EX. US-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\US\US-4 Inactive Members in a Braced Frame.STD when you install the program.
Example Problem No. 4
Where:
- L1 = 180 in., L2 = 240 in.
- P1 = 15 kips, P2 = 30 kips
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 INCH KIP
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 3 480. 0 0
4 0 180. 0 6 480. 180. 0
7 240. 360. 0 ; 8 480. 360. 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 AMERICAN
1 TO 5 TABLE ST W12X26
6 7 8 TA ST W18X35
9 TO 14 TA LD L50505
Properties for all members are assigned from the American (AISC) 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.
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
Define the material properties for steel. The units are changed to inches and then back to feet in order to facilite inputing the values in familiar units.
CONSTANTS MATERIAL STEEL ALL
The CONSTANT command initiates input for material defintions.
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 FT
LOADING 1 DEAD AND LIVE LOAD
Load case 1 is initiated followed by a title. The length UNIT is changed from INCH to FT for input values which follow.
MEMBER LOAD
6 8 UNI GY -1.0
7 UNI GY -1.5
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 30 ; 7 FX 15
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 -30 ; 8 FX -15
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
(-30 and -15) 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 AISC UNIFIED
BEAM 1.0 ALL
UNT 6.0 ALL
UNB 6.0 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). Design will be done according to the specifications of the AISC ASD Code. The BEAM parameter is specified to perform design at every 1/12th point along the member length. UNT and UNB represent the unsupported length of the flanges 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 INCH KIP
SET NL 3
JOINT COORDINATES
1 0 0 0 3 480. 0 0
4 0 180. 0 6 480. 180. 0
7 240. 360. 0 ; 8 480. 360. 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 AMERICAN
1 TO 5 TABLE ST W12X26
6 7 8 TA ST W18X35
9 TO 14 TA LD L50505
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
SUPPORT
1 2 3 PINNED
INACTIVE MEMBERS 9 TO 14
UNIT FT
LOADING 1 DEAD AND LIVE LOAD
MEMBER LOAD
6 8 UNI GY -1.0
7 UNI GY -1.5
PERFORM ANALYSIS
CHANGES
INACTIVE MEMBERS 10 11 13
LOADING 2 WIND FROM LEFT
JOINT LOAD
4 FX 30 ; 7 FX 15
PERFORM ANALYSIS
CHANGE
INACTIVE MEMBERS 9 12 14
LOADING 3 WIND FROM RIGHT
JOINT LOAD
6 FX -30 ; 8 FX -15
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 AISC UNIFIED
BEAM 1.0 ALL
UNT 6.0 ALL
UNB 6.0 ALL
KY 0.5 ALL
CHECK CODE ALL
FINISH
STAAD Output File
PAGE NO. 1 **************************************************** * * * STAAD.Pro CONNECT Edition * * Version 22.12.00.*** * * Proprietary Program of * * Bentley Systems, Inc. * * Date= OCT 27, 2022 * * Time= 15:10:13 * * * * Licensed to: Bentley Systems Inc * **************************************************** 1. STAAD PLANE A PLANE FRAME STRUCTURE WITH TENSION BRACING INPUT FILE: US-4 Inactive Members in a Braced Frame.STD 2. UNIT INCH KIP 3. SET NL 3 4. JOINT COORDINATES 5. 1 0 0 0 3 480. 0 0 6. 