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.
LEO Payload: 3,175 kg (6,999 lb) to a 185 km orbit at 28.60 degrees.
Gross mass: 154,000 kg (339,000 lb).
More... - Chronology...
Payload: 3,175 kg (6,999 lb).
Height: 31.40 m (103.00 ft).
Diameter: 3.05 m (10.00 ft).
Thrust: 2,090.00 kN (469,850 lbf).
Apogee: 185 km (114 mi).
Titan The Titan launch vehicle family was developed by the United States Air Force to meet its medium lift requirements in the 1960's. The designs finally put into production were derived from the Titan II ICBM. Titan outlived the competing NASA Saturn I launch vehicle and the Space Shuttle for military launches. It was finally replaced by the USAF's EELV boosters, the Atlas V and Delta IV. Although conceived as a low-cost, quick-reaction system, Titan was not successful as a commercial launch vehicle. Air Force requirements growth over the years drove its costs up - the Ariane using similar technology provided lower-cost access to space. More...
Associated Manufacturers and Agencies
Martin American manufacturer of rockets, spacecraft, and rocket engines. Martin Marietta Astronautics Group (1956), Denver, CO, USA. More...
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. More...
Titan 2-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 117,866/6,736 kg. Thrust 2,172.23 kN. Vacuum specific impulse 296 seconds. More...
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