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43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Energy efficiency measurements were taken on a 2 kW (nominal) Hall thruster operating at discharge voltages of 100-200 V and 3 mg/s of xenon. Acceleration and current efficiencies were compared to thrust efficiency over a range of magnet coil current values of 0 A -2.5 A. Acceleration efficiencies were obtained with a 4-grid Retarding potential analyzer and current efficiency measurements were calculated from the discharge current as read from the power supply maintaining the anodecathodedoi:10.2514/6.2007-5179 fatcat:d4gab76ghjfbtjko4b6v7ctizm