复合材料层压板分层损伤扩展与压缩强度预测  

Delamination Propagation and Compressive Strength Prediction of Laminated Composite

作　　者：王瑜[1] 赵美英[1] 余明[1] 

机构地区：[1]西北工业大学航空学院

出　　处：《机械科学与技术》2011年第7期1051-1055,共5页Mechanical Science and Technology for Aerospace Engineering

摘　　要：应用三维渐进损伤分析与粘聚区模型方法模拟含分层损伤复合材料层合板在压缩载荷下的分层扩展与整体失效过程。对含损层合板的纤维、基体损伤与层间分层损伤的萌生与扩展以及它们之间的耦合作用进行了研究。计算得到了含分层损伤层合板在压缩载荷作用下的载荷-位移曲线,并预测了其极限强度。结果显示预测数据与实验数据吻合良好。最后讨论了分层参数对含损层合板剩余强度的影响。Three-dimensional progressive damage analysis and the cohesive zone model method are used to simulate the progression of delamination propagation and overall failure in laminated composite with delamination damage under compressive load.The initiation and propagation of the fiber,matrix damage and delamination as well as the coupling effect among them in the damaged laminated composite are investigated.Load-displacement curve and ultimate strength of the laminated composite with delamination damage under compressive load are obtained by numerical analysis,an excellent agreement is shown between the numerical result and test data.Finally,the effect of delamination parameters on the ultimate strength of the damaged laminated composite is discussed.

关 键 词：复合材料 层合板 分层 损伤 粘聚区模型 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]