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) |
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]
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]