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RS-56 (Rocket System-56) was an American liquid-fueled rocket engine, developed by Rocketdyne. RS-56 was derived from the RS-27 engine, which itself is derived from the H-1 engine used in the Saturn I and Saturn IB.
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engine two atlas first engines thrust rocket rocketdyne use stage jettisoned high efficiency seconds ii rs-56-oba rs-56-osa burn rs-27 ma-5a
| Subject | Predicate | Object | Confidence | Src |
|---|---|---|---|---|
| RS-56 | Burn time | RS-56-OBA: 172 RS-56-OSA: 283 sec | 1.00 | infobox |
| RS-56 | Chamber pressure | 4.8 MPa (48 bar) | 1.00 | infobox |
| RS-56 | Country of origin | United States | 1.00 | infobox |
| RS-56 | Cycle | Gas-generator | 1.00 | infobox |
| RS-56 | Diameter | RS-56-OBA: 8.0 ft (2.45 m) 10.0 ft (3.05 m) | 1.00 | infobox |
| RS-56 | First flight | 1991 | 1.00 | infobox |
| RS-56 | Length | RS-56-OBA: 11.3 ft (3.43 m) 8.9 ft (2.7 m) | 1.00 | infobox |
| RS-56 | Manufacturer | Rocketdyne | 1.00 | infobox |
| RS-56 | Predecessor | RS-27A | 1.00 | infobox |
| RS-56 | Propellant | LOX / RP-1 | 1.00 | infobox |
| RS-56 | Specific impulse, sea-level | RS-56-OBA: 263 s (2.58 km/s) RS-56-OSA: 220 s (2.2 km/s) | 1.00 | infobox |
| RS-56 | Specific impulse, vacuum | RS-56-OBA: 299 s (2.93 km/s) RS-56-OSA: 316 s (3.10 km/s) | 1.00 | infobox |
| RS-56 | Status | Retired | 1.00 | infobox |
| RS-56 | Thrust, sea-level | RS-56-OBA: 207,000 lbf (920.8 kN) RS-56-OSA: 60,500 lbf (269.0 kN) | 1.00 | infobox |
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