航空学报 > 2006, Vol. 27 Issue (4): 635-640

大柔性飞机着陆撞击多质量块等效模型

史友进1,2, 张曾錩1   

  1. 1. 南京航空航天大学 振动工程研究所, 江苏 南京 210016;2. 盐城工学院 基础教学部, 江苏 盐城 224003
  • 收稿日期:2005-01-07 修回日期:2005-06-16 出版日期:2006-08-25 发布日期:2006-08-25

An Equivalent Multi-mass System of a Flexible Airplane

SHI You-jin1,2, ZHANG Zeng-chang1   

  1. 1. nstitute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2. Department of Basic Science, Yancheng Institute of Technology, Yancheng 224003, China
  • Received:2005-01-07 Revised:2005-06-16 Online:2006-08-25 Published:2006-08-25

摘要: 考虑飞机结构振动刚性模态和前n阶弹性模态,将飞机机体等效地转化为多质量块等效模型,给出了等效系统力学参量的计算方法,为计及机体振动影响的起落架落震试验设计,通过试验检验或确定起落架着陆载荷、功量等提供模型依据,同时也为起落架设计分析、设计计算提供了简明的等效系统。还给出了大柔性飞机着陆功量、机翼位移、剪力、弯矩计算公式。算例结果表明大柔性飞机的起落架设计有必要考虑机体结构弹性,并从全局出发,采用特殊的构造措施和优化设计技术。

关键词: 航空器结构与设计, 物理模型, 等效模态分析, 大柔性飞机, 起落架, 着陆响应

Abstract: For the case in which the rigid mode and the first n modes of a flexible airplane are considered, the body of the airplane is defined as a multi-mass equivalent system and the calculation formulas of the parameters of the system are derived, which presents a model for testing/verifying landing impact load, landing work etc. under the influence of fuselage vibrations and also presents a simple and clear equivalent system for landing gear design analysis. The formula for calculating the landing work, displacement at the wing tip, the shears and bending moments of the wing of a flexible airplane are also given. From an overall point of view, structure deformation of airplane must be considered and optimization design must be used in landing gear design of a flexible airplane.

Key words: aircraft design, physical model, equivalent modal analysis, flexible airplane, landing gear, landing impact response

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