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Background Information
- First Launch:
- May 1992
- Flight Rate:
- 4-6 per year (Atlas)
- Launch Site:
- SLC-36A & SLC-36B (CCAS, USA)
- Capability:
- 16,050 lb to LEO; 6,970 lb to GTO
History
- Started in 1950s as Air Force ICBM
- Modified in 1960s for space launches
- Cryogenic Centaur upper stage first launched in 1962
- Atlas II is an uprated version of the Atlas I
- Atlas IIA uses upgraded Centaur with RL10A-4 engines
Description
- Two and a half stage vehicle
- Two Rocketdyne MA-5A booster engines burn LO2/RP-1 fed from stage 1 tanks, generating a total of 414,400 lb of thrust
- Stage 1 uses one Rocketdyne MA-5A sustainer engine that burns LO2/RP-1 propellant, generating 60,500 lb of thrust
- Stage 2 (Centaur) uses two Pratt & Whitney RL10A-4 engines that burn LH2/LO2, generating a total of 41,600 lb of thrust
Profile
- Length:
- 150 ft
- Launch Weight:
- 407,140 lb
- Diameter:
- 10 ft
- Liftoff Thrust:
- 474,500 lb
- Payload Fairing:
- 34 ft x 11 ft (14 ft diameter fairing available)
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