EX. UK-25 Analysis of a Structure with Compression-Only Members
This example demonstrates the usage of compression-only members. Since the structural condition is load dependent, the PERFORM ANALYSIS command is specified once for each primary load case.
This problem is installed with the program by default to C:\Users\Public\Public Documents\STAAD.Pro 2023\Samples\Sample Models\UK\UK-25 Analysis of a Structure with Compression-Only Members.STD when you install the program.
UNIT METER KNS
Units for the commands to follow are specified above.
JOINT COORDINATES
1 0 0 ; 2 0 3.5 ; 3 0 7.0 ; 4 5.25 7.0 ; 5 5.25 3.5 ; 6 5.25 0
MEMBER PROPERTY BRITISH
1 TO 10 TA ST UC152X152X30
Members 1 to 10 are assigned the UC152X152X30 section from the British steel table.
UNIT MMS
DEFINE MATERIAL START
ISOTROPIC STEEL
E 210
POISSON 0.3
DENSITY 7.6977e-008
ALPHA 6e-006
DAMP 0.03
TYPE STEEL
STRENGTH FY 0.25 FU 0.4 RY 1.5 RT 1.2
END DEFINE MATERIAL
CONSTANTS
MATERIAL STEEL ALL
UNIT METER
The DEFINE MATERIAL command is used to specify material properties and the CONSTANT is used to assign the material to all members.
SUPPORT
1 6 PINNED
Joints 1 and 6 are declared as pinned-supported.
LOAD 1
JOINT LOAD
2 FX 70
3 FX 45
Input File
STAAD PLANE
* EXAMPLE FOR COMPRESSION-ONLY MEMBERS
UNIT METER KNS
SET NL 3
JOINT COORDINATES
1 0 0 ; 2 0 3.5 ; 3 0 7.0 ; 4 5.25 7.0 ; 5 5.25 3.5 ; 6 5.25 0
MEMBER INCIDENCES
1 1 2 5
6 1 5 ; 7 2 6 ; 8 2 4 ; 9 3 5 ; 10 2 5
MEMBER COMPRESSION
6 TO 9
MEMBER PROPERTY BRITISH
1 TO 10 TA ST UC152X152X30
UNIT MMS
DEFINE MATERIAL START
ISOTROPIC STEEL
E 210
POISSON 0.3
DENSITY 7.6977e-008
ALPHA 6e-006
DAMP 0.03
TYPE STEEL
STRENGTH FY 0.25 FU 0.4 RY 1.5 RT 1.2
END DEFINE MATERIAL
CONSTANTS
MATERIAL STEEL ALL
UNIT METER
SUPPORT
1 6 PINNED
LOAD 1
JOINT LOAD
2 FX 70
3 FX 45
PERFORM ANALYSIS
CHANGE
MEMBER COMPRESSION
6 TO 9
LOAD 2
JOINT LOAD
4 FX -45
5 FX -70
PERFORM ANALYSIS
CHANGE
LOAD 3
REPEAT LOAD
1 1.0 2 1.0
PERFORM ANALYSIS
CHANGE
LOAD LIST ALL
PRINT ANALYSIS RESULTS
FINISHSTAAD Output File
PAGE NO. 1 **************************************************** * * * STAAD.Pro 2023 * * Version 23.00.02.*** * * Proprietary Program of * * Bentley Systems, Inc. * * Date= DEC 14, 2023 * * Time= 9:35:45 * * * * Licensed to: Bentley Systems Inc * **************************************************** 1. STAAD PLANE INPUT FILE: D:\Documentation\STAAD.Pro\_Automated_Py\output\2023-12-14\SPro_Output_Input_Files\Sample .. .STD 2. * EXAMPLE FOR COMPRESSION-ONLY MEMBERS 3. UNIT METER KNS 4. SET NL 3 5. JOINT COORDINATES 6. 1 0 0 ; 2 0 3.5 ; 3 0 7.0 ; 4 5.25 7.0 ; 5 5.25 3.5 ; 6 5.25 0 7. MEMBER INCIDENCES 8. 1 1 2 5 9. 6 1 5 ; 7 2 6 ; 8 2 4 ; 9 3 5 ; 10 2 5 10. MEMBER COMPRESSION 11. 6 TO 9 12. MEMBER PROPERTY BRITISH 13. 1 TO 10 TA ST UC152X152X30 14. UNIT MMS 15. DEFINE MATERIAL START 16. ISOTROPIC STEEL 17. E 210 18. POISSON 0.3 19. DENSITY 7.6977E-008 20. ALPHA 6E-006 21. DAMP 0.03 22. TYPE STEEL 23. STRENGTH FY 0.25 FU 0.4 RY 1.5 RT 1.2 24. END DEFINE MATERIAL 25. CONSTANTS 26. MATERIAL STEEL ALL 27. UNIT METER 28. SUPPORT 29. 