Buckling and vibration of laminated composite plates using various plate theories
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Analytical and finite-element solutions of the classical, first-order, and third-order laminate theories are developed to study the buckling and free-vibration behavior of cross-ply rectangular composite laminates under various boundary conditions. The effects of side-to-thickness ratio, aspect ratio, and lamination schemes on the fundamental frequencies and critical buckling loads are investigated. The study concludes that shear deformation laminate theories accurately predict the behavior of composite laminates, whereas the classical laminate theory overpredicts natural frequencies and buckling loads. © 1989 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
author list (cited authors)
Reddy, J. N., & Khdeir, A. A.