人造地球卫星初轨计算的单位矢量法  

THE UNIT VECTOR METHOD FOR INITIAL ORBIT DETERMINATION OF ARTIFICIAL SATELLITE

作　　者：陆本魁[1] 戎鹏志 吴建民 夏益[1] 张玉祥 周建生 姜希望 史永善 茅永兴 

机构地区：[1]中国科学院紫金山天文台 [2]中国卫星发射测控系统部

出　　处：《宇航学报》1997年第2期1-7,共7页Journal of Astronautics

基　　金：国家自然科学基金

摘　　要：本文在建立两组单位矢量系统Ｒ＊，Ｓ＊，φ＊和ρ＊，Ａ＊，ｈ＊的基础上，给出了初轨计算的新的条件方程形式以及对不等精度、不同类型的观测资料的加权处理方法，这对充分发挥高精度测距资料ρ和测速资料ρ·的作用十分有利。实测计算表明，本方法基本解决了初轨计算中轨道半长轴不易定准的困难，并具有定轨精度高、适用范围广、稳定性能好等优点，对静止卫星转移轨道入轨段超短弧段测量资料的初轨计算，作用尤为明显。In this paper,new condition equations for initial orbit determination are presented based on two sets of unit vectors R *,S *,φ * and ρ *,A *,h *, and a weight method for processing various data with different accuracy is given together,which is advantageous to bring the high accuracy range data ρ and velocity data ρ · fully into play The practical results show that this method has basically solved the problem that semi major axis is hard to determine exactly This method is proved to have virtues such as high accuracy,wide optimum region and good stability These virtues are particularly obvious in the case of orbit determination with ultra short injection arc of transfer orbit of geostationary satellite

关 键 词：人造卫星 初始轨道 定轨方法 单位矢量法 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]