RD-855
| Country of origin | Soviet Union |
|---|---|
| First flight | December 16, 1965 |
| Last flight | January 30, 2009 |
| Designer | Yuzhnoye Design Bureau |
| Manufacturer | Yuzhmash |
| Application | Vernier |
| Associated L/V | R-36, Tsyklon-2 and Tsyklon-3 |
| Status | Out of production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 1.97 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 4 |
| Performance | |
| Thrust (vac.) | 328 kN (74,000 lbf) |
| Thrust (SL) | 285.4 kN (64,200 lbf) |
| Chamber pressure | 6.570 MPa (952.9 psi) |
| Isp (vac.) | 292 s (2.86 km/s) |
| Isp (SL) | 254 s (2.49 km/s) |
| Burn time | up to 127s |
| Restarts | 1 |
| Gimbal range | +/- 41° |
| Dimensions | |
| Length | 1.74 m (5 ft 9 in) |
| Diameter | 3.81 m (12.5 ft) |
| Dry weight | 320 kg (710 lb) |
| Used in | |
| R-36, Tsyklon-2 and Tsyklon-3 first stage vernier | |
| References | |
| References | |
The RD-855 (GRAU Index 8D68M), also known as the RD-68M, is a four nozzle liquid rocket vernier engine, burning N2O4 and UDMH in a gas generator cycle. It was used on the R-36, Tsyklon-2 and Tsyklon-3 first stage as thrust vector control by gimbaling of its nozzle. The engine is distributed through a cylindrical structure that is integrated around the main engine RD-251 module. The structure includes aerodynamic protection for the nozzles and small retro engines to assure the separation of the first stage. The engine was ignited two second before the RD-251 main engine.
The engine was serially produced between 1965 and 1992. It was first launched on December 16, 1965 on an R-36 and its last launch was on January 30, 2009 with the last launch of the Tsyklon-3. The production capability was restarted for the Tsyklon-4 but with the apparent cancellation of the program the engine would still be out of production.
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