Encyclopedia Astronautica
Titan 2-2

N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 28,939/2,404 kg. Thrust 444.82 kN. Vacuum specific impulse 316 seconds.

Cost $ : 4.640 million.

Status: Study 1961.
Gross mass: 28,939 kg (63,799 lb).
Unfuelled mass: 2,404 kg (5,299 lb).
Height: 7.86 m (25.78 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 444.82 kN (99,999 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 160 s.
Burn time: 180 s.
Number: 302 .

More... - Chronology...

Associated Countries
Associated Engines
  • 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
  • Soltan American orbital launch vehicle. The progenitor of the Titan 3 was this design, which used two, 3 segment, 100 inch diameter solid rocket boosters. The 100 inch segmented boosters had already been ground-fired by Aerojet. However the final decision was to develop the more-capable Titan 3C with 5 segment, 120 inch diameter solid rocket boosters. More...
  • Titan 2 American intercontinental ballistic missile. ICBM, developed also as the launch vehicle for the manned Gemini spacecraft in the early 1960's. When the ICBM's were retired in the 1980's they were refurbished and a new series of launches began. More...
  • Titan II GLV American intercontinental ballistic orbital launch vehicle. Version for launch of Gemini manned spacecraft. Developed in parallel with ICBM version. Differed in having redundancy features in systems and MDS (Malfunction Detection System) installed. More...
  • Titan 2B American intercontinental ballistic orbital launch vehicle. Space launch version of Titan 2 ICBM, obtained through minimal modification of ICBM (new wiring and avionics only, and use of existing ICBM re-entry vehicle shroud). Proposed in the late 1980's but never developed. More...
  • Titan 2G American intercontinental ballistic orbital launch vehicle. Space launch version, obtained through minimal refurbishment of decommissioned ICBM's. 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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