The performance metrics of a 2-kW-class thruster operated using magnesium propellant were measured and compared to the performance of the same thruster operated using xenon propellant. When operated with magnesium at a 7 A discharge current, the thruster had thrust ranging from 34±0.8  mN at 200 V using 1.8  mg/s of propellant to 39±1.5  mN at 300 V using 1.8  mg/s of propellant. The thrust-to-power ratio ranged from 24±0.5  mN/kW at 200 V to 18±0.7  mN/kW at 300 V. At a 200 V discharge voltage, the specific impulse was 1930±49  s at 23±5.0% efficiency (at 7 A using 1.8  mg/s). At a 300 V discharge voltage, the specific impulse was 2420±130  s at 21±6.4% efficiency (at 5 A using 1.1  mg/s). The performance of the thruster using magnesium propellant was compared to xenon performance at matched molar propellant flow rates: 5  mg/s for xenon and 1.1  mg/s for magnesium. The xenon-fueled thruster produced 76±1.5  mN of thrust, with a specific impulse of 1550±70  s, at an efficiency of 40±2.0% compared to the magnesium-fueled thruster, which produced 27±1.2  mN of thrust, with a specific impulse of 2420±130  s, at an efficiency of 21±6.4%.


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    Title :

    Performance Comparison Between a Magnesium- and Xenon-Fueled 2 Kilowatt Hall Thruster


    Contributors:


    Publication date :

    2016




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Local classification TIB:    770/7040





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