Buckling of Fibre Reinforced Composite and Sandwich Laminates with Higher-OrderShear Deformation Theories

摘要

A higher-order shear deformation theory, employing C(sup 0) continuous finiteelements, is used to determine the buckling loads of symmetric, crossply composite and multilayer sandwich plates. This theory accounts for the quadratic variation of the transverse shear strains, thus eliminating the use of shear correction coefficients. The discrete element is a nine-noded Lagrangian quadrilateral with nine degrees of freedom per node. Numerical examples are presented to demonstrate the behavior and accuracy of the proposed formulation. In all cases, the comparisons made with theory and/or published data show that the higher-order theory predicts accurate results for composite laminates and provides more realistic values or buckling loads for conventional/multilayer sandwich plates.