First ply failure of composite panels using ABAQUS
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I am using ABAQUS Software for analysis of laminated composite plates (279X279X2.16) and (0/90)4s having 16 plies; trying to perform Buckling and Post buckling analysis using Static Rikโs algorithm.
Firstly, Eigen value analysis is performed in step one, and thus bulking load is predicated.Then Eigen values are incorporated in Static Rikโs Non-linear analysis for imperfection (1% of first Eigen mode,0.05% of second Eigen mode, 0.025% of third mode and 0.025% of forth mode)using edit keywords method.