29 December 2008 Orbit determination of geostationary satellite during maneuvers
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Proceedings Volume 7285, International Conference on Earth Observation Data Processing and Analysis (ICEODPA); 728520 (2008) https://doi.org/10.1117/12.816380
Event: International Conference on Earth Observation Data Processing and Analysis, 2008, Wuhan, China
Abstract
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.
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Min Li, Jianghui Geng, Chuang Shi, Qile Zhao, "Orbit determination of geostationary satellite during maneuvers", Proc. SPIE 7285, International Conference on Earth Observation Data Processing and Analysis (ICEODPA), 728520 (29 December 2008); doi: 10.1117/12.816380; https://doi.org/10.1117/12.816380
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