Abstract We use Kane’s method to derive the equations of motion of a spinning spacecraft with three momentum wheels, a nutation damper, and a spherical pendulum. The spherical pendulum is adopted as a simple mechanical equivalent of fuel sloshing in partially filled tanks. The proposed model is an extension of existing models in the literature. We verify and validate our model for two cases: flat spin and a simple reorientation maneuver. Numerical simulations are in agreement with existing results in the literature. The results confirm the accuracy of the model for a typical spacecraft.


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    Title :

    Attitude Motion of a Spinning Spacecraft with Fuel Sloshing and Nutation Damping


    Contributors:


    Publication date :

    2011




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    Local classification TIB:    770/7040
    BKL:    55.60 Raumfahrttechnik



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