# EX. US-11 Response Spectrum Analysis of a Frame

Dynamic analysis (Response Spectrum) is performed for a steel structure. Results of a static and dynamic analysis are combined. The combined results are then used for steel design.

This problem is installed with the program by default to C:\Users\Public\Public Documents\STAAD.Pro CONNECT Edition\Samples\Sample Models\US\US-11 Response Spectrum Analysis of a Frame.STD when you install the program.

### Example Problem No. 11

Where:

• L1 = 10 ft, L2 = 20 ft
• w = 1.5 k/ft
• P1 = 5.0 kips, P2 = 7.5 kips

Actual input is shown in bold lettering followed by explanation.

```    STAAD PLANE RESPONSE SPECTRUM ANALYSIS
```

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 FEET KIPS
```

Defines the input units for the data that follows.

```    JOINT COORDINATES
1  0  0  0  ;  2  20  0  0
3  0  10  0  ;  4  20  10  0
5  0  20  0  ;  6  20  20  0
```

Joint number followed by X, Y and Z coordinates are provided above. Since this is a plane structure, the Z coordinates are all the same, in this case, zeros.

Note: Semicolons (;) are used as line separators to allow for input of multiple sets of data on one line.
```    MEMBER INCIDENCES
1 1 3 ; 2 2 4 ; 3 3 5 ; 4 4 6
5 3 4 ; 6 5 6
```

Defines the members by the joints to which they are connected.

```    MEMBER PROPERTIES AMERICAN
1 TO 4 TA ST W10X33
5 TA ST W12X40
6 TA ST W8X40
```

Properties for all members are assigned from the American (AISC) steel table. The word ST stands for standard single section.

```    SUPPORTS
1 2 FIXED
```

Fixed supports are specified at joints 1 and 2.

```    UNIT INCH
DEFINE MATERIAL START
ISOTROPIC STEEL
E 29000.
POISSON 0.3
DENSITY 283e-006
ALPHA 6e-006
DAMP 0.03
TYPE STEEL
STRENGTH FY 36 FU 58 RY 1.5 RT 1.2
END DEFINE MATERIAL
CONSTANT
MATERIAL STEEL ALL```

Material constants such as E (modulus of elasticity), Poisson’s ratio and density (DEN) are specified above. Length unit is changed from FT to INCH to facilitate the input.

```    CUT OFF MODE SHAPE 2
```

The number of mode shapes to be considered in dynamic analysis is set to 2. Without the above command, this will be set to the default. See TR.30.1 Cut-Off Frequency, Mode Shapes, or Time .

```    * LOAD 1 WILL BE STATIC LOAD
UNIT FEET
```

Load case 1 is initiated followed by a title. Prior to this, the length unit is changed to METER for specifying distributed member loads. A line starting with an asterisk (*) mark indicates a comment line.

```    SELFWEIGHT Y -1.0
```

The above command indicates that the selfweight of the structure acting in the global Y direction is part of this load case. The factor of -1.0 is meant to indicate that the load acts opposite to the positive direction of global Y, hence downwards.

```    MEMBER LOADS
5  CON  GY  -5.0  6.0
5  CON  GY  -7.5  10.0
5  CON  GY  -5.0  14.0
5  6  UNI  Y  -1.5
```

Load 1 contains member loads also. GY indicates that the load is in the global Y direction while Y indicates local Y direction. The word UNI stands for uniformly distributed load while CON stands for concentrated load. GY is followed by the value of the load and the distance at which it is applied.

```    * NEXT LOAD WILL BE RESPONSE SPECTRUM LOAD
* WITH MASSES PROVIDED IN TERMS OF LOAD.
```

The two lines which begin with the asterisk are comment lines which tell us the purpose of the next load case. Load case 2 is then initiated along with an optional title. This will be a dynamic load case. Permanent masses will be provided in the form of loads. These masses (in terms of loads) will be considered for the eigensolution. Internally, the program converts these loads to masses, hence it is best to specify them as absolute values (without a negative sign). Also, the direction (X, Y, Z etc.) of the loads will correspond to the dynamic degrees of freedom in which the masses are capable of vibrating. In a PLANE frame, only X and Y directions need to be considered. In a SPACE frame, masses (loads) should be provided in all three (X, Y and Z) directions if they are active along all three. The user has the freedom to restrict one or more directions.

```    SELFWEIGHT X 1.0
SELFWEIGHT Y 1.0
```