4 0 180. 0 6 480. 180. 0 7. 7 240. 360. 0 ; 8 480. 360. 0 8. MEMBER INCIDENCE 9. 1 1 4 2 ; 3 5 7 ; 4 3 6 ; 5 6 8 ; 6 4 5 7 10. 8 7 8 ; 9 1 5 ; 10 2 4 ; 11 3 5 ; 12 2 6 11. 13 6 7 ;14 5 8 12. MEMBER TRUSS 13. 9 TO 14 14. MEMBER PROP AMERICAN 15. 1 TO 5 TABLE ST W12X26 16. 6 7 8 TA ST W18X35 17. 9 TO 14 TA LD L50505 18. DEFINE MATERIAL START 19. ISOTROPIC STEEL 20. E 29000 21. POISSON 0.3 22. DENSITY 283E-006 23. ALPHA 6E-006 24. DAMP 0.03 25. TYPE STEEL 26. STRENGTH FY 36 FU 58 RY 1.5 RT 1.2 27. END DEFINE MATERIAL 28. CONSTANT 29. MATERIAL STEEL ALL 30. SUPPORT 31. 1 2 3 PINNED 32. INACTIVE MEMBERS 9 TO 14 33. UNIT FT 34. LOADING 1 DEAD AND LIVE LOAD 35. MEMBER LOAD 36. 6 8 UNI GY -1.0 37. 7 UNI GY -1.5 38. PERFORM ANALYSIS A PLANE FRAME STRUCTURE WITH TENSION BRACING -- PAGE NO. 2 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. 39. CHANGES 40. INACTIVE MEMBERS 10 11 13 41. LOADING 2 WIND FROM LEFT 42. JOINT LOAD 43. 4 FX 30 ; 7 FX 15 44. PERFORM ANALYSIS 45. CHANGE 46. INACTIVE MEMBERS 9 12 14 47. LOADING 3 WIND FROM RIGHT 48. JOINT LOAD 49. 6 FX -30 ; 8 FX -15 50. LOAD COMBINATION 4 51. 1 0.75 2 0.75 52. LOAD COMBINATION 5 53. 1 0.75 3 0.75 54. PERFORM ANALYSIS 55. CHANGE 56. LOAD LIST ALL 57. PRINT MEMBER FORCES MEMBER FORCES A PLANE FRAME STRUCTURE WITH TENSION BRACING -- PAGE NO. 3 MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP FEET (LOCAL ) MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z 1 1 1 8.26 -0.67 0.00 0.00 0.00 -0.00 4 -8.26 0.67 0.00 0.00 0.00 -10.06 2 1 -0.31 0.22 0.00 0.00 0.00 0.00 4 0.31 -0.22 0.00 0.00 0.00 3.25 3 1 15.81 -0.19 0.00 0.00 0.00 -0.00 4 -15.81 0.19 0.00 0.00 0.00 -2.88 4 1 5.97 -0.34 0.00 0.00 0.00 -0.00 4 -5.97 0.34 0.00 0.00 0.00 -5.11 5 1 18.06 -0.65 0.00 0.00 0.00 -0.00 4 -18.06 0.65 0.00 0.00 0.00 -9.71 2 1 2 38.47 -0.05 0.00 0.00 0.00 0.00 5 -38.47 0.05 0.00 0.00 0.00 -0.77 2 2 9.09 0.16 0.00 0.00 0.00 0.00 5 -9.09 -0.16 0.00 0.00 0.00 2.43 3 2 28.81 -0.15 0.00 0.00 0.00 -0.00 5 -28.81 0.15 0.00 0.00 0.00 -2.21 4 2 35.67 0.08 0.00 0.00 0.00 0.00 5 -35.67 -0.08 0.00 0.00 0.00 1.24 5 2 50.46 -0.15 0.00 0.00 0.00 -0.00 5 -50.46 0.15 0.00 0.00 0.00 -2.24 3 1 5 10.14 -2.20 0.00 0.00 0.00 -13.11 7 -10.14 2.20 0.00 0.00 0.00 -19.84 2 5 -0.29 0.42 0.00 0.00 0.00 3.34 7 0.29 -0.42 0.00 0.00 0.00 2.94 3 5 10.88 -0.63 0.00 0.00 0.00 -5.23 7 -10.88 0.63 0.00 0.00 0.00 -4.20 4 5 7.39 -1.33 0.00 0.00 0.00 -7.32 7 -7.39 1.33 0.00 0.00 0.00 -12.68 5 5 15.76 -2.12 0.00 0.00 0.00 -13.76 7 -15.76 2.12 0.00 0.00 0.00 -18.03 4 1 3 23.26 0.72 0.00 0.00 0.00 0.00 6 -23.26 -0.72 0.00 0.00 0.00 10.83 2 3 24.63 0.07 0.00 0.00 0.00 0.00 6 -24.63 -0.07 0.00 0.00 0.00 1.08 3 3 -11.25 -0.16 0.00 0.00 0.00 -0.00 6 11.25 0.16 0.00 0.00 0.00 -2.41 4 3 35.92 0.60 0.00 0.00 0.00 0.00 6 -35.92 -0.60 0.00 0.00 0.00 8.94 5 3 9.01 0.42 0.00 0.00 0.00 -0.00 6 -9.01 -0.42 0.00 0.00 0.00 6.31 A PLANE FRAME STRUCTURE WITH TENSION BRACING -- PAGE NO. 4 MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP FEET (LOCAL ) MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z 5 1 6 9.86 2.20 0.00 0.00 0.00 15.84 8 -9.86 -2.20 0.00 0.00 0.00 17.11 