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The RS-68 (Rocket System-68) was a liquid-fuel rocket engine that used liquid hydrogen (LH2) and liquid oxygen (LOX) as propellants in a gas-generator cycle. It was the largest hydrogen-fueled rocket engine ever flown.
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| Subject | Predicate | Object | Confidence | Src |
|---|---|---|---|---|
| RS-68 | Application | First stage engine | 1.00 | infobox |
| RS-68 | Associated LV | Delta IV · Delta IV Heavy | 1.00 | infobox |
| RS-68 | Chamber pressure | 1,488 psi (10.26 MPa) | 1.00 | infobox |
| RS-68 | Country of origin | United States | 1.00 | infobox |
| RS-68 | Cycle | Gas-generator | 1.00 | infobox |
| RS-68 | Designer | Rocketdyne | 1.00 | infobox |
| RS-68 | Diameter | 2.43 m (8 ft 0 in) | 1.00 | infobox |
| RS-68 | Dry mass | RS-68: 6,600 kg (14,560 lb) RS-68A: 6,740 kg (14,870 lb) | 1.00 | infobox |
| RS-68 | First flight | 20 November 2002 (2002-11-20) | 1.00 | infobox |
| RS-68 | Last flight | 9 April 2024 (2024-04-09) | 1.00 | infobox |
| RS-68 | Length | 5.20 m (17.1 ft) | 1.00 | infobox |
| RS-68 | Manufacturer | Rocketdyne (2002–2005) | 1.00 | infobox |
| RS-68 | Manufacturer | Pratt & Whitney Rocketdyne (2005–2013) | 1.00 | infobox |
| RS-68 | Manufacturer | Aerojet Rocketdyne (2013–2024) | 1.00 | infobox |
| RS-68 | Nozzle ratio | 21.5:1 | 1.00 | infobox |
| RS-68 | Propellant | LOX / .mw-parser-output .template-chem2-su{display:inline-block;font-size:80%;line-height:1;vertical-align:-0.35em}.mw-parser-output .template-chem2-su>span{display:block;text-a… | 1.00 | infobox |
| RS-68 | Specific impulse, vacuum | RS-68: 410 s (4.0 km/s) RS-68A: 411.9 s (4.039 km/s) | 1.00 | infobox |
| RS-68 | Status | Retired | 1.00 | infobox |
| RS-68 | Thrust, sea-level | RS-68: 2,950 kN (660,000 lbf) RS-68A: 3,137 kN (705,000 lbf) | 1.00 | infobox |
| RS-68 | Thrust-to-weight ratio | RS-68: 45.3:1 RS-68A: 47.4:1 | 1.00 | infobox |
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