XRS-2200

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XRS-2200

Part of J-2

XRS-2200
Credit: Boeing / Rocketdyne

Rocketdyne LOx/LH2 rocket engine. Development ended 1999. Linear aerospike engine for X-33 SSTO technology demonstrator. Based on J-2S engine developed for improved Saturn launch vehicles in the 1960's.

AKA: J-2S Linear Aerospike;RS-69. Status: Development ended 1999. Date: 1998. Thrust: 1,192.00 kN (267,972 lbf). Specific impulse: 439 s. Specific impulse sea level: 339 s. Height: 2.01 m (6.59 ft). Diameter: 3.38 m (11.08 ft).

Gas generator cycle; throttling 40% to 119% of nominal thrust; differential thrust between two engines plus-minus 15%. X-33 Advanced Technology Demonstrator Development. Designed for booster applications. Gas generator, pump-fed.

Chamber Pressure: 58.00 bar. Area Ratio: 58. Oxidizer to Fuel Ratio: 5.5.

Country: USA. Engines: XRS-2200. Launch Vehicles: X-33. Propellants: Lox/LH2. Agency: Rocketdyne.

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