Space Systems/Loral (formerly Ford Aerospace, Space Systems Division) has implemented a rigid-body Mirror Motion Compensation (MMC) scheme for the GOES-I/M spacecraft currently being built for NASA and NOAA. This has resulted in a factor of 15 reduction in pointing error due to rigid-body spacecraft motion induced by the periodic black-body calibration maneuvers required for the instruments. For GOES the spacecraft and the payload mirrors are considered as rigid bodies. The structural flexibility effects are small and are included in the total pointing budget as a separate item. This paper extends the MMC technique to include structural flexibility. For large multi-payload platforms, the structural flexibility effects can be more important in sensor pointing jitter as the result of payload motion. Sensitivity results are included to show the importance of the dynamic model fidelity.


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    Title :

    Control-Structure Interaction/Mirror Motion Compensation


    Contributors:
    M. Mclaren (author) / P. Chu (author) / X. Price (author)

    Publication date :

    1992


    Size :

    130 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Control-structure interaction/mirror motion compensation

    Mclaren, Mark / Chu, Peter / Price, Xen | NTRS | 1992




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