Encyclopedia Astronautica
Titan 3A-1


N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 116,573/5,443 kg. Thrust 2,339.76 kN. Vacuum specific impulse 302 seconds.

Cost $ : 11.600 million. No Engines: 2.

Status: Study 1965.
Gross mass: 116,573 kg (256,999 lb).
Unfuelled mass: 5,443 kg (11,999 lb).
Height: 22.28 m (73.09 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 2,339.76 kN (525,999 lbf).
Specific impulse: 302 s.
Specific impulse sea level: 250 s.
Burn time: 147 s.
Number: 241 .

More... - Chronology...


Associated Countries
Associated Engines
  • LR87-11 Aerojet N2O4/Aerozine-50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the -9 model, first flown 1968. First flight 1964. 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 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 23B American orbital launch vehicle. Basic Titan 3A core, originally developed for Titan 3C, with Agena D upper stage replacing Transtage. New radio guidance system, 1.5 m diameter fairing atop Agena. Payload remained attached to the Agena. More...
  • Titan 3D American orbital launch vehicle. Titan 3C without transtage. More...
  • Titan 24B American orbital launch vehicle. Stretched first stage, originally developed for the cancelled MOL program, with Agena D upper stage. Radio guidance system, 1.5 m diameter fairing atop Agena. Payload remained attached to the Agena. 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...
  • 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...

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...

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