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'''RD-0410''' (РД-0410, [[GRAU index]]: 11B91) was a Soviet [[nuclear thermal rocket]] engine developed from 1965 through the 1980s using [[liquid hydrogen]] propellant.<ref name="astronautix1">{{cite web|url=http://www.astronautix.com/engines/rd0410.htm|title=RD-0410 |last=Wade|first=Mark|publisher=[[Encyclopedia Astronautica]]|accessdate=2009-09-25}}</ref> The engine was ground-tested at the [[Semipalatinsk Test Site]],<ref>{{cite web |title=«Konstruktorskoe Buro Khimavtomatiky» - Scientific-Research Complex / RD0410. Nuclear Rocket Engine. Advanced launch vehicles |publisher=KBKhA - [[Chemical Automatics Design Bureau]] |url=http://www.kbkha.ru/?p=8&cat=11&prod=66 |accessdate=2009-09-25}}</ref> and its use was incorporated in the [[List of manned Mars mission plans in the 20th century|Kurchatov Mars 1994]] manned mission proposal.<ref name="astronautix1"/>
'''RD-0410''' (РД-0410, [[GRAU index]]: 11B91) was a Soviet [[nuclear thermal rocket]] engine developed by the [[Chemical Automatics Design Bureau]]<ref>{{Cite web|url=https://kbkha.ru/deyatel-nost/raketnye-dvigateli-ao-kbha/yadernyj-raketnyj-dvigatel-rd0410-rd0411/|title = Ядерный ракетный двигатель РД0410 (РД0411) &#124; АО «Конструкторское Бюро Химавтоматики»}}</ref> in [[Voronezh]] from 1965 through the 1980s using [[liquid hydrogen]] propellant.<ref name="astronautix1">{{cite web|url=http://www.astronautix.com/engines/rd0410.htm|title=RD-0410|last=Wade|first=Mark|publisher=[[Encyclopedia Astronautica]]|access-date=2009-09-25|url-status=dead|archive-url=https://web.archive.org/web/20090408122011/http://www.astronautix.com/engines/rd0410.htm|archive-date=2009-04-08}}</ref> The engine was ground-tested at the [[Semipalatinsk Test Site]],<ref>{{cite web |title="Konstruktorskoe Buro Khimavtomatiky" - Scientific-Research Complex / RD0410. Nuclear Rocket Engine. Advanced launch vehicles |publisher=KBKhA - [[Chemical Automatics Design Bureau]] |url=http://www.kbkha.ru/?p=8&cat=11&prod=66 |access-date=2009-09-25}}</ref> and its use was incorporated in the [[List of crewed Mars mission plans|Kurchatov Mars 1994]] crewed mission proposal.<ref name="astronautix1"/>


This engine had slightly higher performance (exhaust temperature and specific impulse) over [[NERVA]] (the U.S. nuclear thermal rocket engine project). The design of the reactor core included thermal insulation between [[uranium carbide]]/tungsten carbide fuel and the [[zirconium hydride]] moderator. This allowed for a very compact reactor core design. Hydrogen flow cooled the moderator first allowing to keep very low neutron energy and high fission cross-section, then it was heated by the direct contact to the fuel rods. To prevent the chemical reaction between carbide and hydrogen, about 1 percent of [[hexane]] was added to the hydrogen after the moderator passage.<ref>http://www.k204.ru/books/Aviadvigatel2.pdf {{Bare URL PDF|date=August 2024}}</ref>
⚫
The hydrogen boost turbopump was designed by [[KBKhA]].<ref>{{cite conference

⚫
The hydrogen boost turbopump was designed by [[KBKhA]] in [[Voronezh]].<ref>{{cite conference
| first = Y.
| first = Y.
| display-authors = 4
| last = Demyanenko
| last = Demyanenko
| authorlink =
| author2 = A. Dmitrenko
| author3 = A. Ivanov
| coauthors = A. Dmitrenko, A. Ivanov, V. Pershin, A.Shostak, G. Zelkind, A. Minick, R. Bracken
| author4 = V. Pershin| author5 = A. Shostak
| author6 = G. Zelkind| author7 = A. Minick
| author8 = R. Bracken
| title = Ground Test Demonstrator Engine Boost Turbopumps Design and Development
| title = Ground Test Demonstrator Engine Boost Turbopumps Design and Development
| booktitle = 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
| book-title = 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
⚫
| publisher = American Institute of Aeronautics and Astronautics, Inc.
| pages =
⚫
| publisher = American Institute of Aeronautics and Astronautics, Inc.,
| date = July 2005
| date = July 2005
| location = Tucson, Arizona
| location = Tucson, Arizona
| url = http://www.lpre.de/resources/articles/RD0146_Boost_Pump_2005_3945.pdf
| url = http://www.lpre.de/resources/articles/RD0146_Boost_Pump_2005_3945.pdf
⚫
| access-date = 2012-08-21}}</ref>
| doi =
| id =
⚫
| accessdate = 2012-08-21}}</ref>


