An analytical-numerical procedure is applied to investigate the post-buckling behavior of a composite laminated stiffened panel. The panel is modeled by plate elements for which the nonlinear equations are derived (via a variational principle) in terms of the lateral displacement and Airy stress function, and treated by resolving the variables into eigenfunctions in conjunction with a finite-difference scheme.

Issue Section:
Research Papers
Topics:
Buckling, Composite materials, Displacement, Eigenfunctions, Nonlinear equations, Stress, Variational principles
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Copyright © 1988
 by ASME
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