This page no longer updated from 31 October 2001. Latest version can be found at RL-10A-4-2

RL-10 -

Credit: Lockheed Martin. 11,834 bytes. 146 x 231 pixels.

Designer: Pratt and Whitney. Used on stages: Centaur IIIB. Used on launch vehicles: Atlas IIIB. Propellants: Lox/LH2 Thrust(vac): 10,110 kgf. Thrust(vac): 99.10 kN. Isp: 451 sec. Burn time: 740 sec. Mass Engine: 167 kg. Diameter: 1.5 m. Chambers: 1. Chamber Pressure: 39.00 bar. Area Ratio: 84.00. Country: USA. Status: In Production.

For Centaur IIIA, one of Centaur IIAS's two RL10A-4 engines is removed. The remaining engine is re-positioned to a center-mount, and electro-mechanical thrust vector control actuators replace the hydraulically actuated system previously in use. Guidance, tank pressurization, and propellant usage controls for both Atlas and Centaur phases are provided by the inertial navigation unit (INU) located on the forward equipment module. The first Centaur burn lasts about nine minutes after which the Centaur and its payload coast in a parking orbit. During the first burn, approximately ten seconds after ignition, the payload fairing is jettisoned. The second Centaur ignition occurs about 23 minutes into the flight, continues for about three minutes, and is followed several minutes later by the separation of the spacecraft from Centaur.

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