==See also==
==See also==
* [[NERVA]], the American project for nuclear thermal propulsion
* [[Nuclear thermal rocket]]
* [[TEM (nuclear propulsion)]]
* [[NERVA]]
* [[9M730 Burevestnik]]


==References==
==References==
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==Further reading==
==Further reading==
* [http://www.astronautix.com/articles/sovermal.htm Soviet Mars Propulsion - Nuclear Thermal] astronautix.com
* [https://web.archive.org/web/20071206112445/http://www.astronautix.com/articles/sovermal.htm Soviet Mars Propulsion - Nuclear Thermal] astronautix.com
* [http://www.popmech.ru/part/print.php?rubricid=13&articleid=1523 Popular Mechanics article] in Russian
* [http://www.popmech.ru/article/1141-k-marsu-na-reaktore/ Popular Mechanics article] in Russian
* [http://www.novosti-kosmonavtiki.ru/content/numbers/218/58.shtml Russian article]{{deadlink|date=December 2012}}
* [https://archive.today/20130923123830/http://88.210.62.157/content/numbers/218/58.shtml Russian article]
* [https://www.youtube.com/watch?v=nvZjmj1bopw Russian video about RD-0410 Rocket (Russian)]


{{Rocket Engines}}
{{Nuclear propulsion}}
{{Rocket engines}}


{{DEFAULTSORT:Rd-0410}}
{{DEFAULTSORT:Rd-0410}}
[[Category:Nuclear spacecraft propulsion]]
[[Category:Nuclear spacecraft propulsion]]
[[Category:Rocket engines of the Soviet Union]]




Latest revision as of 13:44, 26 August 2024

RD-0410 (РД-0410, GRAU index: 11B91) was a Soviet nuclear thermal rocket engine developed by the Chemical Automatics Design Bureau[1] in Voronezh from 1965 through the 1980s using liquid hydrogen propellant.[2] The engine was ground-tested at the Semipalatinsk Test Site,[3] and its use was incorporated in the Kurchatov Mars 1994 crewed mission proposal.[2]

This engine had slightly higher performance (exhaust temperature and specific impulse) over NERVA (the U.S. nuclear thermal rocket engine project). The design of the reactor core included thermal insulation between uranium carbide/tungsten carbide fuel and the zirconium hydride moderator. This allowed for a very compact reactor core design. Hydrogen flow cooled the moderator first allowing to keep very low neutron energy and high fission cross-section, then it was heated by the direct contact to the fuel rods. To prevent the chemical reaction between carbide and hydrogen, about 1 percent of hexane was added to the hydrogen after the moderator passage.[4]

The hydrogen boost turbopump was designed by KBKhA in Voronezh.[5]

See also

[edit]

References

[edit]
  1. ^ "Ядерный ракетный двигатель РД0410 (РД0411) | АО «Конструкторское Бюро Химавтоматики»".
  2. ^ a b Wade, Mark. "RD-0410". Encyclopedia Astronautica. Archived from the original on 2009-04-08. Retrieved 2009-09-25.
  3. ^ ""Konstruktorskoe Buro Khimavtomatiky" - Scientific-Research Complex / RD0410. Nuclear Rocket Engine. Advanced launch vehicles". KBKhA - Chemical Automatics Design Bureau. Retrieved 2009-09-25.
  4. ^ http://www.k204.ru/books/Aviadvigatel2.pdf [bare URL PDF]
  5. ^ Demyanenko, Y.; A. Dmitrenko; A. Ivanov; V. Pershin; et al. (July 2005). "Ground Test Demonstrator Engine Boost Turbopumps Design and Development" (PDF). 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Tucson, Arizona: American Institute of Aeronautics and Astronautics, Inc. Retrieved 2012-08-21.

Further reading

[edit]


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