Abstract
Post-buckling behavior of imperfect, laminated composite cylindrical panels subjected to axial compressive load has been investigated by using an equilibrium path approach which uses an arc-length method. Influence of the eigen imperfection shapes and its relative magnitude on the post-buckling behavior of the cylindrical panels with different Rt ratios is briefly discussed for different unidirectional lay-up sequences of interest with all the sides considered as simply supported boundary configuration. The confidence gained on the numerical approach is further extended to correlate (or validate) with the experimental post-buckling behavior of various glass-polyester laminated composite cylindrical panels considered in this investigation
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