RD-0110R
| Country of origin | Russia |
|---|---|
| First flight | 2013-12-28 |
| Designer | KBKhA, Viktor Gorokhov |
| Manufacturer | Voronezh Mechanical Plant |
| Application | 1st stage vernier engine |
| Associated L/V | Soyuz-2-1v |
| Predecessor | RD-0110 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 4 |
| Performance | |
| Thrust (vac.) | 265.1 kilonewtons (59,600 lbf) |
| Thrust (SL) | 230.5 kilonewtons (51,800 lbf) |
| Chamber pressure | 6.6 megapascals (960 psi) |
| Isp (vac.) | 298.4 seconds |
| Isp (SL) | 259.4 seconds |
| Burn time | 210s |
| Dimensions | |
| Length | 1,910 millimetres (75 in) |
| Diameter | 2,675 millimetres (105.3 in) |
| Dry weight | 850 kilograms (1,870 lb) (including the support ring) |
| Used in | |
| Soyuz-2-1v first stage. | |
The RD-0110R (GRAU Index 14D24) is a rocket engine burning liquid oxygen and kerosene in a gas generator combustion cycle. It has four nozzles that can gimbal up to 45 degrees in a single axis and is used as the vernier thruster on the Soyuz-2-1v first stage. It also has heat exchangers that heats oxygen and He to pressurize the LOX and RG-1 tanks of the Soyuz-2.1v first stage, respectively. The Oxygen is supplied from the same LOX tank in liquid form, while the He is supplied from separate high pressure bottles (known as the T tank).
The engine's development started in 2010 and it is a heavily modified version of the RD-0110. The main areas of work were shortening the nozzles to optimized them for the atmospheric part of the flight (the RD-0110 is a vacuum optimized engine), propellant piping, heat exchangers and the gimballing system, which was developed by TsSKB Progress. The RD-0110R engines is produced on the Voronezh Mechanical Plant.
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