AbstractAn online attitude determination filter is developed for a nano satellite that has no onboard attitude sensors or gyros. Specifically, the attitude of NASA Ames Research Center's O/OREOS, a passively magnetically stabilized 3U CubeSat, is determined using only an estimate of the solar vector obtained from solar panel currents. The filter is based upon the existing multiplicative extended Kalman filter (MEKF) but instead of relying on gyros to drive the motion model, the filter instead incorporates a model of the spacecraft's attitude dynamics in the motion model. An attitude determination accuracy of five degrees is demonstrated, a performance verified using flight data from the University of Michigan's RAX-1. Although the filter was designed for the specific problem of a satellite without gyros or attitude determination it could also be used to provide smoothing of noisy gyro signals or to provide a backup in the event of gyro failures.

    HighlightsOnline attitude determination performed using only solar panel currents.Filter developed is a modification of the existing MEKF.Algorithm tested using actual flight data from two nano satellites.Attitude determination is performed to a precision of five degrees.


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    Titel :

    Online attitude determination of a passively magnetically stabilized spacecraft


    Beteiligte:
    Burton, R. (Autor:in) / Rock, S. (Autor:in) / Springmann, J. (Autor:in) / Cutler, J. (Autor:in)

    Erschienen in:

    Acta Astronautica ; 133 ; 269-281


    Erscheinungsdatum :

    2017-01-19


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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