摘要
为准确预测受冲击后复合材料结构的剩余强度,以航空用复合材料加筋壁板为研究对象,基于层内损伤和内聚力理论,建立了冲击-剪切全过程仿真分析模型,并通过开展冲击-剪切试验,进行了结果对比分析.结果表明:冲击-剪切全过程仿真分析模型中第一分析步可以较为精确地预测出冲击试验的凹坑深度、分层损伤面积以及损伤外观形貌;同时,第二/三分析步也可以较为精确地预测出冲击后剪切试验的破坏载荷、破坏模式.
In order to predict the residual strength of composite structures after impact,the aviation composite stiffened panels were taken as the research object.The impact-shear whole-process simulation model was established based on the in-layer damage and cohesive force theory,and the results were compared with those of impact-shear tests.It shows that the first analysis step of the impact-shear whole-process simulation model can accurately predict the depth of impact pits,the delamination damage area,and the damage appearance morphology.The second/third analysis steps can predict the failure load and failure mode of the post impact shear test.
作者
孟政委
金三强
张伟
MENG Zhengwei;JIN Sanqiang;ZHANG Wei(Experiment and Meterage Center,China Special Aircraft Research Institute,Jingmen 448035,Hubei,China)
出处
《力学季刊》
CAS
CSCD
北大核心
2023年第3期604-611,共8页
Chinese Quarterly of Mechanics
基金
工信部民用飞机专项科研资助项目(MJZ53N21)。
关键词
复合材料加筋壁板
冲击损伤
剪切强度
全过程仿真分析
composite stiffened plates
impact damage
shear strength
whole process simulation analysis
