RS-2200
Appearance
![]() Linear aerospike test firing | |
Country of origin | United States |
---|---|
Date | 1990's |
Designer | Rocketdyne |
Application | X-33 |
Associated LV | 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
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
- ^ "RS2200 Link". www.hq.nasa.gov. NASA Headquarters. Archived from the original on 2016-03-22. Retrieved 2020-10-03.
- ^ "RS-2200". www.astronautix.com. Encyclopedia Astronautica. Archived from the original on 2020-02-18. Retrieved 2020-10-03.
- ^ 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.
- ^ "XRS-2200/RS-2200 Linear Aerospike Engine Data Sheets". heroicrelics.org. Archived from the original on 2019-09-12. Retrieved 2020-10-02.
- ^ "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.