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全向式气囊着陆装置缓冲过程的仿真研究

邓春燕;裴锦华;   

  1. 南京航空航天大学无人机研究院;
  • 出版日期:2010-02-25 发布日期:2010-02-25

Simulation About Buffer Process of Omni-directional-type Airbag Landing Device

Deng Chunyan Pei Jinhua(Institute of Unmanned Aerial Vehicle Research,Nanjing University of Aeronautics and Astronautics,Nanjing 210016)   

  • Online:2010-02-25 Published:2010-02-25
  • Supported by:
    863高科技研究发展计划(2008AA12A205)项目资助

摘要: 为了探索火星着陆器缓冲着陆技术,以"火星探路者"登陆系统的全向式气囊缓冲装置为对象,采用大型有限元仿真分析技术,实现气囊结构和着陆过程的数学和力学建模,获得全向式缓冲气囊着陆的动态过程仿真;同时得到重要结构部位的过载、重点部位的位移和速度、气囊内部的压力和温度以及气囊结构的动态应力分布等重要指标性参数和变化曲线,确定了"火星探路者"登陆系统的缓冲特性及其仿真分析方法的工程应用。

关键词: 全向式气囊, 缓冲装置, 着陆, 数学模型, 仿真, 航天器

Abstract: In order to explore landing technology of Mars lander,the omni-direction airbag landing device of Mars Pathfinder was used and the structural design and landing mathematic and mechanical model were established by use of modern FEM analysis technology.The simulation process was developed,and the important parameters including a dynamic process of whole airbag to cushion the landing,overload analysis of important structural parts,the displacement and speed changes,internal air pressure and temperature curve and the airbag structure dynamic stress distribution were obtained.The result demonstrates the good buffer property of Mars lander and engineering application of FEM simulation analysis.