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astronautix.com DST-100A


Designer: Isayev. Propellants: N2O4/UDMH Thrust(vac): 10 kgf. Thrust(vac): 0.10 kN. Isp: 304 sec. Burn time: 50,000 sec. Mass Engine: 2 kg. Chambers: 1. Chamber Pressure: 7.70 bar. Area Ratio: 100.00. Oxidizer to Fuel Ratio: 1.85. Country: Russia. Status: In Production. References: 350 . Comments: Bi-propellant hypergolic (self-igniting) engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-100. 450,0000 ignitions.
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Last update 12 March 2001.
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© Mark Wade, 2001 .