Encyclopedia Astronautica
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.

LEO Payload: 13,100 kg (28,800 lb) to a 185 km orbit. Payload: 3,000 kg (6,600 lb) to a GTO.

AKA: SLV-5C.
Status: Out of production.
Gross mass: 626,190 kg (1,380,510 lb).
Payload: 13,100 kg (28,800 lb).
Height: 42.00 m (137.00 ft).
Diameter: 3.05 m (10.00 ft).
Thrust: 10,586.80 kN (2,380,007 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
See also
  • 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...

Associated Stages
  • 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. 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 Transtage N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 12,247/1,950 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds. More...
  • Titan UA1205 Solid propellant rocket stage. Loaded/empty mass 226,233/33,798 kg. Thrust 5,849.41 kN. Vacuum specific impulse 263 seconds. More...

Home - Browse - Contact
© / Conditions for Use