%0 Journal Article
%T 复合材料开孔层板压缩渐进损伤分析<br>Progressive damage analysis of open-hole composite laminates under compression load
%A 周睿
%A 关志东
%A 李星
%A 卓越
%J 北京航空航天大学学报
%D 2015
%R 10.13700/j.bh.1001-5965.2014.0395
%X 摘要 首先,针对纤维增强复合材料开孔层板进行了压缩试验,通过微距数显设备、电镜扫描和X光扫描设备检测了加载过程中的渐进损伤和试验件最终破坏模式,观测了损伤起始和45°与90°铺层间的分层现象. 其次,将复合材料开孔层板失效分为层内失效和层间失效,基于细观损伤力学MMF3理论和界面胶层单元方法建立了开孔压缩损伤跨尺度分析模型.最后,应用该模型对开孔压缩损伤起始、损伤扩展和层板破坏模式进行了预测,获得了纤维和基体损伤起始位置、分层产生位置及扩展过程、最终的分层和压入破坏等计算结果.计算结果与试验结果获得了较好的吻合,表明该计算模型适用于分析复合材料开孔压缩渐进损伤问题.<br>Abstract：Firstly, compressional experiments were conducted on open-hole composite laminates. The progressive damage during the loading process and the final damage mode of the specimen were detected with a digital microscope, scanning electron miroscope and an X-scan equipment. Damage initiation and delamination between layups of 45° and 90° were observed during the experiments. Secondly, the failure modes of composite laminates are divided into intra-laminar failure and inter-laminar failure. A multiscale model based on the micro-mechanics of failure MMF3 theory and the interface cohesive element method for the damage analysis of open-hole compression laminates was developed. At last, the initiation and propagation of the damage and the failure modes of the laminates were predicted with the model. Numerical results such as the damage initiation position of fiber and matrix, the delamination propagation process and the final failure modes are in good agreement with experimental results, which indicates that the model is applicable to analysis of progressive damage of open-hole composite laminates under compression load.
%K 复合材料
%K 开孔层板
%K 压缩试验
%K 渐进损伤
%K 跨尺度&lt
%K br&gt
%K composite
%K open-hole laminates
%K compressional experiment
%K progressive damage
%K multiscale
%U http://bhxb.buaa.edu.cn/CN/abstract/abstract13290.shtml