| RS-2200 | |
| Thrust(Vac): | 2201kN |
| Purpose: | X-33 |
| Dimensions: | Forward End: 6.4m (21feet) wide, 2.4m (07.9feet) longAft End: 2.4m (07.9feet) wide, 2.4m (07.9feet) longForward to Aft: 4.3m (14.1feet) |
| Status: | Development Canceled |
| Nozzle: | Linear Aerospike |
| Specific Impulse Vacuum: | 455 seconds |
| Specific Impulse Sea Level: | 347 seconds |
| Chamber Pressure: | 155bar |
| Thrust To Weight: | 83:1 |
| Thrust(Sl): | 1917kN |
| Country Of Origin: | United States |
| Nozzle Ratio: | 173:1 |
| Cycle: | Gas-generator |
| Mixture Ratio: | 6.0 (LOX:LH2) |
| Type: | Liquid |
| Oxidizer: | LOX |
| Fuel: | LH2 |
| Associated: | XRS-2200 |
| Designer: | Rocketdyne |
| Date: | 1990's |
| Caption: | Linear aerospike test firing |
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]
See main article: Rocketdyne 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.