Navigation accuracy and applicability analysis of GNSS technology in GEO and IGSO spacecraft

At present, the navigation of high-orbit spacecraft mainly relies on ground-based measurement and control systems. In order to study the feasibility of Global Navigation Satellite System (GNSS) technology in high-orbit spacecraft navigation, the navigation accuracy and adaptability of GNSS technology in geostationary earth orbit (GEO) and inclined geosynchronous orbit (IGSO) high-orbit spacecraft were analyzed and studied. The GNSS navigation satellite constellation was simulated using two-line orbital element (TLE) on November 9, 2021. GEO satellites at different sub-satellite points and IGSO satellites at different inclination angles were used as target satellites to carry out navigation experiments. The experimental results show that: In order to meet the number of satellites required for GNSS calculation, the number of visible satellites must be increased by receiving sidelobe signals; for GEO target satellites, when the receiver sensitivity is higher than −169 dB, the navigation accuracy can reach 30 m; the GPS system is used to conduct navigation and orbit determination experiments on 7 different GEO or IGSO orbits; the average accuracy of BeiDou-3 Navigation Satellite System (BDS-3), GPS, GLONASS, and Galileo in high-orbit spacecraft navigation is 28.03 m, 21.16 m, 37.15 m, and 25.09 m, respectively. GPS has the highest accuracy and GLONASS has the lowest accuracy, but it is also 45 m in most periods within.