RS-27
| Country of origin | United States |
|---|---|
| Date | 1974 |
| Designer | Rocketdyne |
| Manufacturer | Rocketdyne |
| Application | Booster |
| Predecessor | H-1 |
| Successor | RS-27A, RS-56 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust (vac.) | 1,023 kN (230,000 lbf) |
| Thrust (SL) | 971 kN (218,000 lbf) |
| Chamber pressure | 4.9 MPa (49 bar) |
| Isp (vac.) | 295 seconds (2.89 km/s) |
| Isp (SL) | 264 seconds (2.59 km/s) |
| Burn time | 274 Sec |
| Dimensions | |
| Length | 3.63 m (11.9 ft) |
| Diameter | 1.07 m (3.51 ft) |
| Dry weight | 1,027 kg (2,264 lb) |
| Used in | |
| Delta 2000, 3000, 5000, 6000, first stage[1] | |
The RS-27 is a liquid-propellant rocket engine developed by Rocketdyne. It was used to power the first stage of the Delta 2000, 3000, 5000, and the first model of the Delta II, the Delta 6000.
The RS-27 was a modified Rocketdyne H-1 from surplus engines built to power the first stage of the Saturn I and Saturn IB and replaced the MB-3 engine that had been used on previous versions of the Delta launcher.[2][3] In addition to its main engine, the RS-27 included two vernier engines to provide vehicle roll control during flight.. RS-27 was later developed into the RS-27A, and RS-56.[4][5]
References
- ↑ "Delta". Astronautix. Retrieved March 2015. Check date values in:
|access-date=(help) - ↑ "RS-27". Astronautix. Retrieved March 2015. Check date values in:
|access-date=(help) - ↑ "Extended Long Tank Delta". SpaceLaunchReport.com. Retrieved March 2015. Check date values in:
|access-date=(help) - ↑ "Atlas IIA(S) Data Sheet". Space Launch Report. Retrieved 9 January 2016.
- ↑ "RS-27A". Astronautix. Retrieved 10 January 2016.
This article is issued from Wikipedia - version of the 9/28/2016. The text is available under the Creative Commons Attribution/Share Alike but additional terms may apply for the media files.