火星着陆器扶正展开动力学研究  

Research on Dynamics of Mars Lander Rectifying and Deployment

作　　者：王永滨[1] 姜毅[1] 丁弘[1] 戈嗣诚[1] 荣伟[1] 

机构地区：[1]北京空间机电研究所,北京100094

出　　处：《航天返回与遥感》2015年第1期24-31,共8页Spacecraft Recovery & Remote Sensing

基　　金：国家863高技术计划资助项目(2008AA12A205)

摘　　要：火星着陆技术是实现对火星探测的关键技术。文章通过对四面体着陆器展开过程进行深入研究,提出了一种应用于四面体火星着陆器扶正展开的方法,并对该方法进行了详细的分析和计算;通过火星着陆器扶正展开动力学的分析,提出了扶正展开系统的动作策略,对实现扶正展开的姿态确认进行了分析和设计;基于Hamilton法建立了扶正展开着陆器的动力学模型,对多姿态下扶正展开执行器的动力学特性进行了分析,获得了扶正及展开过程中的力矩特性,从而可以对翻转动作进行定量的分析,实现翻转能量的最小化。该研究对于火星着陆器的设计具有参考意义。The entry, descent and landing（EDL） is a key technology for Mars exploration. In this paper, a new rectifying and deploying method for a tetrahedral Mars lander is proposed by investigating the deploying process. Detailed analysis and calculations for the new method are also carried out. The paper puts forward the tactic for the Mars landing deployment to rectify and deploy by systemically researching the Mars lander, and then analyzes and designs the discriminating means for the attitude of the Mars lander. The dynamics model of the Mars lander is established based on the Hamilton theory, and dynamics identity is analyzed with multi attitude. The characteristic of moment is obtained in the process of rectifying and deployment, thereby the analyzsis of the action of overturn can be measurable, and the minimization of overturn energy can be achieved accordingly. The research can be as a reference for the design of Mars lander.

关 键 词：气囊缓冲 姿态扶正 着陆器展开 火星探测 

分 类 号：V476.4[航空宇航科学与技术—飞行器设计]