+00 MZ= 0.0000000E+00


X = 0.00000E+00 0Y = -4.46163E-01 2Z = 0.00000E+00 0RX= 0.00000E+00 0RY= 0.00000E+00 0RZ= 0.00000E+00 0

************ END OF DATA FROM INTERNAL STORAGE ************34. ***************************************35. PARAMETER36. CODE BS595037. SGR 0 ALL38. TRACK 2 ALL39. CHECK CODE ALL





FX MY MZ LOCATION

542 — STAAD.Pro



=======================================================================

1 ST UC356X368X129 PASS BS-4.7 (C) 0.809 12500.00 C 0.00 0.00 0.00

=======================================================================MATERIAL DATA




DESIGN DATA (units - kN,m) BS5950-1/2000Section Class : SEMI-COMPACTSquash Load : 4346.00Axial force/Squash load : 0.575

z-z axis y-y axisCompression Capacity : 3992.2 3089.3Shear Capacity : 1846.1 588.0


x-x axis y-y axisSlenderness : 38.323 63.591Radius of gyration (cm) : 15.656 9.435Effective Length : 6.000 6.000LTB Moment Capacity (kNm) and LTB Length (m): 577.91, 6.000LTB Coefficients & Associated Moments (kNm):mLT = 1.00 : mx = 0.00 : my = 0.00 : myx = 0.00Mlt = 0.00 : Mx = 0.00 : My = 0.00 : My = 0.00STAAD SPACE -- PAGE NO. 6

CRITICAL LOADS FOR EACH CLAUSE CHECK (units- kN,m):CLAUSE RATIO LOAD FX VY VZ MZ MYBS-4.7 (C) 0.809 1 2500.0 - - - -Torsion and deflections have not been considered in the design.

_________________________************** END OF TABULATED RESULT OF DESIGN **************40. FINISH





Steel Design per BS 5950-1:2000 6ObjectiveA 6.0m rectangular hollow section (RHS) column is pin ended about both axes and has nointermediate restraints. The column is designed in S355 steel for the factored loading.



Comparison


Slenderness, λ 61.4 61.424 none

Compression capacity, Pc (kN-m) 2,790 2,794.6 none

Table 13-6: Comparison of results for BS 5950 column 2



SGR 1 ALL



STAAD SPACESTART JOB INFORMATIONJOB NAME Example no. 11JOB CLIENT The Steel Construction InstituteJOB COMMENT Pinned column using a non-slender RHS.ENGINEER DATE Jun 2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 0 6 0;MEMBER INCIDENCES1 1 2;*************************************DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03

544 — STAAD.Pro



END DEFINE MATERIALMEMBER PROPERTY BRITISH1 TABLE ST TUB25025010.0CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 FIXED*************************************LOAD 1 AXIAL LOADJOINT LOAD2 FY -2500PERFORM ANALYSIS PRINT STATICS CHECK***************************************PARAMETERCODE BS5950SGR 1 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 114. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE5. JOB COMMENT PINNED COLUMN USING A NON-SLENDER RHS.6. ENGINEER DATE JUN 20037. END JOB INFORMATION8. INPUT WIDTH 799. UNIT METER KN10. JOINT COORDINATES11. 1 0 0 0; 2 0 6 012. MEMBER INCIDENCES13. 1 1 214. *************************************15. DEFINE MATERIAL START16. ISOTROPIC STEEL17. E 2.05E+00818. POISSON 0.319. DENSITY 76.819520. ALPHA 1.2E-00521. DAMP 0.0322. END DEFINE MATERIAL23. MEMBER PROPERTY BRITISH24. 1 TABLE ST TUB25025010.025. CONSTANTS26. MATERIAL STEEL MEMB 127. SUPPORTS28. 1 FIXED29. *************************************



30. LOAD 1 AXIAL LOAD31. JOINT LOAD32. 2 FY -250033. PERFORM ANALYSIS PRINT STATICS CHECKSTAAD SPACE -- PAGE NO. 2





STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1AXIAL LOADCENTER OF FORCE BASED ON Y FORCES ONLY (METE).