1 6 PINNED 30. LOAD 1 31. JOINT LOAD 32. 2 FX 70 33. 3 FX 45 34. PERFORM ANALYSIS STAAD PLANE -- PAGE NO. 2 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS P R O B L E M S T A T I S T I C S ----------------------------------- NUMBER OF JOINTS 6 NUMBER OF MEMBERS 10 NUMBER OF PLATES 0 NUMBER OF SOLIDS 0 NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 2 Using 64-bit analysis engine. SOLVER USED IS THE IN-CORE ADVANCED MATH SOLVER TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 14 TOTAL LOAD COMBINATION CASES = 0 SO FAR. *** LOAD CASE 1 -- START ITERATION NO. 2 **NOTE-Tension/Compression converged after 2 iterations, Case= 1 35. CHANGE 36. MEMBER COMPRESSION 37. 6 TO 9 38. LOAD 2 39. JOINT LOAD 40. 4 FX -45 41. 5 FX -70 42. PERFORM ANALYSIS *** LOAD CASE 2 -- START ITERATION NO. 2 **NOTE-Tension/Compression converged after 2 iterations, Case= 2 43. CHANGE 44. LOAD 3 45. REPEAT LOAD 46. 1 1.0 2 1.0 47. PERFORM ANALYSIS **NOTE-Tension/Compression converged after 1 iterations, Case= 3 48. CHANGE 49. LOAD LIST ALL 50. PRINT ANALYSIS RESULTS STAAD PLANE -- PAGE NO. 3 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS ANALYSIS RESULTS STAAD PLANE -- PAGE NO. 4 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS JOINT DISPLACEMENT (CM RADIANS) STRUCTURE TYPE = PLANE ------------------ JOINT LOAD X-TRANS Y-TRANS Z-TRANS X-ROTAN Y-ROTAN Z-ROTAN 1 1 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0005 2 0.0000 0.0000 0.0000 0.0000 0.0000 0.0007 3 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0001 2 1 0.1609 0.0464 0.0000 0.0000 0.0000 -0.0003 2 -0.1900 -0.0132 0.0000 0.0000 0.0000 0.0003 3 0.0138 0.0030 0.0000 0.0000 0.0000 -0.0000 3 1 0.2889 0.0594 0.0000 0.0000 0.0000 -0.0003 2 -0.2889 -0.0132 0.0000 0.0000 0.0000 0.0002 3 0.0091 0.0080 0.0000 0.0000 0.0000 0.0000 4 1 0.2889 -0.0132 0.0000 0.0000 0.0000 -0.0002 2 -0.2889 0.0594 0.0000 0.0000 0.0000 0.0003 3 -0.0091 0.0080 0.0000 0.0000 0.0000 -0.0000 5 1 0.1900 -0.0132 0.0000 0.0000 0.0000 -0.0003 2 -0.1609 0.0464 0.0000 0.0000 0.0000 0.0003 3 -0.0138 0.0030 0.0000 0.0000 0.0000 0.0000 6 1 0.0000 0.0000 0.0000 0.0000 0.0000 -0.0007 2 0.0000 0.0000 0.0000 0.0000 0.0000 0.0005 3 0.0000 0.0000 0.0000 0.0000 0.0000 0.0001 STAAD PLANE -- PAGE NO. 5 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS SUPPORT REACTIONS -UNIT KNS METE STRUCTURE TYPE = PLANE ----------------- JOINT LOAD FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z 1 1 -0.13 -106.67 0.00 0.00 0.00 0.00 2 114.87 106.67 0.00 0.00 0.00 0.00 3 10.38 0.00 0.00 0.00 0.00 0.00 6 1 -114.87 106.67 0.00 0.00 0.00 0.00 2 0.13 -106.67 0.00 0.00 0.00 0.00 3 -10.38 0.00 0.00 0.00 0.00 0.00 STAAD PLANE -- PAGE NO. 6 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS 