摘要
嫦娥三号(CE-3)着陆器实现了我国首次地外天体软着陆任务,着陆器的制导、导航与控制(GNC)系统是最重要的分系统之一.为了保证着陆的高安全性,对动力下降过程中的制导、导航、避障和姿态控制都提出了很高的要求.针对CE-3着陆器的任务特点,本文提出了自适应动力显式制导、多波束容错导航、分区四元数控制技术.实际在轨飞行结果表明,这些算法合理可行,着陆器着陆精度高,着陆姿态和速度优于需求,圆满完成了软着陆任务.本文全方位地介绍了CE-3着陆器在动力下降阶段,GNC系统的要求、组成、算法以及典型在轨飞行结果.
It is the first time for Chang＇E-3 lander landing on an extraterrestrial celestial body in China. Guidance, navigation and control system is one of the most important systems. Guidance, navigation, hazard avoidance and attitude control are demanded strictly for safe landing during powered descent. Adaptive powered explicit guidance, multibeam fault-tolerant navigation and partition quaternion control are proposed for Chang＇E-3 mission. The results in orbit show that these techniques are reasonable. The landing mission is successful and the performances of landing precision, attitude and velocity are better than the corresponding requirements. This paper presents requirement, composing and technique of Chang＇E-3 GNC system and results in orbit.
出处
《中国科学：技术科学》
EI
CSCD
北大核心
2014年第4期377-384,共8页
Scientia Sinica(Technologica)
基金
国家中长期科技发展规划重大专项资助项目
