RL-10A-4-2

RL-10
Credit - Lockheed Martin

Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 99.100 kN (22,279 lbf). Isp: 451 sec. Burn time: 740 sec. Mass Engine: 167 kg (368 lb). Diameter: 1.53 m (5.00 ft). Chambers: 1. Chamber Pressure: 39.00 bar. Area Ratio: 84.00. Thrust to Weight Ratio: 60.53. Country: USA. Status: In production. First Flight: 2002. Last Flight: 2006. Flown: 16.

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.

RL-10A-4-2 used on Rocket Stages

Used on stage: Centaur IIIB. on launch vehicle: Atlas IIIB.

Used on stage: Centaur V1. on launch vehicle: Atlas V.

Used on stage: Centaur V2.

RL-10A-4-2 used on Spacecraft

Used on: Centaur IIIB.

Used on: Centaur V1.

Used on: Centaur V2.

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© Mark Wade, 1997 - 2007 except where otherwise noted.

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