N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 12,247/1,950 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds.
Cost $ : 14.500 million. No Engines: 2.
More... - Chronology...
Status: Out of production.
Gross mass: 12,247 kg (27,000 lb).
Unfuelled mass: 1,950 kg (4,290 lb).
Height: 4.57 m (14.99 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 71.17 kN (15,999 lbf).
Specific impulse: 311 s.
Burn time: 440 s.
Number: 130 .
AJ10-138 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. More...
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 23C American orbital launch vehicle. Post-MOL standardisation of Titan 3C, with man-rated systems removed, upgraded first stage engines, digital avionics, blowdown solid rocket motor thrust vector control in place of pressure-regulated system, simplified Transtage attitude control system. 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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