The above commands indicate that the selfweight of the structure acting in the global X and Y directions with a factor of 1.0 is taken into consideration for the mass matrix.

```    MEMBER LOADS
5  CON  GX  5.0  6.0
5  CON  GY  5.0  6.0
5  CON  GX  7.5  10.0
5  CON  GY  7.5  10.0
5  CON  GX  5.0  14.0
5  CON  GY  5.0  14.0
```

The mass matrix will also consist of terms derived from the above member loads. GX and GY indicate that the load, and hence the resulting mass, is capable of vibration along the global X and Y directions. The word CON stands for concentrated load. Concentrated forces of 5, 7.5, and 5 kips are located at 6ft, 10ft and 14ft from the start of member 5.

```    SPECTRUM CQC IBC 2012 X 1.0 ACC DAMP 0.05
ZIP 92806 SITE CLASS D TL 12.0```

The SPECTRUM command specifies a 2012 International Buidling Code / ASCE 7-10 seismic response spectrum load. The modal responses will be combined using the CQC method. Here, the spectrum effect is in the global X direction with a factor of 1.0. IBC 2012 response spectra are always given in terms of acceleration (ACC). A damping ratio of 0.05 (5%) is used. The second line then gives the location and site class values (using the US ZIP postal code and IBC/ASCE site class) along with the long period transition time.

```    LOAD LIST  1  3  4
PARAMETER
CODE AISC UNIFIED
SELECT ALL
```

A steel design in the form of a member selection is performed based on the rules of the American Code. Only the member forces resulting from load cases 1, 3 and 4 will be considered for these calculations.

```    FINISH
```

This command terminates the STAAD run.

## Input File

``````STAAD PLANE RESPONSE SPECTRUM ANALYSIS
UNIT FEET KIPS
JOINT COORDINATES
1 0 0 0 ; 2 20 0 0
3 0 10 0 ; 4 20 10 0
5 0 20 0 ; 6 20 20 0
MEMBER INCIDENCES
1 1 3 ; 2 2 4 ; 3 3 5 ; 4 4 6
5 3 4 ; 6 5 6
MEMBER PROPERTIES AMERICAN
1 TO 4 TA ST W10X33
5 TA ST W12X40
6 TA ST W8X40
SUPPORTS
1 2 FIXED
UNIT INCH
DEFINE MATERIAL START
ISOTROPIC STEEL
E 29000.
POISSON 0.3
DENSITY 283e-006
ALPHA 6e-006
DAMP 0.03
TYPE STEEL
STRENGTH FY 36 FU 58 RY 1.5 RT 1.2
END DEFINE MATERIAL
CONSTANT
MATERIAL STEEL ALL
CUT OFF MODE SHAPE 2
UNIT FEET
SELFWEIGHT Y -1.0
5 CON GY -5.0  6.0
5 CON GY -7.5 10.0
5 CON GY -5.0 14.0
5 6 UNI Y -1.5
* NEXT LOAD WILL BE RESPONSE SPECTRUM LOAD
* WITH MASSES PROVIDED IN TERMS OF LOAD.
SELFWEIGHT X 1.0
SELFWEIGHT Y 1.0
5 CON GX 5.0 6.0
5 CON GY 5.0 6.0
5 CON GX 7.5 10.0
5 CON GY 7.5 10.0
5 CON GX 5.0 14.0
5 CON GY 5.0 14.0
SPECTRUM CQC IBC 2012 X 1.0 ACC DAMP 0.05
ZIP 92806 SITE CLASS D TL 12.0
1 0.75 2 0.75
1 0.75 2 -0.75
PERFORM ANALYSIS PRINT MODE SHAPES
PRINT ANALYSIS RESULTS
LOAD LIST 1 3 4
PARAMETER
CODE AISC UNIFIED
SELECT ALL
FINISH
``````

## STAAD Output File

