含损伤缝合复合材料层压板压缩剩余强度估算方法  

Prediction of Compressive Residual Strength for Stitched Composite Laminates with Damage

作　　者：李仲[1] 葛森[2] 杨胜春[2] 吕国志[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中国飞机强度研究所,陕西西安710065

出　　处：《西北工业大学学报》2007年第3期342-346,共5页Journal of Northwestern Polytechnical University

基　　金：航空科学基金(99B23004)资助

摘　　要：提出了用基于平均应力判据的0°层纤维控制的强度破坏准则a0来估算开孔缝合复合材料层压板压缩剩余强度的方法。通过将冲击损伤简化为椭圆孔,采用上述的强度破坏准则估算了含冲击损伤的缝合层压板的冲击后压缩剩余强度。进行了缝合复合材料层压板的开孔压缩和冲击后压缩试验。估算结果与试验结果具有良好的一致性,满足工程精度要求。In this paper a method to predict the compressive residual strength of stitched laminates with central hole was presented by failure criterion of 0°-ply fracture. A serial of tests were conducted to determine the compressive residual strength of stitched laminates with central hole and impact damage. For stitched laminates with impact damage, it is proposed that the impact damage is simplified as an elliptic hole by means of the Nondestructive Inspection, and the compressive residual strength is obtained by use of the failure criterion of 0°-ply fracture based on the failure mechanism for compressive test of laminates with impact damage. Analytical predictions of the compressive residual strength of stitched laminates with central hole and impacted damage predicted by presented method agree well with the experimental results. Its accuracy is satisfactory for the engineering purpose.

关 键 词：复合材料 缝合 破坏判据 剩余强度 

分 类 号：TB302[一般工业技术—材料科学与工程] V215.6[航空宇航科学与技术—航空宇航推进理论与工程]