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{{Short description|Soviet rocket engine}}
{{For | the Dominican Republic national highway #8 | DR-8 }}
{{Refimprove|date=December 2009}}
{{Infobox rocket engine
{{Infobox rocket engine
|name = RD-8 (РД-8)
|name = RD-8 (РД-8)
|image =
|image =
|image_size = 225
|image_size =
|caption = Photo of rocket engine ''RD-8''.
|caption =
|country_of_origin = [[USSR]]/[[Russia]]
|country_of_origin = [[Soviet Union]]
|date =
|date =
|first_date = April 13, 1985
|manufacturer = [[Yuzhnoye Design Bureau]]
|designer =
|last_date =
|status = Operational
|designer = [[Yuzhnoye Design Bureau]]
|purpose = Upper stage vernier
|manufacturer = [[Yuzhmash]]
|type = Liquid
|purpose = Second Stage Vernier
|fuel = rocket grade [[kerosene]]
|associated = [[Zenit (rocket family)|Zenit]]
|oxidiser = [[LOX]]
|predecessor =
|cycle = [[Staged combustion]]
|successor = RD-809M
|status = In Production
|thrust(Vac) = {{convert|78.5|kN|lbf}}<ref name="whatever">[http://www.nkau.gov.ua/nsau/productnsau2.nsf/09e578a9237d8923c2256f9700336d37/3e2b55cce321c673c2256faf005ca84d!OpenDocument RD-8 rocket engine]</ref>
|type = liquid
⚫
|specific_impulse_vacuum = {{convert|342|isp}}
|oxidiser = [[LOX]]
|operating_time = 1100 seconds
|fuel = [[RG-1 (propellant)|RG-1]]
⚫
|chamber_pressure = {{convert|7.8|MPa|psi}}<ref name="whatever" />
|mixture_ratio = 2.4
⚫
|thrust_to_weight =
|cycle = [[Staged combustion cycle (rocket)|Staged Combustion]]
⚫
|length =
|diameter =
|pumps =
⚫
|description =
⚫
|dry_weight = {{convert|380|kg|lb}}
|combustion_chamber = 4
⚫
|used_in = [[Zenit-2]], Zenit-3SL upper stage
|nozzle_ratio =
|thrust =
|thrust_at_altitude =
|thrust(Vac) = {{convert|78.45|kN|abbr=on}}<!--if throttle range >100%, specify corresponding throttle-->
|thrust(SL) =
|throttle_range = <!--leave blank if no throttle-->
⚫
|thrust_to_weight =
⚫
|chamber_pressure = {{convert|7.747|MPa|abbr=on}}
|specific_impulse =
⚫
|specific_impulse_vacuum = {{convert|342|isp|abbr=on}}
|specific_impulse_sea_level =
|total_impulse =
|burn_time = 1100 s
|restarts = <!--leave blank if not restartable-->
|gimbal = ±33°<!--gimbal range in °, leave blank if none-->
|capacity =
|dimensions =
|length = {{convert|1500|mm|abbr=on}}
|diameter = {{convert|4000|mm|abbr=on}}
⚫
|dry_weight = {{convert|380|kg|abbr=on}}
⚫
|used_in = [[Zenit (rocket family)|Zenit]] family second stage
|references = <ref name=gunter-zenit /><ref name=b14643-ukrainepropulsion /><ref name=khai-aktt201301p4450 /><ref name=ukrspexport-rd8 /><ref name=yuzhnoye-rd8 /><ref name=yuzhmash-rd8 />
|notes =
}}
}}


The '''RD-8''' (Russian: {{lang|ru|'''РД-8'''}} and [[GRAU]] Index: '''11D513''') is a [[Soviet Union|Soviet]] / Ukrainian [[liquid-fuel rocket|liquid propellant rocket engine]] burning [[LOX]] and [[RG-1 (propellant)|RG-1]] (a rocket grade [[kerosene]]) in an [[Staged combustion cycle (rocket)|oxidizer rich staged combustion cycle]].<ref name=yuzhnoye-rd8 /><ref name=yuzhmash-rd8 /> It has a four combustion chambers that provide [[Thrust vectoring|thrust vector control]] by [[Gimbaled thrust|gimbaling]] each of the nozzles in a single axis ±33°.<ref name=b14643-ukrainepropulsion /> It was designed in [[Dnipropetrovsk]] by the [[Yuzhnoye Design Bureau]] as the [[vernier thruster]] of the [[Zenit (rocket family)|Zenit]] (GRAU: 11K77) second stage.<ref name=aviadvigatel /> As such, it has always been paired with the [[RD-120]] engine for main propulsion.<ref name=hendrickx2007p80 /><ref name=gunter-zenit />
The '''RD-8''' engine was developed by [[Yuzhnoye Design Bureau]] for the second stage of the [[Zenit rocket]]. It has four hinged chambers and a single turbopump unit. The fuel pair is [[LOX]]/[[kerosene]]. Vacuum thrust is 78.5&nbsp;[[Newton (unit)|kN]] and its specific impulse in vacuum is {{convert|342|isp}}.<ref name="yuzzi">[http://www.yuzhnoye.com/?id=156&lang=en&path=Aerospace%20Technology/Rocket%20Propulsion/Liquid%20Engines/Vernier%20Engines/RD-8/RD-8_e Yuzhnoye SDO - RD-8 Engine]</ref>


