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RS-2200

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RS-2200
Linear aerospike test firing
Country of originUnited States
Date1990's
DesignerRocketdyne
ApplicationX-33
Associated LVXRS-2200
StatusDevelopment Canceled
Liquid-fuel engine
PropellantLOX / LH2
Configuration
Nozzle ratio173:1
Performance
Thrust, vacuum2,201 kN (495,000 lbf)
Thrust, sea-level1,917 kN (431,000 lbf)
Thrust-to-weight ratio83:1
Chamber pressure155 bar (2,250 psi)
Specific impulse, vacuum455 seconds
Specific impulse, sea-level347 seconds
Dimensions
MeasurementForward End: 6.4 m (250 in) wide, 2.4 m (94 in) long

Aft End: 2.4 m (94 in) wide, 2.4 m (94 in) long

Forward to Aft: 4.3 m (170 in)

The Rocketdyne RS-2200 was an experimental linear aerospike rocket engine developed by Rocketdyne for Lockheed Martin's VentureStar program.[1][2] The program was ultimately cancelled in 2001 before any RS-2200 engines were assembled. [3][4][5]

XRS-2200

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The XRS-2200 was a subscale testbed engine that was intended to be developed into the full-scale RS-2200. This engine, unlike its full-scale counterpart, made it to the test stand and accumulated approximately 1,600 seconds of hot-fire testing. [3]

References

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  1. ^ "RS2200 Link". www.hq.nasa.gov. NASA Headquarters. Archived from the original on 2016-03-22. Retrieved 2020-10-03.
  2. ^ "RS-2200". www.astronautix.com. Encyclopedia Astronautica. Archived from the original on 2020-02-18. Retrieved 2020-10-03.
  3. ^ a b "Are Aerospike Engines Better Than Traditional Rocket Engines?". Everyday Astronaut. 2019-10-18. Archived from the original on 2020-09-24. Retrieved 2020-10-02.
  4. ^ "XRS-2200/RS-2200 Linear Aerospike Engine Data Sheets". heroicrelics.org. Archived from the original on 2019-09-12. Retrieved 2020-10-02.
  5. ^ "RS-2200 Linear Aerospike Engine". 1999-11-28. Archived from the original on 1999-11-28. Retrieved 2020-10-02.

Public Domain This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.