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The Atlas II first stage was 3.05 m (10.0 ft) in diameter and 24.90 m (81.7 ft) long. The stage was powered by 3 RS-56 rocket engines (derived from the RS-27 main engine of the Delta II rocket) burning 156 t (344,000 lb) of RP-1 and liquid oxygen.
Atlas II: 1991: 1998: 10: 10: Atlas G derived: Centaur D1A derived: Eutelsat: Same as Atlas I except Atlas stretched 2.74 m, engines uprated, added hydrazine roll control, fixed foam insulation, deleted verniers, and Centaur stretched 0.9 m. Development done by General Dynamics (now part of Lockheed Martin). Atlas IIA: 1992: 2002: 23: 23: Atlas ...
Model NameFirst LaunchLast LaunchTotal Launches195919603Atlas LV-3A19601968491959196391964196851Atlas II. 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. The Vernier engines on the first stage of the Atlas I were replaced by a hydrazine fueled ...
Oct 24, 2019 · The idea and development of the Atlas rocket began in 1945 when the Armed Forces asked members of the aerospace field to develop concepts for long range missiles. The USAAF had plans to develop a missile capable of carrying a payload 5,000 miles from the point of launch.
Originally developed as the first U.S. ICBM weapons system, the Atlas program rapidly evolved into an extremely viable and successful family of space boosters which remain in use today. Atlas vehicle design can be traced back to the days following the conclusion of World War II.
The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels.
Dec 7, 1991 · The Atlas II-Centaur was developed in 1989 specifically to support the launches of U.S. Air Force Defense Support Communications Satellite (DSCS) payloads. The vehicle employed two Rocketdyne booster engines which provided a combined thrust of 408,000 pounds.
