Engineering:RS-2200
From HandWiki
| Country of origin | United States |
|---|---|
| Date | 1990's |
| Designer | Rocketdyne |
| Application | X-33 |
| Associated L/V | XRS-2200 |
| Status | Development Canceled |
| Liquid-fuel engine | |
| Propellant | LOX / LH2 |
| Configuration | |
| Nozzle ratio | 173:1 |
| Performance | |
| Thrust (vac.) | 2,201 kN (495,000 lbf) |
| Thrust (SL) | 1,917 kN (431,000 lbf) |
| Thrust-to-weight ratio | 83:1 |
| Chamber pressure | 155 bar (2,250 psi) |
| Isp (vac.) | 455 seconds |
| Isp (SL) | 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". NASA Headquarters. https://www.hq.nasa.gov/office/pao/History/x-33/rs2200.htm.
- ↑ "RS-2200". Encyclopedia Astronautica. http://www.astronautix.com/r/rs-2200.html.
- ↑ 3.0 3.1 "Are Aerospike Engines Better Than Traditional Rocket Engines?" (in en-US). 2019-10-18. https://everydayastronaut.com/aerospikes/.
- ↑ "XRS-2200/RS-2200 Linear Aerospike Engine Data Sheets". http://heroicrelics.org/info/aerospikes/xrs-rs-2200.html.
- ↑ "RS-2200 Linear Aerospike Engine". 1999-11-28. http://boeing.com:80/space/rdyne/x33/rlv/rs2200/rs2200.htm.
This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.
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