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 at 200 V using of propellant to at 300 V using of propellant. The thrust-to-power ratio ranged from at 200 V to at 300 V. At a 200 V discharge voltage, the specific impulse was at efficiency (at 7 A using ). At a 300 V discharge voltage, the specific impulse was at efficiency (at 5 A using ). The performance of the thruster using magnesium propellant was compared to xenon performance at matched molar propellant flow rates: for xenon and for magnesium. The xenon-fueled thruster produced of thrust, with a specific impulse of , at an efficiency of compared to the magnesium-fueled thruster, which produced of thrust, with a specific impulse of , at an efficiency of .
Performance Comparison Between a Magnesium- and Xenon-Fueled 2 Kilowatt Hall Thruster
Journal of Propulsion and Power ; 32 , 4 ; 1015-1021
2016-04-15
7 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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