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Buckling is a structural instability that can cause a component to fail even when the material remains within the elastic regime. Therefore, determining the critical buckling loads and corresponding mode shapes can be important from a design perspective, even when the applied loads produce only elastic deformations. For components made from laminated composite materials, the elastic properties, ply thicknesses, and stacking sequence can significantly affect the buckling loads and mode shapes.

This example presents a linear buckling analysis of a composite cylinder subjected to compressive loading with fixed-end conditions. The cylinder consists of eight layers (plies) of carbon-fiber-reinforced polymer (CFRP), with different fiber orientations. The analysis uses an Equivalent Single Layer (ESL) theory-based approach. It also investigates the effect of the stacking sequence on the critical load factor for different balanced laminates, including symmetric and antisymmetric angle-ply laminates.