This work describes two algorithms for computing the angular rate and attitude in case of a gyro failure in a spacecraft (SC) with a special mission profile. The source of the problem is presented, two algorithms are suggested, an observability study is carried out, and the efficiency of the algorithms is demonstrated.


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    Title :

    Spacecraft Angular State Estimation after Sensor Failure


    Contributors:

    Publication date :

    2002


    Size :

    10 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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