 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]
- ^ "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.
- ^ "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.