Application of numerical integration techniques for orbit determination of state-of-the-art LEO satellites

Abstract

Classical numerical integration methods have been tested for determining the orbit of most recent Low Earth Orbiter (hereafter LEO) satellites. In general, numerical integration techniques for orbit determination are commonly used to fill the gap between two discrete, observed epochs. In this study orbits have been determined using the EGM96 gravity model by the Euler, Runge-Kutta, Bulirsch-Stoer and Adams-Moulton numerical integration techniques among others. This analysis is performed for a LEO, the GOCE, and for medium altitude satellite, one GPS satellite. The orbits are integrated under different assumptions on the roughness of the force model, considering effects of the ellipticity, high order gravity and non-static Earth generated accelerations on the orbit.