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Gross Mass: 23,050 kg (50,810 lb). Empty Mass: 2,250 kg (4,960 lb). Thrust (vac): 198.398 kN (44,602 lbf). Isp: 451 sec. Burn time: 435 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: 2. Engine: RL-10A-4-2. Status: In production. First Flight: 2001. 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.
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