Back RD-0110 French RD-0110 Galician RD–0110 Hungarian RD-0110 ID RD-0110 Italian RD-0110 Japanese RD-0110 Polish RD-0110 Portuguese РД-0110 Russian РД-0110 Ukrainian
 RD-0110 on display at the Museum of Space and Missile Technology in Saint Petersburg in September 2008 | |
| Country of origin | Soviet Union · Russia |
|---|---|
| First flight | 1965-10-05 |
| Designer | Chemical Automatics Design Bureau |
| Manufacturer | Voronezh Mechanical Plant[1] |
| Application | Upper stage engine |
| Associated LV | Current: Soyuz-2.1a Retired: Molniya-M and most Soyuz family rockets |
| Predecessor | RD-0108 |
| Successor | RD-0124 |
| Status | In production |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Mixture ratio | 2.2[2] |
| Cycle | Gas-generator |
| Configuration | |
| Chamber | 4 main, 4 vernier thruster |
| Performance | |
| Thrust, vacuum | 298.03 kN (67,000 lbf) |
| Thrust-to-weight ratio | 74.36[3] |
| Chamber pressure | 6.8 MPa (990 psi) |
| Specific impulse, vacuum | 325 s (3.19 km/s) |
| Burn time | 250 seconds |
| Dimensions | |
| Length | 1,575 mm (62.0 in) |
| Diameter | 2,240 mm (88 in) |
| Dry mass | 408.5 kg (901 lb) |
| Used in | |
| Molniya-M Block-I and on most Soyuz Block-I | |
| References | |
| References | [4][5] |
The RD-0110 (Russian: Ракетный Двигатель-0110, romanized: Raketnyy Dvigatel-0110, lit. 'Rocket Engine 0110', and its derivatives, the 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 provide attitude control for the stage. It has an extensive flight history with its initial versions having flown more than 64 years ago.[6][7][5]
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