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。
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.
出处
《航空工程进展》
2012年第1期71-76,共6页
Advances in Aeronautical Science and Engineering
关键词
层压板接头
有限元模型
分层
累积损伤
静强度
composite laminate joints
Finite Element Model
delamination
damage accumulation
static strength
