含开孔与含裂缝的复合材料层压板拉伸剩余强度评估  

Residual strength evaluation of laminates with open hole or crack undertensile load

作　　者：汪厚冰[1] 邓凡臣[1] 魏宏艳[1] 李新祥[1] 杨胜春[1] Wang Houbing;Deng Fanchen;Wei Hongyan;Li Xinxiang;Yang Shengchun(Aircraft Strength Research Instituteof China,Xi'an 710065,China)

机构地区：[1]中国飞机强度研究所一室,西安

出　　处：《飞行器强度研究》2022年第4期1-9,共9页Aircraft Strength Research

摘　　要：为研究含开孔和裂缝的碳纤维增强树脂基复合材料(CFRP)层压板在拉伸载荷作用下的剩余强度,针对4种典型铺层、2类损伤形式、4种损伤尺寸的约200件试验件进行试验研究。结果表明,对于具有相同铺层、相同宽度的复合材料层压板,开孔直径与裂缝宽度相等时,两类层压板有相同的剩余强度;加载过程中,裂缝根部较早出现裂缝、分层、应力重新分配,降低裂缝根部的应力集中。基于损伤区纤维断裂判据、经典层压板、理论及复变函数理论的强度计算方法能较准确的计算出含开孔的复合材料层压板剩余强度;计算含裂缝复合材料层压板剩余强度时可将裂缝损伤等效成开孔损伤,计算结果与试验结果吻合较好。Experiments on about 200 composite laminates with two kinds of damage,four typical layups,and tour damage sizes were conducted to investigate the residual strength of composite laminates with open hole or crack.The research indicates that the residual strength of two composite laminates with open hole and crack are equal with same lay-ups and same widths of laminates when the opening diameter is equal to the crack width.itte cracks and delamination appear earlier at the root of crack during the loading process,the stress is redistributed near the root of crack,the stress concentration reduces.The method based on fiber breakage in damage zone criterion,classical laminate theory and complex variable function theory can be used to predict the residual strength of two composite laminates with open hole,the method can also be used for laminate with crack when the crack is equivalent to an open hole,the calculated results are in good agreement with the experimental results.

关 键 词：开孔 裂縫 复合材料 损伤容限 剩余强度 

分 类 号：TB3[一般工业技术—材料科学与工程]