37th Joint Propulsion Conference and Exhibit · 2001 · 44 citations · 6 references
EngineeringAerospace EngineeringPhysicsPlasma PhysicsPower ElectronicsPropulsionAnode MaterialsElectric PropulsionHall Effect ThrustersPropulsion EfficiencyPropulsion System PerformancePropulsion SystemsPerformance CharacterizationPower InputSpecific DischargeSpecific ImpulseThrottlingThrust EfficiencyThruster ConfigurationVoltage
The performance of a two-stage, anode layer Hall thruster was evaluated. Experiments were conducted in single and two-stage configurations. In single-stage configuration, the thruster was operated with discharge voltages ranging from 300 to 1700 V. Discharge specific impulses ranged from 1630 to 4140 sec. Thruster investigations were conducted with input power ranging from 1 to 8.7 kW, corresponding to power throttling of nearly 9: 1. An extensive two-stage performance map was generated. Data taken with total voltage (sum of discharge and accelerating voltage) constant revealed a decrease in thruster efficiency as the discharge voltage was increased. Anode specific impulse values were comparable in the single and two-stage configurations showing no strong advantage for two-stage operation.
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