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RL-10

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RL-10 Credit: Lockheed Martin

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.

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-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.