In this paper, we develop a high-precision satellite orbit determination model for satellites orbiting the Earth. Solving this model entails numerically integrating the differential equation of motion governing a two-body system, employing Fehlberg's formulation and the Runge-Kutta class of embedded integrators with adaptive stepsize control. Relevant primary perturbing forces included in this mathematical model are the full force gravitational field model, Earth's atmospheric drag, third body gravitational effects and solar radiation pressure. Development of the high-precision model required accounting for the perturbing influences of Earth radiation pressure, Earth tides and relativistic effects. The model is then implemented to obtain a high-fidelity Earth orbiting satellite propagator, namely the Satellite Ephemeris Determiner (SED), which is comparable to the popular High Precision Orbit Propagator (HPOP). The architecture of SED, the methodology employed, and the numerical results obtained are presented.

翻译：本文针对绕地卫星建立了一套高精度卫星轨道确定模型。求解该模型需对描述二体系统运动的微分方程进行数值积分，采用Fehlberg公式及具有自适应步长控制的Runge-Kutta类嵌入式积分器。该数学模型包含的主要摄动力为：完整引力场模型、地球大气阻力、第三体引力效应及太阳辐射压。为构建高精度模型，需考虑地球辐射压、地球潮汐及相对论效应的摄动影响。进而将该模型实现为高保真度绕地卫星传播器——即卫星星历确定器（SED），其性能可媲美广泛使用的高精度轨道传播器（HPOP）。本文介绍了SED的架构、采用的方法及数值结果。