单星导航HEO卫星初轨确定算法  

Preliminary orbit determination method of HEO satellite using a single navigation GPS satellite measurements

作　　者：李涛护[1] 刘建胜[1] 秦红磊[1] 李锐[1] 

机构地区：[1]北京航空航天大学电子信息工程学院,北京100191

出　　处：《北京航空航天大学学报》2012年第6期755-759,765,共6页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家973资助项目(2010CB731805);国家自然科学基金资助项目(60902055)

摘　　要：HEO(Highly Elliptical Orbit)轨道卫星利用星载GPS(Global Positioning Sys-tem)进行自主定轨面临的主要难题之一就是解决在单颗导航卫星条件下的初轨确定问题.从理论上分析了利用单颗导航卫星的观测量确定HEO卫星轨道初值的所需满足的条件,指出了利用F.G级数法求解初值存在的问题,提出了一种基于轨道根数约束的迭代批处理算法,该算法无需复杂的数学运算,避免了F.G级数法用短弧资料定初轨时系数矩阵秩亏的影响.仿真结果表明,当先验轨道根数误差在允许范围内取值时,在考虑轨道射入误差的情况下,初值的位置偏差在104m量级,速度偏差在100m/s量级,能够根据单颗导航卫星的短弧观测值可靠地完成轨道初值的确定.The autonomous navigation of highly elliptical orbit （HEO） satellites using GPS needed to solve a key problem of the preliminary orbit determination under the condition of only one navigation satellite. The feasibility by using the pseudo-range received from a single navigation satellite was demonstrated, and the limitation of the F. G method for preliminary orbit determination was figured out. An iterative batch method u- sing orbit elements as constrains was proposed to determine the preliminary orbit. This algorithm did not have complex mathematic operation and could avoid the influence of ill-conditioned equation with short arc data by using F. G method. The simulation results show that its positioning bias is about 104 m and velocity bias is approximate 10μm/s with an acceptable orbit injection errors, and the proposed method using a single navigation satellite measurements could determine the HEO initial orbit credibly.

关 键 词：HEO 初轨确定 自主定轨 GPS 

分 类 号：P135[天文地球—天体力学]