复合材料加筋层合板结构分层扩展分析

Simulation of delamination propagation for stiffened composite laminated plates

采用基于模式混合度的分层扩展准则,研究了复合材料加筋层合板结构分层扩展力学行为,分析了铺层方式对复合材料层合板结构界面力学性能的影响。首先,由计算所得分层前缘处的应变能释放率分量计算求得模式混合度;然后,将其代入材料断裂韧性函数及分层扩展量计算公式,进而预测复合材料加筋层合板结构的分层起始及其扩展行为。并通过对规则对称正交铺层、反对称铺层与用于V-22飞行器结构中的铺层方式下的层合板分层扩展行为进行比较,验证了该方法的有效性。

Delamination initiation and propagation behavior of stiffened composite plates was analyzed using a novel propagation criterion based on mode-mixity.Moreover,the effect of ply sequence on the mechanical performance of a skin-stringer composite laminates was investigated.Mode-mixity was obtained using strain energy release rate components,which was used then to get delamination propagation length and fracture toughness for a given delamination length.The method was certified by comparing the interfacial mechanical behavior of two standard ply sequences with those used for V-22 airplane structures.