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RD-58

January 06, 2023

The RD-58 (manufacturer designation 11D58) is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 which was the first staged combustion engine in the world.[1] The engine was initially created to power the Block D stage of the Soviet Union's abortive N-1 rocket.[5] Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets.[6] An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N-1's roll-control engine.

RD-58M
Country of originUSSR
First flight1967
DesignerOKB-1, V. M. Melnikov
ManufacturerVoronezh Mechanical Plant
ApplicationUpper Stage
Associated LVN-1, Proton-K, Proton-M, Zenit
PredecessorS1.5400
StatusIn Production
Liquid-fuel engine
PropellantLOX / RP-1
CycleOxidizer Rich Staged Combustion
Configuration
Chamber1
Performance
Thrust, vacuum79.46 kilonewtons (17,860 lbf)
Specific impulse, vacuum353 s
Burn timeup to 600 s
Dimensions
Dry weight300 kilograms (660 lb)
Used in
Block D
References
References[1][2][3][4]

The RD-58 uses LOX as the oxidizer and RG-1 as fuel in an oxidizer rich staged combustion cycle. It features a single gimbaled chamber, radial centrifugal pumps with auxiliary booster pumps, and an oxygen-rich preburner.[7] Recent modifications include a lightweight carbon-composite nozzle extender developed by NPO Iskra.[8][9][10]

The Buran spacecraft used two of an evolution of the RD-58M, called 17D12, as its main orbital correction engines. Instead of RG-1, it burned Syntin, and could be ignited 15 times.[11][12] It is assumed that it was the base for the RD-58S, which had practically the same specifications and powered the Blok DM-2M.[13] But the manufacturer states that the engine is compatible with both propellants.[1]

The current version of the engine is the RD-58M (manufacturer designation 11D58M), which has slightly reduced thrust, but increased isp. An even newer version is under development and is known as the RD-58MF (manufacturer designation 11D58MF). It will reduce thrust to 49.03 kilonewtons (11,020 lbf) to keep the same length but increase expansion ratio to 500:1. This will enable it to gain 20s of isp (to an expected 372s). It will eventually fly on the Blok DM-03.[14] This new version of the engine will be built in the Krasnoyarsk Machine-Building Plant.[15][16] During a November 2014 interview, Vladimir Kolmykov, the Deputy General Director of the Chemical Division of Krasnoyarsk Machine-Building Plant, stated that the production of Block-DM was suspended during that year, but work on the stage and development of the RD-58MF will resume during 2015.[17]

Versions

This engine has had many versions through the years:

RD-58 Family of Engines
Name RD-58 RD-58M RD-58M
(Carbon Composite Nozzle) 		RD-58S RD-58Z RD-58MF 17D12
Index 11D58 11D58M 11D58S 11D58Z 11D58MF
Development years 1964-1968 1970-1974 2000-2004 1986-1995 1981-1990 2002-2009 1981-1987
Engine Type Oxidizer Rich Stage Combustion upper stage liquid rocket engine Orbital correction liquid rocket engine
Propellant RG-1/LOX RG-1/LOX RG-1/LOX Syntin/LOX RG-1/LOX RG-1/LOX Syntin/LOX
O/F 2.48 2.48 2.82 ? 2.6 2.82 ?
Chamber Pressure 7.8 MPa (1,130 psi) 7.75 MPa (1,124 psi) 7.9 MPa (1,150 psi) 7.94 MPa (1,152 psi) 7.8 MPa (1,130 psi) 7.9 MPa (1,150 psi) 7.94 MPa (1,152 psi)
Thrust (Vac) 83.4 kN (18,700 lbf) 83.4 kN (18,700 lbf) 85 kN (19,000 lbf) 86.3 kN (19,400 lbf) 71 kN (16,000 lbf) 49.03 kN (11,020 lbf) 86.24 kN (19,390 lbf)
Isp (Vac) 349 s (3.42 km/s) 356 s (3.49 km/s) 361 s (3.54 km/s) 361 s (3.54 km/s) 361 s (3.54 km/s) 372 s (3.65 km/s) 362 s (3.55 km/s)
Nozzle Expansion 189 189 280 189 189 500 189
Ignitions 4 4 7 5 5 ? 15
Burntime 600 seconds 720 seconds 1200 seconds 680 seconds 660 seconds ? seconds 680 seconds
Length 2.27 m (89 in) 2.27 m (89 in) 2.72 m (107 in) 2.27 m (89 in) 2.27 m (89 in) 2.27 m (89 in)
Diameter 1.17 m (46 in) 1.17 m (46 in) 1.4 m (55 in) 1.17 m (46 in) 1.17 m (46 in) 1.17 m (46 in)
Weight 300 kg (660 lb) 310 kg (680 lb) 340 kg (750 lb) 310 kg (680 lb) 300 kg (660 lb) 230 kg (510 lb)
Used on N-1 and Blok D Blok DM Blok DM-SL since 2003 and Blok DM-SLB Blok DM-2M Blok DM-SL 11S861-03 Buran
First Launch 1967-03-10 1974-03-26 2003-06-10 1994-10-13 1999-03-28 ? 1988-11-15
Status Retired Retired In Production Retired Retired In Production Retired
References [2][5][6][7][8][9][11][12][13][14][18][19][20][21][22][23][25]

