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This work is focused on the study of postbuckling aspect of laminated composite stiffened plates subjected to parabolic in-plane loading, using finite element method. The eight-noded degenerated shell element and the three-noded degenerated curved beam element with isoparametric formulation with C0 continuity (FSDT) of the primary variables are used to model the plate skin and stiffeners, respectively. The postbuckling analysis is carried out by solving the nonlinear load-deformation equation by Crisfield arc-length method. The results obtained from the present formulation are compared with available results to ensure accuracy of the formulation. The linear eigen-value buckling analysis is also performed to compare the results. The Green–Lagrange strain displacement relationship in total Lagrangian coordinate system is adopted in the formulation. The effect of different parameters like lamination scheme, number of layers, aspect ratio, stiffener depth and boundary condition, on the postbuckling response of the plates is considered in the present study. |
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