It can only be started once, and as a high altitude engine it has a thrust of {{convert|78.45|kN|abbr=on}} and a [[specific impulse]] of {{convert|342|isp|abbr=on}}.<ref name=yuzhnoye-rd8 /><ref name=yuzhmash-rd8 /> It is the first ever steering engine to use the staged combustion cycle, and as such is the basis for a family of planned engines for the [[Mayak (rocket family)|Mayak]] [[launch vehicle]] family.<ref name=khai-aktt201301p4450 />
The engine was designed for long service life (up to 4000 seconds), high reliability, and is the first smaller upper stage engine to use the staged combustion cycle.<ref name="yuzzi" />


The engine itself is built like a hollow cylinder, with a cylindrical space in the center so the RD-120 nozzle can pass through.<ref name=rsw-zenitstage2 />
⚫
== References ==
{{Reflist}}


==Derivatives==
⚫
{{Rocket Engines}}
Whilst [[Yuzhnoye Design Bureau|Yuzhnoye]]'s propulsion experience had been mostly on [[hypergolic propellant]]s engines, like [[RD-855]] or [[RD-861]], they are considered too toxic for current ecological standards.<ref name=aviadvigatel /><ref name=hendrickx2007p80 /> While Yuzhnoye still offer to develop hypergolic propulsion, such as [[RD-843]] for the [[Vega (rocket)|Vega]]'s [[AVUM]] stage or the [[Tsyklon-4]] project, Yuzhnoye selected a more environmentally friendly [[LOX]] and [[kerosene]] propellant for the [[Mayak (rocket family)|Mayak]] launch vehicle family.<ref name=khai-aktt201301p4450 />

Not only had Yuzhnoye mastered the most complex cycle for the propellant ([[Staged combustion cycle (rocket)|oxidizer rich staged combustion cycle]]) with the RD-8, but they had worked closely with [[NPO Energomash]] during the [[RD-120]] program. The manufacturing is done at its sister company of [[Yuzhmash]] in Dnipropetrovsk, and the RD-120 thrust augmentation project of 2001 to 2003 had been a mixed project between the three companies.<ref name=khai-aktt201301p4450 />

On the base of this experience, a family of derivatives engines were proposed. While the [[RD-801]] and [[RD-810]] are really just based on the general technology, the other members of the family are related enough that they reuse many components of the RD-8.<ref name=khai-aktt201301p4450 /> One characteristic of this family is the limitation of keeping the preburner output temperature below {{convert|500|C|abbr=on}}.<ref name=khai-aktt201301p4450 />

* '''RD-805''' (or '''RD-802'''): A proposed upper stage engine of just {{convert|19.62|kN|abbr=on}} of thrust, it would use a single chamber of the RD-8.<ref name=ukrspexport-rd802 /> While many new components would be required, it is considered a low technological risk since it only needs smaller versions of already developed component.<ref name=khai-aktt201301p4450 />
* '''RD-809''' (sometimes identified as '''RD-809M'''): It is an RD-8 re arranged to minimize its diameter. It would use practically every single component of the RD-8, but arranged without the big hollow section in the middle. It was a proposed engine for a proposed liquid upper stage of the [[Antares (rocket)|Antares]] rocket, then named Taurus II.<ref name=khai-aktt201301p4450 /> It would be capable of five engine burns in a single mission.<ref name=yuzhnoye-rd809 />
* '''RD-809K''': A proposed single nozzle version of the RD-8. It would mix most principal elements of the RD-8 like the turbopumps with a main combustion chamber and nozzle adapted from the [[RD-861K]].<ref name=khai-aktt201301p4450 /><ref name=yuzhnoye-rd809K /> It would be capable of 4 starts in a single mission.<ref name=yuzhnoye-rd809K /> It is expected to be used in a dual engine configuration in the Mayak upper stage.<ref name=khai-aktt201301p4450 />

