This page no longer updated from 31 October 2001. Latest version can be found at Centaur V1

Gross Mass: 22,825 kg. Empty Mass: 2,026 kg. Thrust (vac): 10,115 kgf. Isp: 451 sec. Burn time: 894 sec. Propellants: Lox/LH2 Diameter: 3.0 m. Span: 3.0 m. Length: 12.7 m. Country: USA. No Engines: 1. RL-10A-4-2 Status: Development.

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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Last update 12 March 2001.
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© Mark Wade, 2001 .