单星导航HEO卫星初轨确定算法

HEO(Highly Elliptical Orbit)轨道卫星利用星载GPS(Global Positioning System)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10⁴ m量级,速度偏差在10⁰ m/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.

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

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 using 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 100 m/s with an acceptable orbit injection errors,and the proposed method using a single navigation satellite measurements could determine the HEO initial orbit credibly.