Abstract
The elastostatic responses of a symmetric cross-ply and angle-ply laminated composite panels are analyzed in a comparative fashion using a single-variable lamination theory. A finite-difference computational scheme is developed for the application of the present theory to practical problems of composite mechanics. Deformed shapes as well as critical ply-stresses of the laminated panels are discussed for both the cases of flexural and axial loadings. A comparative analysis is also included to verify the soundness and accuracy of the present computational approach.
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