This paper describes a spacecraft attitude stabilization system that uses a set of 12 low-power magnetic torquers. The low-power magnetic torquer consists of a hard magnetic-material rod inside a solenoid. Discharging a capacitor through the solenoid winding generates a current pulse that changes the magnetic dipole moment of the rod when required. The interaction of this magnetic dipole moment with the Earth's magnetic field creates a torque on the rod that can stabilize the attitude of a spacecraft in a low Earth orbit. Computer simulation results show that a system of 12 low-power magnetic torquers with a combined mass of 3.5 kg or about 8 lb can stabilize a 1400 kg or 3000 Ib spacecraft in a 600 km circular orbit to a local vertical orientation in five to ten orbits. With initial rates of 1 deg/s or less in each axis, the peak power dissipated in the low-power magnetic torquers is 440 mW or less, the average power prior to settling is 125 mW or less and the average power after settling is about 2 mW or less.


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    Titel :

    A spacecraft attitude stabilization system with low-power magnetic torquers


    Beteiligte:
    Polites, M. (Autor:in) / Quarles, C. (Autor:in) / Kadebek, D. (Autor:in) / Clements, J. (Autor:in) / Mentch, D. (Autor:in)


    Erscheinungsdatum :

    2004


    Format / Umfang :

    11 Seiten, 12 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch