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IIIA: 8,686 kg (19,149 lb) IIIB: 10,759 kg (23,720 lb) Payload to Geostationary transfer orbit; Mass: IIIA: 4,060 kg (8,950 lb) IIIB: 4,500 kg (9,900 lb) Payload to 185 km 90° Polar orbit; Mass: IIIA: 7,162 kg (15,790 lb) IIIB: 9,212 kg (20,309 lb) Associated rockets; Family: Atlas: Launch history; Status: Retired: Launch sites
May 24, 2000 · 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.
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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)
Status: Retired 2005. Thrust: 4,148.72 kN (932,670 lbf). Gross mass: 195,628 kg (431,285 lb). Unfuelled mass: 13,725 kg (30,258 lb). Specific impulse: 337 s. Specific impulse sea level: 311 s. Burn time: 132 s. Height: 29.00 m (95.00 ft). Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft).
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Stage Data - Atlas IIIA. Stage 1. 1 x Atlas IIIA. Gross Mass: 195,628 kg (431,285 lb). Empty Mass: 13,725 kg (30,258 lb). Thrust (vac): 4,148.722 kN (932,670 lbf). Isp: 337 sec. Burn time: 132 sec. Isp(sl): 311 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 29.00 m (95.00 ft). Propellants: Lox/Kerosene. No Engines: 1.
The Atlas III was produced in two versions. The baseline was the Atlas IIIA, but the Atlas IIIB, featuring a twin-engine version of the Centaur upper stage, was also produced. [1] Launches . The maiden flight of the Atlas III occurred on May 24, 2000, launching the Eutelsat W4 communications satellite into a geosynchronous orbit.
