Authors: RajanishM, N.V. Nanjundaradhya, Ramesh S Sharma, V Chayapathy
Abstract: The research and development of high performance structural materials for aerospace and automotive have long been focused on the weight saving and minimal environmental impact. Accordingly, lightweight characteristics in structural materials have become one of the basic requirements for all systems where these composite panels are subjected to bending load. Prediction of the flexural strength of a high performance laminated composite is important for engineering application yet difficult in nature. The purpose of this work is to analyze the flexural behaviour and progressive failure process of laminated composites subjected to a bending load. The analysis is based on the classical lamination theory. Only the mechanical properties of constituent fiber and matrix materials under the bending load condition and the laminate geometric parameters are required. All these data will be measured independently before composite fabrication. As one does not know a priori which ply failure corresponds to the ultimate failure, the use of only the stress failure criterion is no longer sufficient for the determination of the laminate ultimate strength.
Keywords: Composites, Matrix, Epoxy resins, Metal Matrix, Glass Fiber.
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