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Titan IV

Background Information
First Launch:
June 1989
Flight Rate:
3-4 per year
Launch Sites:
SLC-40 & SLC-41 (CCAS, USA)
SLC-4E (VAFB, USA)
Capability:
14,000 lb to GTO; 10,000 lb to GEO (with Centaur);
39,000 lb to LEO; 31,100 lb to polar LEO

History

  • USAF Titan ICBM program started in 1950s
  • Titan IV program started as Complementary Expendable Launch Vehicle (CELV)
  • Direct descendant of Titan 34D

Description

  • Three-stage vehicle
    • Stage 0: Two seven-segment solid rocket motors, generating 1,600,000 lb of thrust each
    • Stage 1: Two Aerojet LR-87 engines burn N2O4/A-50, generating 274,000 lb of thrust each
    • Stage 2: One Aerojet LR-91 engine burns N2O4/A-50, generating 105,000 lb of thrust
  • Titan IV available in three configurations
    • Centaur Upper Stage
    • Inertial Upper Stage (IUS)
    • No Upper Stage (NUS)

Profile

Length:
204 ft Launch Weight: 1,907,500 lb (Centaur)
Diameter:
10 ft Liftoff Thrust: 2,800,000 lb
Payload Fairing:
56, 66, 76, and 86 ft x 16 ft available

Other Resources


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