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RD-0255

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(Redirected from RD-0256) Soviet upper stage rocket engine
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RD-0256 (РД-0256)
Country of originUSSR
First flight1981-12-27
DesignerOKB-154
Associated LVR-36M and Dnepr
PredecessorRD-0229
StatusIn Service
Liquid-fuel engine
PropellantN2O4 / UDMH
Mixture ratio2.6
CycleOxidizer Rich Staged combustion
Configuration
Chamber1
Performance
Thrust755 kilonewtons (170,000 lbf)
Used in
RD-0255 Propulsion Module
References
References
RD-0257 (РД-0257)
Country of originUSSR
First flight1981-12-27
DesignerOKB-154
Associated LVR-36M and Dnepr
PredecessorRD-0230
StatusIn Service
Liquid-fuel engine
PropellantN2O4 / UDMH
CycleGas Generator
Configuration
Chamber4
Used in
RD-0255 Propulsion Module
References
References

The RD-0255 (Russian: Ракетный Двигатель-0255, romanizedRaketnyy Dvigatel-0255, lit.'Rocket Engine 0255') is a propulsion module composed of an RD-0256 main engine and a RD-0257 Vernier thruster. Both are liquid-fuel rocket engines, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with dinitrogen tetroxide (N2O4) oxidizer. The RD-0256 main engine operates in the oxidizer rich staged combustion cycle, while the vernier RD-0257 uses the simpler gas generator cycle. It was used on the R-36MUTTKh (GRAU:15A18) and R-36M2 (GRAU:15A18M). Subsequently, it has been in the Dnepr second stage and as of 2016 it is still in active service.

The RD-0256 is an improved version of the RD-0228 (GRAU: 15D84), itself composed of an RD-0229 (GRAU: 15D84) main engine and a RD-0230 (GRAU: 15D79) vernier engine. The RD-0228 was developed between 1967 and 1974 for the first generation of R-36M (GRAU: 15D83) ICBM second stage, but was replaced on subsequent iterations by the RD-0256. The RD-0228 debut was on January 21, 1973. With the START I and START II the RD-0228 was retired and its successor, the RD-0256, only continued as the Dnepr.

See also

References

  1. ^ "RD-0255". Encyclopedia Astronautica. Archived from the original on May 20, 2002. Retrieved 2016-07-06.
  2. ^ "RD-0228". Encyclopedia Astronautica. Archived from the original on June 25, 2002. Retrieved 2016-07-06.
  3. ^ "РД0228, РД0229, РД0230, РД0255, РД0256, РД0257. Межконтинентальные баллистические ракеты РС-20А, РС-20Б, РС-20В" [RD0228, RD0229, RD0230, RD0255, RD0256, RD0257. Intercontinental ballistic missile PC-20А, PC-20Б, PC-20В]. KBKhA. Archived from the original on 5 May 2014.
  4. Krebs, Gunter Dirk (2016-06-13). "Dnepr". Gunter's Space Page. Retrieved 2016-07-05.
  5. Norbert Brügge. "Dnepr, Propulsion". B14643.DE. Retrieved 2015-07-15.
  6. Krebs, Gunter Dirk (2016-05-02). "R-36M Voivode (SS-18, Satan) ICBM". Gunter's Space Page. Retrieved 2016-07-05.
  7. ^ Pillet, Nicolas. "Le deuxième étage de Dniepr" [The second stage of the Dnepr] (in French). Kosmonavtika.com. Retrieved 2016-07-06.

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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