Post-buckling Behavior and Progressive Failure ofLaminated Composite Plates Subjected to CompressiveLoading

摘要

The objective of this work is to study the post-buckling behavior and the progressive failure ofrnsymmetric and un-symmetric laminates that are subjected to uni-axial and bi-axial compressivernloadings. The finite element formulation is developed based on the first-order shear deformationrntheory and incorporates the effects of the geometric non-linearity using von Karman’s theory. Therntensor polynomial form of the maximum stress failure criterion is used in the progressive failurernanalysis. Delamination at any interface is considered to have occurred when any of the transversernstress components in any of the two layers adjacent to the interface becomes equal to or greater thanrnits corresponding strength. The failure progression in symmetric laminates (±45/0/90)2s, (±45)4s, andrn(0/90)4s and un-symmetric laminates (±45/0/90)4, (±45)8, and (0/90)8 is investigated in detail. Arnparametric study is conducted to characterize the effects of stacking sequence, aspect ratio of thernplate, and fiber orientation on the maximum deflection, the first-ply failure load, and the ultimaternload.