References

  1. ^ a b c "Engines". RSC Energiya Official Page. RSC Energiya. Retrieved 2015-08-01.
  2. ^ a b "DESCRIPTION OF ZENIT-2SLB, ZENIT-3SLB, ZENIT-3SLBF INTEGRATED LAUNCH VEHICLES". (PDF). Space International Services. 2014-10-01. p. 29. Archived from the original (PDF) on 2016-06-25. Retrieved 2015-06-03.
  3. ^ Kiselev, Anatoli I.; Medvedev, Alexander A.; Menshikov, Valery A. (2012). "Section 2.2.2 Carrier rocket booster units". Astronautics: Summary and Prospects. Springer Science & Business Media. pp. 304–305. ISBN 978-3709106488.
  4. ^ Zak, Anatoly. "Block D upper stage". russianspaceweb.com. Retrieved 2015-06-03.
  5. ^ a b c . Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  6. ^ a b "Zenit-3SL". Spaceflight 101. Retrieved July 14, 2014.
  7. ^ a b c "Двигательная установка. 11Д58М" [The propulsion system. 11D58M] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  8. ^ a b c Sokolovskiy, M.I.; Petukhov, S.N.; Semenov, Yu.P.; Sokolov, B.A. (2008). "Разработка углерод-углеродного соплового насадка для жидкостных ракетных двигателей" [The development of carbon-carbon nozzle extension for liquid rocket engines] (PDF). Thermophysics and Aeromechanics (in Russian). 15 (N°4): 721–727. Retrieved 2015-08-02.
  9. ^ a b c d Mezhevov, A.V.; Skoromnov, V.I.; Kozlov, A.V.; Tupitsin, N.N.; Khaskekov, V.G. (2006). "Внедрениесоплового насадка радиационного охлаждения из углерод-углеродного композиционного материала на камеру маршевого двигателя 11Д58М разгонного Блока ДМ-SL" [Installation of a Radiation-Cooled Nozzle of Carbon-Carbon Composite Material to the Combustion Chamber of Main Engine 11D58M of Block DM-SL] (PDF). Вестник СГАУ [Bulletin SSAU] (in Russian). RSC Energia (2-2 (10) 2006). Retrieved 2015-08-01.
  10. ^ a b [Extendable nozzle and nozzle extensions for SRM and LRE]. www.npoiskra.ru (in Russian). NPO Iskra. Archived from the original on 4 March 2016.
  11. ^ a b c . Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  12. ^ a b c Hendrickx, Bart; Vis, Bert (2007-10-04). Energiya-Buran: The Soviet Space Shuttle (UK 2007 ed.). Springer. pp. 127–131. ISBN 978-0-387-69848-9. Retrieved 2015-08-01.
  13. ^ a b c . Encyclopedia Astronautica. Archived from the original on 2006-06-14. Retrieved 2015-07-31.
  14. ^ a b "Двигательная установка. 11Д58МФ" [The propulsion system. 11D58MF] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  15. ^ "Research and development". www.krasm.com (in Russian). JSC Krasnoyarsk Machine-Building Plant. Retrieved 2015-06-10.
  16. ^ "2014-02-28 Our Krasnoyarsk Krai "Krasmash. Future projects"". www.krasm.com (in Russian). JSC Krasnoyarsk Machine-Building Plant. Retrieved 2015-06-10.
  17. ^ Galina Yakovleva (2014-11-10). "Владимир КолмыКоВ: "Перед Красмашем стоят серьезные задачи"" [Vladimir Kolmykov: "Serious challenges ahead for Krasmash"] (PDF). Журнал "Синева" [Magazine "Sineva"] (in Russian). 2014 (Sineva № 7-8): 2. Retrieved 2015-08-03.
  18. ^ a b "Двигательная установка. 11Д58" [The propulsion system. 11D58] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  19. ^ a b . Encyclopedia Astronautica. Archived from the original on March 19, 2002. Retrieved 2015-07-31.
  20. ^ a b . Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  21. ^ a b . Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  22. ^ a b "Двигательная установка. 11Д58С" [The propulsion system. 11D58S] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  23. ^ a b . Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  24. ^ . Encyclopedia Astronautica. Archived from the original on March 19, 2002. Retrieved 2015-07-31.
  25. ^ "Энергия, Ракетно-Космическая Корпорация имени С.П.Королева, открытое акционерное общество" [Open Joint Stock Company S.P. Korolev Rocket and Space Corporation Energia] (PDF) (in Russian). K204. 1998-10-12. Retrieved 2015-08-03.

