The invention relates to a satellite orbit semi-major axis flat root long-period term modeling method, which comprises the following steps: carrying out long-time orbit recursion on a satellite, converting an orbit semi-major axis instantaneous root into an orbit semi-major axis flat root, carrying out sliding filtering processing on the orbit semi-major axis flat root by adopting a sliding filtering method, and carrying out long-period term modeling on the orbit semi-major axis flat root from the perspective of numerical calculation. The optimal calculation time period of the long-period term is obtained by constructing an optimal correlation coefficient calculation method, and furthermore, in the determined calculation time period range, segmented Fourier fitting is performed by taking the geographic longitude of the ascending node of the current circle of orbit as an independent variable and taking the orbit semi-major axis flat root long-period term as a dependent variable, so that the optimal calculation time period of the long-period term is obtained. And finally, a high-precision mathematical model of the orbit semi-major axis flat root long-period term is obtained. According to the method, the calculation process is simple and efficient, the obtained model is high in precision, and accurate modeling of the long-period term of the orbit semi-major axis flat root can be achieved.
本发明涉及一种卫星轨道半长轴平根长周期项建模方法,该方法通过对卫星进行长时间轨道递推,将轨道半长轴瞬根转换为轨道半长轴平根,采用滑动滤波方法对轨道半长轴平根进行滑动滤波处理,再从数值计算角度出发,通过构建最优相关性系数计算方法得到长周期项的最优的计算时间周期,进一步在确定的计算时间周期范围内,采用以当圈轨道的升交点地理经度为自变量,以轨道半长轴平根长周期项为因变量,进行分段傅里叶拟合,最终得到高精度的轨道半长轴平根长周期项数学模型。本发明计算过程简单、高效,得到的模型精度高,能够实现对轨道半长轴平根的长周期项的精确建模。
Satellite orbit semi-major axis flat root long period term modeling method
一种卫星轨道半长轴平根长周期项建模方法
12.11.2024
Patent
Elektronische Ressource
Chinesisch
Semi-Major Axis Knowledge and GPS Orbit Determination
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|Semi-Major Axis Knowledge and GPS Orbit Determination
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