FX MY MZ LOCATION=======================================================================

1 ST TUB25025010.0 PASS BS-4.7 (C) 0.895 1

546 — STAAD.Pro



2500.00 C 0.00 0.00 0.00=======================================================================MATERIAL DATA




DESIGN DATA (units - kN,m) BS5950-1/2000Section Class : SEMI-COMPACTSquash Load : 3368.95Axial force/Squash load : 0.742



x-x axis y-y axisSlenderness : 61.424 61.424Radius of gyration (cm) : 9.768 9.768Effective Length : 6.000 6.000LTB check unnecessary for this section






Steel Design per BS 5950-1:2000 7ObjectiveA 6.0m circular hollow section (CHS) column is pin ended about both axes and has nointermediate restraints. The column is designed in S355 steel for the factored loading.





Comparison


Effective area, Aeff (cm2) 77.6 77.63 none

Slenderness, λ 42.2 42.413 none

Compression capacity, Pc (kN-m) 2,561 2,562.3 none

Table 13-7: Comparison of results for BS 5950 column 2



SGR 1 ALL



STAAD SPACESTART JOB INFORMATIONJOB NAME Example no. 12JOB CLIENT The Steel Construction InstituteJOB COMMENT Pinned column using a slender CHS.ENGINEER DATE Jun-2003END JOB INFORMATIONINPUT WIDTH 79UNIT METER KNJOINT COORDINATES1 0 0 0; 2 0 6 0;MEMBER INCIDENCES1 1 2;*************************************DEFINE MATERIAL STARTISOTROPIC STEELE 2.05e+008POISSON 0.3DENSITY 76.8195ALPHA 1.2e-005DAMP 0.03END DEFINE MATERIALMEMBER PROPERTY BRITISH1 TABLE ST PIP4066.3CONSTANTSMATERIAL STEEL MEMB 1SUPPORTS1 FIXED*************************************

548 — STAAD.Pro



LOAD 1 AXIAL FORCEJOINT LOAD2 FY -2500PERFORM ANALYSIS PRINT STATICS CHECK***************************************PARAMETERCODE BS5950SGR 1 ALLTRACK 2 ALLCHECK CODE ALLFINISH




2. START JOB INFORMATION3. JOB NAME EXAMPLE NO. 124. JOB CLIENT THE STEEL CONSTRUCTION INSTITUTE5. JOB COMMENT PINNED COLUMN USING A SLENDER CHS.6. ENGINEER DATE JUN-20037. END JOB INFORMATION8. INPUT WIDTH 799. UNIT METER KN10. JOINT COORDINATES11. 1 0 0 0; 2 0 6 012. MEMBER INCIDENCES13. 1 1 214. *************************************15. DEFINE MATERIAL START16. ISOTROPIC STEEL17. E 2.05E+00818. POISSON 0.319. DENSITY 76.819520. ALPHA 1.2E-00521. DAMP 0.0322. END DEFINE MATERIAL23. MEMBER PROPERTY BRITISH24. 1 TABLE ST PIP4066.325. CONSTANTS26. MATERIAL STEEL MEMB 127. SUPPORTS28. 1 FIXED29. *************************************30. LOAD 1 AXIAL FORCE31. JOINT LOAD32. 2 FY -250033. PERFORM ANALYSIS PRINT STATICS CHECKSTAAD SPACE -- PAGE NO. 2







STAAD SPACE -- PAGE NO. 3STATIC LOAD/REACTION/EQUILIBRIUM SUMMARY FOR CASE NO. 1AXIAL FORCECENTER OF FORCE BASED ON Y FORCES ONLY (METE).













