Energy-Loss mechanisms of a low-discharge-voltage hall thruster

Document Type

Article

Publication Date

1-1-2010

Abstract

The findings of the probe study and thrust stand measurements performed on an Aerojet BPT-2000 Hall thruster at discharge voltage from 100 to 300 V for 3 to 5 mg/s flow of xenon were examined. Voltage utilization efficiencies were obtained by a four-grid retarding potential analyzer (RPA) probe placed 0.55m downstream from the thruster faceplate at 0.15, and 30° to the thruster centerline. The Faraday probe was enclosed in an alumina sheath with an outer diameter of 4.75 mm. Energy efficiency can further be separated into voltage utilization efficiency and current efficiency, where the voltage utilization efficiency is the percentage of the anode-cathode potential that the ions are accelerated through and the current efficiency is the ratio of exhausted current to discharge current. The results showed that current levels were nearly constant for each mass-flow rate until the discharge voltage dropped below 200V, where the current increased rapidly.

Publication Title

Journal of Propulsion and Power

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