Encyclopedia Astronautica

Credit: Boeing / Rocketdyne
Rocketdyne N2O4/MMH rocket engine. 16.7 kN. Out of Production. Isp=340s. Pump-fed high performance upper stage engine for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Tested extensively but no production.

The Rocketdyne Company completed the advanced technology development phase of this pump-fed high performance upper stage engine. Its performance, mass, and extended space storability make it a candidate for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Applications: kick stages, deep space, Space Transfer Vehicle, Orbit Transfer Vehicle. Dry Mass: 54 kg. Length: 120 cm. Maximum Diameter: 60 cm. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 3.3 kg/sec. Fuel: monomethyl hydrazine at 1.68 kg/sec. Thrust: 16.68 kN vacuum. Isp: 340 sec vacuum minimum. Expansion Ratio: 400:1. Thrust Chamber Materials: columbium. Thrust Chamber Cooling: radiative. Combustion Chamber Pressure: 102 atm at injector end. Combustion Chamber Cooling regenerative by Oxidizer. Combustion Chamber Ignition: hypergolic. Burn Time: 4000 sec in 10 starts. Gas generator, pump-fed.

Engine: 54 kg (119 lb). Chamber Pressure: 103.00 bar. Thrust to Weight Ratio: 31.48.

Status: Out of Production.
Height: 1.20 m (3.90 ft).
Diameter: 0.60 m (1.96 ft).
Thrust: 16.70 kN (3,754 lbf).
Specific impulse: 340 s.
Burn time: 4,000 s.
First Launch: 1983.

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