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Atlas IIA

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)

Other Resources


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