Device employs only 2 gyro wheels and 3 gimbals to effect control of 3 components of vehicle angular rate; moderate degradation of transient response is experienced, due to increased cross-coupling between vehicle axes; it is shown that gyro controller is efficient device when its energy requirements are compared to those for flywheel controller; digital simulation results presented illustrate time response of attitude control system employing advanced gyro controller.


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    Title :

    Gyro momentum exchange device for space vehicle attitude control


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 1 , n 5


    Publication date :

    1963


    Size :

    9 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



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