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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    Title :

    Relative navigation algorithm research of chaser spacecraft


    Contributors:
    Hong Deng, (author) / Weichao Zhong, (author) / Zhaowei Sun, (author) / Shunan Wu, (author)

    Published in:

    Publication date :

    2011-03-01


    Size :

    419727 byte





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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