2 6 10.95 0.37 0.00 0.00 0.00 2.68 8 -10.95 -0.37 0.00 0.00 0.00 2.82 3 6 -0.35 -0.33 0.00 0.00 0.00 -2.10 8 0.35 0.33 0.00 0.00 0.00 -2.78 4 6 15.61 1.92 0.00 0.00 0.00 13.89 8 -15.61 -1.92 0.00 0.00 0.00 14.95 5 6 7.14 1.40 0.00 0.00 0.00 10.30 8 -7.14 -1.40 0.00 0.00 0.00 10.75 6 1 4 0.67 8.26 0.00 0.00 0.00 10.06 5 -0.67 11.74 0.00 0.00 0.00 -44.76 2 4 29.78 -0.31 0.00 0.00 0.00 -3.25 5 -29.78 0.31 0.00 0.00 0.00 -2.92 3 4 20.77 0.38 0.00 0.00 0.00 2.88 5 -20.77 -0.38 0.00 0.00 0.00 4.69 4 4 22.84 5.97 0.00 0.00 0.00 5.11 5 -22.84 9.03 0.00 0.00 0.00 -35.76 5 4 16.08 6.48 0.00 0.00 0.00 9.71 5 -16.08 8.52 0.00 0.00 0.00 -30.05 7 1 5 -1.47 16.60 0.00 0.00 0.00 58.64 6 1.47 13.40 0.00 0.00 0.00 -26.67 2 5 17.51 -0.33 0.00 0.00 0.00 -2.85 6 -17.51 0.33 0.00 0.00 0.00 -3.76 3 5 44.21 0.36 0.00 0.00 0.00 2.75 6 -44.21 -0.36 0.00 0.00 0.00 4.52 4 5 12.03 12.20 0.00 0.00 0.00 41.84 6 -12.03 10.30 0.00 0.00 0.00 -22.82 5 5 32.05 12.72 0.00 0.00 0.00 46.04 6 -32.05 9.78 0.00 0.00 0.00 -16.61 8 1 7 2.20 10.14 0.00 0.00 0.00 19.84 8 -2.20 9.86 0.00 0.00 0.00 -17.11 2 7 14.58 -0.29 0.00 0.00 0.00 -2.94 8 -14.58 0.29 0.00 0.00 0.00 -2.82 3 7 14.67 0.35 0.00 0.00 0.00 4.20 8 -14.67 -0.35 0.00 0.00 0.00 2.78 4 7 12.58 7.39 0.00 0.00 0.00 12.68 8 -12.58 7.61 0.00 0.00 0.00 -14.95 5 7 12.65 7.86 0.00 0.00 0.00 18.03 8 -12.65 7.14 0.00 0.00 0.00 -10.75 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 TENSION BRACING -- PAGE NO. 5 MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP FEET (LOCAL ) MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z 2 1 -33.43 0.00 0.00 0.00 0.00 0.00 5 33.43 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 -25.07 0.00 0.00 0.00 0.00 0.00 5 25.07 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 -25.73 0.00 0.00 0.00 0.00 0.00 4 25.73 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 -19.29 0.00 0.00 0.00 0.00 0.00 4 19.29 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 -29.90 0.00 0.00 0.00 0.00 0.00 5 29.90 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 -22.42 0.00 0.00 0.00 0.00 0.00 5 22.42 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 -22.26 0.00 0.00 0.00 0.00 0.00 6 22.26 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 -16.69 0.00 0.00 0.00 0.00 0.00 6 16.69 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 TENSION BRACING -- PAGE NO. 6 MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- KIP FEET (LOCAL ) MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z 3 6 -17.56 0.00 0.00 0.00 0.00 0.00 7 17.56 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 -13.17 0.00 0.00 0.00 0.00 0.00 7 13.17 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 -17.77 0.00 0.00 0.00 0.00 0.00 8 17.77 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 -13.33 0.00 0.00 0.00 0.00 0.00 8 13.33 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 ************** 58. LOAD LIST 1 4 5 59. PARAMETER 60. CODE AISC UNIFIED 61. BEAM 1.0 ALL 62. UNT 6.0 ALL 63. UNB 6.0 ALL 64. KY 0.5 ALL 65. CHECK CODE ALL PARAMETER 1 A PLANE FRAME STRUCTURE WITH TENSION BRACING -- PAGE NO. 7 STAAD.PRO CODE CHECKING - AISC 