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Atlas I

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

Other Resources


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