Buckling characteristics of anisotropic laminated cylindrical panels are presented using an isoparametric nine-noded rectangular element. Kinematic relations, extended to include the first-order shear deformation theory, are utilized in the formulation. Numerical results are presented for laminated cylindrical panels under uniaxial compression loading to illustrate the influence of panel sizes, orientation of layers, material properties, and boundary conditions on the buckling loads. Results for plates are also presented as special cases and are compared with the available solutions.

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