FX MY MZ LOCATION=======================================================================

1 ST PIP4066.3 PASS BS-4.7 (C) 0.976 12500.00 C 0.00 0.00 0.00

=======================================================================MATERIAL DATA


SECTION PROPERTIES (units - cm)Member Length = 600.00

550 — STAAD.Pro



Gross Area = 79.20 Net Area = 79.20 Eff. Area = 77.63z-z axis y-y axis

Moment of inertia : 15850.002 15850.002Plastic modulus : 1009.000 1009.000Elastic modulus : 780.020 780.020Effective modulus : 780.020 780.020Shear Area : 47.520 47.520

DESIGN DATA (units - kN,m) BS5950-1/2000Section Class : SLENDERSquash Load : 2811.60Axial force/Squash load : 0.889



x-x axis y-y axisSlenderness : 42.413 42.413Radius of gyration (cm) : 14.147 14.147Effective Length : 6.000 6.000LTB check unnecessary for this section








552 — STAAD.Pro


Notes

Lists of Tables and FiguresTables

Table 1-1: Comparison of member stress, in psi, for static truss no. 1 2

Table 1-2: Comparison of member force, in kN, for static truss no. 2 5

Table 1-3: Comparison of member force, in kN, for static truss no. 3 8

Table 1-4: Comparison of support reactions, in N, for static truss no. 4 13

Table 1-5: Comparison of member forces, in N, for static truss no. 4 13



Table 1-8: Comparison of Support Reaction, in kips, for verification problem no. 1 23

Table 1-9: Comparison of deflection (δ) for verification problem no. 7 26

Table 1-10: Comparison of stress (σ) and Deflection (δ) for verification problem 12 29

Table 1-11: Comparison of member forces, in N, for static truss no. 7 32

Table 2-1: Comparison of results for static beam no. 1 36









Table 2-10: Comparison of stress (σ), psi, and Deflection (δ), in. for verification modelno. 5 70




Table 2-14: Comparison of stress (σ) for verification model #11 85




Table 3-3: Comparison of results for static frame no.3 99




Table 3-6: Comparison of reaction, in kips, for verification problem no. 4 112

Table 3-7: Comparison of moment, in kip-ft, for verification problem no. 6 115

Table 3-8: Comparison of max. moment, in kip-ft, for verification model no. 8 118

Table 3-9: Comparison of max. moment, in kip-ft, for verification problem no. 9 121



Table 3-12: Comparison of axial force results (kN) for static frame no.12 132

Table 3-13: Comparison of max. Force, F, and max. Moments,M, for verificationproblem no. 10 136


Table 4-2: Comparison of results for static element no.2 153

Table 4-3: Comparison of results for plate bending finite element 157

Table 4-4: Comparison of results for problem 161




Table 4-8: Comparison of results for cylindrical roof structure 184





Table 4-13: Vertical deflections due to unit pressure, 10-3 in 212

Table 4-14: Maximum bending stress due to unit pressure 212




Table 4-18: Comparison of results uniform pressure load case 243

Table 4-19: Comparison of results linearly varying pressure load case 243

Table 5-1: Comparison of results for static solid no. 1 251

Table 5-2: Comparison of results for static solid no. 2 254

Table 6-1: Comparison of displacements for the frame 263

Table 7-1: Comparison of frequency for dynamic analysis truss 270

Table 7-2: Comparison of results for dynamic beam no. 1 273




554 — STAAD.Pro

Table 7-6: Comparison of period, in sec., for verification problem no. 2 285

Table 7-7: Modal stiffness and natural frequencies 288


Table 8-1: Comparison of results forconcrete beam designed per ACI 318-02 291

Table 8-2: Comparison of results for concrete beam-column designed per ACI 318-02 297



