RL-10A-4 RL-10 Credit - Lockheed Martin Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 92.500 kN (20,795 lbf). Isp: 449 sec. Burn time: 392 sec. Mass Engine: 168 kg (370 lb). Diameter: 1.17 m (3.83 ft). Length: 2.29 m (7.51 ft). Chambers: 1. Chamber Pressure: 39.12 bar. Area Ratio: 84.00. Oxidizer to Fuel Ratio: 5.50. Thrust to Weight Ratio: 36.17. Country: USA. Status: Out of production. First Flight: 1992. Last Flight: 2004. Flown: 106. RL-10A-4 used on Rocket Stages Used on stage: Centaur IIA. on launch vehicle: Atlas IIA. Used on stage: Centaur IIA. on launch vehicle: Atlas IIAS. RL-10A-4 used on Spacecraft Used on: Centaur IIA. Bibliography and Further Reading RL10 Derviative Options, Pratt and Whitney Fact Sheet, ca. 1995..                   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.

Encyclopedia Astronautica topic index 0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z Enter your search terms   Web www.astronautix.com Submit search form