RD-0233
| Country of origin | Oxidizer Rich Staged Combustion[1] |
|---|---|
| Configuration | |
| Chamber | 1[2] |
| Performance | |
| Thrust | 520 kilonewtons (120,000 lbf)[2] |
| Chamber pressure | 20.5 megapascals (2,970 psi)[2] |
| Specific impulse, vacuum | 310 s (3.0 km/s)[2] |
| Specific impulse, sea-level | 285 s (2.79 km/s)[2] |
| Burn time | 121 seconds[2] |
| Used in | |
| UR-100N core stage[2] | |
The RD-0233 (
ICBM.[5] While the engine is out of production, the ICBM as well as Rokot and Strela remain operational as of 2015.[5]
See also
Space portal
- ICBMfor which this engine was originally developed for.
- Rokot - launch vehicle that is a repurposed UR-100N.
- Strela - launch vehicle that is a repurposed UR-100N.
- Rocket engine using liquid fuel
References
- ^ a b c d e f g "RD-0233, RD-0234, RD-0235, RD-0236, RD-0237. Intercontinental ballistic missiles RS-18". KBKhA. Archived from the original on 5 May 2014.
- ^ a b c d e f g h "RD-0233". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-19.
- Khrunichev State Research and Production Space Center. Archived from the originalon 27 May 2011.
- ^ "RD-0234". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-19.
- ^ a b Zak, Anatoly. "UR-100N Family". RussianSpaceWeb.com. Retrieved 2015-06-19.
External links
- KbKhA official information on the engine. (Archived)
- Encyclopedia Astronautica information on the propulsion module.
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