N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 50,000/3,000 kg. Thrust 444.82 kN. Vacuum specific impulse 316 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated.
Cost $ : 4.640 million.
Status: Study 1965.
More... - Chronology...
Gross mass: 50,000 kg (110,000 lb).
Unfuelled mass: 3,000 kg (6,600 lb).
Height: 13.40 m (43.90 ft).
Diameter: 4.57 m (14.99 ft).
Span: 4.57 m (14.99 ft).
Thrust: 444.82 kN (99,999 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 160 s.
Burn time: 320 s.
LR91-7 Aerojet N2O4/Aerozine-50 rocket engine. 444.8 kN. Study 1961. Version used on Stage 2 of Gemini Titan 2 Launch Vehicle. Isp=316s. 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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