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DST-200A
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Designer: Isayev. Propellants: N2O4/UDMH. Thrust(vac): 200 N (40 lbf). Isp: 300 sec. Burn time: 10,000 sec. Mass Engine: 1.70 kg (3.70 lb). Chambers: 1. Chamber Pressure: 7.00 bar. Area Ratio: 100.00. Oxidizer to Fuel Ratio: 1.85. Thrust to Weight Ratio: 11.76. Country: Russia. Status: In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-200. 100,0000 ignitions
Bibliography and Further Reading - Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1998 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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