Rocketdyne XRS-2200

The Rocketdyne XRS-2200 was an experimental linear aerospike engine developed in the mid-1990s for the Lockheed Martin X-33 program.^[1][2][3] The XRS-2200 engine's powerpack (Turbomachinery and Gas Generator) was derived from the Rocketdyne J-2 engine, the upper stage engine of the Saturn V moon rocket developed under the Apollo Program in the 1960's. The XRS-2200 used the J-2's combustion cycle and propellant choice.^[4]

XRS-2200

Rocketdyne XRS-2200 hotfire test
Country of origin	United States
Date	1999
Designer	Rocketdyne
Manufacturer	Rocketdyne
Application	X-33
Predecessor	J-2
Status	Experimental
Liquid-fuel engine
Propellant	LOX / LH2
Cycle	Gas Generator
Configuration
Nozzle ratio	58:1
Performance
Thrust, vacuum	1,184 kN (266,000 lbf)
Thrust, sea-level	909 kN (204,000 lbf)
Chamber pressure	58 bar (840 psi)
Specific impulse, vacuum	439 seconds (4.31 km/s)
Specific impulse, sea-level	339 seconds (3.32 km/s)
Dimensions
Length	2.01 m (6 ft 7 in)

Rocketdyne intended to develop the subscale XRS-2200 into the RS-2200 for use on the VentureStar. While the X-33 program was cancelled, two XRS-2200 engines were produced and tested.^[5]