```                                                                  PAGE NO.    1
****************************************************
*                                                  *
*           STAAD.Pro CONNECT Edition              *
*           Version  22.08.00.***                  *
*           Proprietary Program of                 *
*           Bentley Systems, Inc.                  *
*           Date=    OCT 19, 2021                  *
*           Time=    17:54:46                      *
*                                                  *
*  Licensed to: Bentley Systems Inc                *
****************************************************
1. STAAD PLANE RESPONSE SPECTRUM ANALYSIS
INPUT FILE: US-11 Response Spectrum Analysis of a Frame.STD
2. UNIT FEET KIPS
3. JOINT COORDINATES
4. 1 0 0 0 ; 2 20 0 0
5. 3 0 10 0 ; 4 20 10 0
6. 5 0 20 0 ; 6 20 20 0
7. MEMBER INCIDENCES
8. 1 1 3 ; 2 2 4 ; 3 3 5 ; 4 4 6
9. 5 3 4 ; 6 5 6
10. MEMBER PROPERTIES AMERICAN
11. 1 TO 4 TA ST W10X33
12. 5 TA ST W12X40
13. 6 TA ST W8X40
14. SUPPORTS
15. 1 2 FIXED
16. UNIT INCH
17. DEFINE MATERIAL START
18. ISOTROPIC STEEL
19. E 29000.
20. POISSON 0.3
21. DENSITY 283E-006
22. ALPHA 6E-006
23. DAMP 0.03
24. TYPE STEEL
25. STRENGTH FY 36 FU 58 RY 1.5 RT 1.2
26. END DEFINE MATERIAL
27. CONSTANT
28. MATERIAL STEEL ALL
29. CUT OFF MODE SHAPE 2
30. *LOAD 1 WILL BE STATIC LOAD
31. UNIT FEET
33. SELFWEIGHT Y -1.0
35. 5 CON GY -5.0  6.0
36. 5 CON GY -7.5 10.0
37. 5 CON GY -5.0 14.0
38. 5 6 UNI Y -1.5
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    2
39. * NEXT LOAD WILL BE RESPONSE SPECTRUM LOAD
40. * WITH MASSES PROVIDED IN TERMS OF LOAD.
42. SELFWEIGHT X 1.0
43. SELFWEIGHT Y 1.0
45. 5 CON GX 5.0 6.0
46. 5 CON GY 5.0 6.0
47. 5 CON GX 7.5 10.0
48. 5 CON GY 7.5 10.0
49. 5 CON GX 5.0 14.0
50. 5 CON GY 5.0 14.0
51. SPECTRUM CQC IBC 2012 X 1.0 ACC DAMP 0.05
52. ZIP 92806 SITE CLASS D TL 12.0
53. LOAD COMBINATION 3
54. 1 0.75 2 0.75
55. LOAD COMBINATION 4
56. 1 0.75 2 -0.75
57. PERFORM ANALYSIS PRINT MODE SHAPES
P R O B L E M   S T A T I S T I C S
-----------------------------------
NUMBER OF JOINTS          6  NUMBER OF MEMBERS       6
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 =     2, TOTAL DEGREES OF FREEDOM =      12
TOTAL LOAD COMBINATION  CASES =     2  SO FAR.
***NOTE: MASSES DEFINED UNDER LOAD#       2 WILL FORM
THE FINAL MASS MATRIX FOR DYNAMIC ANALYSIS.
EIGEN METHOD   : SUBSPACE
-------------------------
NUMBER OF MODES REQUESTED              =     2
NUMBER OF EXISTING MASSES IN THE MODEL =     8
NUMBER OF MODES THAT WILL BE USED      =     2
***  EIGENSOLUTION : ADVANCED METHOD ***
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    3
CALCULATED FREQUENCIES FOR LOAD CASE       2
MODE            FREQUENCY(CYCLES/SEC)         PERIOD(SEC)
1                       4.493                  0.22258
2                      16.308                  0.06132
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    4
MODE SHAPES
-----------
JOINT  MODE   X-TRANS   Y-TRANS   Z-TRANS    X-ROTAN    Y-ROTAN    Z-ROTAN
1     1    0.00000   0.00000   0.00000  0.000E+00  0.000E+00  0.000E+00
2     1    0.00000   0.00000   0.00000  0.000E+00  0.000E+00  0.000E+00
3     1    0.67185   0.00308   0.00000  0.000E+00  0.000E+00 -3.367E-03
4     1    0.67185  -0.00308   0.00000  0.000E+00  0.000E+00 -3.367E-03
5     1    1.00000   0.00360   0.00000  0.000E+00  0.000E+00 -1.467E-03
6     1    1.00000  -0.00360   0.00000  0.000E+00  0.000E+00 -1.467E-03
MODE SHAPES
-----------
JOINT  MODE   X-TRANS   Y-TRANS   Z-TRANS    X-ROTAN    Y-ROTAN    Z-ROTAN
1     2    0.00000   0.00000   0.00000  0.000E+00  0.000E+00  0.000E+00
2     2    0.00000   0.00000   0.00000  0.000E+00  0.000E+00  0.000E+00
3     2   -0.08832   0.00516   0.00000  0.000E+00  0.000E+00 -2.620E-03
