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DMT-600
Isayev N2O4/UDMH rocket engine. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 6,000 ignitions

Status: In Production. Thrust: 600 N (130 lbf). Unfuelled mass: 4.20 kg (9.20 lb). Specific impulse: 301 s. Burn time: 5,000 s.

Engine: 4.20 kg (9.20 lb). Chamber Pressure: 9.00 bar. Area Ratio: 46.5. Thrust to Weight Ratio: 14.52. Oxidizer to Fuel Ratio: 1.85.



Subtopics

DMT-600 MMH Isayev N2O4/MMH rocket engine. Hermes. In Production. Version of DMT-600 using MMH in place of UDMH, adaptation to western market (was discussed for European Hermes space plane project). 6,000 ignitions

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

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