含Cohesive单元的舱门蒙皮低速冲击有限元仿真  

Finite Element Simulation for Application to Low Velocity Impact Problem of Aircraft Door Skin with Cohesive Element

作　　者：左锐[1] 左洪福[1] 芦吉云[1] 徐瑀童 ZUO Rui ZUO Hong-fu LU Ji-yun XU Yu-tong(College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 211100, China)

机构地区：[1]南京航空航天大学民航学院,南京211100

出　　处：《兵器装备工程学报》2017年第2期163-167,共5页Journal of Ordnance Equipment Engineering

基　　金：航空发动机机队维修决策优化方法与关键技术项目(U1533202);国家自然科学基金资助项目(51405223);江苏省普通高校研究生科研创新计划项目(KYLX15_0313);中央高校基本科研业务费专项基金资助项目(NS2015072)

摘　　要：利用3D Hashin失效准则预测复合材料气密性舱门蒙皮4种层内损伤模式:纤维拉伸、纤维压缩、基体拉伸和基体压缩,进行低速冲击有限元仿真分析;使用Cohesive单元结合QUADS失效准则代替VCCT技术模拟分层失效;比较不同网格密度、冲击位置以及冲击能量下对数值分析的影响。仿真结果表明:冲击点越接近筋条缘条中央位置,冲击损伤面积越大,应作为舱门健康监测研究中重要监测对象之一。Composite skin of airtight aircraft door 3D impact simulation, predicting 4 kinds of inner-layer FE model was built for the application to damage with 3D Hashin failure criteria： low velocity tensile fiber mode, compressive fiber mode, tensile matrix mode and compressive matrix mode. The delamination failure was implemented by the cohesive zone model with QUADS instead of VCCT technology. By making comparison numerical analysis of different mesh densities, impact energies and locations, simulation results show that the nearer the location important monitoring locations in is to the flange center, the larger damage area gets, which references for aircraft door health mnnitnrln~,

关 键 词：气密性舱门 低速冲击 健康监测 冲击能量 

分 类 号：V258.3[一般工业技术—材料科学与工程]