4     2   -0.08832  -0.00516   0.00000  0.000E+00  0.000E+00 -2.620E-03
5     2    1.00000   0.00780   0.00000  0.000E+00  0.000E+00 -7.148E-03
6     2    1.00000  -0.00780   0.00000  0.000E+00  0.000E+00 -7.148E-03
RESPONSE SPECTRUM LOAD     2
RESPONSE LOAD CASE      2
MODAL WEIGHT (MODAL MASS TIMES g) IN KIPS         GENERALIZED
MODE           X             Y             Z              WEIGHT
1       1.984110E+01  2.545506E-33  0.000000E+00    9.680166E+00
2       2.373892E-01  2.473935E-28  0.000000E+00    1.272852E+00
CQC           MODAL COMBINATION METHOD USED.
DYNAMIC WEIGHT X Y Z   2.007858E+01  2.007858E+01  0.000000E+00 KIPS
MISSING WEIGHT X Y Z  -9.338434E-05 -2.007858E+01  0.000000E+00 KIPS
MODAL WEIGHT X Y Z   2.007849E+01  2.473961E-28  0.000000E+00 KIPS
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    5
MODE                 ACCELERATION-G     DAMPING
----                 --------------     -------
1                      1.03090       0.05000
2                      0.74526       0.05000
MODAL BASE ACTIONS
MODAL BASE ACTIONS        FORCES IN KIPS LENGTH IN FEET
-----------------------------------------------------------
MOMENTS ARE ABOUT THE ORIGIN
MODE     PERIOD        FX          FY          FZ          MX          MY          MZ
1      0.223       20.45       -0.00        0.00        0.00        0.00     -222.06
2      0.061        0.18       -0.00        0.00        0.00        0.00        2.19
PARTICIPATION FACTORS
MASS  PARTICIPATION FACTORS IN PERCENT         BASE SHEAR IN KIPS
--------------------------------------         ------------------
MODE    X     Y     Z     SUMM-X   SUMM-Y   SUMM-Z       X        Y        Z
1   98.82  0.00  0.00   98.817    0.000    0.000     20.45     0.00     0.00
2    1.18  0.00  0.00   99.999    0.000    0.000      0.18     0.00     0.00
---------------------------
TOTAL SRSS  SHEAR     20.46     0.00     0.00
TOTAL 10PCT SHEAR     20.46     0.00     0.00
TOTAL ABS   SHEAR     20.63     0.00     0.00
TOTAL CQC   SHEAR     20.46     0.00     0.00
58. PRINT ANALYSIS RESULTS
ANALYSIS RESULTS
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    6
JOINT DISPLACEMENT (INCH RADIANS)    STRUCTURE TYPE = PLANE
------------------
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   0.00000
2    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
3    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
4    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
2    1    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
2    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
3    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
4    0.00000   0.00000   0.00000   0.00000   0.00000   0.00000
3    1   -0.00151  -0.01706   0.00000   0.00000   0.00000  -0.00248
2    0.48043   0.00220   0.00000   0.00000   0.00000   0.00241
3    0.35919  -0.01115   0.00000   0.00000   0.00000  -0.00005
4   -0.36146  -0.01445   0.00000   0.00000   0.00000  -0.00366
4    1    0.00151  -0.01706   0.00000   0.00000   0.00000   0.00248
2    0.48043   0.00220   0.00000   0.00000   0.00000   0.00241
3    0.36146  -0.01115   0.00000   0.00000   0.00000   0.00366
4   -0.35919  -0.01445   0.00000   0.00000   0.00000   0.00005
5    1    0.00313  -0.02369   0.00000   0.00000   0.00000  -0.00244
2    0.71519   0.00258   0.00000   0.00000   0.00000   0.00105
3    0.53874  -0.01584   0.00000   0.00000   0.00000  -0.00104
4   -0.53404  -0.01970   0.00000   0.00000   0.00000  -0.00262
6    1   -0.00313  -0.02369   0.00000   0.00000   0.00000   0.00244
2    0.71519   0.00258   0.00000   0.00000   0.00000   0.00105
3    0.53404  -0.01584   0.00000   0.00000   0.00000   0.00262
4   -0.53874  -0.01970   0.00000   0.00000   0.00000   0.00104
