The buckling and postbuckling responses of unstiffened cylindrically curved composite panels are studied using a geometrically nonlinear Rayleigh-Ritz solution and the finite element code STAGS. Loading is either end-shortening, or temperature-induced due to thermal stresses that arise when temperature is increased while axial displacement is restricted. Comparisons are made between three laminates, (+-45/90)_s, (+-45/90_2)_s, and (+-45/0_2)_s, two sets of boundary conditions. Buckling and postbuckling responses are found to be strongly dependent on mateirla orthotropy and substatially affected by the amount of cricumferential restraint along the straight edge boundaries.
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