==See also==
*[[RD-120]] – The [[Zenit (rocket family)|Zenit]] second stage main engine which is the companion of the RD-8 and the basis for some of its derivatives.
*[[Zenit (rocket family)|Zenit]] – The launch vehicle family for which the RD-8 was developed.
*[[Mayak (rocket family)|Mayak]] – Prospective [[Ukraine|Ukrainian]] launch vehicle family for which the RD-805, RD-809 and RD-809K are being developed.
*[[Yuzhnoe Design Bureau]] - The RD-8 designer bureau.
*[[Yuzhmash]] - A multi-product machine-building company that's closely related to Yuzhnoe and manufactures the RD-8.

⚫
==References==
{{reflist|refs=
<ref name=aviadvigatel>{{cite web |url=http://www.k204.ru/books/Aviadvigatel2.pdf |title=Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные |trans-title=Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry |pages=265–266 |language=ru |access-date=2015-07-25}}</ref>
<ref name=b14643-ukrainepropulsion>{{cite web |url=http://www.b14643.de/Spacerockets/Diverse/Ukrainian_Rocket_engines/engines.htm |title=Ukrainian space-rocket and missile liquid-propellant engines |first=Norbert |last=Brügge |publisher=B14643.de |date=2016-07-11 |access-date=2016-07-14 }}{{dead link|date=April 2018 |bot=InternetArchiveBot |fix-attempted=yes }}</ref>
<ref name=gunter-zenit>{{cite web |url=http://space.skyrocket.de/doc_lau_fam/zenit.htm |title=Zenit family |publisher=Gunter's Space Page |author=Gunter Dirk Krebs |date=2015-12-15 |access-date=2016-07-14}}</ref>
<ref name=hendrickx2007p80>{{cite book |url=https://books.google.com/books?id=VRb1yAGVWNsC&dq=RD-8&pg=PA80 |last1=Hendrickx |first1=Bart |last2=Vis |first2=Bert |title=Energiya-Buran: The Soviet Space Shuttle |publisher=Springer |isbn=978-0-387-69848-9 |pages=80 |edition=UK 2007 |date=2007-10-04}}</ref>
<ref name=khai-aktt201301p4450>{{cite journal |last1=Degtyarev |first1=A . V. |last2=Shulga |first2=V . A. |last3=Zhivotov |first3=A . I. |last4=Dibrivny |first4=A . V. |title=Создание семейства кислородно-керосиновых жидкостных ракетных двигателей на базе отработанных технологий для перспективных ракет-носителей гп "Кб «Южное" |journal=Авиационно - космическая техника и технология |date=2013 |volume=2013 nr. 01 |issue=98 |pages=44–50 |url=http://www.khai.edu/csp/nauchportal/Arhiv/AKTT/2013/AKTT113/Degtyar.pdf |access-date=2016-07-14 |trans-title=The development of LOX - kerosene liquid rocket engines family for perspective launch vehicles of SDO Yuzhnoye based on proven technologies |publisher=National Aerospace university them. NE Zhukovsky |language=ru |issn=1727-7337 |archive-url=https://web.archive.org/web/20160816211603/http://www.khai.edu/csp/nauchportal/Arhiv/AKTT/2013/AKTT113/Degtyar.pdf |archive-date=2016-08-16 |url-status=dead }}</ref>
<ref name=rsw-zenitstage2>{{cite web |url=http://www.russianspaceweb.com/zenit_stage2.html |title=Stage II of the Zenit rocket |last=Zak |first=Anatoly |publisher=Russian Space Web |date=2013-01-31 |access-date=2016-07-14}}</ref>
<ref name=ukrspexport-rd8>{{cite web |url=http://catalog.use.kiev.ua/index.php?page=catalog&cat_id=30&view=product&id=282 |title=RD-8 |publisher=Defense Industry Of Ukraine Products And Services |access-date=2016-07-14 |archive-url=https://web.archive.org/web/20160818174749/http://catalog.use.kiev.ua/index.php?page=catalog&cat_id=30&view=product&id=282 |archive-date=2016-08-18 |url-status=dead }}</ref>
<ref name=ukrspexport-rd802>{{cite web |url=http://catalog.use.kiev.ua/index.php?page=catalog&cat_id=30&view=product&id=285 |title=RD-802 |publisher=Defense Industry Of Ukraine Products And Services |access-date=2016-07-14}}</ref>
<ref name=yuzhnoye-rd8>{{cite web |url=http://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-8/ |title=RD-8 |publisher=Yuzhnoye |access-date=2016-07-14 |archive-url=https://web.archive.org/web/20160709080344/http://www.yuzhnoye.com/en/technique/rocket-engines/steering/rd-8/ |archive-date=2016-07-09 |url-status=dead }}</ref>
<ref name=yuzhnoye-rd809>{{cite web |url=http://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-809/ |title=RD-809 |publisher=Yuzhnoye |access-date=2016-07-14}}</ref>
<ref name=yuzhnoye-rd809K>{{cite web |url=http://www.yuzhnoye.com/en/technique/rocket-engines/marching/rd-809k/ |title=RD-809K |publisher=Yuzhnoye |access-date=2016-07-14}}</ref>
<ref name=yuzhmash-rd8>{{cite web |url=http://www.yuzhmash.com/production/index/rengines?id=15 |title=Liquid rocket engine RD-8 |publisher=Yuzhmash |access-date=2016-07-14}}</ref>
}}

