Abstract
An analytical methodology is presented to study the post-buckling behavior of laminated cylindrical shells under axial compression and lateral pressure. Non-linear inplane stress-strain relations for transverse ( E 22) and shear ( G 12) modulus is considered. The user defined material subroutine UMAT in finite element analysis package, ABAQUS, with an updated Lagrangian formulation, and large displacement and small strain kinematic relations, is employed in this study. Numerical analyses are conducted to demonstrate the effect of material non-linearity and stacking sequence on the post-buckling behavior of laminated shells.
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