剪切载荷作用下碳/环复合材料层压板的损伤扩展特性  

THE CRACK PROPAGATION OF CARBON/EPOXY COMPOSITE LAMINATES COMPOSED OF DIFFERENT PLIES UNDER SHEAR LOAD

作　　者：陶梅贞[1] 吴宏伟[1] 

机构地区：[1]西北工业大学502教研室,西安710072

出　　处：《宇航学报》1993年第3期52-58,共7页Journal of Astronautics

摘　　要：本文对含中心穿透裂纹的碳/环复合材料层压板在剪切载荷作用下的损伤扩展规律进行了研究。通过对以[±45/O_6]_s、[(±45)_3/O_2]_s、[O/±45/O]_s和[90/±45/90]_s四种层压板为主的多种层压板进行试验研究和理论计算,对工程上常用的以O°、±45°、90°三种铺层构成的各种π/4层压板在含裂纹时的板内应力分布、裂纹扩展方向、断裂机理和含裂纹时的极限强度(剩余强度)进行了分析。试件由T300/648E制成。研究表明,铺层组分比例的不同对裂纹的扩展方向和含裂纹层压板的极限强度有较大的影响。本文在探讨损伤扩展规律的基础上,也为工程应用提供了有意义的结果。In this paper the crack propagation properties of C/E composite laminates containing crack under shear load are studied. By way of the tests and finite element calculation for T300/648E [±45/O6]s, [(±45)3/O2]s, [0/±45/0]s and [90/±45/90]s laminates, the crack propagation direction, the fracture mechanisms and ultimate strength (residual strength) of laminates containing different components of 0°,±45°,90° plies were alanyzed . The calculated and experimental results show that the laminate components have greater influence on crack propagation direction and ultimate strength. On the basis of exploration the damage propagation behaviour the useful results for engineeirng are offered.

关 键 词：剪切载荷 碳环复合材料 裂纹扩展 

分 类 号：V258.3[一般工业技术—材料科学与工程]