Dynamic characters and control strategy for short tethered satellite system in deployment are studied in this paper. Tether elastic oscillation and sub-satellite attitude motion are considered in the dynamic model. Sub-satellite releasing method with an initial velocity and a negative acceleration is proposed for fast deployment. It is indicated that the short dimension and fast deployment make dynamic characteristics of both the tether and the sub-satellite different from those of the long-tether systems. Control strategy is designed based on these dynamic characters. Thrusters are considered to provide active control for the tether and the attitude of the sub-satellite. Variable structure control is adopted, taking into account the nonlinear dynamics of the system and the on-off output of the thrusters. Numerical simulation shows that the tethered sub-satellite can be deployed to designed direction in or out of the orbit plane with thrust control. The tension of the tether is positive during deployment. The in-plane angle of the tether is controlled within 0.1... The out-of-plane angle passively keeps near its initial releasing value. In addition, the attitude angles of the sub-satellite are controlled or passively remain within 0.5... This fast deployment provides flexibility for tether assisted space operations. (ProQuest: ... denotes formulae/symbols omitted.)


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    Title :

    Attitude dynamics and thrust control for short tethered sub-satellite in deployment


    Contributors:


    Publication date :

    2015



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik
    Local classification TIB:    275/7040






    Precision tethered satellite attitude control

    Kline-Schoder, Robert J. | NTRS | 1990


    Deployment dynamics of tethered satellite systems

    MODI, V. / MISRA, A. | AIAA | 1978