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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
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