Country of origin | United States |
---|---|
Manufacturer | Rocketdyne |
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
- ^ "Atlas IIA(S) Data Sheet". Space Launch Report. Retrieved 9 January 2016.
- ^ "RS-56-OSA". Astronautix. Archived from the original on 11 November 2017. Retrieved 8 January 2016.
- ^ "RS-56-OBA". Astronautix. Archived from the original on 11 November 2017. Retrieved 8 January 2016.