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RD-0233

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RD-0233 (РД-0233)
Country of originUSSR
First flight1973-04-09
DesignerOKB-154
Associated LVUR-100N, Rokot and Strela
StatusOut of Production
Liquid-fuel engine
PropellantN2O4 / UDMH
CycleOxidizer Rich Staged Combustion
Configuration
Chamber1
Performance
Thrust520 kilonewtons (120,000 lbf)
Chamber pressure20.5 megapascals (2,970 psi)
Specific impulse, vacuum310 s (3.0 km/s)
Specific impulse, sea-level285 s (2.79 km/s)
Burn time121 seconds
Used in
UR-100N core stage

The RD-0233 (Russian: Ракетный Двигатель-0233, romanizedRaketnyy Dvigatel-0233, lit.'Rocket Engine 0233', GRAU index: 15D95) and RD-0234 (GRAU index: 15D96) are liquid-fueled rocket engines which burn a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N2O4) oxidizer in an oxidizer-rich staged combustion cycle. The only difference between the RD-0233 and the RD-0234 is that the latter has a heat exchanger to heat the pressuring gasses for the tanks. Three RD-0233 and one RD-0234 are used on the first stage of the UR-100UTTKh ICBM. While the engine is out of production, the ICBM as well as Rokot and Strela remain operational as of 2015.

See also

References

  1. ^ "RD-0233, RD-0234, RD-0235, RD-0236, RD-0237. Intercontinental ballistic missiles RS-18". KBKhA. Archived from the original on 5 May 2014.
  2. ^ "RD-0233". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-19.
  3. "Rockot Launch Vehicle". Khrunichev State Research and Production Space Center. Archived from the original on 27 May 2011.
  4. "RD-0234". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-19.
  5. ^ Zak, Anatoly. "UR-100N Family". RussianSpaceWeb.com. Retrieved 2015-06-19.

External links

Rocket engines and solid motors for orbital launch vehicles
Liquid
fuel
Cryogenic
Hydrolox
(LH2 / LOX)
Methalox
(CH4 / LOX)
Semi-
cryogenic
Kerolox
(RP-1 / LOX)
Storable
Hypergolic (Aerozine,
UH 25, MMH, or UDMH
/ N2O4, MON, or HNO3)
Other
Solid
fuel
  • * Different versions of the engine use different propellant combinations
  • Engines in italics are under development
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