RL-10A-3 RL-10 Credit - Lockheed Martin Government Designation: LR-119. Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 65.600 kN (14,747 lbf). Isp: 444 sec. Burn time: 470 sec. Mass Engine: 131 kg (288 lb). Diameter: 1.53 m (5.00 ft). Length: 2.49 m (8.16 ft). Chambers: 1. Chamber Pressure: 28.00 bar. Area Ratio: 57.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 51.07. Country: USA. Status: Study 1968. First Flight: 1967. Last Flight: 1983. Flown: 112. RL-10A-3 used on Rocket Stages Used on stage: Centaur D/E. on launch vehicle: Atlas Centaur SLV-3C. Used on stage: Centaur D/E. on launch vehicle: Atlas Centaur SLV-3D. Used on stage: Centaur D/E. on launch vehicle: Saturn IB-A. Used on stage: Centaur D/E. on launch vehicle: Saturn IB-CE. Used on stage: Centaur D/E. on launch vehicle: Saturn V-Centaur. Used on stage: Centaur D/E. on launch vehicle: Titan 3BAS2. Used on stage: Centaur D/E. on launch vehicle: Titan 3E. Used on stage: Centaur D/E. on launch vehicle: Titan 3L2. Used on stage: Centaur D/E. on launch vehicle: Titan 3L4. RL-10A-3 used on Spacecraft Used on: Centaur D/E. Bibliography and Further Reading Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...                   Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted.

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