Hall Effect Thruster with High Specific Impulse

Details Hall Effect Thruster with High Specific Impulse Hall Effect Thruster with High Specific Impulse

Oct 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.555e..16b&link_type=abstract

Proceedings of the 4th International Spacecraft Propulsion Conference (ESA SP-555). 2-9 June, 2004, Chia Laguna (Cagliari), Sard

Computer Science

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Characterization results acquired on a laboratory model of high specific impulse Hall effect thruster operating in the power range of 600-2300 W and discharge voltage varying in the range of 300-800 V are presented. The results of plume study (spectral distribution and angular divergence) are also given. An influence of different factors (propellant utilization efficiency, ion flow divergence, energy spectrum, etc.) upon the performance at transition from traditional operation modes (discharge voltage dU =300-350 V) to modes with higher specific impulse (with dU up to 800 V) was analyzed basing on this experimental data and several newly formed dimensionless parameters.

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