CAJ | 학술논문

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.
위료탐색화성착륙기완충착륙기술,이"화성탐로자"등륙계통적전향식기낭완충장치위대상,채용대형유한원방진분석기술,실현기낭결구화착륙과정적수학화역학건모,획득전향식완충기낭착륙적동태과정방진;동시득도중요결구부위적과재、중점부위적위이화속도、기낭내부적압력화온도이급기낭결구적동태응력분포등중요지표성삼수화변화곡선,학정료"화성탐로자"등륙계통적완충특성급기방진분석방법적공정응용.
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.