Table 9-1: Comparison of compressive strength results for a built-up column 307

Table 9-2: Comparison of results for beam shear 314

Table 9-3: Comparison of results for a angle in tension 320

Table 9-4: Comparison of results for a flexure member 327

Table 9-5: Comparison of results for a member with interacting loads 333

Table 9-6: Comparison of results for a double-angle column 339


Table 10-1: Comparison of results for ASD column no. 1 354








Table 10-9: Comparison of results for ASD beam no. 9 379








Table 10-17: Comparison of results for ASD beam-column no. 17 405

Table 10-18: Comparison of results for ASD beam-column no. 18 409

Table 11-1: Comparison of results for beam no. 1 414

Table 11-2: Comparison of results for beam no. 2 417

Table 11-3: Comparison of results for column no. 3 420





Table 11-7: Comparison of results for AISC LRFD 7 430
























Table 13-1: Comparison of results for BS 5950 beam 1 516

Table 13-2: Comparison of results for BS 5950 Beam 2 522

Table 13-3: Comparison of results for BS 5950 beam 3 528

Table 13-4: Comparison of results for BS 5950-1 beam 4 534


Table 13-6: Comparison of results for BS 5950 column 2 544

Table 13-7: Comparison of results for BS 5950 column 2 548

556 — STAAD.Pro

Figures

Figure 1-1: Space truss 2

Figure 1-2: Plane articulate truss 5

Figure 1-3: Plane truss 8





Figure 1-8: Plane truss model 26

Figure 1-9: Model of two member truss 29

Figure 1-10: Plane truss subject to differential thermal loading 32

Figure 2-1: Simple supported beam with partial, trapezoidal load 36

Figure 2-2: Fixed support beam with temperature load 40

Figure 2-3: Cantilevered member with a tapered, hollow shaft cross section 44

Figure 2-4: Cantilevered member with a compression only support 47

Figure 2-5: Cantilevered member subject to torsional loads 53

Figure 2-6: Beam A) problem sketch and B) mathematical model 56

Figure 2-7: Column A) problem sketch and B) mathematical model 60


Figure 2-9: One-half beam for mathematical model 65

Figure 2-10: Locomotive axle model 69



Figure 2-13: Beam with a tapering cross section 79

Figure 2-14: Model of a rigid wire suspended by wires 84

Figure 2-15: Curved beam 87

Figure 3-1: Simple supported beam with partial, trapezoidal load 92

Figure 3-2: Rigid bar hanging from a pair of rods 96

Figure 3-3: Bent plate frame 99

Figure 3-4: 3x2 bay plane frame 102

Figure 3-5: Frame subject to temperature change 108

Figure 3-6: Cantilever model 112

Figure 3-7: 1x1 bay plane frame 115

Figure 3-8: Unequal leg bay model 118

Figure 3-9: Two story frame model 121


Figure 3-10: Frame subject to imposed displacements 124



Figure 3-13: Space frame model 135

Figure 4-1: Cantilever beam modeled with elements 140

Figure 4-2: STAAD.Pro Model showing Node numbers 141

Figure 4-3: Element numbers at a) the middle section and b) the free end 141

Figure 4-4: Fixed support beam with temperature load 153

Figure 4-5: Model 157

Figure 4-6: Cantilevered, curved plate with coupling load at free end 161

Figure 4-7: Simply-supported, equilateral triangle with thermal load 166

Figure 4-8: Finite element model of a simply-supported, equilateral triangle 167

Figure 4-9: Finite element model of a circular plate 174

Figure 4-10: Finite element model of warped, cantilever plate 180

Figure 4-11: Finite element model of cylindrical roof structure 184


Figure 4-13: Semi-circular plate finite element model 198





Figure 4-18: One quarter of rectangular plate with hole 221

Figure 4-19: Model with nodes and elements labeled 222



Figure 5-1: Entire model 249

Figure 5-2: Free end section with node numbers 250

Figure 6-1: Ten story, plane frame 263


Figure 7-2: Model for dynamic beam no. 1 273




Figure 7-6: Beam supported on springs 285


558 — STAAD.Pro

Figure 12-1: Beam with load cases as shown 498

Figure 12-2: Compression member designed per AS 4100 503

Figure 12-3: Tension member designed per AS 4100 507

Figure 12-4: Member under combined stress designed per AS 4100 511


560 — STAAD.Pro

Notes

Bentley Systems, Incorporated

685 Stockton Drive, Exton, PA 19341 USA

+1 (800) 236-8539

www.bentley.com

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