Post-buckling Behavior and Progressive Failure of Laminated Composite Plates Subjected to Compressive Loading

摘要

The objective of this work is to study the post-buckling behavior and the progressive failure of symmetric and un-symmetric laminates that are subjected to uni-axial and bi-axial compressive loadings. The finite element formulation is developed based on the first-order shear deformation theory and incorporates the effects of the geometric non-linearity using von Karman's theory. The tensor polynomial form of the maximum stress failure criterion is used in the progressive failure analysis. Delamination at any interface is considered to have occurred when any of the transverse stress components in any of the two layers adjacent to the interface becomes equal to or greater than its corresponding strength. The failure progression in symmetric laminates (±45/0/90){sub}(2s), (±45){sub}(4s), and (0/90){sub}(4s) and un-symmetric laminates (±45/0/90){sub}4, (±45){sub}8, and (0/90){sub}8 is investigated in detail. A parametric study is conducted to characterize the effects of stacking sequence, aspect ratio of the plate, and fiber orientation on the maximum deflection, the first-ply failure load, and the ultimate load.