Rocketdyne XRS-2200
Aerospike rocket engine by Rocketdyne From Wikipedia, the free encyclopedia
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 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]
References
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