RL-10A-3A RL-10 Credit - Lockheed Martin Designer: Pratt and Whitney. Propellants: Lox/LH2. Thrust(vac): 73.400 kN (16,501 lbf). Isp: 444 sec. Burn time: 550 sec. Mass Engine: 141 kg (310 lb). Diameter: 1.01 m (3.31 ft). Length: 1.78 m (5.83 ft). Chambers: 1. Chamber Pressure: 32.31 bar. Area Ratio: 61.00. Oxidizer to Fuel Ratio: 5.00. Thrust to Weight Ratio: 53.24. Country: USA. First Flight: 1984. Last Flight: 2005. Flown: 134. RL-10A-3A used on Rocket Stages Used on stage: Centaur G. on launch vehicle: Titan 4. Used on stage: Centaur G. on launch vehicle: Titan 4B. Used on stage: Centaur G Prime. Used on stage: Centaur G STS. Used on stage: Centaur I. on launch vehicle: Atlas G. Used on stage: Centaur I. on launch vehicle: Atlas I. Used on stage: Centaur II. on launch vehicle: Atlas II. RL-10A-3A used on Spacecraft Used on: Centaur G. Used on: Centaur G Prime. Used on: Centaur I. Used on: Centaur II. 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