Energy Efficiency in Low Voltage Hall Thrusters

Jerry Ross, Lyon King
2007 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit   unpublished
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 anodecathode
more » ... anodecathode potential. The acceleration efficiency and current efficiency were divergent in the region of maximum thrust efficiency. Acceleration efficiency increased with decreasing magnet current where the cathode-to-ground potential was determined to account for a portion of the increase in the region of interest. Nomenclaturė m flow rate of propellant as determined by the mass flow controller i ion energy η a acceleration efficiency η β beam divergence as an efficiency η c current efficiency η e energy efficiency η p propellant efficiency η T thrust efficiency Φ CT G cathode-to-ground potential (< 0) Φ max maximum available acceleration potential V ion velocity vector e elementary charge f i ionization mass fraction I d discharge current I sp specific impulse M mass of a xenon atom/ion P power P s I d V d P in P s P out kinetic power in the beam Q average particle charge number q particle charge number T thrust * PhD Candidate, Michigan Technological University, Houghton MI, student member † Associate Professor,
doi:10.2514/6.2007-5179 fatcat:d4gab76ghjfbtjko4b6v7ctizm