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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.
Firstly, compression tests were carried out on the perforated laminates of fiber-reinforced composite materials. The gradual damage during the loading process and the final failure mode of the test pieces were detected by a macro digital display device, an electron microscope and an X-ray scanning device. The damage initiation And the delamination between 45 ° and 90 ° plies.Secondly, the failure of perforated plies of composites was divided into in-layer failure and inter-layer failure, and based on meso-damage mechanics MMF3 theory and interface adhesive layer unit method, Pore compression damage model.At last, this model is used to predict the damage initiation, damage propagation and failure mode of the hole, and the damage start position, layer position and expansion process of the fiber and matrix are obtained, The final stratification and press-in damage, etc. The calculated results are in good agreement with the experimental results, indicating that the calculation model is suitable for analyzing the asymptotic damage of composite materials under open-hole compression.