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.
Recommended Citation
S. Abrate, "On The Use Of Levy's Method For Symmetrically Laminated Composite Plates," Composites, vol. 24, no. 8, pp. 659 - 661, Elsevier, Jan 1993.
The definitive version is available at https://doi.org/10.1016/0010-4361(93)90129-V
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
