复合材料蒙皮对机身段适坠性能的影响研究

牟浩蕾; 冯振宇; 邹田春; 张晓敏

复合材料蒙皮对机身段适坠性能的影响研究

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

基金项目:

中国民航局科技项目(MHRD201010)资助

详细信息

作者简介:
牟浩蕾(1987-)，硕士，研究方向为运输类飞机适坠性审定技术，mhl589@163.com

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- 被引次数: 0
出版历程
- 收稿日期: 2012-03-22
- 刊出日期: 2015-06-10

Effects of Composite Skin on Crashworthiness of Composite Fuselage Section

1.
Civil Aircraft Airworthiness Certification Technology and Management Research Center,Civil Aviation University of China,Tianjin 300300

摘要

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。
- 机身结构 /
- 复合材料蒙皮 /
- 破坏模式 /
- 加速度
Abstract: Facing the requirements for crashworthiness design of transport aircraft composite fuselage section, theeffects of composite skin on crashworthiness of composite fuselage section have been studied. This paper establishesthe finite element model of composite fuselage section in HyperMesh, and analyzes the dynamic response characteristics of composite fuselage section subjected to impact with the vertical velocity of 6. 67m/s by changing compositeply angles and plies in LS-DYNA. The data of deformation, displacement, strain and stress are obtained. The acceleration history curves and failure modes of fuselage section under different conditions are given. The results showthat a seat's peak overload can be significantly reduced by selecting appropriate composite ply angles and plies, andthe crashworthiness of composite fuselage section can be effectively improved.
- aircraft /
- composite fuselage section /
- composite skin /
- dynamic response

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参考文献(13)

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