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RDMT-400A
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Designer: NII Mash. Propellants: N2O4/UDMH. Thrust(vac): 400 N (80 lbf). Isp: 290 sec. Mass Engine: 2.80 kg (6.10 lb). Chambers: 1. Thrust to Weight Ratio: 14.64. Country: Russia. Status: Developed 1980's. Experimental low-thrust thruster. Niobium combustion chamber with coating.
Bibliography and Further Reading - Haeseler, Dietrich, Datasheets from NII Mashinostroeniye, Nishnaya Salda,
1992 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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