Encyclopedia Astronautica
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.

Cost $ : 4.640 million.

Status: Retired 2005.
Gross mass: 39,500 kg (87,000 lb).
Unfuelled mass: 4,500 kg (9,900 lb).
Height: 9.94 m (32.61 ft).
Diameter: 3.05 m (10.00 ft).
Span: 3.05 m (10.00 ft).
Thrust: 459.51 kN (103,302 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 160 s.
Burn time: 223 s.
Number: 57 .

More... - Chronology...


Associated Countries
Associated Engines
  • 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 405A American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit SDS and NOSS-2 payloads from Cape Canaveral. More...
  • Titan 403A American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit Lacrosse, SDS and NOSS-2 payloads from Vandenberg. More...
  • Titan 404A American orbital launch vehicle. Version of Titan 4 with no upper stage, configured for launch of heavy-weight, low altitude KH-12 and Improved CRYSTAL payloads from Vandenberg. More...
  • Titan 404B American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. More...
  • Titan 403B American orbital launch vehicle. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. 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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