This page no longer updated from 31 October 2001.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

astronautix.com RS-2200

RS-2200 engine test
RS-2200 engine test -

Credit: Boeing. 26,324 bytes. 314 x 288 pixels.



Manufacturer Name: RS-2200. Designer: Rocketdyne. Developed in: 1998. Application: . Used on stages: Venturestar. Propellants: Lox/LH2 Thrust(vac): 224,540 kgf. Thrust(vac): 2,201.00 kN. Isp: 455 sec. Isp (sea level): 347 sec. Diameter: 6.4 m. Length: 4.3 m. Chambers: 1. Chamber Pressure: 153.00 bar. Area Ratio: 173.00. Oxidizer to Fuel Ratio: 6.00. Country: USA. Status: In Production.

The RS-2200 Linear Aerospike Engine is being developed for use on the Lockheed Martin Skunk Works’ Reusable Launch Vehicle, the production follow-on to the X-33. The Aerospike allows the smallest, lowest cost RLV to be developed because the engine fills the base, reducing base drag, and is integral to the vehicle, reducing installed weight when compared to a bell-shaped engine. The. Aerospike is the same as bell shaped rocket engines except that its nozzle is open to the atmosphere. The open plume compensates for decreasing atmospheric pressure as the vehicle ascends, keeping the engine’s performance very high along the entire trajectory. This altitude compensating feature allows a simple, low-risk gas generator cycle to be. used. Over $500 million were invested in Aerospike engines up to the contract award date of the X-33, and full size linear engines have accumulated 73 tests and over 4,000 seconds of operation. Throttling, Percent Thrust: 20-109. Dimensions: Forward End: 6.4 m wide X 2.36 m long. Aft End: 2.36 m wide X 2.36 m long. Length: 4.32 m. 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 .