分层损伤对含孔复合材料层合板剩余强度影响  

Effect analysis of delamination damage on the residual strength of notched composite laminates

作　　者：肖梦丽[1] 张勇波[1] 王治华[1] 傅惠民[1] 杨鑫[1] 

机构地区：[1]北京航空航天大学小样本技术研究中心,北京100191

出　　处：《航空动力学报》2016年第5期1081-1086,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(11501022);北京市自然科学基金(3154034)

摘　　要：以国产碳纤维复合材料CCF300/QY8911含孔层合板静力拉伸试验为基础,建立了符合其损伤失效模式的有限元三维预测模型.通过引入Cohesive界面单元分析了层合板拉伸过程中的分层扩展,数值模拟的结果与试验结果吻合较好,破坏载荷预测结果与试验数据相比误差在5%以内.根据CCF300复合材料构件在制造过程和实际使用中产生的孔边分层缺陷的情况,在孔边预置分层,分析了初始分层损伤对于层合板剩余强度的影响.结果表明表面预制分层对剩余强度影响较小,但会引起自由边提前分层失效.Based on CCF300/QY8911 notched composite laminates static tensile test, three-dimension prediction finite element model consistent with its failure mode was estab- lished. The growth of delamination in the process of tension was simulated by introducing Cohesive interface element, the simulation result had a good agreement with experimental data, the relative error of failure load between experimental data and numerical prediction was less than 5%. Given the delamination defects produced around the hole edge in the process of manufacturing and utilization of composite laminates, a prefab delamination was set near the hole for analysis, and the effect on the residual strength of laminates was inves- tigated. The effect of embedded delamination near the surface layer on the residual strength was small, while the embedded delamination could disable delamination produced in advance near the free edge.

关 键 词：复合材料层合板 渐进失效分析 分层损伤 剩余强度 有限元方法 

分 类 号：V258[一般工业技术—材料科学与工程] O211[航空宇航科学与技术—航空宇航制造工程]