RS-56
| Country of origin | United States |
|---|---|
| First flight | 1991 |
| Manufacturer | Rocketdyne |
| Status | retired |
| Liquid-fuel engine | |
| Propellant | LOX / RP-1 |
| Cycle | Gas-generator cycle |
| Performance | |
| Thrust, sea-level | RS-56-OBA: 207,000 lbf (920.8 kN) RS-56-OSA: 60,500 lbf (269.0 kN) |
| Chamber pressure | 4.8 MPa (48 bar) |
| Specific impulse, vacuum | RS-56-OBA: 299 s (2.93 km/s) RS-56-OSA: 316 s (3.10 km/s) |
| Specific impulse, sea-level | RS-56-OBA: 263 s (2.58 km/s) RS-56-OSA: 220 s (2.2 km/s) |
| Burn time | RS-56-OBA: 172 RS-56-OSA: 283 sec |
| Dimensions | |
| Length | RS-56-OBA: 11.3 ft (3.43 m) 8.9 ft (2.7 m) |
| Diameter | RS-56-OBA: 8.0 ft (2.45 m) 10.0 ft (3.05 m) |
| Used in | |
| Atlas II | |
RS-56 was an American liquid-fueled rocket engine, developed by Rocketdyne. RS-56 was derived from the RS-27 rocket engine,[1] which itself is derived from the Rocketdyne H-1 rocket engine used in the Saturn I and Saturn IB. Two variants of this engine were built, both for use on the Atlas II rocket series. The first, RS-56-OBA, was a booster engine, while the RS-56-OSA was designed for use as a sustainer and produced lower thrust but at a higher specific impulse.[2][3]
References[edit]
- ^ "Atlas IIA(S) Data Sheet". Space Launch Report. Retrieved 9 January 2016.
- ^ "RS-56-OSA". Astronautix. Archived from the original on 9 February 2014. Retrieved 8 January 2016.
- ^ "RS-56-OBA". Astronautix. Archived from the original on 9 February 2014. Retrieved 8 January 2016.
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| Solid fuel |
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