成型工艺对复合材料Ⅰ型断裂韧度的影响  

Effects of Forming Process on Composite mode Ⅰ Interlaminar Fracture Toughness

作　　者：陈星伊[1] 黎增山[1] 黄骁[1] 寇哲君 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中航复合材料有限责任公司,北京101300

出　　处：《航空材料学报》2016年第5期58-63,共6页Journal of Aeronautical Materials

基　　金：航空科学基金(2015A51010)

摘　　要：采用双悬臂梁试验和假设检验的方法,对比分析了两种不同成型工艺对复合材料Ⅰ型层间断裂韧度的影响,并采用有限元模型对这一过程进行了模拟。研究表明:硅橡胶软模成型试验件的Ⅰ型断裂韧度均值略高于金属硬模成型试验件;而两种工艺试验件的Ⅰ型断裂韧度方差不存在显著差异,且两种工艺成型的试验件的裂纹扩展过程相似。在试验的基础上建立了有限元模型,对裂纹扩展过程进行了模拟,与试验结果吻合良好,可以有效地预测裂纹扩展过程。In order to compare and analyse the effect of two different kinds of forming process on composite mode Ⅰ interlaminar fracture toughness, the DCB specimens were tested by using hypothesis inspection method. A finite element model was also used to simulate the crack propagation process. The results demonstrate that the average of mode Ⅰ interlaminar fracture toughness from silicon rubber flexible mold forming is a bit higher than that from metal rigid mold forming. Howevers the variance of mode Ⅰ interlaminar fracture toughness from the two groups shows no significant difference. The crack propagation process of the two forming process is similar. The established finite element model, which is identical to the test results, can predict the process of the crack expansion effectively.

关 键 词：成型工艺 复合材料 界面 Ⅰ型断裂韧度 

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]