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RD-214

From Wikipedia, the free encyclopedia
Not to be confused withRD-0214.
RD-214 (РД-214)
Museum of Space and Missile Technology (Saint Petersburg). RD-214 for Kosmos LV first stage.
Country of originUSSR
Date1955-1959
DesignerEnergomash,V.Glushko
ManufacturerPlant No. 19 named after I. V. Stalin
AssociatedLVR-12andKosmos-2
StatusRetired
Liquid-fuel engine
PropellantAK-27I/TM-185
Mixture ratio3.97
CycleGas Generator
Configuration
Chamber4
Nozzle ratio9.42
Performance
Thrust, vacuum730.2 kilonewtons (164,200 lbf)
Thrust, sea-level635.2 kilonewtons (142,800 lbf)
Chamberpressure4.36 megapascals (632 psi)
Specific impulse,vacuum264 s (2.59 km/s)
Specific impulse,sea-level230 s (2.3 km/s)
Burn time140 s
Dimensions
Length2,380 millimetres (94 in)
Diameter1,480 millimetres (58 in)
Dry mass655 kilograms (1,444 lb)
Used in
R-12andKosmos-2
References
References[1][2]

TheRD-214(GRAUIndex8D59) was aliquidrocket engine,burningAK-27I(a mixture of 73%nitric acidand 27%N2O4+iodinepassivantandTM-185(akeroseneandgasolinemix) in thegas generatorcycle.[2][3]As was the case with manyV-2influenced engines, the single turbine was driven by steam generated bycatalyticdecomposition ofhydrogen peroxide.It also had four combustion chambers andvector controlwas achieved by refractory vanes protruding into the nozzle's exhaust.[4]

Development

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For the requirements to have storable propellants and higher thrust,Glushko'sOKB-456developed theRD-211,which had four combustion chambers, each having twice the thrust of the RD-100, a Russian adaptation of the V-2 A-4 engine.[5]The four chambers were fed from a singleturbopumppowered by steam generated from catalytic decomposition of hydrogen peroxide.[6]When then came the requirement for theBurancruise missileproject, a version for that application was developed in theRD-212.[7]Both RD-211 and RD-212 proved too weak for the application and the project were abandoned for theRD-213for Buran.[8]WhenYangel'sOKB-586was tasked with developing the first storable propellantballistic missilein the Soviet arsenal, the RD-211 proved too weak. Thus, the project was definitely abandoned and the more powerfulRD-214was developed.[2]While Korolev's refusal to use toxic propellants basically left him out of the ballistic missile development race, the basic design of the RD-211 also served as basis for theRD-107/RD-108engine, which went to be the most flown rocket engines in history.[5]

The initial R-12 was a pad launched missile. It had significant operative issues on readiness and vulnerability. Thus, the silo launched R-12U was developed. For this development theRD-214Uwas developed. When Yangel used the R-12U as the basis for theKosmos-263S1, the RD-214F was developed and fire tested, but in the end the stock R-12U was used as first stage. So it was for all subsequent 63S1M and 11K63.[1][5][9]

Versions

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This engine many versions:

