一种航天器天文自主定轨方法  

A Method of Celestial Autonomous Orbit Determination for Spacecraft

作　　者：杨博[1] 房建成[1] 伍小洁[1] 赵建辉[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《中国惯性技术学报》2000年第3期33-36,78,共5页Journal of Chinese Inertial Technology

基　　金：航天 8 63青年基金!( 863 2 .99.1 )

摘　　要：提出用星敏感器和地平仪测量星光角距作为主要观测量 ,用地平仪直接测量得到地心方向矢量 ,用间接测得的地心距离作为补充观测量 ,并用推广卡尔曼滤波方法来实时确定航天器的轨道。文中对系统的构成、模型的建立、以及卡尔曼滤波的方法都作了认真的仿真研究 。The authors put forward an autonomous realtime determination of position for spacecraft by using the extended Kalman filtering.The starlight angular distance observed by star sensor and horizontal instrument is taken as the main observation.The geocentric direction directly observed and the geocentric distance indirectly observed by horizontal instrument are used as compensative observation.The system constructing,model building and Kalman filtering are all studied with simulations,and the results are satisfied.

关 键 词：航天器 天文导航 自主定轨 

分 类 号：V448.224[航空宇航科学与技术—飞行器设计]