论文部分内容阅读
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。
Aiming at the long-time ephemeris forecast of high eccentricity orbit and the low output efficiency of dense output ephemeris, a new ephemeris forecasting method is proposed. The method obtains the satellite ephemeris by establishing the satellite perturbation model and numerical integration of the satellite motion equation. Based on the standard 8-order Adams-Cowell multi-step method, the orbital integrator of this method adopts different integral steps for different periods of one orbital period for the characteristics of large eccentricity orbits. At the same time, Interval spacing satellite ephemeris interpolation formula. This method reduces the calculation times of the right function of the satellite motion equation and is especially suitable for situations where the satellite ephemeris needs to be densely output. The validity and accuracy of this method are verified by mathematical simulation with the HPOP (High Precision Orbit Propagator) model of STK (Satellite Tool Kit) as the verification standard. The example shows that this method has less computational time than the standard multi-step method and HPOP model when the prediction accuracy is low.