Journal of Propulsion and Power · 2006 · 112 citations · 54 references
EngineeringHall ThrusterPlasma SciencePlasma PhysicsPlasma ElectronicsPlasma SimulationPlasma TheoryPlasma ConfinementPulse PowerElectrical EngineeringAnode EfficiencyMechatronicsApplied Plasma PhysicRocket EnginePropulsionHall-effect ThrustersIon PropulsionEnergy Efficient DriveAerospace EngineeringPart 2Electric PropulsionPlasma MeasurementsGas Discharge PlasmaPlasma ApplicationIon Thrusters
A phenomenological performance model incorporating a partially ionized plasma with multiply charged ions was used to analyze the performance and plasma measurements of a high‑specific‑impulse (2000–3000 s) Hall thruster. Across 300–900 V, anode efficiency ranged from 57–69 %, yielding 89–97 % voltage, 86–90 % mass, 77–81 % current, and 97–99 % charge utilization; the impact of multiply charged ions on discharge current was modest (≤3 % efficiency loss) but significant for current scaling, and efficient high‑specific‑impulse operation was achieved by regulating electron current with the magnetic field, with the electron Hall parameter remaining nearly constant (≈210 at 300 V to ≈160 at 400–900 V).
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.
54
Plasma oscillations in Hall thrusters
Edgar Choueiri · Physics of Plasmas · 2001 · 501 citations
Hall Thrusters, Calculated Contours, Space Plasma Physics +15
Principles of Plasma Diagnostics
S. J. Zweben · Fusion Technology · 1990 · 372 citations