Encyclopedia Astronautica
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.

First Flown: late 1968 Titan 3, 1989 Titan 4. Dry Mass: 589 kg. Length: 281 cm. Maximum Diameter: 163 cm (skirt outer diameter). Mounting: fixed, but turbine exhaust utilized for roll control. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 97 kg/sec. Fuel: Aerozine-50 at 54.7 kg/sec. Mixture Ratio: 1.86:1. Thrust: 467 kN vacuum. Isp: 316 sec vacuum. Expansion Ratio: 49.2:1. Combustion Chamber Pressure: 58.5 atm. Cooling Method: fuel regenerative thrust chamber, with separate ablative skirt. Burn Time: 247 secs.Used in Titan 4-2; Titan 3B-2; Titan 3A-2.

Thrust (sl): 232.700 kN (52,313 lbf). Thrust (sl): 23,725 kgf. Engine: 589 kg (1,298 lb). Chamber Pressure: 59.30 bar. Area Ratio: 49.2. Thrust to Weight Ratio: 80.8501649339037. Oxidizer to Fuel Ratio: 1.86. Coefficient of Thrust vacuum: 1.85833549524615. Coefficient of Thrust sea level: 1.01730985422051.

Status: Out of production.
Height: 2.81 m (9.21 ft).
Diameter: 1.63 m (5.34 ft).
Thrust: 467.00 kN (104,985 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 160 s.
Burn time: 247 s.
Number: 267 .

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Associated Countries
See also
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 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 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 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...
  • 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...
  • Titan 3D American orbital launch vehicle. Titan 3C without transtage. More...
  • Titan 3E American orbital launch vehicle. Titan 3D with Centaur D-1T upper stage. Used by NASA for deep space missions in 1970's. More...
  • Titan 34B American orbital launch vehicle. Stretched Titan core, originally developed for Titan 3M MOL, with Agena D upper stage. Guidance provided by the Agena upper stage. The Agena and its payload were completely enclosed in a 3.05 m diameter shroud. 'Ascent Agena' seperated after orbital insertion and did not remain attached to the payload. More...
  • Titan 34D American orbital launch vehicle. Stretched Titan core designed for use with 5 1/2 segment solid rocket motors. IUS (Interim/Inertial Upper Stage) solid upper stages, Transtage, or used without upper stages. More...
  • Titan 4 American orbital launch vehicle. Developed to handle military payloads designed for launch on Shuttle from Vandenberg before the USAF pulled out of the Shuttle program after the Challenger disaster. Further stretch of core from Titan 34, 7-segment solid rocket motors (developed for MOL but not used until 25 years later). Enlarged Centaur G used as upper stage (variant of stage designed for Shuttle but prohibited for flight safety reasons after Challenger). Completely revised electronics. All the changes resulted in major increase in cost of launch vehicle and launch operations. More...
  • Titan 4B American orbital launch vehicle. Titan 4 with Upgraded Solid Rocket Motors replacing UA1207. Developed to improve performance for certain missions, and reduce number of field joints in motor after Challenger and Titan 34D explosions involving segmented motors. More...

Associated Manufacturers and Agencies
  • Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. More...

Associated Propellants
  • 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...

Associated Stages
  • Titan 4-2 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 39,500/4,500 kg. Thrust 459.51 kN. Vacuum specific impulse 316 seconds. More...
  • Titan 3A-2 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 29,188/2,653 kg. Thrust 453.71 kN. Vacuum specific impulse 316 seconds. More...
  • Titan 3B-2 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 37,560/2,900 kg. Thrust 460.31 kN. Vacuum specific impulse 316 seconds. More...

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