This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Used on stages: Ion . Propellants: Electric/Mercury Thrust(vac): 28 kgf. Thrust(vac): 0.27 kN. Isp: 5,300 sec. Burn time: 1,900,000 sec. Chambers: 1. Country: USA. Status: Study 1981. Comments: Ion engine design for shuttle-sized upper stage.
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Last update 12 March 2001.
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© Mark Wade, 2001 .