N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 37,560/2,900 kg. Thrust 460.31 kN. Vacuum specific impulse 316 seconds.
Cost $ : 4.640 million.
Status: Study 1965.
More... - Chronology...
Gross mass: 37,560 kg (82,800 lb).
Unfuelled mass: 2,900 kg (6,300 lb).
Height: 8.60 m (28.20 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 460.31 kN (103,483 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 145 s.
Burn time: 230 s.
Number: 51 .
LR91-11 Aerojet N2O4/Aerozine-50 rocket engine. 467 kN. Out of production. Isp=316s. Second stage engine for Titan 3 and 4. First flight 1968. More...
Associated Launch Vehicles
Titan 3BAS2 American orbital launch vehicle. Configuration of Titan 3B proposed by Martin in mid-1960's. Titan 3B for deep space missions with Centaur upper stage, Algol strapons for liftoff thrust augmentation. Never flown. More...
Titan 3M American orbital launch vehicle. Man-rated launch vehicle designed for MOL and other missions of the 1970's. Malfunction Detection System initiated abort procedures during launch. Also suited for launch of 'bulbous and lifting body payloads'. 7 segment UA1207 motors developed but not used until Titan 4 in 1990's. Cancelled with MOL program in 1969. More...
Titan 3B American orbital launch vehicle. Titan core with Agena upper stage. Found to be more cost effective and higher performance than using Transtage. More...
Commercial Titan 3 American orbital launch vehicle. Commercial version of Titan 34D military booster. It differed in having a lengthened second stage and a 4 m diameter payload shroud to handle shuttle-class or Ariane-type dual payloads. 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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