This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
|J-2S - |
Credit: Boeing / Rocketdyne. 11,843 bytes. 157 x 237 pixels.
Manufacturer Name: J-2S. Designer: Rocketdyne. Developed in: 1967. Application: . Propellants: Lox/LH2 Thrust(vac): 121,066 kgf. Thrust(vac): 1,187.00 kN. Isp: 426 sec. Isp (sea level): 200 sec. Burn time: 475 sec. Mass Engine: 1,400 kg. Diameter: 2.0 m. Length: 3.4 m. Chambers: 1. Chamber Pressure: 30.00 bar. Area Ratio: 28.00. Thrust to Weight Ratio: 73.18. Country: USA. Status: Developed 1965-1969.
J-2 version proposed for Saturn follow-on vehicles, using results of J-2X technology program. Simplified, improved performance. J-2S provided the basis for X-33 linear aerospike engine thirty years later. Designed for booster applications. Tap-off, pump-fed. J-2X developed most of the simplification features of the J-2S between 1964 and 1967.
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 .