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 2024\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
LOAD 2
JOINT LOAD
4 FX -45
5 FX -70
LOAD 3
JOINT LOAD
2 FX 70
3 FX 45
4 FX -45
5 FX -70
PERFORM ANALYSIS
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
FINISH
PAGE NO. 1
****************************************************
* *
* STAAD.Pro 2023 *
* Version 23.00.03.** *
* Proprietary Program of *
* Bentley Systems, Inc. *
* Date= JUL 4, 2024 *
* Time= 11:21:44 *
* *
* Licensed to: Bentley Systems Inc *
****************************************************
1. STAAD PLANE
INPUT FILE: D:\Documentation\STAAD.Pro\_Automated_Py\output\2024-07-04\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= JUL 4,2024 TIME= 11:21:46 ****
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