“火星探路者”舱伞系统动力学特性仿真研究

目前，国内尚未对“火星探路者”减速下降过程中由“降落伞 后锥体 着陆器”组成的舱伞三体系统的动力学特性进行过相关研究。为了全面掌握“火星探路者”减速下降过程中舱伞系统的动力学特性，采用多体动力学的方法，建立了包括降落伞拉直、充气、全张满、抛防热大底，以及着陆器与后锥体分离等过程的全过程动力学模型，并利用模型仿真研究了“火星探路者”舱伞系统的动力学特性。研究结果表明，火星探测器舱伞系统的速度和姿态稳定所需的时间比地球环境下长、高度损失更大，进入舱纵轴需要较长的时间才能趋于垂直，系统摆角的摆动幅度较大。这些是火星探测器降落伞系统进行开伞点设计和时序设计时需要特别注意的问题，其结论可为中国开展火星探测器降落伞减速系统的设计提供重要参考。

Dynamic characteristics simulation analysis for parachute-vehicle system of Mars Pathfinder

So far, the dynamic characteristics of parachute-backshell-lander three-body system for Mars Pathfinder during deceleration descending process have not been studied in China. To master the dynamis characteristics of the Mars Pathfinder parachute-payload system during descending, using the method of multi-body dynamics，an end-to-end dynamic model including parachute deployment, inflation, parachute filling, heat shield separation lander separation from backshell was proposed. The dynamic characteristics of the parachute-vehicle system for Mars Pathfinder during deceleration descending were studied with themodel. The results show that the stable time for the velocity and attitude of parachute-payload system of Mars Pathfinder is longer than that on Earth，the altitude loss is more than that on Earth, the symmetry axis of the probe takes longer time to become vertical, and the amplitude of swing angle is larger. These should be specially noted when designing parachute-opening time and timing of work of Marsprobe. The conclusion could provide technology reference for parachute system design of Mars probe.