Aerojet N2O4/Aerozine-50 rocket engine. 1096.8 kN. Out of Production. Isp=297s. Used on Titan 2 launch vehicle. Engines refurbished for space launcher versions from decommissioned missiles between 1974-1982.
Configuration: twin fixed motors with individual turbo-pumped assemblies. Application: Titan 2 Stage 1. First Flown: 1962 ICBM. Sept. 1988 orbital. Dry Mass: 739 kg. Length: 3.13 m. Maximum Diameter: 1.14 m. Engine Cycle: Gas generator. Propellants: hypergolic nitrogen tetroxide and Aerozine-50, delivered at 750 kg/sec. Mixture Ratio: 1.93:1. Thrust: 1913 kN sea level. Isp: 259 sec at sea level. Expansion Ratio: 8:1. Combustion Chamber Pressure: 53.3 atm. Burn Time: 158 sec.
Thrust (sl): 956.500 kN (215,030 lbf). Thrust (sl): 97,534 kgf. Engine: 739 kg (1,629 lb). Chamber Pressure: 54.00 bar. Area Ratio: 8. Thrust to Weight Ratio: 151.34. Oxidizer to Fuel Ratio: 1.93.
Status: Out of Production.
More... - Chronology...
Height: 3.13 m (10.26 ft).
Diameter: 1.14 m (3.74 ft).
Thrust: 1,096.80 kN (246,570 lbf).
Specific impulse: 297 s.
Specific impulse sea level: 259 s.
Burn time: 155 s.
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...
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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