Rocketdyne XRS-2200

Summary

XRS-2200
Twin Linear Aerospike XRS-2200 Engine PLW edit.jpg
Rocketdyne XRS-2200 hotfire test
Country of originUnited States
Date1999
DesignerRocketdyne
ManufacturerRocketdyne
ApplicationX-33
PredecessorJ-2S
StatusExperimental
Liquid-fuel engine
PropellantLOX / LH2
CycleGas Generator
Configuration
Nozzle ratio58
Performance
Thrust (vacuum)1,184 kN (266,000 lbf)
Thrust (sea-level)909 kN (204,000 lbf)
Chamber pressure5.8 MPa (58 bar)
Specific impulse (vacuum)439 seconds (4.31 km/s)
Specific impulse (sea-level)339 seconds (3.32 km/s)
Dimensions
Length2.01 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 design was based on the J-2S linear aerospike engine developed in the 1960s and therefore 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]

References

  1. ^ "Boeing Rocketdyne XRS-2200 Linear Aerospike". engineering.purdue.edu. Retrieved 2019-08-26.
  2. ^ "XRS-2200 Link". www.hq.nasa.gov. Washington D.C., U.S.A.: NASA Headquarters. Retrieved 2019-09-29.
  3. ^ Rowbotham, Maureen. "XRS-2200 linear aerospike engine - Use of Pro/ENGINEER for determining mass properties". U.S.: American Institute of Aeronautics and Astronautics. doi:10.2514/6.1999-2334. Retrieved 2019-09-29.
  4. ^ "XRS-2200". www.astronautix.com. Encyclopedia Astronautica. Retrieved 2019-08-26.
  5. ^ D'Agostino, M.G. "X-33 XRS-2200 Linear Aerospike Engine Sea Level Plume Radiation" (PDF). NASA Technical Reports Server.