High Thrust Density Electric Propulsion for Heavy Payload In-Space Transportation

Details High Thrust Density Electric Propulsion for Heavy Payload In-Space Transportation High Thrust Density Electric Propulsion for Heavy Payload In-Space Transportation

Oct 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.555e.126a&link_type=abstract

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

Physics

Scientific paper

Mission studies for a crewed Mars mission clearly show that with chemical propulsion the trip times are too long and the propellant mass is very high. For these kinds of missions stationary, electric thrusters are preferable because of their high thrust levels and high specific impulse. In view of this, thermal arcjets, MPD self-field and MPD applied-field thrusters and, most recently, hybrid thrusters have been developed in the US, Russia and in Germany at the Institute of Space Systems (IRS) of the Universität Stuttgart. Based on a brief review of the state of the art of stationary high power thermal and MPD arcjets and hybrid thrusters, future development needs and trends are presented in this publication.

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