Encyclopedia Astronautica

Isayev N2O4/MMH rocket engine. 0.600 kN. 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 Isp=305s.

Application: Hermes.

Engine: 4.20 kg (9.20 lb). Chamber Pressure: 9.00 bar. Area Ratio: 46.5. Thrust to Weight Ratio: 14.57. Oxidizer to Fuel Ratio: 1.65.

Status: In Production.
Unfuelled mass: 4.20 kg (9.20 lb).
Thrust: 600 N (130 lbf).
Specific impulse: 306 s.
Burn time: 5,000 s.

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Associated Propellants
  • N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...

  • Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1998 via Dietrich Haeseler.

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