Abstract

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.

Department(s)

Mechanical and Aerospace Engineering

Keywords and Phrases

composite plates; Levy's method; material properties; plate rigidity; symmetric laminates

International Standard Serial Number (ISSN)

0010-4361

Document Type

Article - Journal

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2023 Elsevier, All rights reserved.

Publication Date

01 Jan 1993

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