RS-27A
Gas Generator | |
| Configuration | |
|---|---|
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 1,054.2 kN |
| Thrust, sea-level | 890.1 kN (200,102 lbf) |
| Thrust-to-weight ratio | 102.47 |
| Chamber pressure | 4.8MPa (700 psia) |
| Specific impulse, vacuum | 302 seconds (2.96 km/s) |
| Specific impulse, sea-level | 255 seconds (2.50 km/s) |
| Burn time | 265 Sec |
| Dimensions | |
| Length | 3.78 m (12.40 ft) |
| Diameter | 1.70 m (5.58 ft) |
| Dry weight | 1,147 kg (2,528 lb) |
| Used in | |
| Delta 7000, first stage[1] | |
The RS-27A is a
its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude.The RS-27A main engine is neither restartable nor
throttleable. In addition to its main engine, it includes two vernier engines to provide vehicle roll control during flight.[3]
When used as the main booster propulsion system for the Delta II family of launch vehicles, has an operational duration of 265 seconds.
The last RS-27A engine was used for the ICESat-2 launch on 15 September, 2018.
References
- ^ Astronautix: RS-27A Engine
- ^ Astronautix: RS-27 Engine
- ^ "RS-27A Engine". purdue.edu. Retrieved May 7, 2023.
External links
- Aerojet Rocketdyne RS-27A Product Page
- Pratt and Whitney RS-27A Brochure Archived 2022-05-31 at the Wayback Machine
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