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Gross Mass: 22,825 kg (50,320 lb). Empty Mass: 2,026 kg (4,466 lb). Thrust (vac): 99.194 kN (22,300 lbf). Isp: 451 sec. Burn time: 894 sec. Propellants: Lox/LH2. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 12.68 m (41.60 ft). Country: USA. No Engines: 1. Engine: RL-10A-4-2. Status: In production. First Flight: 2002. Last Flight: 2006. No Launched: 8. Centaur is powered by either one or two Pratt & Whitney RL10A-4-2 turbopump-fed engines burning liquid oxygen and liquid hydrogen. For typical, high-energy mission applications, Centaur will be configured with one RL10 engine. For heavy payload, low earth orbit missions, Centaur will use two RL10 engines to maximize boost phase mission performance. Guidance, tank pressurization, and propellant usage controls for both Atlas and Centaur phases are provided by the inertial navigation unit (INU) located on the Centaur forward equipment module.
Used on Launch Vehicles:
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