摘要
针对低轨卫星的轨道拟合问题，分析了传统大气阻力模型、经验力模型和伪随机脉冲模型的基本特性。以GFZ提供的GRACE—A卫星精密星历作为基本观测量，分别采用上述三个力学模型进行了轨道动力学拟合实验。实验结果表明：采用伪随机脉冲模型得到的轨道精度最高，R、T、N三个方向RMS不超过0．002m；其次是经验力模型，RMS不超过0．004m；大气阻力模型精度最差，R和T方向RMS分别不超过0．02m和0．03m，N方向则基本不超过0．06m。
The basic property of the traditional atmospheric drag force model, empirical model and pseudo stochastic pulse model are analyzed in this paper to resolve the problem of LEOS orbit fitting. The precise ephemeris of GRACE - A provided by GFZ is used as basic measurement to verify the performance of these three model. The result shows that the orbit precision using the pseudo stochastic pulse model is the best, and the RMS in R, T and N direction is less than 0.002m. The second best result comes from the empirical model, with the RMS less than 0.004m. For the atmospheric drag force model, the RMS is less than 0.02m,0.03m and 0.06m in R,T and S direction respectively.
出处
《测绘科学与工程》
2015年第6期8-12,16,共6页
Geomatics Science and Engineering
基金
国家自然科学基金资助项目（41104047,41174026）.
关键词
伪随机脉冲
经验力模型
轨道拟合
pseudo stochastic pulse
empirical model
orbit fitting
