复合材料层板开孔拉伸损伤分析  

Damage analysis of open-hole tension laminates

作　　者：黎增山[1] 关志东[1] 何为[1] 刘德博[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《复合材料学报》2012年第1期169-175,共7页Acta Materiae Compositae Sinica

基　　金：国家安全重大基础研究(973)项目(2010CB631104)

摘　　要：针对纤维增强复合材料层板开孔拉伸,将复合材料层板的失效分为层内失效和层间失效,建立了复合材料层板开孔拉伸损伤分析模型。该模型基于逐渐损伤分析,对不同复合材料开孔层板进行了失效预测,并与文献试验结果进行了对比,破坏强度和失效模式均与文献试验结果非常吻合。结果表明本文中所建立的层板开孔拉伸损伤分析模型能够模拟含孔层合板拉伸过程中的损伤起始、损伤扩展和最终破坏模式,并最终预测含孔层合板拉伸失效模式和破坏强度。A model for the damage analysis of the open-hole tension composite laminates was developed. The model divided the failure modes of composite laminates into intra-laminar and inter-laminar damage. The model simulated damage initiation, damage progression, final damage and predicted failure mode and failure load of laminates with central circular holes subjected to tensile load based on progressive failure analysis methodology. The failure modes and failure loads of different laminates were predicted and compared with the experimental results. The results show that the model could predict the {allure mode and failure load of open-hole tension laminates exactly.

关 键 词：复合材料 开孔拉伸 损伤分析 逐渐损伤 失效模式 

分 类 号：V257[一般工业技术—材料科学与工程] TB330.1[航空宇航科学与技术—航空宇航制造工程]