==External links==
* [http://www.yuzhnoye.com/en/home/ Yuzhnoye Design Bureau English-language home page] {{Webarchive|url=https://web.archive.org/web/20210629020706/https://www.yuzhnoye.com/en/home/ |date=2021-06-29 }}
* [http://www.yuzhmash.com/ Yuzhmash Home Page]

⚫
{{Rocket engines}}
{{Russian and Soviet military designation sequences}}
{{Russian and Soviet military designation sequences}}


{{Rocket-stub}}
{{DEFAULTSORT:Rd-8 (Rocket Engine)}}
{{DEFAULTSORT:Rd-8 (Rocket Engine)}}
⚫
[[Category:Rocket engines of Russia]]
[[Category:Rocket engines of the Soviet Union]]
[[Category:Rocket engines of the Soviet Union]]
[[Category:Rocket engines using kerosene propellant]]
[[Category:Rocket engines using kerosene propellant]]
[[Category:Rocket engines using the staged combustion cycle]]
[[Category:Yuzhnoye rocket engines]]
[[Category:Yuzhmash rocket engines]]
⚫
[[Category:Rocket engines of Ukraine]]

Latest revision as of 19:29, 4 October 2023

RD-8 (РД-8)
Country of originSoviet Union
First flightApril 13, 1985
DesignerYuzhnoye Design Bureau
ManufacturerYuzhmash
ApplicationSecond Stage Vernier
Associated LVZenit
SuccessorRD-809M
StatusIn Production
Liquid-fuel engine
PropellantLOX / RG-1
Mixture ratio2.4
CycleStaged Combustion
Configuration
Chamber4
Performance
Thrust, vacuum78.45 kN (17,640 lbf)
Chamber pressure7.747 MPa (1,123.6 psi)
Specific impulse, vacuum342 s (3.35 km/s)
Burn time1100 s
Gimbal range±33°
Dimensions
Length1,500 mm (59 in)
Diameter4,000 mm (160 in)
Dry weight380 kg (840 lb)
Used in
Zenit family second stage
References
References[1][2][3][4][5][6]

The RD-8 (Russian: РД-8 and GRAU Index: 11D513) is a Soviet / Ukrainian liquid propellant rocket engine burning LOX and RG-1 (a rocket grade kerosene) in an oxidizer rich staged combustion cycle.[5][6] It has a four combustion chambers that provide thrust vector control by gimbaling each of the nozzles in a single axis ±33°.[2] It was designed in Dnipropetrovsk by the Yuzhnoye Design Bureau as the vernier thruster of the Zenit (GRAU: 11K77) second stage.[7] As such, it has always been paired with the RD-120 engine for main propulsion.[8][1]

It can only be started once, and as a high altitude engine it has a thrust of 78.45 kN (17,640 lbf) and a specific impulse of 342 s (3.35 km/s).[5][6] It is the first ever steering engine to use the staged combustion cycle, and as such is the basis for a family of planned engines for the Mayak launch vehicle family.[3]

The engine itself is built like a hollow cylinder, with a cylindrical space in the center so the RD-120 nozzle can pass through.[9]

Derivatives[edit]

Whilst Yuzhnoye's propulsion experience had been mostly on hypergolic propellants engines, like RD-855 or RD-861, they are considered too toxic for current ecological standards.[7][8] While Yuzhnoye still offer to develop hypergolic propulsion, such as RD-843 for the Vega's AVUM stage or the Tsyklon-4 project, Yuzhnoye selected a more environmentally friendly LOX and kerosene propellant for the Mayak launch vehicle family.[3]

