The type of control system to be designed is highly dependent upon the vehicle configuration and the mission functions. In cases where high pointing accuracy is required an active control system is necessary. This system consists of some attitude sensing device, a torque producing device, and the associated electronics. This paper is primarily concerned with the design of an active control system for holding the desired vehicle angular rates during small disturbances. (Author)


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    Title :

    Spacecraft Attitude Control Using Feedback Parameter Optimization


    Contributors:

    Publication date :

    1968


    Size :

    49 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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