RS-2200

Linear aerospike test firing

Country of origin| United States
Date| 1990's
Designer| Rocketdyne
Application| VentureStar
Predecessor| XRS-2200
Status| Development Canceled
Liquid-fuel engine
Propellant| LOX / LH2
Configuration
Nozzle ratio| 173:1
Performance
Thrust, vacuum| 2,201 kN (495,000 lbf)
Thrust, sea-level| 1,917 kN (431,000 lbf)
Thrust-to-weight ratio| 83:1
Chamber pressure| 155 bar (2,250 psi)
Specific impulse, vacuum| 455 seconds
Specific impulse, sea-level| 347 seconds
Dimensions
Measurement| Forward 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

[edit]

Main article: Rocketdyne XRS-2200

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

## References

[edit]

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.

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