| Country of origin | USSR |
|---|---|
| Date | 1969-1975 |
| Designer | Energomash, V.Glushko |
| Manufacturer | PA Yuzhmash[1] |
| Associated LV | R-36M and Dnepr |
| Status | Out of production |
| Liquid-fuel engine | |
| Propellant | N2O4 / UDMH |
| Mixture ratio | 2.67 |
| Cycle | Oxidizer-rich staged combustion |
| Configuration | |
| Chamber | 1[2] |
| Performance | |
| Thrust, vacuum | 1,128 kilonewtons (254,000 lbf) |
| Thrust, sea-level | 1,040 kilonewtons (230,000 lbf) |
| Chamber pressure | 20.6 megapascals (2,990 psi) |
| Specific impulse, vacuum | 318 s (3.12 km/s) |
| Specific impulse, sea-level | 293 s (2.87 km/s) |
| Gimbal range | 7°[3] |
| Dimensions | |
| Length | 2,150 millimetres (85 in) |
| Diameter | 1,080 millimetres (43 in) |
| Dry weight | 870 kilograms (1,920 lb) |
| Used in | |
| R-36M and R-36MUTTKh core stage (15А14 and 15A18) | |
| References | |
| References | [2][4] |
The RD-263 (GRAU Index 15D117) is a liquid rocket engine, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle.[2] Four RD-263 engines form a propulsion module RD-264 (GRAU Index 15D119).[5] For the R-36M KB Yuzhnoye only ordered the first stage propulsion to Energomash, instead of both stages, arguing that they were overworked with the RD-270 development. By April 1970 Yuzhnoye was getting the engine documentation. By the end of 1972 Energomash started to test fire the engines in its own test stand. And by September 1973 the engine was certified for flight.[1] While the engine is out of production, the ICBM as well as the Dnepr remain operational as of 2015.[3]
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npoem-elwas invoked but never defined (see the help page). - ^ Cite error: The named reference
ea-rd264was invoked but never defined (see the help page).
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