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Atlas II

Background Information
First Launch:
December 1991
Flight Rate:
4-6 per year (Atlas)
Launch Site:
SLC-36A & SLC-36B (CCAS, USA)
Capability:
14,950 lb to LEO; 6,500 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

Description

  • Two and a half stage vehicle
  • Two Rocketdyne MA-5A booster engines burn LO2/RP-1 propellant 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, generating 59,000 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:
150 ft
Launch Weight:
412,600 lb
Diameter:
10 ft
Liftoff Thrust:
473,400 lb
Payload Fairing:
34 ft x 11 ft (14 ft diameter fairing available)

Other Resources


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