复合材料剪切板的裂纹扩展与剩余强度  

Crack Propagation and Residual Strength of Composite Shear Panel

作　　者：张延辉[1] 陶梅贞[1] 

机构地区：[1]西北工业大学

出　　处：《西北工业大学学报》1998年第3期377-381,共5页Journal of Northwestern Polytechnical University

摘　　要：对剪切载荷下带中心裂纹层板的损伤情况、宏观裂纹的扩展及剩余强度问题进行了计算和分析，着重探讨了裂尖铺层的破坏形式、宏观裂纹扩展及剩余强度三者的特点及相互关系。对两种材料Ｔ３００／６４８Ｅ和Ｔ３００／ＱＹ８９１１进行了比较，发现裂纹的扩展不仅与铺层形式有关，还与材料有关，且有明显规律可循。另外，层板铺层不同，裂尖损伤的累积过程也不同。裂尖铺层的２向（垂直于纤维向）破坏和面内剪切破坏尤其是前者对层板的剩余强度影响较大。所得结论得到了实验的验证。In this paper, the finite element method is used to estimate the crack propagation direction, the residual strength and the failure modes of the plies near the crack tip of the composite shear panel. Some experiments were done to compare with the finite element results. They are in good agreement. Certain relationships were found to exist between the residual strength and the failure modes of the plies near the crack tip. Among the failure modes, the 2direction tensional failure and the inplane shear failure, especially the firstmentioned one, show significant effect on the residual strength. Different layups make the laminates have different damage accumulation processes. Two P.R.C.types of laminates, T300/648E and T300/QY8911, were compared. The results show that, the crack propagation direction depends on not only the layup but also the material mechanical properties. The same tendency of crack propagation was found for the two types of the laminates.

关 键 词：剪切载荷 裂纹扩展 剩余强度 飞机 复合材料 

分 类 号：TB332.01[一般工业技术—材料科学与工程] V214.4[航空宇航科学与技术—航空宇航推进理论与工程]