Aerojet N2O4/Aerozine-50 rocket engine. 35.6 kN. Out of production. Originally developed for Vanguard and Able. Two used, thrust uprated from 3540 kgf to 3628 kgf, with higher specific impulse, in Transtage. Isp=311s. Flown 1964-1980.
Engine: 110 kg (240 lb). Chamber Pressure: 7.00 bar. Area Ratio: 40. Thrust to Weight Ratio: 32.9863636363636. Oxidizer to Fuel Ratio: 2. Coefficient of Thrust vacuum: 4.39646147665109.
Status: Out of production.
More... - Chronology...
Unfuelled mass: 110 kg (240 lb).
Diameter: 1.53 m (5.00 ft).
Thrust: 35.60 kN (8,003 lbf).
Specific impulse: 311 s.
Burn time: 440 s.
First Launch: 1958.
Number: 80 .
Associated Launch Vehicles
Titan 3A American orbital launch vehicle. Titan with Transtage third stage. Core for Titan 3C. More...
Titan 3C American orbital launch vehicle. Titan 3A with five segment solid motors. Man-rated design originally developed for Dynasoar spaceplane. More...
Titan 3C7 American orbital launch vehicle. Variant of Titan 3C with seven segment solid motors. Proposed by Martin for precise delivery of payloads beyond Titan 3C capacity into geosynch orbit. Never flown. 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...
Titan Transtage N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 12,247/1,950 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds. More...
Titan Transtage Stretch N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 15,000/2,200 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds. 20% stretch of Transtage to handle geosynch insertion of larger payloads launched by Titan 3C7. Masses estimated. More...
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