一种非线性模型下的复合材料螺栓连接失效分析  

The Failure Analysis of Composite Bolted Joint Structure Based on a Nonlinear Model

作　　者：李沛城[1] 常楠[2] 赵美英[1] 黄河源[1] Li Peicheng;Chang Nan;Zhao Meiying;Huang Heyuan(School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China;Chengdu Aircraft Design & Research Institute,Aviation Industry Corporation ofChina,Ltd.,Chengdu 610041,China)

机构地区：[1]西北工业大学航空学院 [2]中国航空工业集团有限公司成都飞机设计研究所

出　　处：《航空工程进展》2019年第2期171-178,共8页Advances in Aeronautical Science and Engineering

摘　　要：复合材料螺栓连接结构已广泛应用于飞机结构件,研究其拉伸失效问题具有重要意义。结合Hashin失效准则、能量耗散率方法、Puck失效准则和材料损伤连续退化方法,建立一种包含面内损伤和层间损伤的复合材料三维非线性模型;将含开孔层合板准静态拉伸试验结果与有限元数值模拟结果进行对比,两者之间的应力应变响应及最终断裂失效模式一致,证明该本构模型是有效的;在此基础上,对复合材料单钉双搭接螺栓连接结构进行拉伸失效分析。结果表明:数值模拟所得位移载荷响应与试验结果吻合良好,极限拉伸载荷误差不超过5%,满足工程应用要求;加载过程中的孔边变形和损伤累积使得螺栓连接结构整体刚度下降,其最终破坏模式为中搭接板挤压失效。Composite bolted joints have been widely used in aircraft structures.It is important to study their tensile failure.A three dimensional nonlinear model is established by combining the Hashin's criterion,energy dissipation rate method,Puck's criterion and continuum damage degradation method,including intra-laminar and inter-laminar damage.Comparing the results of quasi-static tensile test on notched laminate with the numerical simulation results,both of the stress strain response and final failure mode are consistent,hence the constitutive model is validated,and then the constitutive model is adopted to analyze the tensile failure of the double lap single bolt composite joint.Results show the displacement-load curves between numerical simulation and test are in good agreement.Meanwhile,the deviation of ultimate tensile load is no more than 5%,which meets the requirement of engineering application.Furthermore,the overall structural stiffness of composite bolted joint decreases due to the hole edge deformation and damage accumulation,and the ultimate failure mode is bearing failure of the mid-plate.

关 键 词：复合材料 非线性 开孔板 螺栓连接 失效准则 连续损伤退化 

分 类 号：TB33[一般工业技术—材料科学与工程]