V. Bent Beam Thermal Loading
To find member forces and moments due to a temperature load on a Zee shaped plane bent.
Reference
Seeley, F.B., and Smith, J.O., Advanced Mechanics of Materials, 2nd Edition, John Wiley and Sons, 1955, Pages 494-497.
Problem
Calculate reactions and maximum moments in the structure due to a temperature increase of 430 ºF. Do not consider shear deformation.
E = 26,400 ksi |
α = 7.26744 x 10-6 in/in/ºF |
OD = 12 in |
ID = 10.255 in |
STAAD Input
The file C:\Users\Public\Public Documents\STAAD.Pro 2023\Samples \Verification Models\01 Beams\Bent Beam Thermal Loading.STD is typically installed with the program.
STAAD PLANE :A FIXED-FIXED ZEE SHAPED PLANE BENT BEAM
START JOB INFORMATION
ENGINEER DATE 18-Sep-18
END JOB INFORMATION
*
* REFERENCE: Seeley, F.B., and Smith, J.O., Advanced Mechanics of Materials,
* 2nd Edition, John Wiley and Sons, 1955, Pages 494-497
*
SET SHEAR
UNIT INCHES POUND
JOINT COORDINATES
1 0 0 0; 2 240 0 0; 3 240 240 0; 4 480 240 0;
MEMBER INCIDENCES
1 1 2; 2 2 3; 3 3 4;
MEMBER PROPERTY AMERICAN
1 TO 3 TABLE ST PIPE OD 12 ID 10.255
PRINT MEMBER PROPERTIES
DEFINE MATERIAL START
ISOTROPIC MATERIAL1
E 2.64e+07
POISSON 0.3
ALPHA 7.26744e-06
END DEFINE MATERIAL
CONSTANTS
MATERIAL MATERIAL1 ALL
* DONOT PROVIDE POISSON'S RATIO, NO SHEAR DEFORMATION CONSIDERED
SUPPORTS
1 4 FIXED
LOAD 1
TEMPERATURE LOAD
1 TO 3 TEMP 430
PERFORM ANALYSIS
PRINT SUPPORT REACTION
PRINT MEMBER FORCES LIST 1
FINISH
STAAD Output
SUPPORT REACTIONS -UNIT POUN INCH STRUCTURE TYPE = PLANE ----------------- JOINT LOAD FORCE-X FORCE-Y FORCE-Z MOM-X MOM-Y MOM Z 1 1 8949.43 7729.42 0.00 0.00 0.00 781127.94 4 1 -8949.43 -7729.42 0.00 0.00 0.00 781127.94 ************** END OF LATEST ANALYSIS RESULT ************** 34. PRINT MEMBER FORCES LIST 1 MEMBER FORCES LIST 1 :A FIXED-FIXED ZEE SHAPED PLANE BENT BEAM -- PAGE NO. 5 MEMBER END FORCES STRUCTURE TYPE = PLANE ----------------- ALL UNITS ARE -- POUN INCH (LOCAL ) MEMBER LOAD JT AXIAL SHEAR-Y SHEAR-Z TORSION MOM-Y MOM-Z 1 1 1 8949.43 7729.42 0.00 0.00 0.00 781127.94 2 -8949.43 -7729.42 0.00 0.00 0.00 1073932.12