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DST-200A
Part of DST engine series Family
Isayev N2O4/UDMH rocket engine. In Production. Bi-propellant hypergolic engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime compared to DST-200. 100,0000 ignitions.

Status: In Production. Thrust: 200 N (40 lbf). Unfuelled mass: 1.70 kg (3.70 lb). Specific impulse: 300 s. Burn time: 10,000 s.

Engine: 1.70 kg (3.70 lb). Chamber Pressure: 7.00 bar. Area Ratio: 100. Thrust to Weight Ratio: 11.76. Oxidizer to Fuel Ratio: 1.85.



Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Agency: Isayev bureau. Bibliography: 350.

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