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The RD-250 (Russian: Ракетный Двигатель-250, romanized: Raketnyy Dvigatel-250, lit. 'Rocket Engine 250', GRAU index: 8D518) is the base version of a dual-nozzle family of liquid-fuel rocket engines, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (.mw-parser-output…
Overview & Possible technological transfer to North Korea
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r-36 grau index three module used tsyklon-2 tsyklon-3 engine version engines stage propulsion north korea first launch family icbm yuzhmash
| Subject | Predicate | Object | Confidence | Src |
|---|---|---|---|---|
| RD-250 | Associated LV | R-36, Tsyklon-2 and Tsyklon-3 | 1.00 | infobox |
| RD-250 | Chamber | 2 | 1.00 | infobox |
| RD-250 | Chamber pressure | 8.33 MPa (1,208 psi) | 1.00 | infobox |
| RD-250 | Country of origin | Soviet Union | 1.00 | infobox |
| RD-250 | Cycle | Gas-generator | 1.00 | infobox |
| RD-250 | Designer | OKB-456 | 1.00 | infobox |
| RD-250 | Dry mass | 788 kg (1,737 lb) | 1.00 | infobox |
| RD-250 | First flight | December 16th, 1965 | 1.00 | infobox |
| RD-250 | Manufacturer | PA Yuzhmash | 1.00 | infobox |
| RD-250 | Mixture ratio | 2.6 | 1.00 | infobox |
| RD-250 | Propellant | N2O4 / UDMH | 1.00 | infobox |
| RD-250 | Specific impulse, sea-level | 270 s (2.6 km/s) | 1.00 | infobox |
| RD-250 | Specific impulse, vacuum | 301 s (2.95 km/s) | 1.00 | infobox |
| RD-250 | Status | Out of Production | 1.00 | infobox |
| RD-250 | Thrust, sea-level | 788 kN (177,000 lbf) | 1.00 | infobox |
| RD-250 | Thrust, vacuum | 882 kN (198,000 lbf) | 1.00 | infobox |
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