Analysis Type:

Buckling Transversely Isotropic

Model Type:

3D

Comparison:

MSC/NASTRAN

Reference:

Jones, R.M., Mechanics of Composite Material, Hemisphere Publishing Corp., 1975, pp 260261.

Description:

A fourlayered transversely isotropic square plate is simplysupported and subjected to an inplane load. Determine the buckling load factor.

Element Type:  shell  
Units:  IPS  
Dimensions:  length: 10 width: 10 thickness: 0.1  
Ply layup: 0/90/90/0  Thickness of each ply: 0.025  
Shell Properties:  
Extensional Stiffness  A11=1.54e06  A12=18,779  A16=0 
A16=0  A26=0  
A66=37,500  
Extensionalâ€“Bending Coupling Stiffness  B11=0  B12=0  B16=0 
B22=0  B26=0  
B66=0  
Bending Stiffness  D11=2,198.75  D12=15.6495  D16=0 
D22=367.762  D26=0  
D66=31.25  
Transverse Shear Stiffnesses  A55=32,553  A45=0  A44=17,940 
Material Properties:  
Mass Density: 0.002  Cost Per Unit Mass: 0  
Young's Moduli  E1=3e7  E2=750,000  E3=750,000 
Poisson's Ratio  Nu21=0.25  Nu31=0.25  Nu32=0 
Shear Moduli  G21=375,000  G31=375,000  G32=E2/[2*(1+Nu32)] 
Coefficients of Thermal Expansion  a1=0  a2=0  a3=0 
Constraints:  Fixed in out of plane (zdirection) translation along all outer edges (AB, BC, CD, and DA). Fixed in translation in all directions at point D Fixed in x & zdirection translation at point A  
Loads:  Inplane force/unit length load=1: in +xdirection along edge DA in xdirection along edge BC 
Theory  Structure  % Difference  
Buckling Load Factor  268.73  267  0.6% 
Convergence %: 0.0 % on buckling load factor.  Max P: 6  No. Equations: 455 