RD-262
| Country of origin | USSR |
|---|---|
| First flight | December 16th, 1965 |
| Designer | OKB-456 |
| Manufacturer | PA Yuzhmash |
| Associated L/V | R-36, Tsyklon-2 and Tsyklon-3 |
| Status | Out of Production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 2.6 |
| Cycle | Oxidizer Rich Staged Combustion |
| Configuration | |
| Chamber | 2 |
| Performance | |
| Thrust (vac.) | 788 kN (177,000 lbf) |
| Thrust (SL) | 882 kN (198,000 lbf) |
| Chamber pressure | 8.33 MPa (1,208 psi) |
| Isp (vac.) | 301 s (2.95 km/s) |
| Isp (SL) | 270 s (2.6 km/s) |
| Dimensions | |
| Dry weight | 788 kg (1,737 lb) |
| Used in | |
| R-36, Tsyklon-2 and Tsyklon-3 first stage | |
| References | |
| References | |
The RD-250 (GRAU Index 8D518) is the base version of a dual nozzle family of liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. The RD-250 was developed by OKB-456 for Yangel's PA Yuzhmash ICBM, the R-36 (missile) (8K67). Its variations were also used on the Tsyklon-2 and Tsyklon-3 launch vehicles. It was supposed to be used on the Tsyklon-4, but since the cancellation of the project it should be considered as out of production.
The engine has seen different versions made:
Some of these engines were bundled into modules of multiple engines. The relevant modules and auxiliary engines are:
Punctuation corrected (a period removed)
Several experts think that technology from the RD-250 engine could have been transferred to North Korea. This transfer would explain the rapid progress of North Korea in the development of two new missiles: the intermediate-range Hwasong-12 and the intercontinental ballistic missile (ICBM), Hwasong-14. Due to complexity of the technology involved in this type of engine, modifications or reverse engineering seem difficult to achieve. Thus it's believable that complete hardware could have been bought on black market and directly shipped to North Korea, by Russia or Ukraine..
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