Orbit determination and prediction of GEO satellite of BeiDou during repositioning maneuver |
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Authors: | Fen Cao XuHai Yang ZhiGang Li BaoQi Sun Yao Kong Liang Chen Chugang Feng |
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Institution: | 1. National Time Service Center, Chinese Academy of Sciences, China;2. Key Laboratory of Precision Navigation and Timing Technology, National Time Service Center of Chinese Academy of Sciences, China;3. Graduate University of Chinese Academy of Sciences, China;4. Shanghai Astronomical Observatory of Chinese Academy of Sciences, China |
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Abstract: | In order to establish a continuous GEO satellite orbit during repositioning maneuvers, a suitable maneuver force model has been established associated with an optimal orbit determination method and strategy. A continuous increasing acceleration is established by constructing a constant force that is equivalent to the pulse force, with the mass of the satellite decreasing throughout maneuver. This acceleration can be added to other accelerations, such as solar radiation, to obtain the continuous acceleration of the satellite. The orbit determination method and strategy are illuminated, with subsequent assessment of the orbit being determined and predicted accordingly. The orbit of the GEO satellite during repositioning maneuver can be determined and predicted by using C-Band pseudo-range observations of the BeiDou GEO satellite with COSPAR ID 2010-001A in 2011 and 2012. The results indicate that observations before maneuver do affect orbit determination and prediction, and should therefore be selected appropriately. A more precise orbit and prediction can be obtained compared to common short arc methods when observations starting 1 day prior the maneuver and 2 h after the maneuver are adopted in POD (Precise Orbit Determination). The achieved URE (User Range Error) under non-consideration of satellite clock errors is better than 2 m within the first 2 h after maneuver, and less than 3 m for further 2 h of orbit prediction. |
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Keywords: | BeiDou GEO satellite Repositioning maneuver Orbit determination and prediction Quick orbit recovery URE |
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