RD-0214
| Country of origin | Soviet Union · Russia |
|---|---|
| First flight | RD-0207: 1963-11-06 RD-0214: 1967-03-10 |
| Designer | OKB-154, Yankel I. Guerchkovitch |
| Manufacturer | Voronezh Mechanical Plant |
| Application | Vernier thruster |
| Status | In production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 2.54 |
| Cycle | Gas-generator |
| Configuration | |
| Chamber | 4 |
| Performance | |
| Thrust, vacuum | 30.9 kN (6,900 lbf) |
| Chamber pressure | 5.3 MPa (770 psi) |
| Specific impulse, vacuum | RD-0207: 297 s (2.91 km/s) RD-0214: 293 s (2.87 km/s) |
| Burn time | RD-0207: 133 seconds RD-0214: 270 seconds |
| Dimensions | |
| Length | 524 mm (20.6 in) |
| Diameter | 3,780 mm (149 in) |
| Dry mass | 90 kg (200 lb) |
| Used in | |
| Proton third stage | |
The RD-0214 (Russian: Ракетный Двигатель-0214 [РД-0214], romanized: Raketnyy Dvigatel-0214, lit. 'Rocket Engine 0214', GRAU index: 8D811) is a vernier thruster rocket engine burning unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N2O4) oxidizer in a gas-generator cycle. It has four nozzles that can each gimbal 45 degrees in plane to provide thrust vectoring control to the RD-0212 propulsion module of Proton rocket's third stage. It is a revised version of the RD-0207 (Russian: РД-0214, GRAU index: 8D67).