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动力学定轨是空间飞行器精密轨道确定的基本方法.然而,有些情况下,对飞行器进行精确的力学建模是困难的.基于函数逼近理论,给出了B样条逼近空间飞行器统计意义下的轨道确定方法.为了验证方法的有效性,分别对LEO(Low Earth Orbit)、MEO(Medium Earth Orbit)和HEO(Highly Eccentric Orbit)卫星进行了轨道确定数值试验,计算结果证实方法精度可靠、解算稳定.B样条逼近轨道确定方法与坐标系的选择无关,既可以在协议天球坐标系下解算,又可以在协议地球坐标系下解算.B样条逼近可以直接计算飞行器位置和速度,不需要对动力学状态方程进行积分,也不需要计算状态转移矩阵,使得定轨计算量相对于动力学定轨大幅减少.方法既有一定的理论意义,又可以作为工程应用中空间飞行器轨道确定的一个常规算法.
Kinetic orbit determination is the basic method to determine the precise orbit of a spacecraft, however, in some cases, it is difficult to accurately model the aircraft.According to the theory of function approximation, B-spline approximation is given in the statistical sense of spacecraft Orbit determination method.In order to verify the effectiveness of the method, the orbital determinations of LEO (Low Earth Orbit), MEO (Medium Earth Orbit) and HEO (Highly Eccentric Orbit) satellites were carried out respectively. The results show that the method is reliable and solvable Stable.BB spline approximation orbit determination method has nothing to do with the choice of coordinate system, can be solved under the agreement celestial coordinate system, but also can be solved under the agreement earth coordinate system.B-spline approximation can directly calculate the aircraft position and velocity, It is not necessary to integrate the dynamic equation of state, nor to calculate the state transition matrix, so that the amount of orbit determination greatly reduces compared with the kinetic orbit determination.The method has certain theoretical significance and can be used as spacecraft orbit determination in engineering application A conventional algorithm.