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    7
SUPPORT REACTIONS -UNIT KIPS FEET    STRUCTURE TYPE = PLANE
-----------------
JOINT  LOAD   FORCE-X   FORCE-Y   FORCE-Z     MOM-X     MOM-Y     MOM Z
1    1      4.57     40.20      0.00      0.00      0.00    -14.33
2     10.23      5.16      0.00      0.00      0.00     59.43
3     11.10     34.02      0.00      0.00      0.00     33.83
4     -4.24     26.28      0.00      0.00      0.00    -55.32
2    1     -4.57     40.20      0.00      0.00      0.00     14.33
2     10.23      5.16      0.00      0.00      0.00     59.43
3      4.24     34.02      0.00      0.00      0.00     55.32
4    -11.10     26.28      0.00      0.00      0.00    -33.83
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    8
MEMBER END FORCES    STRUCTURE TYPE = PLANE
-----------------
ALL UNITS ARE -- KIPS FEET     (LOCAL )
MEMBER  LOAD  JT     AXIAL   SHEAR-Y  SHEAR-Z   TORSION     MOM-Y      MOM-Z
1    1     1     40.20     -4.57     0.00      0.00      0.00     -14.33
3    -39.87      4.57     0.00      0.00      0.00     -31.39
2     1      5.16     10.23     0.00      0.00      0.00      59.43
3      5.16     10.23     0.00      0.00      0.00      42.85
3     1     34.02      4.24     0.00      0.00      0.00      33.83
3    -33.78     -4.24     0.00      0.00      0.00     -55.68
4     1     26.28    -11.10     0.00      0.00      0.00     -55.32
3    -26.03     11.10     0.00      0.00      0.00       8.59
2    1     2     40.20      4.57     0.00      0.00      0.00      14.33
4    -39.87     -4.57     0.00      0.00      0.00      31.39
2     2      5.16     10.23     0.00      0.00      0.00      59.43
4      5.16     10.23     0.00      0.00      0.00      42.85
3     2     34.02     11.10     0.00      0.00      0.00      55.32
4    -33.78    -11.10     0.00      0.00      0.00      -8.59
4     2     26.28     -4.24     0.00      0.00      0.00     -33.83
4    -26.03      4.24     0.00      0.00      0.00      55.68
3    1     3     15.73     -8.85     0.00      0.00      0.00     -44.36
5    -15.40      8.85     0.00      0.00      0.00     -44.14
2     3      0.89      0.85     0.00      0.00      0.00       1.21
5      0.89      0.85     0.00      0.00      0.00       8.86
3     3     12.46     -6.00     0.00      0.00      0.00     -32.36
5    -12.21      6.00     0.00      0.00      0.00     -39.74
4     3     11.13     -7.27     0.00      0.00      0.00     -34.18
5    -10.88      7.27     0.00      0.00      0.00     -26.46
4    1     4     15.73      8.85     0.00      0.00      0.00      44.36
6    -15.40     -8.85     0.00      0.00      0.00      44.14
2     4      0.89      0.85     0.00      0.00      0.00       1.21
6      0.89      0.85     0.00      0.00      0.00       8.86
3     4     12.46      7.27     0.00      0.00      0.00      34.18
6    -12.21     -7.27     0.00      0.00      0.00      26.46
4     4     11.13      6.00     0.00      0.00      0.00      32.36
6    -10.88     -6.00     0.00      0.00      0.00      39.74
5    1     3     -4.28     24.15     0.00      0.00      0.00      75.75
4      4.28     24.15     0.00      0.00      0.00     -75.75
2     3      0.00      4.23     0.00      0.00      0.00      42.32
4      0.00      4.23     0.00      0.00      0.00      42.32
3     3     -3.21     21.28     0.00      0.00      0.00      88.55
4      3.21     14.94     0.00      0.00      0.00     -88.55
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.    9
MEMBER END FORCES    STRUCTURE TYPE = PLANE
-----------------
ALL UNITS ARE -- KIPS FEET     (LOCAL )
MEMBER  LOAD  JT     AXIAL   SHEAR-Y  SHEAR-Z   TORSION     MOM-Y      MOM-Z
4     3     -3.21     14.94     0.00      0.00      0.00      25.08
