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Atlas III. The Atlas III (known as the Atlas II-AR (R for Russian) early in development [3]) was an American orbital launch vehicle, used in the years between 2000 and 2005. [4] It was developed from the highly successful Atlas II rocket and shared many components. [1] It was the first member of the Atlas family since the Atlas A to feature a ...
May 24, 2000 · ATLAS IIIA-CENTAUR FACT SHEET. By Cliff Lethbridge. Atlas IIIA-Centaur Launch, Photo Courtesy Lockheed-Martin. Classification: Space Launch Vehicle. Length: 170 feet, 2 inches. Diameter: 10 feet. Date of First Cape Canaveral Launch: May 24, 2000. Date of Final Cape Canaveral Launch: March 13, 2004. Number of Cape Canaveral Launches: 2.
Atlas IIIA: 2000: 2004: 2: 2: 1xRD-180: 1xRL10A: Eutelsat W4: Major revision of Atlas IIA, with new RD-180 first-stage engine, normal staging, first stage stretched 4.4 m and strengthened. First single RL10 engine Centaur. Atlas IIIB: 2002: 2005: 4: 4: 1xRD-180: 1xRL10A: Same as Atlas IIIA, except for Centaur stretched 1.7 m and an optional ...
- December 17, 1957; 65 years ago
- 1957–2010s (decade)
The single-stage Atlas IIIA booster uses a high-performance RD-180 propulsion system produced by a U.S./Russian joint venture (RD AMROSS) comprised of Pratt & Whitney (U.S.) and NPO Energomash (Russia). The RD-180 burns liquid oxygen and RP-1 propellant and develops a lift-off (sea-level) thrust of 2.6 MN. The RD-180 throttles to various levels ...
Atlas III. The Atlas III (known as the Atlas II-AR (R for Russian) early in development) was an American orbital launch vehicle, used in the years between 2000 and 2005. It was the first member of the Atlas family since the Atlas A to feature a "normal" staging method, compared to the previous Atlas family members, which were equipped with two ...
The single-stage Atlas IIIA booster uses a high-performance RD-180 propulsion system produced by a U.S./Russian joint venture (RD AMROSS) comprised of Pratt & Whitney (U.S.) and NPO Energomash (Russia). The RD-180 burns liquid oxygen and RP-1 propellant and develops a lift-off (sea-level) thrust of 2.6 MN.
