BUCKLING AND DYNAMIC BEHAVIOUR OF LAMINATED COMPOSITE STRUCTURES USING A DISCRETE HIGHER-ORDER DISPLACEMENT MODEL

This paper deals with buckling and free vibrations of multilaminated structures of arbitrary geometry and lay-up using a single layer higher order shear deformation theory discrete model. This model is based on an eight-node C0 serendipity finite element with 10 degrees of freedom per node to contemplate general applications. The present model is tested on the evaluation of buckling loads and free vibrations of multilaminated plates and shells. The effects of different number of layers, lamination angles, material anisotropy, and length or radius to thickness ratios are studied.

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