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Engine Model: RDMT-2600. Designer: NII Mash. Propellants: GOX/Alcohol. Thrust(vac): 2.600 kN (585 lbf). Isp: 270 sec. Mass Engine: 5.00 kg (11.00 lb). Chambers: 1. Thrust to Weight Ratio: 53.00. Country: Russia. Status: Developed 1980's. Experimental low-thrust thruster.
Bibliography:- Haeseler, Dietrich, Datasheets from NII Mashinostroeniye, Nishnaya Salda,
1992 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2008 except where otherwise noted.
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