Postbuckling Response Simulations of Laminated Anisotropic Panels
Publication: Journal of Aerospace Engineering
Volume 5, Issue 3
Abstract
Numerical simulations are used in conjunction with experiments to study the buckling and postbuckling responses and failure initiation of flat, unstiffened composite panels. The numerical simulations are conducted using two‐dimensional shear‐flexible finite elements. The effect of the laminate stacking sequence on the buckling and postbuckling responses is studied. Correlation between numerical and experimental results is good through buckling, but the numerical models overestimate the postbuckling stiffness of the panels when nominal values of the material properties are used. To explain the discrepancies in the postbuckling stiffnesses, analytic sensitivity derivatives are calculated and used to study the sensitivity of the buckling and postbuckling responses to variations in different material and lamination parameters. Experimental results indicate that failure occurs along a nodal line. Numerical results show that the location of failure initiation corresponds to that of the maximum transverse shear‐strain energy density in the panel, which occurs at the edge of the panel at a nodal line. However, the transverse shear deformation has a negligible effect on the global response characteristics of the panel.
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Information & Authors
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Published In
Journal of Aerospace Engineering
Volume 5 • Issue 3 • July 1992
Pages: 347 - 368
Copyright
Copyright © 1992 ASCE.
History
Published online: Jul 1, 1992
Published in print: Jul 1992
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