RL-10A-3A

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RL-10A-3A

Part of RL-10

RL-10
Credit: Lockheed Martin

Pratt and Whitney LOx/LH2 rocket engine. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984.

Number: 134 . Thrust: 73.40 kN (16,501 lbf). Unfuelled mass: 141 kg (310 lb). Specific impulse: 444 s. Burn time: 550 s. Height: 1.78 m (5.83 ft). Diameter: 1.01 m (3.31 ft).

Engine: 141 kg (310 lb). Chamber Pressure: 32.31 bar. Area Ratio: 61. Thrust to Weight Ratio: 53.2400806451613. Oxidizer to Fuel Ratio: 5. Coefficient of Thrust vacuum: 1.67432171823688.

Country: USA. Spacecraft: Space Tug. Launch Vehicles: Atlas G Centaur, Titan 4, Atlas I, Atlas II. Propellants: Lox/LH2. Stages: Centaur G, Centaur I, Centaur II, Centaur G STS, Centaur G Prime. Agency: Pratt and Whitney.

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