This page no longer updated from 31 October 2001. Latest version can be found at RL-10B-2

Rl10B2 -

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Designer: Pratt and Whitney. Used on stages: Delta 3 - 2, Delta 4 - 2. Used on launch vehicles: Delta 3 , Delta IV Large, Delta IV Medium, Delta IV Medium+ (4, 2), Delta IV Medium+ (5, 2), Delta IV Medium+ (5, 4). Propellants: Lox/LH2 Thrust(vac): 11,222 kgf. Thrust(vac): 110.00 kN. Isp: 462 sec. Burn time: 700 sec. Diameter: 2.1 m. Chambers: 1. Area Ratio: 250.00. Country: USA. Status: In Production. First Flight: 1998. Last Flight: 1999. Flown: 2.

The upgraded cryogenic second-stage Pratt & Whitney RL10B-2 engine is based on the 30-year heritage of the reliable RL10 engine. It incorporates an extendable exit cone for increased specific impulse (Isp) and payload capability. The basic engine and turbo pump are unchanged relative to the RL10. The engine gimbal system uses electromechanical actuators that increase reliability while reducing both cost and weight. The propulsion system and attitude control system (ACS) utilize flight-proven off-the-shelf components. The second-stage propulsion system produces a thrust of 24,750 lb with a total propellant load of 37,090 lb, providing a total burn time of approxi-mately 700 sec. Missions requiring more than one restart are accommodated by adding an extra helium bottle for the additional tank repressurization.

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Last update 12 March 2001.
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© Mark Wade, 2001 .