Periodical orbit maneuver makes a serious problem for navigation users to get correct Geostationary (GEO) orbit information in real-time. As a result, it is very difficult to use GEO satellite for navigation application purpose. In this presentation, the precision of the orbit determination of GEO satellite without maneuver operation has been introduced at first. Then, two strategies of orbit determination during satellite maneuvers are discussed in details. One method is called as maneuver force modeling; the other is empiric force parameter estimation. The results show the residual is of the order of 40 cm by using these strategies, and the position difference between dynamic orbit and kinematics orbit is about 10 m.

Date Published: 29 December 2008
PDF: 8 pages
Proc. SPIE 7285, International Conference on Earth Observation Data Processing and Analysis (ICEODPA), 728520 (29 December 2008); doi: 10.1117/12.816380

Published in SPIE Proceedings Vol. 7285:
International Conference on Earth Observation Data Processing and Analysis (ICEODPA)
Deren Li; Jianya Gong; Huayi Wu, Editor(s)