page_title: Atlas II
section_title: Specifications
hierarchical_section_title: Atlas II / Specifications
context_page_description: Atlas II was a member of the Atlas family of launch vehicles, which evolved from the successful Atlas missile program of the 1950s. It was designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. Sixty-three launches of the Atlas II, IIA and IIAS models were carried out between 1991 and 2004; all sixty-three launches were successes, making the Atlas II the most reliable launch system in history. The Atlas line was continued by the Atlas III, used between 2000 and 2005, and the Atlas V which is still in use.
context_section_description: General Characteristics
  Primary function: Launch vehicle
  Primary contractor: Lockheed Martin – airframe, assembly, avionics, test and systems integration
  Principal subcontractors: Rocketdyne (Atlas engine, MA-5); Pratt & Whitney (Centaur engine, RL-10) and Honeywell & Teledyne (avionics)
  Power Plant: Three MA-5A (RS-56) Rocketdyne engines, two Pratt & Whitney RL10A-4 Centaur engines
  Thrust: 494,500 lbf (2,200 kN)
  Length: Up to 156 ft (47.54 m); 16 ft (4.87 m) high engine cluster
  Core Diameter: 10 feet (3.04 m)
  Gross Liftoff Weight: 414,000 lb (204,300 kg)
  First Launch: February 10, 1992
  Models: II, IIA, and IIAS
  Launch Site: Cape Canaveral AFS, Florida
caption: Atlas launch vehicle evolution. (USAF)
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