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:

    Conference:

    Intelligent Systems and Control (ISC 2002) ; 2002 ; Tsukuba, Japan


    Publication date :

    2002-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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