This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com

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.


Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .