Encyclopedia Astronautica
ATE


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.

More... - Chronology...


Associated Countries
See also
Associated Manufacturers and Agencies
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...

Home - Browse - Contact
© / Conditions for Use