A technique is presented for achieving active control of nutation on a dual-spin spacecraft with an articulated payload through use of the payload's control system. Using the Orbiting Solar Observatory (OSO)-8 as an illustration, the closed-form solution to the nutation/control system dynamic interaction is presented. Control system design criteria are developed which establish the basic stability of the interaction. Design procedures are described to achieve the most effective nutation damping. Limitations on the amount of damping which can be achieved are characterized as functions of spacecraft and payload mass properties and servo-design parameters. The design techniques presented are verified through a series of on-orbit tests recently conducted on the OSO-8 spacecraft.


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    Title :

    Dual-spin-spacecraft nutation control using articulated payloads


    Additional title:

    Doppelspin-Nutationsregelung eines Raumfahrzeuges mit Nutzlast


    Contributors:

    Published in:

    Publication date :

    1980


    Size :

    10 Seiten, 13 Bilder, 9 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English