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astronautix.com J-2S

J-2S
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.


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