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基于复合材料分层损伤模型的层压板静强度分析
引用本文:余明,赵美英,王瑜.基于复合材料分层损伤模型的层压板静强度分析[J].航空工程进展,2012(1):71-76.
作者姓名:余明  赵美英  王瑜
作者单位:西北工业大学航空学院,西安710072
摘    要:对层压板进行强度分析时同时考虑面内失效和分层损伤可以得到更加合理的强度预测值。基于复合材料层压板分层机理分别采用Hashin准则和分层因子进行面内损伤和分层损伤的计算,并结合材料性能退化发展了一种能够考虑分层损伤的层压板累积损伤模型。该模型能够模拟层压板面内和分层损伤产生、发展直至最终破坏的完整过程。通过对两种典型复合材料层压板单钉连接接头的失效分析,表明计算结果与传统三维有限元计算结果相比精度较高,并能有效预测各层间分层损伤的扩展情况。

关 键 词:层压板接头  有限元模型  分层  累积损伤  静强度

Static Strength Analysis of Composite Laminate Based on Delamination Damage Model
Yu Ming,Zhao Meiying,Wang Yu.Static Strength Analysis of Composite Laminate Based on Delamination Damage Model[J].Advances in Aeronautical Science and Engineering,2012(1):71-76.
Authors:Yu Ming  Zhao Meiying  Wang Yu
Institution:(School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China)
Abstract:Considering the in-plane failure and delamination failure can get more reasonable strength prediction value when analyzing the strength of laminate. Based on the mechanism of laminate delaminatiort, a new pro- gressive damage model capable of simulating the composite delamination failure is established. The Hashin cri- terion and a simple failure criterion are introduced to predict in-plane failure and delamination failure and a pro- posed property degradation model is adopted. The model is capable of assessing the initiation and propagation of in-plane and delamination damage in laminates until its finally breakage and of predicting the ultimate strength of the laminates. Through failure analysis, the results of two composite single fastener joints demonstrate better agreement with the experiments compare with the traditional 3D progressive damage model. The delamination distribution between each two layers is also predicted.
Keywords:composite laminate joints  Finite Element Model  delamination  damage accumulation  static strength
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