EX. UK-4 Inactive Members in a Braced Frame
This example is a typical case of a load-dependent structure where the structural condition changes for different load cases. In this example, different bracing members are made inactive for different load cases. This is done to prevent these members from carrying any compressive forces.
This problem is installed with the program by default to C:\Users\Public\Public Documents\STAAD.Pro 2024\Samples \Sample Models\UK\UK-4 Inactive Members in a Braced Frame.STD when you install the program.
Where:
- L1 = 4.5 m, L2 = 6.0m
- P1 = 45 kN, P2 = 90 kN
Actual input is shown in bold lettering followed by explanation.
STAAD PLANE
* A PLANE FRAME STRUCTURE WITH TENSION BRACING
Every input has to start with the term STAAD
. The term PLANE
signifies that the structure is a plane frame structure and the geometry is defined through X and Y axes.
UNIT METER KNS
Defines the input units for the data that follows.
SET NL 3
This structure has to be analyzed for three primary load cases. Consequently, the modeling of our problem requires us to define three sets of data, with each set containing a load case and an associated analysis command. Also, the members which get switched off in the analysis for any load case have to be restored for the analysis for the subsequent load case. To accommodate these requirements, it is necessary to have two commands, one called SET NL
and the other called CHANGE
. The SET NL
command is used above to indicate the total number of primary load cases that the file contains. The CHANGE
command will come in later (after the PERFORM ANALYSIS
command).
JOINT COORDINATES
1 0 0 0 3 12. 0. 0.
4 0 4.5 0 6 12. 4.5 0.
7 6. 9. 0. ; 8 12. 9. 0.
Joint number followed by X, Y and Z coordinates are provided above. Since this is a plane structure, the Z coordinates are given as all zeros.
MEMBER INCIDENCE
1 1 4 2 ; 3 5 7 ; 4 3 6 ; 5 6 8 ; 6 4 5 7
8 7 8 ; 9 1 5 ; 10 2 4 ; 11 3 5 ; 12 2 6
13 6 7 ; 14 5 8
Defines the members by the joints to which they are connected.
MEMBER TRUSS
9 TO 14
The preceding command defines that members 9 through 14 are of type truss. This means these members can only carry axial tension/compression and no moments.
MEMBER PROP BRITISH
1 TO 5 TABLE ST UB305X165X40
6 7 8 TA ST UB457X152X52
9 TO 14 TA LD UA150X150X10
Properties for all members are assigned from the British steel table.
The word ST
stands for standard single section. The word LD
stands for long leg back-to-back double angle. Since the spacing between the two angles of the double angle is not provided, it is assumed to be 0.0.
UNIT MMS
DEFINE MATERIAL START
ISOTROPIC STEEL
E 210
POISSON 0.3
DENSITY 7.68191e-008
ALPHA 6e-006
DAMP 0.03
TYPE STEEL
STRENGTH FY 0.24821 FU 0.399894 RY 1.5 RT 1.2
END DEFINE MATERIAL
CONSTANTS
MATERIAL STEEL ALL
The DEFINE MATERIAL
command is used to define a material. The CONSTANT
command is used to assign this material all members. Length unit is changed from METER to MMS.
SUPPORT
1 2 3 PINNED
Pinned supports are specified at Joints 1, 2 and 3. The word PINNED
signifies that no moments will be carried by these supports.
INACTIVE MEMBERS 9 TO 14
The preceding command makes the listed members inactive. The stiffness contribution of these members will not be considered in the analysis till they are made active again.
UNIT METER
LOADING 1 DEAD AND LIVE LOAD
Load case 1 is initiated followed by a title. The length UNIT is changed from MMS to METER for input values which follow.
MEMBER LOAD
6 8 UNI GY -4.5
7 UNI GY -6.75
Load 1 contains member loads. GY
indicates that the load acts in the global Y direction. The word UNI
stands for uniformly distributed load. The load is applied on members 6, 7, and 8.
PERFORM ANALYSIS
This command instructs the program to proceed with the analysis. It is worth noting that members 9 to 14 will not be used in this analysis since they were declared inactive earlier. In other words, for dead and live load, the bracing members are not used to carry any load.
CHANGES
The members inactivated earlier are restored using the CHANGE
command.
