2023/11/25 by Aravind Gundakaram, Abhirath Sangala, Gundakaram, Aravind +13
Engineering · #Earth and Planetary Astrophysics (astro-ph.EP) #FOS: Computer and information sciences #FOS: Mathematics #FOS: Physical sciences #Mathematical Software (cs.MS) #Numerical Analysis (math.NA) #Space Satellite Systems and Control #Spacecraft Design and Technology #Spacecraft Dynamics and Control
paper · pdf · doi:10.48550/arxiv.2311.15028
openalex publication_date 2023/11/25 · openalex created_date 2023/11/29 · openalex updated_date 2026/07/28
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.