EXPECTED ORBIT DETERMINATION ACCURACY OF HIGH ALTITUDE, HIGHLY INCLINED SATELLITE ORBITS

摘要

This study seeks to estimate the expected orbit determination accuracy for high altitude, highly inclined satellites using the Global Positioning System. Sun-synchronous and critically inclined orbits were studied for this paper. Gipsy-Oasis II was used for observation simulation and satellite state estimation. Data simulation and error estimation was accomplished through the processing of multiple satellite orbits through a prescribed range of initial conditions, most notably perigee altitude and orbit eccentricity. A filter auto-tuner was developed to automate filter tuning and thus minimize satellite state estimation error. Errors introduced into the orbit determination process were JGM-31-σ gravity clones, reduced fidelity atmospheric density models, and errors in the a priori satellite state. Results illustrate the expected state estimation accuracy given a desired orbit type, eccentricity, and altitude. As expected, the primary factor influencing state accuracy is the orbit altitude.