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Abstract

The effects of the strip delamination width on the buckling loads of the simply supported carbon/epoxy woven laminated composite plates have been investigated. For this purpose, 3D finite elements models of the square carbon/epoxy laminated plates have been established. Each of these models possesses four layers and different delamination width between second and third layers. Firstly, the harmony between theoretical and finite element solutions results of the plate without delamination has been shown. Then, the buckling loads have been determined for each model and different fiber orientation angles. The results show that important decrease in the buckling loads occur after a certain value of the delamination width. The changing ratios of the results of the symmetric or antisymmetric cases are approximately the same for each angle. For the high values of orientation angles, the values and changing ratios of the buckling loads are also higher than those of the low angles.

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Delamination Width Effect on Buckling Loads of Simply Supported Woven-Fabric Laminated Composite Plates Made of Carbon/Epoxy

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