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Engine Model: RDMT-135. Designer: NII Mash. Application: Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. Propellants: N2O4/UDMH. Thrust(vac): 135 N (30 lbf). Isp: 260 sec. Mass Engine: 1.20 kg (2.60 lb). Chambers: 1. Chamber Pressure: 9.00 bar. Thrust to Weight Ratio: 11.66. Country: Russia. Status: In Production. Low-thrust attitude control 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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