  • RD-211:GRAUIndex8D57.Original design for theR-12.Based on the RD-100, itself an adaptation of the V-2 A4 engine. This engine already had four separate combustion chambers, anH2O2steam driven turbine and required vanes in the exhaust to control the rocket.[1][6]
  • RD-212:GRAUIndex8D41.Originally developed from the RD-211 for theBurancruise missileproject. Project drop in favor of RD-213 due to insufficient thrust.[1][7]
  • RD-213:GRAUIndex8D13.Similar to the RD-214. Developed for theBurancruise missileproject. Cancelled with the project.[1][8]
  • RD-214:GRAUIndex8D59.Original version of the engine designed for theR-12(8K63).[1]
  • RD-214U:GRAUIndex8D59.Improved version of the engine. Flew on theR-12U(8K63S) andKosmos-2(11K63) launch vehicle.[1]
  • RD-214F:GRAUIndex11D45.Project for the initial version ofKosmos-2(63S1).[1]
RD-214 Family of Engines[1]
Engine RD-211 RD-212 RD-213 RD-214 RD-214U RD-214F
AKA 8D57 8D41 8D13 8D59 8D59U 11D45
Development 1953-1955 1954-1956 1956-1957 1955-1959 1959-1960 1960-1962
Engine type Gas generator[2]
Propellant AK-27I(73%nitric acid,27%N2O4,andiodinepassivant) /TM-185(akeroseneandgasolinemix)[2]
Combustion chamber pressure 3.923 megapascals (569.0 psi) 3.923 megapascals (569.0 psi) 4.66 megapascals (676 psi) 4.36 megapascals (632 psi) 4.36 megapascals (632 psi) 4.38 megapascals (635 psi)
Thrust, vacuum 642.3 kilonewtons (144,400 lbf) 622.7 kilonewtons (140,000 lbf) 749.2 kilonewtons (168,400 lbf) 730.2 kilonewtons (164,200 lbf) 730.6 kilonewtons (164,200 lbf) 729.6 kilonewtons (164,000 lbf)
Thrust, sea level 549.2 kilonewtons (123,500 lbf) 559 kilonewtons (126,000 lbf) 686.5 kilonewtons (154,300 lbf) 635.2 kilonewtons (142,800 lbf) 635.5 kilonewtons (142,900 lbf) 635.5 kilonewtons (142,900 lbf)
Isp,vacuum 253 s (2.48 km/s) 254 s (2.49 km/s) 264 s (2.59 km/s) 264 s (2.59 km/s) 264 s (2.59 km/s) 264 s (2.59 km/s)
Isp,sea level 224 s (2.20 km/s) 227 s (2.23 km/s) 231 s (2.27 km/s) 230 s (2.3 km/s) 230 s (2.3 km/s) 230 s (2.3 km/s)
Burn time 122s 100s 110s 140s
Length 2,700 millimetres (110 in) 2,500 millimetres (98 in) 2,500 millimetres (98 in) 2,380 millimetres (94 in) 2,380 millimetres (94 in) 2,380 millimetres (94 in)
Diameter 1,650 millimetres (65 in) 1,480 millimetres (58 in) 1,480 millimetres (58 in) 1,500 millimetres (59 in) 1,480 millimetres (58 in) 1,480 millimetres (58 in)
Dry weight 635 kilograms (1,400 lb) 642 kilograms (1,415 lb) 625 kilograms (1,378 lb) 655 kilograms (1,444 lb) 655 kilograms (1,444 lb) 655 kilograms (1,444 lb)
Use R-12(8K63) Project BuranProject BuranProject R-12(8K63) R-12U(8K63S)
Kosmos-2(11K63)		 Project forKosmos-2(63S1)

See also

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References

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  1. ^abcdefghi"NPO Energomash list of engines".NPO Energomash.Retrieved2015-06-26.
  2. ^abcde"RD-214".Encyclopedia Astronautica.Archived fromthe originalon 2015-08-24.Retrieved2015-06-26.
  3. ^"Nitric acid/Kerosene".Encyclopedia Astronautica.Archived fromthe originalon 2016-03-13.Retrieved2015-06-26.
  4. ^"Soviet rocket's engines (NPO Energomash)".Buran-Energia.Retrieved2015-06-27.
  5. ^abc"R-12".Encyclopedia Astronautica.Archived fromthe originalon March 5, 2002.Retrieved2015-06-26.
  6. ^ab"RD-211".Encyclopedia Astronautica.Archived fromthe originalon January 8, 2002.Retrieved2015-06-26.
  7. ^ab"RD-212".Encyclopedia Astronautica.Archived fromthe originalon January 8, 2002.Retrieved2015-06-26.
  8. ^ab"RD-213".Encyclopedia Astronautica.Archived fromthe originalon May 5, 2002.Retrieved2015-06-26.
  9. ^Zak, Anatoly."Kosmos-2".RussianSpaceWeb.Retrieved2015-06-26.
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