一种大椭圆轨道卫星星历预报方法

A Method of Ephemeris Prediction for High Eccentricity Orbit Satellites

针对大偏心率轨道长时间星历预报,稠密输出星历的低效率问题,提出了一种新的星历预报方法。该方法通过建立卫星摄动力模型,对卫星运动方程进行数值积分来获取卫星星历。该方法的轨道积分器以标准的8阶Adams-Cowell多步法为基础,针对大偏心率轨道的特性,在一个轨道周期的不同时段内采用不同的积分步长,同时引入了用于生成小间隔等间距卫星星历的插值公式。该方法降低了卫星运动方程右函数的计算次数,尤其适用于需要稠密输出卫星星历的情况。以STK(Satellite Tool Kit,卫星工具包)的HPOP(High Precision Orbit Propagator,高精度轨道预报)模型为验证基准,通过数学仿真校验了该方法的有效性和精度。算例表明,该方法在预报精度损失很小的情况下,计算时间远小于标准的多步法和HPOP模型。

To increase the computing efficiency of ephemeris prediction for high eccentricity orbit satellites,a variable-step Adams-Cowell integrator with interpolation is proposed in this paper.Used for orbital integration,the method is based on the traditional 8-order Adams-Cowell multi-step method.Based on the characteristics of high eccentricity orbits,variable integral step lengths are adopted at different time in an orbital period.An interpolation formula is introduced to generate ephemerides with a small interval.The proposed method decreases the rounds of satellite motion equation computing,and it is especially applicable for situations where ephemerides are designed to be frequently output.It is validated by using Satellite Tool Kit（STK）High Precision Orbit Propagator（HPOP）model simulation results.Numerical simulation validates the effectiveness and accuracy of the approach proposed.Examples show that the computing time of the method is far less than that of the traditional multi-step method or HPOP model while keeping a similar accuracy.