The transfer function matrix is obtained for a three-input and three-output model of minimum sensors and actuators for the attitude control system of flexible spacecraft, and a method is described for determining the poles and zeros of this transfer function. Three cases are considered: (1) the actuators and the sensors are all attached to the primary body, (2) the actuators are on the primary body and the sensors are on the sub-body, and (3) the actuators are on the sub-body and the sensors are on the primary body. The zero-determination problem is shown to reduce to eigenvalue calculations of a matrix which is constructed from the inertial and modal matrices in a simple fashion.


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    Title :

    Determination of poles and zeros of transfer functions for flexible spacecraft attitude control


    Contributors:
    Ohkami, Y. (author) / Likins, P. W. (author)


    Publication date :

    1976-07-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





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