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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). 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 during atmospheric ascent to effectively manage the air-loads experienced by the vehicle enabling minimum Atlas vehicle and launch site infrastructure changes. Additionally, throttling results in satellite experienced flight environments that are nearly identical to Atlas IIAS.
Cost $ : 50.000 million.
Country: USA. Engines: RD-180. Launch Vehicles: Timberwind Centaur, Atlas 3A, Atlas 3B DEC, Atlas 3B. Propellants: Lox/Kerosene. Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z � 1997-2017 Mark Wade - Contact � / Conditions for Use |
