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RD-0216

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Not to be confused with RD-216.
RD-0216 (РД-0216)
Country of originUSSR
First flight1965-04-19
DesignerOKB-154
ManufacturerPO Motorostroitel or Perm
ApplicationICBM propulsion
Associated LVUR-100
SuccessorRD-0235
StatusRetired
Liquid-fuel engine
PropellantN2O4 / UDMH
CycleOxidizer Rich Staged combustion
Configuration
Chamber1
Performance
Thrust219 kilonewtons (49,000 lbf)
Chamber pressure17.4 megapascals (2,520 psi)
Specific impulse313 s (3.07 km/s)
Used in
UR-100 Core Stage
RD-0235 (РД-0235)
Country of originUSSR
First flight1973-04-09
DesignerOKB-154
ManufacturerKrasny Oktyabr factory
ApplicationICBM propulsion
Associated LVUR-100N, Rokot and Strela
StatusOut of Production
Liquid-fuel engine
PropellantN2O4 / UDMH
CycleOxidizer Rich Staged combustion
Configuration
Chamber1
Performance
Thrust240 kilonewtons (54,000 lbf)
Chamber pressure17.5 megapascals (2,540 psi)
Specific impulse320 s (3.1 km/s)
Used in
UR-100N Second Stage

The RD-0216 (Russian: Ракетный Двигатель-0216, romanized: Raketnyy Dvigatel-0216, lit. 'Rocket Engine 0216') and RD-0217 are liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. The only difference between the RD-0216 and the RD-0217 is that the latter doesn't have a heat exchanger to heat the pressuring gasses for the tanks. Three RD-0216 and one RD-0217 were used on the first stage of the UR-100 ICBM. The engines were manufactured until 1974 and stayed in operational use until 1991. More than 1100 engines were produced.

For the UR-100N project, while first stage propulsion was based on the more powerful RD-0233 engine. The second stage used a variation of the RD-0217 called the RD-0235 (GRAU Index 15D113). It used a vacuum optimized nozzle extension, and thus had an extra 10 seconds of isp and 21 kilonewtons (4,700 lbf) of more thrust. It has a fixed nozzle and relies on the RD-0236 vernier engine for thrust vectoring. While the engine has been out of production for a while, the UR-100NU and the Rokot and Strela use it as of 2015.

See also

References

  1. ^ "RD-0216, RD-0217. Intercontinental ballistic missile RS-10". KBKhA. Retrieved 2015-06-19.
  2. ^ Lardier, Christian. "Liquid Propellant Engines in the Soviet Union". Thirty-third IAA History Symposium. 19. American Astronautical Society: 39–73.
  3. ^ "RD-0216". Encyclopedia Astronautica. Archived from the original on 2016-03-03. Retrieved 2015-06-19.
  4. "RD-0217". Encyclopedia Astronautica. Archived from the original on 2016-03-03. Retrieved 2015-06-19.
  5. ^ "RD-0216, RD-0217. Intercontinental ballistic missile RS-10". KBKhA. Retrieved 2015-06-19.
  6. ^ "RD-0235". Encyclopedia Astronautica. Archived from the original on 2015-08-24. Retrieved 2015-06-19.
  7. Zak, Anatoly. "UR-100 Family". RussianSpaceWeb.com. Retrieved 2015-06-19.
  8. "Rockot Launch Vehicle". Khrunichev State Research and Production Space Center. 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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