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Aerojet 50kW
Redmond electric/xenon rocket engine. Effort 2001-2003 developed a 50 kW Hall thruster in parallel to NASA's in-house development of the NASA-457M thruster.

Date: 2001-2004.

In 2001, Redmond Rocket Center was competitively selected to design a 50 kW Hall thruster as a complementary effort to NASA GRC's in-house development of the NASA-457M thruster. A contract option for thruster fabrication was exercised and the thruster was delivering to NASA GRC in 2002 and tested in 2003. In FY04, the high-power Hall thruster development funded by the ISTP was refocused on the GRC developed, NASA-457M, 50 kW Hall thruster.

Electrical Input Power: 50.00 kW.



Country: USA. Propellants: Electric/Xenon. Agency: Redmond.

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