大偏心率轨道星上快速计算方法

Fast on-Orbit Prediction Algorithm for High Eccentricity Orbit

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.

The usual orbit computation methods include the analytical and numerical approaches. For sat- ellites 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 ve- locities of the high eccentricity orbit satellites can be calculated more precisely, easily and quickly.