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The RD-180 (Russian: Ракетный Двигатель-180 (РД-180), romanized: Raketnyy Dvigatel-180, lit. 'Rocket Engine-180') is a rocket engine that was designed and built in Russia. It features a dual combustion chamber, dual-nozzle design and is fueled by a RP-1/LOX mixture. The RD-180 is derived from the RD-170 line of rocket engines, which were used in the…
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| Subject | Predicate | Object | Confidence | Src |
|---|---|---|---|---|
| RD-180 | Application | Booster | 1.00 | infobox |
| RD-180 | Burn time | 270 seconds | 1.00 | infobox |
| RD-180 | Chamber | 2 | 1.00 | infobox |
| RD-180 | Chamber pressure | 26.7 MPa (3,870 psi) | 1.00 | infobox |
| RD-180 | Country of origin | Russia | 1.00 | infobox |
| RD-180 | Cycle | Staged combustion | 1.00 | infobox |
| RD-180 | Designer | NPO Energomash | 1.00 | infobox |
| RD-180 | Diameter | 3.15 m (10.3 ft) | 1.00 | infobox |
| RD-180 | Dry mass | 5,480 kg (12,080 lb) | 1.00 | infobox |
| RD-180 | First flight | 24 May 2000 (2000-05-24) | 1.00 | infobox |
| RD-180 | Length | 3.56 m (11.7 ft) | 1.00 | infobox |
| RD-180 | Manufacturer | NPO Energomash | 1.00 | infobox |
| RD-180 | Mass flow | 1,250 kg/s (165,000 lb/min) | 1.00 | infobox |
| RD-180 | Mixture ratio | 2.72 (73% O 2, 27% RP-1) | 1.00 | infobox |
| RD-180 | Nozzle ratio | 36.87 | 1.00 | infobox |
| RD-180 | Predecessor | RD-170 | 1.00 | infobox |
| RD-180 | Propellant | LOX / RP-1 | 1.00 | infobox |
| RD-180 | Specific impulse, sea-level | 311 s (3.05 km/s) | 1.00 | infobox |
| RD-180 | Specific impulse, vacuum | 338 s (3.31 km/s) | 1.00 | infobox |
| RD-180 | Status | Active | 1.00 | infobox |
| RD-180 | Throttle range | 47–100% | 1.00 | infobox |
| RD-180 | Thrust, sea-level | 3,830 kN (860,000 lbf) | 1.00 | infobox |
| RD-180 | Thrust, vacuum | 4,150 kN (930,000 lbf) | 1.00 | infobox |
| RD-180 | Thrust-to-weight ratio | 78.44 | 1.00 | infobox |
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