摘要
对当今人卫轨道改进问题，由于力学模型的复杂，精密星历和状态转移矩阵的计算均采用数值方法，这就需要积分两组常微分方程．本文针对状态转移矩阵在定轨中的作用，对定轨弧段不太长的情况，给出了状态转移矩阵的一种分析算法，从而避免数值求解两组常微分方程的问题。
Because of the complexity of force models, the precise ephemeris and the state transition matrix in orbit determination are usually obtained by solving two groups of ordinary differential equations with numerical integration. In this paper, a simplified analytical method for computing the state transition matrix is presented. This method is not only very efficient for the case that the orbit arc is not too long, but also it can avoid the integration of two groups of differential equations at the same time. A practical test justifies the efficiency of the method.
出处
《天文学报》
CSCD
北大核心
1999年第2期113-121,共9页
Acta Astronomica Sinica
关键词
轨道改进
精密星历
状态转移矩阵
人造卫星
orbit determination, precise ephemeris, state transition matrix, analytical method
