Number: 60 . Thrust: 66.70 kN (14,995 lbf). Unfuelled mass: 131 kg (288 lb). Specific impulse: 410 s. Specific impulse sea level: 10 s. Burn time: 482 s. Diameter: 0.92 m (3.00 ft).
Engine: 131 kg (288 lb). Chamber Pressure: 24.00 bar. Area Ratio: 40. Thrust to Weight Ratio: 45. Coefficient of Thrust vacuum: 1.76.
Subtopics RL-10A-1 Pratt and Whitney LOx/LH2 rocket engine. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961. RL-10A-3 Pratt and Whitney LOx/LH2 rocket engine. First flight 1967. RL-10A-3A Pratt and Whitney LOx/LH2 rocket engine. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984. RL-10A-4 Pratt and Whitney LOx/LH2 rocket engine. Out of production. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992. RL-10A-4-1 Pratt and Whitney LOx/LH2 rocket engine. Out of production. Used on Atlas IIIA launch vehicle. First flight 2000. Version with one of engines removed; remaining engine re-positioned to center-mount; new electro-mechanical gimbals. RL-10A-4-2 Pratt and Whitney LOx/LH2 rocket engine. In production. Used on Atlas IIIB launch vehicle. First flight 2002. Two engines; electro-mechanical thrust vector control actuators replaced earlier hydraulically actuated system. RL-10A-5 Pratt and Whitney LOx/LH2 rocket engine. Throttleable to 30% of thrust, sea level version of RL10. Four engines were built and were used on the DC-X and the upgraded DC-XA VTOVL SSTO launch vehicle demonstrators. First flight 1993. RL-10A-5KA Pratt and Whitney LOx/LH2 rocket engine. Kistler proposal. Design 1992. Throttleable to 30% of thrust, sea level version of RL10 with extendable nozzle for high altitude operation. RL-10B-2 Pratt and Whitney LOx/LH2 rocket engine. In production. Used on Delta 3 , Delta IV launch vehicles. First flight 1998. Extendable exit cone for increased specific impulse; electromechanical actuators replace hydraulic systems. RL-10B-X Pratt and Whitney LOx/LH2 rocket engine. Design concept 1994. RL-10C Pratt and Whitney LOx/LH2 rocket engine. In Production. Used in Delta 3 - 2. First flight 1998. RL-10C-X Pratt and Whitney LOx/LH2 rocket engine. Design concept 1994. Country: USA. Spacecraft: CEV SAIC. Launch Vehicles: Saturn C-2, Saturn B-1, Nova B, Nova A, Saturn C-3, Saturn I. Propellants: Lox/LH2. Stages: Saturn IV, Nova A-3, Nova B-3. Agency: Pratt and Whitney. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9RetroSearch is an open source project built by @garambo | Open a GitHub Issue
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