INACTIVE MEMBERS 10 11 13
A new set of members are made inactive. The stiffness contribution from these members will not be used in the analysis till they are made active again. They have been inactivated to prevent them from being subject to compressive forces for the next load case.
LOADING 2 WIND FROM LEFT
Load case 2 is initiated followed by a title.
JOINT LOAD
4 FX 135 ; 7 FX 65
Load 2 contains joint loads. FX
indicates that the load is a force in the global X direction. Nodes 4 and 7 are subjected to the loads.
PERFORM ANALYSIS
This command instructs the program to proceed with the analysis. The analysis will be performed for load case 2 only.
CHANGE
The above CHANGE command is an instruction to re-activate all inactive members.
INACTIVE MEMBERS 9 12 14
Members 9, 12 and 14 are made inactive. The stiffness contribution of these members will not be used in the analysis till they are made active again. They have been inactivated to prevent them from being subject to compressive forces for the next load case.
LOADING 3 WIND FROM RIGHT
Load case 3 is initiated followed by a title.
JOINT LOAD
6 FX -135 ; 8 FX -65
Load 3 contains joint loads at nodes 6 and 8. FX indicates that the load is a force in the global X direction. The negative numbers
(-135 and -65) indicate that the load is acting along the negative global X direction.
LOAD COMBINATION 4
1 0.75 2 0.75
LOAD COMBINATION 5
1 0.75 3 0.75
Load combination case 4 involves the algebraic summation of the results of load cases 1 and 2 after multiplying each by a factor of 0.75. For load combinations, the program simply gathers the results of the component primary cases, factors them appropriately, and combines them algebraically. Thus, an analysis in the real sense of the term (multiplying the inverted stiffness matrix by the load vector) is not carried out for load combination cases. Load combination case 5 combines the results of load cases 1 and 3.
PERFORM ANALYSIS
This command instructs the program to proceed with the analysis. Only primary load case 3 will be considered for this analysis. (As explained earlier, a combination case is not truly analyzed for, but handled using other means.)
CHANGE
The above CHANGE
command will re-activate all inactive members.
LOAD LIST ALL
At the end of any analysis, only those load cases for which the analysis was done most recently, are recognized as the "active" load cases. The LOAD LIST ALL
command enables all the load cases in the structure to be made active for further processing.
PRINT MEMBER FORCES
The preceding PRINT
command is an instruction to produce a report, in the output file, of the member end forces.
LOAD LIST 1 4 5
A LOAD LIST
command is a means of instructing the program to use only the listed load cases for further processing.
PARAMETER
CODE EN 1993-1-1:2005
NA 1
BEAM 1 ALL
UNL 1.8 ALL
KY 0.5 ALL
The PARAMETER
command is used to specify the steel design parameters (information on these parameters can be obtained from the manual where the implementation of the code is explained). The BEAM
parameter is specified to perform design at every 1/12th point along the member length. UNL
represents the unsupported length to be used for calculation of allowable bending stress. KY 0.5 ALL
sets the effective length factor for column buckling about the local Y-axis to be 0.5 for ALL members.
CHECK CODE ALL
The above command instructs the program to perform a check to determine how you defined member sizes along with the latest analysis results meet the code requirements.
FINISH
This command terminates the STAAD run.
Input File
STAAD PLANE A PLANE FRAME STRUCTURE WITH
* TENSION BRACING
UNIT METER KNS
SET NL 3
JOINT COORDINATES
1 0 0 0 3 12. 0. 0.
4 0 4.5 0 6 12. 4.5 0.
7 6. 9. 0. ; 8 12. 9. 0.
