飞机复合材料长桁面外拉伸失效分析  

OUT-OF-PLANE TENSION FAILURE ANALYSIS OF COMPOSITE STRINGER FOR AIRCRAFT

作　　者：黄文超[1] 朱照泽 HUANG WenChao;ZHU ZhaoZe(AVIC SAC Commercial Aircraft Company Limited,Shenyang 110179,China)

机构地区：[1]中航沈飞民用飞机有限责任公司,沈阳110000

出　　处：《机械强度》2019年第3期753-757,共5页Journal of Mechanical Strength

摘　　要：考虑几何、材料以及接触非线性因素,引入Hoffman材料失效准则,采用Newton-Raphson增量迭代方法建立复合材料长桁面外拉伸失效有限元仿真方法。设计验证性试验,测试三种不同长桁构型面外拉伸失效载荷和破坏模式,绘制载荷-位移曲线,证明有限元分析方法准确、有效。分析有限元和试验测试结果,研究复合材料长桁面外拉伸失效影响因素,给出飞机强度设计指导。The nonlinear effects of geometry,material and contact are considered,the finite element analysis(hereinafter FEA) method of composite stringer out-of-plane tension failure is established precisely by using Hoffman material failure criteria and Newton-Raphson increment iteration method.A verification test is designed to test the failure load and failure mode of three different stringer configurations.Then the load-displacement curve is drawn to verify the validity of the FEA method.The influence factors of out-of-plane tension failure of composite stringer are studied,which can guide the strength design of aircraft.

关 键 词：非线性 复合材料 长桁 面外拉伸 

分 类 号：TB332[一般工业技术—材料科学与工程]