Efficiency analysis of a low discharge voltage Hall thruster
Document Type
Conference Proceeding
Publication Date
1-1-2008
Abstract
Power loss mechanisms for a 2 kW (nominal) Hall thruster operating at low discharge voltages were examined through thrust stand measurements and probe studies. Operating conditions included discharge voltages ranging from 100 V to 300 V and mass flow rates of 3 to 5 mg/s of xenon. Thrust stand measurements indicate a minimum thrust efficiency of 15% at 100 V at 3 mg/s and a maximum of 59% at 300 V and 5 mg/s. Retarding potential analyzer, emissive and Faraday probes were utilized to quantify multiple sources of inefficiency. The ratio of exhausted ion current to discharge current was found to be the dominant loss mechanism at low discharge voltage.
Publication Title
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Recommended Citation
Ross, J.,
Sommerville, J.,
&
King, L.
(2008).
Efficiency analysis of a low discharge voltage Hall thruster.
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.
http://doi.org/10.2514/6.2008-4722
Retrieved from: https://digitalcommons.mtu.edu/michigantech-p/13958