Optimal Hybridization of Symmetric, Cross‐Ply Laminates against Biaxial Buckling
Publication: Journal of Aerospace Engineering
Volume 6, Issue 4
Abstract
Optimal ratio of the thickness of the inner layers made of a low‐stiffness fiber‐reinforced material to the total laminate thickness is determined for sandwich hybrid laminates, with the objective of maximizing the buckling load for a given laminate thickness. The sandwich plate is constructed as a symmetric, cross‐ply laminate with outer layers made of a high‐stiffness fiber composite material and inner layers made of a low‐stiffness fiber‐composite material. The fiber orientations of high‐ and low‐stiffness materials (0° or 90°) are determined optimally, noting that the orientations of outer and inner layers affect the maximum buckling load in the case of hybrid laminates. The relative stiffness of outer layers to inner layers is shown to affect the optimal level of hybridization. The optimal laminate configurations are shown to be sensitive to the relative magnitudes of biaxial buckling loads as well as to the changes in the aspect ratio.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 6 • Issue 4 • October 1993
Pages: 394 - 406
Copyright
Copyright © 1993 American Society of Civil Engineers.
History
Received: Apr 29, 1991
Published online: Oct 1, 1993
Published in print: Oct 1993
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