MEMBER INCIDENCE
1 1 4 2 ; 3 5 7 ; 4 3 6 ; 5 6 8 ; 6 4 5 7
8 7 8 ; 9 1 5 ; 10 2 4 ; 11 3 5 ; 12 2 6
13 6 7 ; 14 5 8
MEMBER TRUSS
9 TO 14
MEMBER PROP BRITISH
1 TO 5 TABLE ST UB305X165X40
6 7 8 TA ST UB457X152X52
9 TO 14 TA LD UA150X150X10
UNIT MMS
DEFINE MATERIAL START
ISOTROPIC STEEL
E 210
POISSON 0.3
DENSITY 7.68191e-008
ALPHA 6e-006
DAMP 0.03
TYPE STEEL
STRENGTH FY 0.24821 FU 0.399894 RY 1.5 RT 1.2
END DEFINE MATERIAL
CONSTANTS
MATERIAL STEEL ALL
SUPPORT
1 2 3 PINNED
INACTIVE MEMBERS 9 TO 14
UNIT METER
LOADING 1 DEAD AND LIVE LOAD
MEMBER LOAD
6 8 UNI GY -4.5
7 UNI GY -6.75
PERFORM ANALYSIS
CHANGES
INACTIVE MEMBERS 10 11 13
LOADING 2 WIND FROM LEFT
JOINT LOAD
4 FX 135 ; 7 FX 65
PERFORM ANALYSIS
CHANGE
INACTIVE MEMBERS 9 12 14
LOADING 3 WIND FROM RIGHT
JOINT LOAD
6 FX -135 ; 8 FX -65
LOAD COMBINATION 4
1 0.75 2 0.75
LOAD COMBINATION 5
1 0.75 3 0.75
PERFORM ANALYSIS
CHANGE
LOAD LIST ALL
PRINT MEMBER FORCES
LOAD LIST 1 4 5
PARAMETER
CODE EN 1993-1-1:2005
NA 1
UNL 1.8 ALL
KY 0.5 ALL
CHECK CODE ALL
FINISH
PAGE NO. 1
****************************************************
* *
* STAAD.Pro 2023 *
* Version 23.00.03.** *
* Proprietary Program of *
* Bentley Systems, Inc. *
* Date= JUL 4, 2024 *
* Time= 11:22:58 *
* *
* Licensed to: Bentley Systems Inc *
****************************************************
1. STAAD PLANE A PLANE FRAME STRUCTURE WITH
INPUT FILE: D:\Documentation\STAAD.Pro\_Automated_Py\output\2024-07-04\SPro_Output_Input_Files\Sample .. .STD
2. * TENSION BRACING
3. UNIT METER KNS
4. SET NL 3
5. JOINT COORDINATES
6. 1 0 0 0 3 12. 0. 0.
7. 4 0 4.5 0 6 12. 4.5 0.
8. 7 6. 9. 0. ; 8 12. 9. 0.
9. MEMBER INCIDENCE
10. 1 1 4 2 ; 3 5 7 ; 4 3 6 ; 5 6 8 ; 6 4 5 7
11. 8 7 8 ; 9 1 5 ; 10 2 4 ; 11 3 5 ; 12 2 6
12. 13 6 7 ; 14 5 8
13. MEMBER TRUSS
14. 9 TO 14
15. MEMBER PROP BRITISH
16. 1 TO 5 TABLE ST UB305X165X40
17. 6 7 8 TA ST UB457X152X52
18. 9 TO 14 TA LD UA150X150X10
19. UNIT MMS
20. DEFINE MATERIAL START
21. ISOTROPIC STEEL
22. E 210
23. POISSON 0.3
24. DENSITY 7.68191E-008
25. ALPHA 6E-006
26. DAMP 0.03
27. TYPE STEEL
28. STRENGTH FY 0.24821 FU 0.399894 RY 1.5 RT 1.2
29. END DEFINE MATERIAL
30. CONSTANTS
31. MATERIAL STEEL ALL
32. SUPPORT
33. 1 2 3 PINNED
34. INACTIVE MEMBERS 9 TO 14
35. UNIT METER
36. LOADING 1 DEAD AND LIVE LOAD
37. MEMBER LOAD
38. 6 8 UNI GY -4.5
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 2
* TENSION BRACING
39. 7 UNI GY -6.75
40. PERFORM ANALYSIS
P R O B L E M S T A T I S T I C S
-----------------------------------
NUMBER OF JOINTS 8 NUMBER OF MEMBERS 14
NUMBER OF PLATES 0 NUMBER OF SOLIDS 0
NUMBER OF SURFACES 0 NUMBER OF SUPPORTS 3
Using 64-bit analysis engine.
