Buckling Analysis of Woven Glass Epoxy Laminated Composite Plate

摘要: Buckling behavior of laminated composite plates subjected to in-plane loads is an important consideration in the preliminary design aircraft components. The sizing many structural subcomponents structures often determined by stability constraints. objective current study understand influence length-to-thickness ratio, aspect fiber orientation and cut-out shapes on buckling load for glass epoxy plate clamped-free-clamped-free configuration FE analysis using MSC Patran/Nastran. Initially, was carried out aluminum plates, both; experimentally numerically; two different geometric configurations predict critical test results were compared with FEA predictions, check validity methodology. same methodology further followed analyzing plates. shows effect fiber, shape ratio plate.