360-16 LRFD (V1.2) ***************************************************** ALL UNITS ARE - KIP 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 A PLANE FRAME STRUCTURE WITH TENSION BRACING -- PAGE NO. 8 STAAD.PRO CODE CHECKING - AISC 360-16 LRFD (V1.2) ***************************************************** ALL UNITS ARE - KIP FEET (UNLESS OTHERWISE Noted). - Member : 1 |-----------------------------------------------------------------------------| | Member No: 1 Profile: ST W12X26 (AISC SECTIONS)| | Status: PASS Ratio: 0.138 Loadcase: 5 | | Location: 15.00 Ref: Eq.H1-3b | | Pz: 18.06 C Vy: -.6472 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 9.708 | |-----------------------------------------------------------------------------| - Member : 2 |-----------------------------------------------------------------------------| | Member No: 2 Profile: ST W12X26 (AISC SECTIONS)| | Status: PASS Ratio: 0.319 Loadcase: 5 | | Location: 15.00 Ref: Eq.H1-1a | | Pz: 50.46 C Vy: -.1491 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 2.237 | |-----------------------------------------------------------------------------| - Member : 3 |-----------------------------------------------------------------------------| | Member No: 3 Profile: ST W12X26 (AISC SECTIONS)| | Status: PASS Ratio: 0.220 Loadcase: 1 | | Location: 15.00 Ref: Eq.H1-3a(H1-1b) | | Pz: 10.14 C Vy: -2.197 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 19.84 | |-----------------------------------------------------------------------------| - Member : 4 |-----------------------------------------------------------------------------| | Member No: 4 Profile: ST W12X26 (AISC SECTIONS)| | Status: PASS Ratio: 0.256 Loadcase: 4 | | Location: 15.00 Ref: Eq.H1-3b | | Pz: 35.92 C Vy: 0.5957 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: -8.935 | |-----------------------------------------------------------------------------| - Member : 5 |-----------------------------------------------------------------------------| | Member No: 5 Profile: ST W12X26 (AISC SECTIONS)| | Status: PASS Ratio: 0.192 Loadcase: 1 | | Location: 15.00 Ref: Eq.H1-3a(H1-1b) | | Pz: 9.864 C Vy: 2.197 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: -17.11 | |-----------------------------------------------------------------------------| - Member : 6 |-----------------------------------------------------------------------------| | Member No: 6 Profile: ST W18X35 (AISC SECTIONS)| | Status: PASS Ratio: 0.259 Loadcase: 1 | | Location: 20.00 Ref: Cl.F2.2 | | Pz: 0.6707 C Vy: -11.74 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 44.76 | |-----------------------------------------------------------------------------| - Member : 7 |-----------------------------------------------------------------------------| | Member No: 7 Profile: ST W18X35 (AISC SECTIONS)| | Status: PASS Ratio: 0.340 Loadcase: 1 | | Location: 0.00 Ref: Eq.H1-1b | | Pz: 1.474 T Vy: 16.60 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 58.64 | |-----------------------------------------------------------------------------| A PLANE FRAME STRUCTURE WITH TENSION BRACING -- PAGE NO. 9 STAAD.PRO CODE CHECKING - AISC 360-16 LRFD (V1.2) ***************************************************** ALL UNITS ARE - KIP FEET (UNLESS OTHERWISE Noted). - Member : 8 |-----------------------------------------------------------------------------| | Member No: 8 Profile: ST W18X35 (AISC SECTIONS)| | Status: PASS Ratio: 0.182 Loadcase: 1 | | Location: 10.00 Ref: Cl.F2.2 | | Pz: 2.197 C Vy: 0.1365 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: -31.52 | |-----------------------------------------------------------------------------| - Member : 9 |-----------------------------------------------------------------------------| | Member No: 9 Profile: LD L50505 (AISC SECTIONS)| | Status: PASS Ratio: 0.126 Loadcase: 4 | | Location: 0.00 Ref: Cl.D2 | | Pz: 25.07 T Vy: 0.000 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 0.000 | |-----------------------------------------------------------------------------| - Member : 10 |-----------------------------------------------------------------------------| | Member No: 10 Profile: LD L50505 (AISC SECTIONS)| | Status: PASS Ratio: 0.097 Loadcase: 5 | | Location: 0.00 Ref: Cl.D2 | | Pz: 19.29 T Vy: 0.000 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 0.000 | |-----------------------------------------------------------------------------| - Member : 11 |-----------------------------------------------------------------------------| | Member No: 11 Profile: LD L50505 (AISC SECTIONS)| | Status: PASS Ratio: 0.113 Loadcase: 5 | | Location: 0.00 Ref: Cl.D2 | | Pz: 22.42 T Vy: 0.000 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 0.000 | |-----------------------------------------------------------------------------| - Member : 12 |-----------------------------------------------------------------------------| | Member No: 12 Profile: LD L50505 (AISC SECTIONS)| | Status: PASS Ratio: 0.084 Loadcase: 4 | | Location: 0.00 Ref: Cl.D2 | | Pz: 16.69 T Vy: 0.000 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 0.000 | |-----------------------------------------------------------------------------| - Member : 13 |-----------------------------------------------------------------------------| | Member No: 13 Profile: LD L50505 (AISC SECTIONS)| | Status: PASS Ratio: 0.066 Loadcase: 5 | | Location: 0.00 Ref: Cl.D2 | | Pz: 13.17 T Vy: 0.000 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 0.000 | |-----------------------------------------------------------------------------| - Member : 14 |-----------------------------------------------------------------------------| | Member No: 14 Profile: LD L50505 (AISC SECTIONS)| | Status: PASS Ratio: 0.067 Loadcase: 4 | | Location: 0.00 Ref: Cl.D2 | | Pz: 13.33 T Vy: 0.000 Vx: 0.000 | | Tz: 0.000 My: 0.000 Mx: 0.000 | |-----------------------------------------------------------------------------| 66. FINISH *********** END OF THE STAAD.Pro RUN *********** **** DATE= OCT 27,2022 TIME= 15:10:14 **** ************************************************************ * 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 * ************************************************************