Encyclopedia Astronautica

Rocketdyne N2O4/MMH rocket engine. 20 kN. Developed 1990's. Advance technology engine for maneuvering stages. Isp=347s.

Engine: 58 kg (127 lb). Chamber Pressure: 88.80 bar. Area Ratio: 400. Thrust to Weight Ratio: 35.1506204084502. Oxidizer to Fuel Ratio: 1.86. Coefficient of Thrust vacuum: 1.93961344573183. Coefficient of Thrust sea level: 0.

Status: Developed 1990's.
Unfuelled mass: 58 kg (127 lb).
Height: 1.72 m (5.64 ft).
Diameter: 0.76 m (2.51 ft).
Thrust: 20.00 kN (4,496 lbf).
Specific impulse: 347 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...

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