January 06, 2023
manufacturer, designation, 11d58, rocket, engine, developed, 1960s, energia, project, managed, mikhail, melnikov, based, previous, 5400, which, first, staged, combustion, engine, world, engine, initially, created, power, block, stage, soviet, union, abortive, . The RD 58 manufacturer designation 11D58 is a rocket engine developed in the 1960s by OKB 1 now RKK Energia The project was managed by Mikhail Melnikov and it was based on the previous S1 5400 which was the first staged combustion engine in the world 1 The engine was initially created to power the Block D stage of the Soviet Union s abortive N 1 rocket 5 Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets 6 An alternative version of the RD 58 chamber featuring a shorter nozzle was used as the N 1 s roll control engine RD 58MCountry of originUSSRFirst flight1967DesignerOKB 1 V M MelnikovManufacturerVoronezh Mechanical PlantApplicationUpper StageAssociated LVN 1 Proton K Proton M ZenitPredecessorS1 5400StatusIn ProductionLiquid fuel enginePropellantLOX RP 1CycleOxidizer Rich Staged CombustionConfigurationChamber1PerformanceThrust vacuum79 46 kilonewtons 17 860 lbf Specific impulse vacuum353 sBurn timeup to 600 sDimensionsDry weight300 kilograms 660 lb Used inBlock DReferencesReferences 1 2 3 4 The RD 58 uses LOX as the oxidizer and RG 1 as fuel in an oxidizer rich staged combustion cycle It features a single gimbaled chamber radial centrifugal pumps with auxiliary booster pumps and an oxygen rich preburner 7 Recent modifications include a lightweight carbon composite nozzle extender developed by NPO Iskra 8 9 10 The Buran spacecraft used two of an evolution of the RD 58M called 17D12 as its main orbital correction engines Instead of RG 1 it burned Syntin and could be ignited 15 times 11 12 It is assumed that it was the base for the RD 58S which had practically the same specifications and powered the Blok DM 2M 13 But the manufacturer states that the engine is compatible with both propellants 1 The current version of the engine is the RD 58M manufacturer designation 11D58M which has slightly reduced thrust but increased isp An even newer version is under development and is known as the RD 58MF manufacturer designation 11D58MF It will reduce thrust to 49 03 kilonewtons 11 020 lbf to keep the same length but increase expansion ratio to 500 1 This will enable it to gain 20s of isp to an expected 372s It will eventually fly on the Blok DM 03 14 This new version of the engine will be built in the Krasnoyarsk Machine Building Plant 15 16 During a November 2014 interview Vladimir Kolmykov the Deputy General Director of the Chemical Division of Krasnoyarsk Machine Building Plant stated that the production of Block DM was suspended during that year but work on the stage and development of the RD 58MF will resume during 2015 17 Versions EditThis engine has had many versions through the years RD 58 GRAU Index 11D58 Original version developed for the Blok D of the N1 rocket 5 18 RD 58M GRAU Index 11D58M Improved version developed for the Proton rocket Blok D 7 19 RD 58M Carbon carbon nozzle