 |
Background Information
- First Launch:
- July 1990
- Flight Rate:
- 4-6 per year
- Launch Site:
- SLC-36B (CCAS)
- Capability:
- 13,000 lb to LEO; 5,240 lb to GTO
History
- Started in 1950s as Air Force ICBM
- Modified in 1960s for space launch
- Cryogenic Centaur upper stage first launched in 1962
- Atlas I is Atlas G/Centaur with an expanded metal payload fairing
Description
- Two and a half stage vehicle
- Two Rocketdyne MA-5 booster engines burn LO2/RP-1 fed from stage 1 tanks, generating a total of 377,500 lb of thrust
- Stage 1 uses one Rocketdyne MA-5 sustainer engine that burns LO2/RP-1, generating 59,000 lb of thrust; two verniers provide an additional 1,300 lb of thrust
- Stage 2 (Centaur) uses two Pratt & Whitney RL10A-3-3A engines that burn LH2/LO2, generating a total of 33,000 lb of thrust
Profile
- Length:
- 138 ft
- Launch Weight:
- 361,300 lb
- Diameter:
- 10 ft
- Liftoff Thrust:
- 437,800 lb
- Payload Fairing:
- 34 ft x 11 ft
|