Abstract
The buckling strengths of fiber-composite laminate shells with a given material system are maximized with respect to fiber orientations using a sequential linear programming method together with a simple move-limit strategy. While a modified Riks nonlinear solution algorithm is utilized to analyse the buckling and postbuckling behaviour of composite shells, both linear and nonlinear in-plane shear formulations are employed to form the finite-element constitutive matrix for fiber-composite laminae. Results of the optimization study for simply supported composite cylindrical shells using both linear and nonlinear in-plane shear formulations are presented.
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