SOLVER USED IS THE IN-CORE ADVANCED MATH SOLVER
TOTAL PRIMARY LOAD CASES = 1, TOTAL DEGREES OF FREEDOM = 18
TOTAL LOAD COMBINATION CASES = 0 SO FAR.
41. CHANGES
42. INACTIVE MEMBERS 10 11 13
43. LOADING 2 WIND FROM LEFT
44. JOINT LOAD
45. 4 FX 135 ; 7 FX 65
46. PERFORM ANALYSIS
47. CHANGE
48. INACTIVE MEMBERS 9 12 14
49. LOADING 3 WIND FROM RIGHT
50. JOINT LOAD
51. 6 FX -135 ; 8 FX -65
52. LOAD COMBINATION 4
53. 1 0.75 2 0.75
54. LOAD COMBINATION 5
55. 1 0.75 3 0.75
56. PERFORM ANALYSIS
57. CHANGE
58. LOAD LIST ALL
59. PRINT MEMBER FORCES
MEMBER FORCES
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 3
* TENSION BRACING
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 11.15 -0.90 0.00 0.00 0.00 0.00
4 -11.15 0.90 0.00 0.00 0.00 -4.06
2 1 -1.07 0.78 0.00 0.00 0.00 -0.00
4 1.07 -0.78 0.00 0.00 0.00 3.49
3 1 68.16 -0.68 0.00 0.00 0.00 0.00
4 -68.16 0.68 0.00 0.00 0.00 -3.05
4 1 7.56 -0.09 0.00 0.00 0.00 -0.00
4 -7.56 0.09 0.00 0.00 0.00 -0.43
5 1 59.49 -1.18 0.00 0.00 0.00 0.00
4 -59.49 1.18 0.00 0.00 0.00 -5.33
2 1 2 51.94 -0.07 0.00 0.00 0.00 0.00
5 -51.94 0.07 0.00 0.00 0.00 -0.32
2 2 46.05 0.54 0.00 0.00 0.00 -0.00
5 -46.05 -0.54 0.00 0.00 0.00 2.41
3 2 129.15 -0.47 0.00 0.00 0.00 -0.00
5 -129.15 0.47 0.00 0.00 0.00 -2.09
4 2 73.50 0.35 0.00 0.00 0.00 -0.00
5 -73.50 -0.35 0.00 0.00 0.00 1.57
5 2 135.82 -0.40 0.00 0.00 0.00 -0.00
5 -135.82 0.40 0.00 0.00 0.00 -1.81
3 1 5 13.68 -2.95 0.00 0.00 0.00 -5.29
7 -13.68 2.95 0.00 0.00 0.00 -8.01
2 5 -0.99 1.45 0.00 0.00 0.00 3.48
7 0.99 -1.45 0.00 0.00 0.00 3.03
3 5 47.36 -2.44 0.00 0.00 0.00 -6.17
7 -47.36 2.44 0.00 0.00 0.00 -4.82
4 5 9.52 -1.13 0.00 0.00 0.00 -1.35
7 -9.52 1.13 0.00 0.00 0.00 -3.73
5 5 45.79 -4.05 0.00 0.00 0.00 -8.59
7 -45.79 4.05 0.00 0.00 0.00 -9.62
4 1 3 31.40 0.97 0.00 0.00 0.00 0.00
6 -31.40 -0.97 0.00 0.00 0.00 4.38
2 3 103.89 0.21 0.00 0.00 0.00 -0.00
6 -103.89 -0.21 0.00 0.00 0.00 0.93
3 3 -48.62 -0.59 0.00 0.00 0.00 0.00
6 48.62 0.59 0.00 0.00 0.00 -2.65
4 3 101.47 0.88 0.00 0.00 0.00 -0.00
6 -101.47 -0.88 0.00 0.00 0.00 3.98
5 3 -12.91 0.29 0.00 0.00 0.00 0.00
6 12.91 -0.29 0.00 0.00 0.00 1.29
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 4
* TENSION BRACING
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
5 1 6 13.32 2.95 0.00 0.00 0.00 6.39
8 -13.32 -2.95 0.00 0.00 0.00 6.90
2 6 47.69 1.28 0.00 0.00 0.00 2.86
8 -47.69 -1.28 0.00 0.00 0.00 2.92
3 6 -1.29 -1.13 0.00 0.00 0.00 -2.15
8 1.29 1.13 0.00 0.00 0.00 -2.92
4 6 45.76 3.18 0.00 0.00 0.00 6.94
8 -45.76 -3.18 0.00 0.00 0.00 7.37
5 6 9.02 1.37 0.00 0.00 0.00 3.18
8 -9.02 -1.37 0.00 0.00 0.00 2.99
6 1 4 0.90 11.15 0.00 0.00 0.00 4.06
5 -0.90 15.85 0.00 0.00 0.00 -18.14
2 4 134.22 -1.07 0.00 0.00 0.00 -3.49
5 -134.22 1.07 0.00 0.00 0.00 -2.96
3 4 89.65 1.43 0.00 0.00 0.00 3.05
