大偏心率轨道星上快速计算方法

doi:10.3969/j.issn.1674-1579.2015.04.004

摘要/Abstract

摘要： 卫星星上轨道的计算方法通常有解析方法和数值积分方法等.采用数值积分方法计算量较大，对于大偏心率的探测器任务轨道，解析方法也不适用.通过引入精密轨道与二体轨道的位置差，利用位置差拟合切比雪夫多项式系数，大大提高拟合精度.该方法计算精度高、计算速度快，可以很好地解决大偏心率椭圆轨道的星上轨道计算问题.

关键词: 大偏心率轨道, 切比雪夫多项式, 轨道拟合, 精密星历

Abstract: The usual orbit computation methods include the analytical and numerical approaches. For satellites in high eccentricity orbit, numerical method brings more computation, and a perturbation analysis solution is inapplicable. A new method of prediction for high eccentricity orbit is developed, which adopts the position bias between the precise trajectory and twobody dynamic orbit to fit the Chebyshev polynomial coefficients. This method can improve the precision of fitting orbit, and the positions and velocities of the high eccentricity orbit satellites can be calculated more precisely, easily and quickly.

Key words: high eccentricity orbit, Chebyshev polynomial, orbit fitting, precise ephemeris

中图分类号:

V412.41

胡少春, 黄翔宇. 大偏心率轨道星上快速计算方法[J]. 空间控制技术与应用, 2015, 41(4): 20-23.

HU Shao-Chun, HUANG Xiang-Yu. Fast onOrbit Prediction Algorithm for High Eccentricity Orbit[J]. , 2015, 41(4): 20-23.

参考文献

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