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卫星的精密定轨指的是从观测数据中获取指定预报开始时刻的高精度参数轨道。由于GPS观测数据中不可避免的带有随机误差和系统误差等非线性影响因素,因而不可能确定一条能够精确地拟合所有观测值的轨道,所以需要利用大量的观测数据使用统计学原理对航天器轨道状态进行估计。本文以低轨卫星为研究对象,分析了精密定轨的基本理论方法,包括摄动力模型以及最小二乘估计法。最后分别通过批处理和递推算法对GRACE-A卫星数据进行计算,实现了低轨卫星的定轨,并达到了一定的精度。
Precise orbit determination of a satellite refers to the acquisition of high-precision parameter orbits from the observed data at the beginning of a given forecast. Due to the unavoidable non-linear factors such as random error and system error in GPS observation data, it is impossible to determine an orbit that can accurately fit all the observations. Therefore, a large amount of observation data is needed to use statistical principles to measure the spacecraft Orbit state is estimated. In this paper, the low-orbit satellites as the research object, the basic theory of precision orbit determination method, including the perturbation model and the least-squares estimation method. Finally, the data of GRACE-A satellite are calculated by batch processing and recursion algorithm, respectively, and the orbit determination of LEO satellites is achieved and a certain degree of accuracy is achieved.