摘要
研究了空间飞行器向小天体着陆阶段基于导航相机和激光测距仪的自主光学导航方案。采用扩展卡尔曼滤波方法设计了导航滤波器。利用数值仿真验证了其系统性能 ,并着重分析了测量误差、初始状态误差、参数误差等各种误差源对导航滤波器的影响。
An autonomous optical navigation scheme for landing of spacecraft on a small celestial body based on navigation camera and laser range finder measurements was studied. The navigation filter was designed using extended Kalman filtering technique. Numerical simulations were used to demonstrate the system performance and to analyze the influence of various error sources including observation errors, initial state errors and parameter errors upon the filter. Simulation shows the filter's performance is sensitive to the error of the a priori spin rate of the target body.
出处
《高技术通讯》
EI
CAS
CSCD
2002年第8期42-46,共5页
Chinese High Technology Letters
基金
86 3高技术资助 86 3 2 5 3.4
国防"十五"民用航天预研资助
