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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    Titel :

    Spacecraft Angular State Estimation after Sensor Failure


    Beteiligte:
    I. Y. Bar-Itzhack (Autor:in) / R. R. Harman (Autor:in)

    Erscheinungsdatum :

    2002


    Format / Umfang :

    10 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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