# 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 CONNECT Edition\Samples\Sample Models\UK\UK-4 Inactive Members in a Braced Frame.STD when you install the program.

### Example Problem No. 4

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.

Note: Semicolons (;) are used as line separators to allow for input of multiple sets of data on one line.
```    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

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
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
6 8 UNI GY -4.5
7 UNI GY -6.75
PERFORM ANALYSIS
CHANGES
INACTIVE MEMBERS 10 11 13
4 FX 135 ; 7 FX 65
PERFORM ANALYSIS
CHANGE
INACTIVE MEMBERS 9 12 14
6 FX -135 ; 8 FX -65
1 0.75 2 0.75
1 0.75 3 0.75
PERFORM ANALYSIS
CHANGE
PRINT MEMBER FORCES
PARAMETER
CODE EN 1993-1-1:2005
NA 1
BEAM 1 ALL
UNL 1.8 ALL
KY 0.5 ALL
CHECK CODE ALL
FINISH
``````

```                                                                  PAGE NO.    1
****************************************************
*                                                  *
*           Version  22.04.00.**                   *
*           Proprietary Program of                 *
*           Bentley Systems, Inc.                  *
*           Date=    APR 21, 2020                  *
*           Time=    15:41:16                      *
*                                                  *
*  Licensed to: Bentley Systems Inc                *
****************************************************
1. STAAD PLANE A PLANE FRAME STRUCTURE WITH
INPUT FILE: UK-4 Inactive Members in a Braced Frame.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
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
45. 4 FX 135 ; 7 FX 65
46. PERFORM ANALYSIS
47. CHANGE
48. INACTIVE MEMBERS 9 12 14
51. 6 FX -135 ; 8 FX -65
53. 1 0.75 2 0.75
55. 1 0.75 3 0.75
56. PERFORM ANALYSIS
57. CHANGE
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. BEAM 1 ALL
65. UNL 1.8 ALL
66. KY 0.5 ALL
67. CHECK CODE ALL
STEEL DESIGN
STAAD.PRO CODE CHECKING - BS EN 1993-1-1:2005
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NATIONAL ANNEX - NA to BS EN 1993-1-1:2005
PROGRAM CODE REVISION V1.13 BS_EC3_2005/1
A PLANE FRAME STRUCTURE WITH                             -- PAGE NO.    7
* TENSION BRACING
ALL UNITS ARE - KNS  METE (UNLESS OTHERWISE Noted)
FX            MY             MZ       LOCATION
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*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            1
1 ST  UB305X165X40 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.097         5
59.49 C          0.00          -5.33        4.50
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            2
2 ST  UB305X165X40 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.149         5
135.82 C          0.00          -1.81        4.50
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            3
3 ST  UB305X165X40 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.112         5
45.79 C          0.00          -9.62        4.50
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            4
4 ST  UB305X165X40 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.129         4
101.47 C          0.00           3.98        4.50
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            5
5 ST  UB305X165X40 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.096         4
45.76 C          0.00           7.37        4.50
A PLANE FRAME STRUCTURE WITH                             -- PAGE NO.    8
* TENSION BRACING
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            6
6 ST  UB457X152X52 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.176         4
101.34 C          0.00         -15.82        6.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            7
7 ST  UB457X152X52 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.241         5
146.24 C          0.00          19.84        0.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            8
8 ST  UB457X152X52 (BRITISH SECTIONS)
PASS     EC-6.3.3-662       0.096         5
50.12 C          0.00           9.62        0.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER            9
9 LD  UA150X150X10 (BRITISH SECTIONS)
PASS     EC-6.2.3 (T)       0.085         4
117.24 T          0.00           0.00        0.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER           10
10 LD  UA150X150X10 (BRITISH SECTIONS)
PASS     EC-6.2.3 (T)       0.061         5
83.41 T          0.00           0.00        0.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER           11
11 LD  UA150X150X10 (BRITISH SECTIONS)
PASS     EC-6.2.3 (T)       0.074         5
102.46 T          0.00           0.00        0.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER           12
12 LD  UA150X150X10 (BRITISH SECTIONS)
PASS     EC-6.2.3 (T)       0.050         4
68.84 T          0.00           0.00        0.00
A PLANE FRAME STRUCTURE WITH                             -- PAGE NO.    9
* TENSION BRACING
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER           13
13 LD  UA150X150X10 (BRITISH SECTIONS)
PASS     EC-6.2.3 (T)       0.042         5
57.59 T          0.00           0.00        0.00
*** WARNING:BEAM PARAM CHANGED FROM DEFAULT OF 3
DESIGN MIGHT NOT PROVIDE THE WORST CASE
UTILIZATION FOR MEMBER           14
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 **************
68. FINISH
*********** END OF THE STAAD.Pro RUN ***********
**** DATE= APR 21,2020   TIME= 15:41:17 ****
A PLANE FRAME STRUCTURE WITH                             -- PAGE NO.   10
* TENSION BRACING
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