RS-56
American kerolox rocket engine
Country of origin | United States |
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First flight | 1991 |
Manufacturer | Rocketdyne |
Predecessor | RS-27A |
Status | Retired |
Liquid-fuel engine | |
Propellant | LOX / RP-1 |
Cycle | Gas-generator |
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 (Rocket System-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
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Rocket engines and solid motors for orbital launch vehicles
fuel
Cryogenic |
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Semi- cryogenic |
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Storable |
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Other |
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![](http://upload.wikimedia.org/wikipedia/commons/thumb/4/4d/RS-68_rocket_engine_test.jpg/120px-RS-68_rocket_engine_test.jpg)
fuel
- China
- Europe
- India
- Iran
- Salman
- Rafe
- Israel
- Japan
- USA
- * Different versions of the engine use different propellant combinations
- Engines in italics are under development