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Engine Model: Ion. Propellants: Electric/Mercury. Thrust(vac): 275 N (62 lbf). Isp: 5,300 sec. Burn time: 1,900,000 sec. Chambers: 1. Country: USA. Status: Study 1981.

Conceptual ion engine design of the 1970's for a shuttle-sized upper stage.

Ion used on Rocket Stages
Ion used on Spacecraft
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© Mark Wade, 1997 - 2008 except where otherwise noted.