This paper studies single-axis equations of motion that are applicable to a spacecraft or to a space experiment pointing assembly whose motion has been perfectly isolated from the carrier vehicle. It considers four state estimators for implementation in the control loop for a stellar observation experiment. It is shown via closed-loop covariance analysis that the best achievable pointing performance with the best of the first three estimators is limited to about 0.125 are-sec (rms) with the given rate-gyro and star-tracker inaccuracies. It is also shown that the fourth estimator has the capability of achieving a pointing performance far superior to the performance achievable using the first three estimators. The fourth estimator relies on the ability to accurately generate the desired control torque.


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    Title :

    On attitude estimation schemes for fine-pointing control


    Additional title:

    Lageschaetzungsmethode zur Feinausrichtungssteuerung


    Contributors:
    Joshi, S.M. (author)


    Publication date :

    1978


    Size :

    8 Seiten, 3 Bilder, 8 Tabellen, 8 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English