5 -89.65 -1.43 0.00 0.00 0.00 5.55
4 4 101.34 7.56 0.00 0.00 0.00 0.43
5 -101.34 12.69 0.00 0.00 0.00 -15.82
5 4 67.91 9.44 0.00 0.00 0.00 5.33
5 -67.91 10.81 0.00 0.00 0.00 -9.44
7 1 5 -1.98 22.41 0.00 0.00 0.00 23.75
6 1.98 18.09 0.00 0.00 0.00 -10.77
2 5 72.35 -1.12 0.00 0.00 0.00 -2.94
6 -72.35 1.12 0.00 0.00 0.00 -3.79
3 5 196.97 1.25 0.00 0.00 0.00 2.71
6 -196.97 -1.25 0.00 0.00 0.00 4.81
4 5 52.78 15.97 0.00 0.00 0.00 15.61
6 -52.78 14.41 0.00 0.00 0.00 -10.92
5 5 146.24 17.75 0.00 0.00 0.00 19.84
6 -146.24 12.63 0.00 0.00 0.00 -4.47
8 1 7 2.95 13.68 0.00 0.00 0.00 8.01
8 -2.95 13.32 0.00 0.00 0.00 -6.90
2 7 63.55 -0.99 0.00 0.00 0.00 -3.03
8 -63.55 0.99 0.00 0.00 0.00 -2.92
3 7 63.87 1.29 0.00 0.00 0.00 4.82
8 -63.87 -1.29 0.00 0.00 0.00 2.92
4 7 49.88 9.52 0.00 0.00 0.00 3.73
8 -49.88 10.73 0.00 0.00 0.00 -7.37
5 7 50.12 11.23 0.00 0.00 0.00 9.62
8 -50.12 9.02 0.00 0.00 0.00 -2.99
9 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
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 5
* TENSION BRACING
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 -156.32 0.00 0.00 0.00 0.00 0.00
5 156.32 0.00 0.00 0.00 0.00 0.00
3 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
4 1 -117.24 0.00 0.00 0.00 0.00 0.00
5 117.24 0.00 0.00 0.00 0.00 0.00
5 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
10 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 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
3 2 -111.22 0.00 0.00 0.00 0.00 0.00
4 111.22 0.00 0.00 0.00 0.00 0.00
4 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
5 2 -83.41 0.00 0.00 0.00 0.00 0.00
4 83.41 0.00 0.00 0.00 0.00 0.00
11 1 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
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 -136.62 0.00 0.00 0.00 0.00 0.00
5 136.62 0.00 0.00 0.00 0.00 0.00
4 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
5 3 -102.46 0.00 0.00 0.00 0.00 0.00
5 102.46 0.00 0.00 0.00 0.00 0.00
12 1 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
2 2 -91.79 0.00 0.00 0.00 0.00 0.00
6 91.79 0.00 0.00 0.00 0.00 0.00
3 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
4 2 -68.84 0.00 0.00 0.00 0.00 0.00
6 68.84 0.00 0.00 0.00 0.00 0.00
5 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
13 1 6 0.00 0.00 0.00 0.00 0.00 0.00
7 0.00 0.00 0.00 0.00 0.00 0.00
2 6 0.00 0.00 0.00 0.00 0.00 0.00
7 0.00 0.00 0.00 0.00 0.00 0.00
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 6
* TENSION BRACING
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 6 -76.79 0.00 0.00 0.00 0.00 0.00
7 76.79 0.00 0.00 0.00 0.00 0.00
4 6 0.00 0.00 0.00 0.00 0.00 0.00
7 0.00 0.00 0.00 0.00 0.00 0.00
5 6 -57.59 0.00 0.00 0.00 0.00 0.00
7 57.59 0.00 0.00 0.00 0.00 0.00
14 1 5 0.00 0.00 0.00 0.00 0.00 0.00
8 0.00 0.00 0.00 0.00 0.00 0.00
