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astronautix.com XRS-2200
XRS-2200
XRS-2200 -

Credit: Boeing / Rocketdyne. 7,138 bytes. 166 x 139 pixels.

Manufacturer Name: RS-69. Other Designations: J-2S Linear Aerospike. Designer: Rocketdyne. Developed in: 1998. Application: . Used on stages: X-33. Used on launch vehicles: X-33. Propellants: Lox/LH2 Thrust(vac): 121,600 kgf. Thrust(vac): 1,192.00 kN. Isp: 439 sec. Isp (sea level): 339 sec. Diameter: 3.4 m. Length: 2.0 m. Chambers: 1. Chamber Pressure: 58.00 bar. Area Ratio: 58.00. Oxidizer to Fuel Ratio: 5.50. Country: USA. Status: In Production.

Linear aerospike engine for X-33 SSTO technology demonstrator. Based on J-2S engine developed for improved Saturn launch vehicles in the 1960's. 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.

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Last update 12 March 2001.
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