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 1 1 1 -106.67 0.13 0.00 0.00 0.00 -0.00 2 106.67 -0.13 0.00 0.00 0.00 0.45 2 1 30.22 -0.21 0.00 0.00 0.00 0.00 2 -30.22 0.21 0.00 0.00 0.00 -0.73 3 1 -6.94 0.03 0.00 0.00 0.00 -0.00 2 6.94 -0.03 0.00 0.00 0.00 0.09 2 1 2 -29.91 0.24 0.00 0.00 0.00 0.38 3 29.91 -0.24 0.00 0.00 0.00 0.46 2 2 0.15 -0.12 0.00 0.00 0.00 -0.08 3 -0.15 0.12 0.00 0.00 0.00 -0.33 3 2 -11.49 -0.03 0.00 0.00 0.00 -0.08 3 11.49 0.03 0.00 0.00 0.00 -0.03 3 1 3 0.12 -0.15 0.00 0.00 0.00 -0.46 4 -0.12 0.15 0.00 0.00 0.00 -0.33 2 3 0.12 0.15 0.00 0.00 0.00 0.33 4 -0.12 -0.15 0.00 0.00 0.00 0.46 3 3 27.79 -0.00 0.00 0.00 0.00 0.03 4 -27.79 0.00 0.00 0.00 0.00 -0.03 4 1 4 0.15 0.12 0.00 0.00 0.00 0.33 5 -0.15 -0.12 0.00 0.00 0.00 0.08 2 4 -29.91 -0.24 0.00 0.00 0.00 -0.46 5 29.91 0.24 0.00 0.00 0.00 -0.38 3 4 -11.49 0.03 0.00 0.00 0.00 0.03 5 11.49 -0.03 0.00 0.00 0.00 0.08 5 1 5 30.22 0.21 0.00 0.00 0.00 0.73 6 -30.22 -0.21 0.00 0.00 0.00 0.00 2 5 -106.67 -0.13 0.00 0.00 0.00 -0.45 6 106.67 0.13 0.00 0.00 0.00 0.00 3 5 -6.94 -0.03 0.00 0.00 0.00 -0.09 6 6.94 0.03 0.00 0.00 0.00 0.00 6 1 1 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 2 1 137.81 0.00 0.00 0.00 0.00 0.00 5 -137.81 0.00 0.00 0.00 0.00 0.00 3 1 12.51 0.00 0.00 0.00 0.00 0.00 5 -12.51 0.00 0.00 0.00 0.00 0.00 7 1 2 137.81 0.00 0.00 0.00 0.00 0.00 6 -137.81 0.00 0.00 0.00 0.00 0.00 STAAD PLANE -- PAGE NO. 7 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS 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 2 0.00 0.00 0.00 0.00 0.00 0.00 6 0.00 0.00 0.00 0.00 0.00 0.00 3 2 12.51 0.00 0.00 0.00 0.00 0.00 6 -12.51 0.00 0.00 0.00 0.00 0.00 8 1 2 0.00 0.00 0.00 0.00 0.00 0.00 4 0.00 0.00 0.00 0.00 0.00 0.00 2 2 53.66 0.00 0.00 0.00 0.00 0.00 4 -53.66 0.00 0.00 0.00 0.00 0.00 3 2 20.72 0.00 0.00 0.00 0.00 0.00 4 -20.72 0.00 0.00 0.00 0.00 0.00 9 1 3 53.66 0.00 0.00 0.00 0.00 0.00 5 -53.66 0.00 0.00 0.00 0.00 0.00 2 3 0.00 0.00 0.00 0.00 0.00 0.00 5 0.00 0.00 0.00 0.00 0.00 0.00 3 3 20.72 0.00 0.00 0.00 0.00 0.00 5 -20.72 0.00 0.00 0.00 0.00 0.00 10 1 2 -44.55 -0.31 0.00 0.00 0.00 -0.82 5 44.55 0.31 0.00 0.00 0.00 -0.81 2 2 -44.55 0.31 0.00 0.00 0.00 0.81 5 44.55 -0.31 0.00 0.00 0.00 0.82 3 2 42.29 0.00 0.00 0.00 0.00 -0.01 5 -42.29 -0.00 0.00 0.00 0.00 0.01 ************** END OF LATEST ANALYSIS RESULT ************** 51. FINISH STAAD PLANE -- PAGE NO. 8 * EXAMPLE FOR COMPRESSION-ONLY MEMBERS *********** END OF THE STAAD.Pro RUN *********** **** DATE= DEC 14,2023 TIME= 9:35:46 **** ************************************************************ * For technical assistance on STAAD.Pro, please visit * * http://www.bentley.com/en/support/ * * * * Details about additional assistance from * * Bentley and Partners can be found at program menu * * Help->Technical Support * * * * Copyright (c) Bentley Systems, Inc. * * http://www.bentley.com * ************************************************************