RD-214
Museum of Space and Missile Technology (Saint Petersburg). RD-214 for Kosmos LV first stage. | |
| Country of origin | USSR |
|---|---|
| Date | 1955-1959 |
| Designer | Energomash, V.Glushko |
| Manufacturer | Plant No. 19 named after I. V. Stalin |
| Associated LV | R-12 and Kosmos-2 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | AK-27I / TM-185 |
| Mixture ratio | 3.97 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 4 |
| Nozzle ratio | 9.42 |
| Performance | |
| Thrust, vacuum | 730.2 kilonewtons (164,200 lbf) |
| Thrust, sea-level | 635.2 kilonewtons (142,800 lbf) |
| Chamber pressure | 4.36 megapascals (632 psi) |
| Specific impulse, vacuum | 264 s (2.59 km/s) |
| Specific impulse, sea-level | 230 s (2.3 km/s) |
| Burn time | 140 s |
| Dimensions | |
| Length | 2,380 millimetres (94 in) |
| Diameter | 1,480 millimetres (58 in) |
| Dry mass | 655 kilograms (1,444 lb) |
| Used in | |
| R-12 and Kosmos-2 | |
| References | |
| References | |
The RD-214 (GRAU Index 8D59) was a liquid rocket engine, burning AK-27I (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant and TM-185 (a kerosene and gasoline mix) in the gas generator cycle. As was the case with many V-2 influenced engines, the single turbine was driven by steam generated by catalytic decomposition of hydrogen peroxide. It also had four combustion chambers and vector control was achieved by refractory vanes protruding into the nozzle's exhaust.