Version of the RD 58M that replaces the regeneratively cooled nozzle for a carbon carbon extension manufactured by NPO Iskra Used on Zenit 3SL s Blok DM SL since June 10 2003 on the Thuraya 2 launch 8 9 10 RD 58MF GRAU Index 11D58MF Reduced thrust and increased specific impulse version expected to fly on the Proton and Zenit rocket Blok DM 03 Will probably also use a carbon carbon nozzle extension 20 RD 58S GRAU Index 11D58S Version designed to use Syntin synthetic propellant rather than RG 1 Used on the Blok DM 2M Probably developed based on the 17D12 13 21 22 RD 58Z GRAU Index 11D58Z Version adapted to the Zenit Blok DM SL 9 23 17D12 Orbital maneuvering engines DOM of the Buran propulsion system 17D11 burned Syntin LOX 11 12 24 RD 58 Family of Engines Name RD 58 RD 58M RD 58M Carbon Composite Nozzle RD 58S RD 58Z RD 58MF 17D12Index 11D58 11D58M 11D58S 11D58Z 11D58MFDevelopment years 1964 1968 1970 1974 2000 2004 1986 1995 1981 1990 2002 2009 1981 1987Engine Type Oxidizer Rich Stage Combustion upper stage liquid rocket engine Orbital correction liquid rocket enginePropellant RG 1 LOX RG 1 LOX RG 1 LOX Syntin LOX RG 1 LOX RG 1 LOX Syntin LOXO F 2 48 2 48 2 82 2 6 2 82 Chamber Pressure 7 8 MPa 1 130 psi 7 75 MPa 1 124 psi 7 9 MPa 1 150 psi 7 94 MPa 1 152 psi 7 8 MPa 1 130 psi 7 9 MPa 1 150 psi 7 94 MPa 1 152 psi Thrust Vac 83 4 kN 18 700 lbf 83 4 kN 18 700 lbf 85 kN 19 000 lbf 86 3 kN 19 400 lbf 71 kN 16 000 lbf 49 03 kN 11 020 lbf 86 24 kN 19 390 lbf Isp Vac 349 s 3 42 km s 356 s 3 49 km s 361 s 3 54 km s 361 s 3 54 km s 361 s 3 54 km s 372 s 3 65 km s 362 s 3 55 km s Nozzle Expansion 189 189 280 189 189 500 189Ignitions 4 4 7 5 5 15Burntime 600 seconds 720 seconds 1200 seconds 680 seconds 660 seconds seconds 680 secondsLength 2 27 m 89 in 2 27 m 89 in 2 72 m 107 in 2 27 m 89 in 2 27 m 89 in 2 27 m 89 in Diameter 1 17 m 46 in 1 17 m 46 in 1 4 m 55 in 1 17 m 46 in 1 17 m 46 in 1 17 m 46 in Weight 300 kg 660 lb 310 kg 680 lb 340 kg 750 lb 310 kg 680 lb 300 kg 660 lb 230 kg 510 lb Used on N 1 and Blok D Blok DM Blok DM SL since 2003 and Blok DM SLB Blok DM 2M Blok DM SL 11S861 03 BuranFirst Launch 1967 03 10 1974 03 26 2003 06 10 1994 10 13 1999 03 28 1988 11 15Status Retired Retired In Production Retired Retired In Production RetiredReferences 2 5 6 7 8 9 11 12 13 14 18 19 20 21 22 23 25 References Edit a b c Engines RSC Energiya Official Page RSC Energiya Retrieved 2015 08 01 a b DESCRIPTION OF ZENIT 2SLB ZENIT 3SLB ZENIT 3SLBF INTEGRATED LAUNCH VEHICLES Land Launch User s Guide Revision B PDF Space International Services 2014 10 01 p 29 Archived from the original PDF on 2016 06 25 Retrieved 2015 06 03 Kiselev Anatoli I Medvedev Alexander A Menshikov Valery A 2012 Section 2 2 2 Carrier rocket booster units Astronautics Summary and Prospects Springer Science amp Business Media pp 304 305 ISBN 978 3709106488 Zak Anatoly Block D upper stage russianspaceweb com Retrieved 2015 06 03 a b c RD 58 Encyclopedia Astronautica Archived from the original on 2016 08 03 Retrieved 2015 07 31 a b Zenit 3SL Spaceflight 101 Retrieved July 14 2014 a b c Dvigatelnaya ustanovka 11D58M