4      3.21     21.28     0.00      0.00      0.00     -25.08
6    1     5      8.85     15.40     0.00      0.00      0.00      44.14
6     -8.85     15.40     0.00      0.00      0.00     -44.14
2     5      0.00      0.89     0.00      0.00      0.00       8.86
6      0.00      0.89     0.00      0.00      0.00       8.86
3     5      6.64     12.21     0.00      0.00      0.00      39.74
6     -6.64     10.88     0.00      0.00      0.00     -39.74
4     5      6.64     10.88     0.00      0.00      0.00      26.46
6     -6.64     12.21     0.00      0.00      0.00     -26.46
************** END OF LATEST ANALYSIS RESULT **************
59. LOAD LIST 1 3 4
60. PARAMETER
61. CODE AISC UNIFIED
62. SELECT ALL
PARAMETER 1
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.   10
STAAD.PRO MEMBER SELECTION - AISC 360-16 LRFD (V1.2)
********************************************************
ALL UNITS ARE - KIPS FEET (UNLESS OTHERWISE Noted).
***NOTE : AISC 360-16 Design Statement for STAAD.Pro.
*** AXIS CONVENTION ***:
========================
The capacity results and intermediate results in the report follow the notations
and axes labels as defined in the AISC 360-16 code.
The analysis results are reported in STAAD.Pro axis convention and the AISC 360:16
design results are reported in AISC 360-16 code axis convention.
AISC Spec.      STAAD.Pro      Description
------------    -----------     -------------
X               Z          Axis typically parallel to the sections principal major axis.
Y               Y          Axis typically parallel to the sections principal minor axis.
Z               X          Longitudinal axis perpendicular to the cross section.
SECTION FORCES AXIS MAPPING: -
AISC Spec.      STAAD.Pro      Description
------------    -----------     -------------
Pz              FX         Axial force.
Vy              FY         Shear force along minor axis.
Vx              FZ         Shear force along major axis.
Tz              MX         Torsional moment.
My              MY         Bending moment about minor axis.
Mx              MZ         Bending moment about major axis.
*** DESIGN MESSAGES ***:
=======================
1. Section classification reported is for the cross section and loadcase that
produced the worst case design ratio for flexure/compression Capacity results.
2. Results for any Capacity/Check that is not relevant for a section/loadcase
based on the code clause in AISC 360-16 will not be shown in the report.
3. Bending results are reported as being �about� the relevant axis (X/Y), while
the results for shear are reported as being for shear forces �along� the axis.
E.g : Mx indicates bending about the X axis, while Vx indicates shear along
the X axis.
*** ABBREVIATIONS ***:
======================
F-T-B = Flexural-Torsional Buckling
L-T-B = Lateral-Torsional Buckling
F-L-B = Flange Local Buckling
W-L-B = Web Local Buckling
L-L-B = Leg Local Buckling
C-F-Y = Compression Flange Yielding
T-F-Y = Tension Flange Yielding
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.   11
STAAD.PRO MEMBER SELECTION - AISC 360-16 LRFD (V1.2)
********************************************************
ALL UNITS ARE - KIPS FEET (UNLESS OTHERWISE Noted).
- Member :     1
|-----------------------------------------------------------------------------|
|  Member No:        1       Profile:  ST  W10X26              (AISC SECTIONS)|
|  Status:        PASS       Ratio:         0.851       Loadcase:        3    |
|  Location:     10.00       Ref:      Eq.H1-3b                               |
|  Pz:       33.78     C     Vy:        4.242           Vx:      0.000        |
|  Tz:       0.000           My:        0.000           Mx:      55.68        |
|-----------------------------------------------------------------------------|