Not only had Yuzhnoye mastered the most complex cycle for the propellant (oxidizer rich staged combustion cycle) with the RD-8, but they had worked closely with NPO Energomash during the RD-120 program. The manufacturing is done at its sister company of Yuzhmash in Dnipropetrovsk, and the RD-120 thrust augmentation project of 2001 to 2003 had been a mixed project between the three companies.[3]

On the base of this experience, a family of derivatives engines were proposed. While the RD-801 and RD-810 are really just based on the general technology, the other members of the family are related enough that they reuse many components of the RD-8.[3] One characteristic of this family is the limitation of keeping the preburner output temperature below 500 °C (932 °F).[3]

  • RD-805 (or RD-802): A proposed upper stage engine of just 19.62 kN (4,410 lbf) of thrust, it would use a single chamber of the RD-8.[10] While many new components would be required, it is considered a low technological risk since it only needs smaller versions of already developed component.[3]
  • RD-809 (sometimes identified as RD-809M): It is an RD-8 re arranged to minimize its diameter. It would use practically every single component of the RD-8, but arranged without the big hollow section in the middle. It was a proposed engine for a proposed liquid upper stage of the Antares rocket, then named Taurus II.[3] It would be capable of five engine burns in a single mission.[11]
  • RD-809K: A proposed single nozzle version of the RD-8. It would mix most principal elements of the RD-8 like the turbopumps with a main combustion chamber and nozzle adapted from the RD-861K.[3][12] It would be capable of 4 starts in a single mission.[12] It is expected to be used in a dual engine configuration in the Mayak upper stage.[3]

See also[edit]

  • RD-120 – The Zenit second stage main engine which is the companion of the RD-8 and the basis for some of its derivatives.
  • Zenit – The launch vehicle family for which the RD-8 was developed.
  • Mayak – Prospective Ukrainian launch vehicle family for which the RD-805, RD-809 and RD-809K are being developed.
  • Yuzhnoe Design Bureau - The RD-8 designer bureau.
  • Yuzhmash - A multi-product machine-building company that's closely related to Yuzhnoe and manufactures the RD-8.

References[edit]

  1. ^ a b Gunter Dirk Krebs (2015-12-15). "Zenit family". Gunter's Space Page. Retrieved 2016-07-14.
  2. ^ a b Brügge, Norbert (2016-07-11). "Ukrainian space-rocket and missile liquid-propellant engines". B14643.de. Retrieved 2016-07-14.[permanent dead link]
  3. ^ a b c d e f g h i j Degtyarev, A . V.; Shulga, V . A.; Zhivotov, A . I.; Dibrivny, A . V. (2013). "Создание семейства кислородно-керосиновых жидкостных ракетных двигателей на базе отработанных технологий для перспективных ракет-носителей гп "Кб «Южное"" [The development of LOX - kerosene liquid rocket engines family for perspective launch vehicles of SDO Yuzhnoye based on proven technologies] (PDF). Авиационно - космическая техника и технология (in Russian). 2013 nr. 01 (98). National Aerospace university them. NE Zhukovsky: 44–50. ISSN 1727-7337. Archived from the original (PDF) on 2016-08-16. Retrieved 2016-07-14.
  4. ^ "RD-8". Defense Industry Of Ukraine Products And Services. Archived from the original on 2016-08-18. Retrieved 2016-07-14.
  5. ^ a b c "RD-8". Yuzhnoye. Archived from the original on 2016-07-09. Retrieved 2016-07-14.
  6. ^ a b c "Liquid rocket engine RD-8". Yuzhmash. Retrieved 2016-07-14.
  7. ^ a b "Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные" [Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry] (PDF) (in Russian). pp. 265–266. Retrieved 2015-07-25.
  8. ^ a b Hendrickx, Bart; Vis, Bert (2007-10-04). Energiya-Buran: The Soviet Space Shuttle (UK 2007 ed.). Springer. p. 80. ISBN 978-0-387-69848-9.
  9. ^ Zak, Anatoly (2013-01-31). "Stage II of the Zenit rocket". Russian Space Web. Retrieved 2016-07-14.
  10. ^ "RD-802". Defense Industry Of Ukraine Products And Services. Retrieved 2016-07-14.
  11. ^ "RD-809". Yuzhnoye. Retrieved 2016-07-14.
  12. ^ a b "RD-809K". Yuzhnoye. Retrieved 2016-07-14.

External links[edit]

Retrieved from "https://en.wikipedia.org/w/index.php?title=RD-8&oldid=1178611236"