An attitude control system consisting of motor-driven inertial wheels in conjunction with an over-riding mass ejection system is proposed for use in space vehicles. Control by mass ejection is used to compensate for initial disturbances during separation from the booster, and for removal of unwanted momentum stored in the wheels. The use of reaction wheels permits fine, damped attitude control. A laboratory model of a single-axis control system was constructed for experimentation and evaluation. The choice of a suitable platform configuration, selection of a prime mover for the inertial wheel, and the philosophy, in the design of the electronics and pneumatics are discussed. Emphasis was placed upon minimization of weight and power consumption. System evaluation includes a discussion of efficiencies, reliability, and torque-speed-power relationships. Sources of disturbances, methods of sensing, and general equations of motion are presented in the Appendix. (Author)


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    Titel :

    Reaction Wheel Attitude Control for Space Vehicles


    Beteiligte:
    R. W. Froelich (Autor:in) / H. Patapoff (Autor:in)

    Erscheinungsdatum :

    1959


    Format / Umfang :

    2 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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