The controller design for the Solar Dynamics Observatory (SDO) is presented. SDO is a momentum biased spacecraft with three flexible appendages. Its primary scientific instrument, the solar oscillations imager (SOI), is rigidly attached to the spacecraft bus and has arc-second pointing requirements. Meeting these requirements necessitates the use of an active nutation controller (ANC) which is here mechanized with a small reaction wheel oriented along a bus transverse axis. The ANC does its job by orchestrating the transfer of angular momentum out of the bus transverse axes and into the momentum wheel. A simulation study verifies that the controller provides quick, stable, and accurate response.


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    Title :

    High precision active nutation control for a flexible momentum biased spacecraft


    Contributors:
    Laskin, R. A. (author) / Kopf, E. H. (author)

    Publication date :

    1984-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English