Several schemes in current use for sequential estimation of spacecraft attitude using Kalman filters are examined. These differ according to their treatment of the attitude error, namely: using the complete four-component quaternion; using a truncated quaternion in which one of the components has been eliminated; or using a quaternion referred to approximate body-fixed axes. These schemes are examined for the case of a spacecraft carrying line-of-sight attitude sensors and three-axis gyros whose measurements are corrupted by noise on both the drift rate and the drift-rate ramp. The analysis of the covariance is carried out in detail. The historical development of Kalman filtering of attitude is reviewed.


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    Title :

    Kalman filtering for spacecraft attitude estimation


    Contributors:

    Conference:

    Aerospace Sciences Meeting ; 1982 ; Orlando, FL


    Publication date :

    1982-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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