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RD-0110
 | |
| Country of origin | USSR |
|---|---|
| First flight | 1965-10-05 |
| Designer | KBKhA |
| Manufacturer | Voronezh Mechanical Plant[1] |
| Application | Upper Stage |
| Associated LV | Molniya-M and Soyuz |
| Predecessor | RD-0108 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Mixture ratio | 2.2[2] |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 4 |
| Performance | |
| Thrust, vacuum | 298 kilonewtons (67,000 lbf) |
| Thrust-to-weight ratio | 74.36[3] |
| Chamber pressure | 6.8 megapascals (990 psi) |
| Specific impulse, vacuum | 326 seconds |
| Burn time | 250 s |
| Dimensions | |
| Length | 1,575 millimetres (62.0 in) |
| Diameter | 2,240 millimetres (88 in) |
| Dry mass | 408.5 kilograms (901 lb) |
| Used in | |
| Molniya-M Block-I and on most Soyuz Block-I | |
| References | |
| References | [4] |
The RD-0110 (or RO-8, RD-0108, RD-461 ) is a rocket engine burning liquid oxygen and kerosene in a gas generator combustion cycle. It has four fixed nozzles and the output of the gas generator is directed to four secondary vernier nozzles to supply vector control of the stage. It has an extensive flight history with its initial versions having flown more than 57 years ago (as of February 2018).[5][6][7]
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