Critical in-plane normal and shear loads of rectangular anisotropic laminated plates are presented. These were calculated using the shell code FASOR, which includes the effect of transverse shear deformation. For simply-supported orthotropic laminates with midplane symmetry normal buckling loads are verified by a closed-form solution derived from transverse shear deformation plate theory. Results are compared to previously pub lished solutions from three-dimensional elasticity theory and classical plate theory.
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