Stability of Curved Composite Panels with Random Material Properties
Publication: Journal of Aerospace Engineering
Volume 15, Issue 2
Abstract
The initial buckling behavior of thick laminated composite curved panels with random material properties subjected to various in-plane edge loads has been investigated. For this purpose, an approach is presented to obtain the governing equation and the buckling load statistics with the help of an accurate finite element in conjunction with first-order perturbation technique. A higher order shear deformation theory has been used for the laminate. The laminate material properties, subjected to inherent variations about the mean value, have been modeled as random variables. Results for second-order statistics of buckling load have been presented for laminated spherical panels and validated with available results in literature and Monte Carlo simulation. The influence of curvature-to-side ratio, side-to-thickness ratios and edge support conditions on buckling load statistics has been studied. The sensitivity of buckling load statistics for spherical panels to variations in material properties has been compared with that of cylindrical panels.
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Published In
Journal of Aerospace Engineering
Volume 15 • Issue 2 • April 2002
Pages: 46 - 54
Copyright
Copyright © 2002 American Society of Civil Engineers.
History
Received: Mar 19, 2001
Accepted: Nov 20, 2001
Published online: Apr 1, 2002
Published in print: Apr 2002
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