2 5 -77.83 0.00 0.00 0.00 0.00 0.00
8 77.83 0.00 0.00 0.00 0.00 0.00
3 5 0.00 0.00 0.00 0.00 0.00 0.00
8 0.00 0.00 0.00 0.00 0.00 0.00
4 5 -58.38 0.00 0.00 0.00 0.00 0.00
8 58.38 0.00 0.00 0.00 0.00 0.00
5 5 0.00 0.00 0.00 0.00 0.00 0.00
8 0.00 0.00 0.00 0.00 0.00 0.00
************** END OF LATEST ANALYSIS RESULT **************
60. LOAD LIST 1 4 5
61. PARAMETER
62. CODE EN 1993-1-1:2005
63. NA 1
64. UNL 1.8 ALL
65. KY 0.5 ALL
66. CHECK CODE ALL
STEEL DESIGN
STAAD.PRO CODE CHECKING - BS EN 1993-1-1:2005
********************************************
NATIONAL ANNEX - NA to BS EN 1993-1-1:2005
PROGRAM CODE REVISION V1.14 BS_EC3_2005/1
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 7
* TENSION BRACING
ALL UNITS ARE - KNS METE (UNLESS OTHERWISE Noted)
MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/
FX MY MZ LOCATION
=======================================================================
1 ST UB305X165X40 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.097 5
59.49 C 0.00 -5.33 4.50
2 ST UB305X165X40 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.149 5
135.82 C 0.00 -1.81 4.50
3 ST UB305X165X40 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.112 5
45.79 C 0.00 -9.62 4.50
4 ST UB305X165X40 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.129 4
101.47 C 0.00 3.98 4.50
5 ST UB305X165X40 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.096 4
45.76 C 0.00 7.37 4.50
6 ST UB457X152X52 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.176 4
101.34 C 0.00 -15.82 6.00
7 ST UB457X152X52 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.241 5
146.24 C 0.00 19.84 0.00
8 ST UB457X152X52 (BRITISH SECTIONS)
PASS EC-6.3.3-662 0.096 5
50.12 C 0.00 9.62 0.00
9 LD UA150X150X10 (BRITISH SECTIONS)
PASS EC-6.2.3 (T) 0.085 4
117.24 T 0.00 0.00 0.00
10 LD UA150X150X10 (BRITISH SECTIONS)
PASS EC-6.2.3 (T) 0.061 5
83.41 T 0.00 0.00 0.00
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 8
* TENSION BRACING
ALL UNITS ARE - KNS METE (UNLESS OTHERWISE Noted)
MEMBER TABLE RESULT/ CRITICAL COND/ RATIO/ LOADING/
FX MY MZ LOCATION
=======================================================================
11 LD UA150X150X10 (BRITISH SECTIONS)
PASS EC-6.2.3 (T) 0.074 5
102.46 T 0.00 0.00 0.00
12 LD UA150X150X10 (BRITISH SECTIONS)
PASS EC-6.2.3 (T) 0.050 4
68.84 T 0.00 0.00 0.00
13 LD UA150X150X10 (BRITISH SECTIONS)
PASS EC-6.2.3 (T) 0.042 5
57.59 T 0.00 0.00 0.00
14 LD UA150X150X10 (BRITISH SECTIONS)
PASS EC-6.2.3 (T) 0.042 4
58.38 T 0.00 0.00 0.00
************** END OF TABULATED RESULT OF DESIGN **************
67. FINISH
*********** END OF THE STAAD.Pro RUN ***********
**** DATE= JUL 4,2024 TIME= 11:23: 0 ****
A PLANE FRAME STRUCTURE WITH -- PAGE NO. 9
* TENSION BRACING
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