In this paper, the relative navigation algorithm of chaser spacecraft with orbit maneuvering is investigated. Based on the relative motion dynamic model and linear relative measurement model, a robust H filter for chaser spacecraft is proposed, which contains affine norm-bounded uncertainties, disturbances, and non-Gaussian noise. The necessary and sufficient conditions for the existence of robust H filter are obtained in terms of a linear matrix inequality(LMI). The filter design is then cast into a convex optimization problem subject to LMI constraints. The numerical simulation results show that the relative position precision is 0.1m and the relative velocity precision is 0.02m/s when the chaser spacecraft has orbit maneuvering, which illustrates the effectiveness and advantage of the proposed navigation algorithm.


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    Titel :

    Relative navigation algorithm research of chaser spacecraft


    Beteiligte:
    Hong Deng, (Autor:in) / Weichao Zhong, (Autor:in) / Zhaowei Sun, (Autor:in) / Shunan Wu, (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.03.2011


    Format / Umfang :

    419727 byte





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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