High-specific impulse Hall thrusters, part 2: Efficiency analysis

Performance and plasma measurements of a high-specific impulse (2000-3000 s) Hall thruster were analyzed using a phenomenological performance model that accounted for a partially ionized plasma containing multiply charged ions. Anode efficiency over discharge voltages of 300-900 V ranged from 57 to 69 %, which corresponded to 89-97% voltage utilization, 86-90% mass utilization, 77-81% current utilization, and 97-99% charge utilization. Although the net decrease of efficiency due to multiply charged ions was at most 3 %, the effects of multiply charged ions on the discharge current could not be neglected because the increase of the discharge current with voltage was primarily due to the increasing fraction of multiply charged ions. This and the fact that the maximum deviation of the electron current from its average value was only +5/-14% illustrated how efficient operation at high-specific impulse was enabled through the regulation of the electron current with the applied magnetic field. The electron Hall parameter, defined by acceleration zone plasma properties, was nearly constant with voltage, decreasing from an average of 210 at 300 V to an average of 160 between 400 to 900 V. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc.

Duke Scholars

Author Alec Gallimore Thomas Lord Department of Mechanical Engineering and Materia ...