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 1day prior the maneuver and 2h 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 2m within the first 2h after maneuver, and less than 3m for further 2h of orbit prediction.


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    Title :

    Orbit determination and prediction of GEO satellite of BeiDou during repositioning maneuver


    Contributors:
    Cao, Fen (author) / Yang, XuHai (author) / Li, ZhiGang (author) / Sun, BaoQi (author) / Kong, Yao (author) / Chen, Liang (author) / Feng, Chugang (author)

    Published in:

    Advances in Space Research ; 54 , 9 ; 1828-1837


    Publication date :

    2014-07-09


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






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