N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 350,000/20,000 kg. Thrust 4,344.46 kN. Vacuum specific impulse 296 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated.
Cost $ : 11.600 million. No Engines: 4.
Status: Study 1965.
More... - Chronology...
Gross mass: 350,000 kg (770,000 lb).
Unfuelled mass: 20,000 kg (44,000 lb).
Height: 29.90 m (98.00 ft).
Diameter: 4.57 m (14.99 ft).
Span: 4.57 m (14.99 ft).
Thrust: 4,344.46 kN (976,674 lbf).
Specific impulse: 296 s.
Specific impulse sea level: 258 s.
Burn time: 210 s.
LR87-7 Aerojet N2O4/Aerozine-50 rocket engine. 1086.1 kN. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Isp=296s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962. More...
Associated Launch Vehicles
Titan 3L2 American orbital launch vehicle. Variant of Titan with 15 foot Large Diameter Core, 2 x 7 segment strap-ons. Man-rated, optimized for delivery of heavy payloads into LEO. Never developed. More...
Titan 3L4 American orbital launch vehicle. Variant of Titan with 15 foot Large Diameter Core, 4 x 7 segment strap-ons. Man rated, optimized for delivery of 40,000 pound manned payloads into 250 nm / 50 deg space station orbit. 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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