Spacecraft attitude control is described by a nonlinear dynamic mathematical model. When Euler parameters are used to define the orientation of a spacecraft with respect to an inertial frame, the model takes a certain form where the components of one factor are quadratic or higher order functions of the state vehicles. Large-angle maneuvers have traditionally been accomplished as a succession of small-angle rotations from a sequence of defined operating points about which the model is linearized. Alternatively, a sequence off single axis rotations are performed. These processes are computationally burdensome and are unable to produce fast multi-axial rotational maneuvers.


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    Title :

    Nonlinear Methods for Spacecraft Attitude Maneuvers


    Contributors:

    Publication date :

    1985


    Size :

    160 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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