RL-10A-1 RL-10 Credit - Lockheed Martin Government Designation: LR-115. Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 66.700 kN (14,995 lbf). Isp: 425 sec. Isp (sea level): 10 sec. Burn time: 430 sec. Mass Engine: 131 kg (288 lb). Diameter: 1.53 m (5.00 ft). Chambers: 1. Chamber Pressure: 24.00 bar. Area Ratio: 47.00. Thrust to Weight Ratio: 51.94. Country: USA. First Flight: 1961. Last Flight: 1967. Flown: 44. RL-10A-1 used on Rocket Stages Used on stage: Centaur C. on launch vehicle: Atlas Centaur LV-3C. Used on stage: Centaur C. on launch vehicle: Juno V-B. Used on stage: Centaur C. on launch vehicle: Saturn A-1. Used on stage: Centaur C. on launch vehicle: Saturn A-2. Used on stage: Centaur C. on launch vehicle: Saturn B-1. Used on stage: Centaur C. on launch vehicle: Saturn C-2. Used on stage: Centaur C. on launch vehicle: Saturn I. RL-10A-1 used on Spacecraft Used on: Centaur C.                   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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