NCF/环氧层板开孔拉伸渐进损伤分析  

Progressive damage of an open-hole NCF/epoxy laminate subjected to tensile load

作　　者：王震宇[1] 刘玲[1] 宫占峰[2] 薛元德[1] 

机构地区：[1]同济大学航空航天与力学学院,上海200092 [2]中国商用飞机有限责任公司上海飞机设计研究院,上海201210

出　　处：《复合材料学报》2013年第S1期147-152,共6页Acta Materiae Compositae Sinica

基　　金：中国商用飞机有限责任公司上海飞机设计研究院预研项目(DKWX11-317)

摘　　要：本文以碳纤维非褶皱无纺布(Non-crimped fabric,NCF)/环氧对称层板为研究对象,采用RTM工艺制备了准各向同性板,根据ASTM D5766标准测试了层板的开孔拉伸性能。结果得到,该层板的开孔拉伸强度和模量可分别达到435MPa和48Gpa。根据测试结果,假设层板由传统的单向层组合而成,应用已有的开孔拉伸渐进损伤分析方法,结合Hashin失效准则,在ABAQUS软件中对该简化层板进行了开孔拉伸强度预测和渐进损伤分析。结果发现,采用传统的单向板分析方法,预测得到的开孔拉伸极限强度和渐进损伤过程,与试验结果比较吻合。In the present study,carbon fiber non-crimped fabrics(NCF)and epoxy resin were applied to manufacture a quasi-isotropic laminate by using of RTM process.Open-hole tensile properties of the resulted laminate were tested according to ASTM D5766standard.Testing results show that the obtained open-hole strength and modulus are 435MPa and 48GPa,respectively.On the basis of experimental results,the NCF laminate was assumed as a traditional laminate consisting of unidirectional lamina,and the already existing progressive damage analysis method of open-hole tension was adapted to analyze the strength and progressive damage of the NCF laminate by using finite element software,ABAQUS.Results have shown that the ultimate strength and progressive failure can be well predicted by using Hashin failure criterion and traditional analysis method that used for unidirectional laminate,as well as,the predicted results are coherent with that from the experimental.

关 键 词：NCF 开孔拉伸 渐进损伤 Hashin准则 

分 类 号：TB331[一般工业技术—材料科学与工程]