复合材料蒙皮对机身段适坠性能的影响研究  

Effects of Composite Skin on Crashworthiness of Composite Fuselage Section

作　　者：牟浩蕾[1] 冯振宇[1] 邹田春[1] 张晓敏[1] 

机构地区：[1]中国民航大学民用航空器适航审定技术与管理研究中心,天津300300

出　　处：《机械科学与技术》2013年第5期699-703,共5页Mechanical Science and Technology for Aerospace Engineering

基　　金：中国民航局科技项目(MHRD201010)资助

摘　　要：针对运输类飞机复合材料机身段适坠性设计的需要,研究了复合材料蒙皮对典型机身段适坠性能的影响。利用HyperMesh建立机身段模型,采用LS-DYNA设置复合材料蒙皮铺层角度和铺层数,分析模型在6.67 m/s坠撞速度时的动态响应特性。仿真结果得到了机身段结构的变形、位移、应变和应力等数据,给出了座椅与地板连接处的加速度-时间历程曲线和机身段的破坏模式。仿真结果表明选取合适的蒙皮铺层角度和铺层数,可显著降低座椅处的过载峰值,有效提高复合材料机身段适坠性能。Facing the requirements for crashworthiness design of effects of composite skin on crashworthiness of composite finite element model of composite istics of composite fuselage fuselage fuselage transport aircraft composite fuselage section, the section have been studied. This paper establishes section in HyperMesh, and analyzes the dynamic response character- section subjected to impact with the vertical velocity of 6.67m/s by changing composite ply angles and plies in LS-DYNA. The data of deformation, displacement, strain and stress are obtained. The ac- celeration history curves and failure modes of fuselage section under different conditions are given. The results show that a seatg peak overload can be significantly reduced by selecting appropriate composite ply angles and plies, and the crashworthiness of composite fuselage section can be effectively improved.

关 键 词：机身结构 复合材料蒙皮 破坏模式 加速度 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]