The propulsion system 11D58M in Russian Ecoruspace Retrieved 2015 07 31 a b c Sokolovskiy M I Petukhov S N Semenov Yu P Sokolov B A 2008 Razrabotka uglerod uglerodnogo soplovogo nasadka dlya zhidkostnyh raketnyh dvigatelej The development of carbon carbon nozzle extension for liquid rocket engines PDF Thermophysics and Aeromechanics in Russian 15 N 4 721 727 Retrieved 2015 08 02 a b c d Mezhevov A V Skoromnov V I Kozlov A V Tupitsin N N Khaskekov V G 2006 Vnedreniesoplovogo nasadka radiacionnogo ohlazhdeniya iz uglerod uglerodnogo kompozicionnogo materiala na kameru marshevogo dvigatelya 11D58M razgonnogo Bloka DM SL Installation of a Radiation Cooled Nozzle of Carbon Carbon Composite Material to the Combustion Chamber of Main Engine 11D58M of Block DM SL PDF Vestnik SGAU Bulletin SSAU in Russian RSC Energia 2 2 10 2006 Retrieved 2015 08 01 a b Razdvizhnye sopla i soplovye nasadki dlya RDTT i ZhRD Extendable nozzle and nozzle extensions for SRM and LRE www npoiskra ru in Russian NPO Iskra Archived from the original on 4 March 2016 a b c 17D12 Encyclopedia Astronautica Archived from the original on 2016 08 03 Retrieved 2015 07 31 a b c Hendrickx Bart Vis Bert 2007 10 04 Energiya Buran The Soviet Space Shuttle UK 2007 ed Springer pp 127 131 ISBN 978 0 387 69848 9 Retrieved 2015 08 01 a b c Block DM 2M 11S861 01 Encyclopedia Astronautica Archived from the original on 2006 06 14 Retrieved 2015 07 31 a b Dvigatelnaya ustanovka 11D58MF The propulsion system 11D58MF in Russian Ecoruspace Retrieved 2015 07 31 Research and development www krasm com in Russian JSC Krasnoyarsk Machine Building Plant Retrieved 2015 06 10 2014 02 28 Our Krasnoyarsk Krai Krasmash Future projects www krasm com in Russian JSC Krasnoyarsk Machine Building Plant Retrieved 2015 06 10 Galina Yakovleva 2014 11 10 Vladimir KolmyKoV Pered Krasmashem stoyat sereznye zadachi Vladimir Kolmykov Serious challenges ahead for Krasmash PDF Zhurnal Sineva Magazine Sineva in Russian 2014 Sineva 7 8 2 Retrieved 2015 08 03 a b Dvigatelnaya ustanovka 11D58 The propulsion system 11D58 in Russian Ecoruspace Retrieved 2015 07 31 a b RD 58M Encyclopedia Astronautica Archived from the original on March 19 2002 Retrieved 2015 07 31 a b RD 58MF Encyclopedia Astronautica Archived from the original on 2016 08 03 Retrieved 2015 07 31 a b RD 58S Encyclopedia Astronautica Archived from the original on 2016 08 03 Retrieved 2015 07 31 a b Dvigatelnaya ustanovka 11D58S The propulsion system 11D58S in Russian Ecoruspace Retrieved 2015 07 31 a b RD 58Z Encyclopedia Astronautica Archived from the original on 2016 08 03 Retrieved 2015 07 31 17D11 Encyclopedia Astronautica Archived from the original on March 19 2002 Retrieved 2015 07 31 Energiya Raketno Kosmicheskaya Korporaciya imeni S P Koroleva otkrytoe akcionernoe obshestvo Open Joint Stock Company S P Korolev Rocket and Space Corporation Energia PDF in Russian K204 1998 10 12 Retrieved 2015 08 03 Retrieved from https en wikipedia org w index php title RD 58 amp oldid 1129935198, wikipedia, wiki, book, books, library,

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