Abstract
A postbuckling analysis is presented for a shear-deformable laminated cylindrical panel of finite length subjected to compressive axial loads. The governing equations are based on Reddy's higher-order shear deformation shell theory with a von Karman-Donnell type of kinematic non-linearity. The non-linear prebuckling deformations and initial geometric imperfections of the panel are both taken into account. A boundary layer theory of shell buckling, which includes the effects of non-linear prebuckling deformations, large deflections in the postbuckling range and initial geometric imperfections of the shell, is extended to the case of shear-deformable laminated cylindrical panels under axial compression. A singular perturbation technique is employed to determine the buckling loads and postbuckling equilibrium paths. The numerical illustrations concern the postbuckling response of perfect and imperfect, moderately thick and thin cross-ply laminated cylindrical panels. The effects played by transverse shear deformation, panel geometric parameters, total number of plies, fibre orientation, the character of in-plane boundary conditions and initial geometric imperfections are studied.
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