- Member :     2
|-----------------------------------------------------------------------------|
|  Member No:        2       Profile:  ST  W10X26              (AISC SECTIONS)|
|  Status:        PASS       Ratio:         0.846       Loadcase:        3    |
|  Location:      0.00       Ref:      Eq.H1-3b                               |
|  Pz:       34.02     C     Vy:        11.10           Vx:      0.000        |
|  Tz:       0.000           My:        0.000           Mx:      55.32        |
|-----------------------------------------------------------------------------|
- Member :     3
|-----------------------------------------------------------------------------|
|  Member No:        3       Profile:  ST  W12X22              (AISC SECTIONS)|
|  Status:        PASS       Ratio:         0.951       Loadcase:        1    |
|  Location:      0.00       Ref:      Eq.H1-1a                               |
|  Pz:       15.73     C     Vy:       -8.850           Vx:      0.000        |
|  Tz:       0.000           My:        0.000           Mx:     -44.36        |
|-----------------------------------------------------------------------------|
- Member :     4
|-----------------------------------------------------------------------------|
|  Member No:        4       Profile:  ST  W12X22              (AISC SECTIONS)|
|  Status:        PASS       Ratio:         0.951       Loadcase:        1    |
|  Location:      0.00       Ref:      Eq.H1-1a                               |
|  Pz:       15.73     C     Vy:        8.850           Vx:      0.000        |
|  Tz:       0.000           My:        0.000           Mx:      44.36        |
|-----------------------------------------------------------------------------|
- Member :     5
|-----------------------------------------------------------------------------|
|  Member No:        5       Profile:  ST  W12X35              (AISC SECTIONS)|
|  Status:        PASS       Ratio:         0.980       Loadcase:        3    |
|  Location:      0.00       Ref:      Cl.F2.2                                |
|  Pz:       3.209     T     Vy:        21.28           Vx:      0.000        |
|  Tz:       0.000           My:        0.000           Mx:      88.55        |
|-----------------------------------------------------------------------------|
- Member :     6
|-----------------------------------------------------------------------------|
|  Member No:        6       Profile:  ST  W12X26              (AISC SECTIONS)|
|  Status:        PASS       Ratio:         0.821       Loadcase:        1    |
|  Location:      0.00       Ref:      Eq.H1-3b                               |
|  Pz:       8.850     C     Vy:        15.40           Vx:      0.000        |
|  Tz:       0.000           My:        0.000           Mx:      44.14        |
|-----------------------------------------------------------------------------|
63. FINISH
****************************************************************************
**WARNING** SOME MEMBER SIZES HAVE CHANGED SINCE LAST ANALYSIS.
IN THE POST PROCESSOR, MEMBER QUERIES WILL USE THE LAST
ANALYSIS FORCES WITH THE UPDATED MEMBER SIZES.
TO CORRECT THIS INCONSISTENCY, PLEASE DO ONE MORE ANALYSIS.
FROM THE UPPER MENU, PRESS RESULTS, UPDATE PROPERTIES, THEN
FILE SAVE; THEN ANALYZE AGAIN WITHOUT THE GROUP OR SELECT
COMMANDS.
****************************************************************************
*********** END OF THE STAAD.Pro RUN ***********
**** DATE= OCT 19,2021   TIME= 17:54:47 ****
RESPONSE SPECTRUM ANALYSIS                               -- PAGE NO.   12
************************************************************
*   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                    *
************************************************************
```