Buckling of Laminated Composite Rectangular Plates
Publication: Journal of Aerospace Engineering
Volume 18, Issue 4
Abstract
The present study estimates the critical/buckling loads of laminated composite rectangular plates under in-plane uniaxial and biaxial loadings. The formulation is based on the first-order shear deformation theory and von-Karman-type nonlinearity. Chebyshev series is used for spatial discretisation and quadratic extrapolation is used for linearization. An incremental iterative approach is used for estimation of the critical load. Different combinations of simply supported, clamped and free boundary conditions are considered. The effects of plate aspect ratio, lamination scheme, number of layers and material properties on the critical loads are studied.
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© 2005 ASCE.
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Received: Oct 30, 2003
Accepted: Oct 15, 2004
Published online: Oct 1, 2005
Published in print: Oct 2005
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