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]
 Museum of Space and Missile Technology (Saint Petersburg). RD-214 for Kosmos LV first stage. | |
| Country of origin | USSR |
|---|---|
| Date | 1955-1959 |
| Designer | Energomash,V.Glushko |
| Manufacturer | Plant No. 19 named after I. V. Stalin |
| AssociatedLV | R-12andKosmos-2 |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | AK-27I/TM-185 |
| Mixture ratio | 3.97 |
| Cycle | Gas Generator |
| Configuration | |
| Chamber | 4 |
| Nozzle ratio | 9.42 |
| Performance | |
| Thrust, vacuum | 730.2 kilonewtons (164,200 lbf) |
| Thrust, sea-level | 635.2 kilonewtons (142,800 lbf) |
| Chamberpressure | 4.36 megapascals (632 psi) |
| Specific impulse,vacuum | 264 s (2.59 km/s) |
| Specific impulse,sea-level | 230 s (2.3 km/s) |
| Burn time | 140 s |
| Dimensions | |
| Length | 2,380 millimetres (94 in) |
| Diameter | 1,480 millimetres (58 in) |
| Dry mass | 655 kilograms (1,444 lb) |
| Used in | |
| R-12andKosmos-2 | |
| References | |
| References | [1][2] |
Development
editFor 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
editThis 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]
| 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
edit
- R-12 Dvina-Ballistic missilefor which this engine was originally developed for.
- Kosmos-2-launch vehiclethat uses an R-12 as first stage.
- Rocket engine using liquid fuel
References
edit- ^abcdefghi"NPO Energomash list of engines".NPO Energomash.Retrieved2015-06-26.
- ^abcde"RD-214".Encyclopedia Astronautica.Archived fromthe originalon 2015-08-24.Retrieved2015-06-26.
- ^"Nitric acid/Kerosene".Encyclopedia Astronautica.Archived fromthe originalon 2016-03-13.Retrieved2015-06-26.
- ^"Soviet rocket's engines (NPO Energomash)".Buran-Energia.Retrieved2015-06-27.
- ^abc"R-12".Encyclopedia Astronautica.Archived fromthe originalon March 5, 2002.Retrieved2015-06-26.
- ^ab"RD-211".Encyclopedia Astronautica.Archived fromthe originalon January 8, 2002.Retrieved2015-06-26.
- ^ab"RD-212".Encyclopedia Astronautica.Archived fromthe originalon January 8, 2002.Retrieved2015-06-26.
- ^ab"RD-213".Encyclopedia Astronautica.Archived fromthe originalon May 5, 2002.Retrieved2015-06-26.
- ^Zak, Anatoly."Kosmos-2".RussianSpaceWeb.Retrieved2015-06-26.