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Titan III

Background Information
First Launch:
December 1989
Flight Rate:
2 -3 per year (Dependent on TIV ESMC demand)
Launch Sites:
SLC-40 & SLC-41 (CCAS, USA)
SLC-4E/4W (VAFB, USA)
Capability:
32,500 lb (single), 31,600 lb (dual) to LEO
11,000+ lb (dependent on spacecraft and PKM) to GTO

History

  • Marketing and engineering for commercial Titan began November 1982
  • Direct descendant of Titan 34D
  • Titan III has flown more than 200 payloads to orbit

Description

  • Two-stage storable liquid-propellant core with two strap-on solid rocket motors
  • Stage 1 burns N2O4/A-50 in two Aerojet engines generating 546,000 lb of total thrust
  • Stage 2 burns N2O4/A-50 in one Aerojet engine generating 104,000 lb of thrust
  • Booster stage uses two UTC-CSD solid rocket motors generating 2,792,000 lb of total thrust

Profile

Length:
155 ft
Launch Weight:
1.5M lb (Centaur)
Diameter:
10 ft (core)
Liftoff Thrust:
2,792,000 lb
Payload Fairing:
34.2 ft x 13.1 ft

Other Resources


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