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Atlas E

Background Information
First Launch:
October 1960
Flight Rate:
1-2 per year
Launch Site:
SLC-3W (VAFB, USA)
Capability:
1,750 lb to 100 NM polar orbit (no AKM)*

History

  • Program started 1945
  • First Atlas flight in December 1957
  • Derived from Atlas ICBM (D, E, and F)
  • Became the standardized U.S. Air Force launch vehicle in 1962
  • Progressed into Atlas-Centaur

Description

  • One and a half stage vehicle
  • Two boosters (stage 1/2) and one sustainer (stage 1)
  • Two Rocketdyne MA-3 booster engines burn LO2/RP-1, generating a total thrust of 330,000 lb
  • Rocketdyne MA sustainer engine burns LO2/RP-1, generating 60,000 lb of thrust

Profile

Length:
92.3 ft
Launch Weight:
269,000 lb
Diameter:
10 ft
Liftoff Thrust:
390,000 lb
Payload Fairing:
24 ft x 7 ft

Other Resources


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