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RD-0216

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Not to be confused withRD-216.
RD-0216 (РД-0216)
Country of originUSSR
First flight1965-04-19[1]
DesignerOKB-154[1]
ManufacturerPO Motorostroitel or Perm[2]
ApplicationICBMpropulsion
AssociatedLVUR-100[1]
SuccessorRD-0235
StatusRetired
Liquid-fuel engine
PropellantN2O4[3]/UDMH[3]
CycleOxidizer Rich Staged combustion[1]
Configuration
Chamber1[3]
Performance
Thrust219 kilonewtons (49,000 lbf)[3]
Chamberpressure17.4 megapascals (2,520 psi)[3]
Specific impulse313 s (3.07 km/s)[3]
Used in
UR-100Core Stage[4]
RD-0235 (РД-0235)
Country of originUSSR
First flight1973-04-09[5]
DesignerOKB-154[5]
ManufacturerKrasny Oktyabr factory[2]
ApplicationICBMpropulsion
AssociatedLVUR-100N,RokotandStrela[5]
StatusOut of Production
Liquid-fuel engine
PropellantN2O4[6]/UDMH[6]
CycleOxidizer Rich Staged combustion[5]
Configuration
Chamber1[6]
Performance
Thrust240 kilonewtons (54,000 lbf)[6]
Chamberpressure17.5 megapascals (2,540 psi)[6]
Specific impulse320 s (3.1 km/s)[6]
Used in
UR-100NSecond Stage[6]

TheRD-0216andRD-0217areliquidrocket engines,burningN2O4andUDMHin theoxidizer rich staged combustioncycle.[1][3]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.[3]Three RD-0216 and one RD-0217 were used on the first stage of theUR-100ICBM.[7]The engines were manufactured until 1974 and stayed in operational use until 1991. More than 1100 engines were produced.[3]

For theUR-100Nproject, while first stage propulsion was based on the more powerfulRD-0233engine. The second stage used a variation of the RD-0217 called theRD-0235(GRAUIndex15D113).[8]It used a vacuum optimized nozzle extension, and thus had an extra 10 seconds ofispand 21 kilonewtons (4,700 lbf)[6]of more thrust. It has a fixed nozzle and relies on theRD-0236vernier engineforthrust vectoring.While the engine has been out of production for a while, theUR-100NUand theRokotandStrelause it as of 2015.[6]

See also

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References

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  1. ^abcde"RD-0216, RD-0217. Intercontinental ballistic missile RS-10".KBKhA.Retrieved2015-06-19.
  2. ^abLardier, Christian. "Liquid Propellant Engines in the Soviet Union".Thirty-third IAA History Symposium.19.American Astronautical Society: 39–73.
  3. ^abcdefghi"RD-0216".Encyclopedia Astronautica.Archived fromthe originalon 2016-03-03.Retrieved2015-06-19.
  4. ^"RD-0217".Encyclopedia Astronautica.Archived fromthe originalon 2016-03-03.Retrieved2015-06-19.
  5. ^abcd"RD-0216, RD-0217. Intercontinental ballistic missile RS-10".KBKhA.Retrieved2015-06-19.
  6. ^abcdefghi"RD-0235".Encyclopedia Astronautica.Archived fromthe originalon 2015-08-24.Retrieved2015-06-19.
  7. ^Zak, Anatoly."UR-100 Family".RussianSpaceWeb.Retrieved2015-06-19.
  8. ^"Rockot Launch Vehicle".Khrunichev State Research and Production Space Center.Retrieved2015-06-19.
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