Encyclopedia Astronautica

Aerojet N2O4/Aerozine-50 rocket engine. 444.8 kN. Titan 2 ICBM Stage 2. Out of Production. Isp=315s. Scaled down version of stage 1 engine featuring fixed single chamber. Gas generator cycle. First flight 1962.

Propellant flow rate: 163 kg/sec. Mixture Ratio: 1.80.

Application: Titan 2-2.


Engine: 500 kg (1,100 lb). Chamber Pressure: 56.20 bar. Area Ratio: 49.2. Thrust to Weight Ratio: 90.71. Oxidizer to Fuel Ratio: 1.8.

Status: Out of Production.
Height: 2.80 m (9.10 ft).
Diameter: 1.68 m (5.51 ft).
Thrust: 444.80 kN (99,995 lbf).
Specific impulse: 315 s.
Burn time: 175 s.
First Launch: 1962.

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Titan 2 American intercontinental ballistic missile. ICBM, developed also as the launch vehicle for the manned Gemini spacecraft in the early 1960's. When the ICBM's were retired in the 1980's they were refurbished and a new series of launches began. More...

Associated Manufacturers and Agencies
  • Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. More...

Associated Propellants
  • N2O4/Aerozine-50 Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Aerozine was a 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. More...

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