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astronautix.com DST-100


Designer: Isayev. Propellants: N2O4/UDMH Thrust(vac): 10 kgf. Thrust(vac): 0.10 kN. Isp: 276 sec. Burn time: 10,000 sec. Mass Engine: 1 kg. Chambers: 1. Chamber Pressure: 15.00 bar. Area Ratio: 43.00. Oxidizer to Fuel Ratio: 1.85. Country: Russia. Status: In Production. References: 350 . Comments: Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions.
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Last update 12 March 2001.
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