Testing the PPS X000 Plasma Thruster at High Discharge Voltage

Details Testing the PPS X000 Plasma Thruster at High Discharge Voltage Testing the PPS X000 Plasma Thruster at High Discharge Voltage

Oct 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.555e..43d&link_type=abstract

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

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Logic

Scientific paper

High-voltage characterization of the PPS X000 techno- logical demonstrator is described. The thruster was operated up to a total power of 6.5 kW and a discharge voltage of 1 kV. Thruster efficiency peaked near 700 V at 58%, and a maximum specific impulse near 3200 s was measured. Besides the demonstrated propulsive performance domain, these tests showed an order-of- magnitude range of stable thruster operation in discharge voltage and power. Functional limits of the present design were attributed to a minimum plasma and/or current density at high voltage, as well as magnetic circuit saturation above 800 V.

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