Aerospace Engineering Commons^™

On The Use Of Levy's Method For Symmetrically Laminated Composite Plates, Serge Abrate

Mechanical and Aerospace Engineering Faculty Research & Creative Works

For rectangular plates with two opposite edges simply supported and no bending twisting coupling, Levy's method can yield exact solutions for static deflections, free vibrations and buckling loads. However, three distinct solutions are obtained, depending on the relative magnitude of the plate rigidities, which in turn are functions of material properties, laminate thickness and lay-up. In this communication a stiffness invariant formulation is used to identify those laminates which fall under the three cases defined. © 1993.