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RS-68
RS-68 -

Credit: Boeing / Rocketdyne. 9,511 bytes. 154 x 232 pixels.

Manufacturer Name: RS-68. Designer: Rocketdyne. Developed in: 1998. Application: . Used on stages: Delta RS-68. Used on launch vehicles: Delta IV Large, Delta IV Medium, Delta IV Medium+ (4, 2), Delta IV Medium+ (5, 2), Delta IV Medium+ (5, 4), Delta IV Small. Propellants: Lox/LH2 Thrust(vac): 337,807 kgf. Thrust(vac): 3,312.00 kN. Isp: 420 sec. Isp (sea level): 365 sec. Mass Engine: 6,597 kg. Chambers: 1. Chamber Pressure: 95.92 bar. Area Ratio: 21.50. Country: USA. Status: In Production.

In the 1990's Rocketdyne was simultaneously developing the first two new large liquid-fueled rocket engines in the United States in more than 25 years. One of these - the RS-68 - would power the Delta IV evolved expendable launch vehicle (EELV) being developed by The Boeing Company. The bell nozzle RS-68 is a liquid hydrogen-liquid oxygen booster engine that develops 650,000 lb. of sea level thrust. The RS-68 utilizes a simplified design philosophy resulting in a drastic reduction in parts compared to current cryogenic engines. This design approach results in lower development and production costs. The engine can be throttled to 60% of full thrust level. Designed for booster applications. Gas generator, pump-fed.

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Last update 12 March 2001.
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