RD-0410: Difference between revisions
Content deleted Content added
No edit summary |
No edit summary |
||
| Line 1: | Line 1: | ||
'''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 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"/> |
||
This engine had slightly higher performance (exhaust temperature and specific impulse) over [[NERVA]] (the U.S. nuclear thermal rocket engine project), but much less thrust: only 35.2 kN compared to 333.6 kN of NERVA. The design of the reactor core included thermal insulation between [[uranium carbide]]/tungsten carbide fuel and the [[zirconium hydride]] moderator. This solution 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 pct of [[heptane]] was added to the hydrogen after the moderator passage. |
This engine had slightly higher performance (exhaust temperature and specific impulse) over [[NERVA]] (the U.S. nuclear thermal rocket engine project), but much less thrust: only 35.2 kN compared to 333.6 kN of NERVA. (Remember NERVA at 178+ tons could not be flown to space). The design of the reactor core included thermal insulation between [[uranium carbide]]/tungsten carbide fuel and the [[zirconium hydride]] moderator. This solution 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 pct of [[heptane]] was added to the hydrogen after the moderator passage. |
||
The hydrogen boost turbopump was designed by [[KBKhA]] in [[Voronezh]].<ref>{{cite conference |
The hydrogen boost turbopump was designed by [[KBKhA]] in [[Voronezh]].<ref>{{cite conference |
||
Revision as of 17:04, 17 June 2015
RD-0410 (РД-0410, GRAU index: 11B91) was a Soviet nuclear thermal rocket engine developed from 1965 through the 1980s using liquid hydrogen propellant.[1] The engine was ground-tested at the Semipalatinsk Test Site,[2] and its use was incorporated in the Kurchatov Mars 1994 manned mission proposal.[1]
This engine had slightly higher performance (exhaust temperature and specific impulse) over NERVA (the U.S. nuclear thermal rocket engine project), but much less thrust: only 35.2 kN compared to 333.6 kN of NERVA. (Remember NERVA at 178+ tons could not be flown to space). The design of the reactor core included thermal insulation between uranium carbide/tungsten carbide fuel and the zirconium hydride moderator. This solution 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 pct of heptane was added to the hydrogen after the moderator passage.
The hydrogen boost turbopump was designed by KBKhA in Voronezh.[3]
See also
- Nuclear Thermal Rocket
- NERVA, the American project for nuclear thermal propulsion
References
- ^ a b Wade, Mark. "RD-0410". Encyclopedia Astronautica. Retrieved 2009-09-25.
- ^ ""Konstruktorskoe Buro Khimavtomatiky" - Scientific-Research Complex / RD0410. Nuclear Rocket Engine. Advanced launch vehicles". KBKhA - Chemical Automatics Design Bureau. Retrieved 2009-09-25.
- ^ 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.
{{cite conference}}: Unknown parameter|booktitle=ignored (|book-title=suggested) (help)
Further reading
- Soviet Mars Propulsion - Nuclear Thermal astronautix.com
- Popular Mechanics article in Russian
- Russian article
- Russian video about RD-0410 Rocket (Russian)
| Liquid fuel |
|  | ||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Solid fuel |
| |||||||||||||||||
| ||||||||||||||||||
 | This rocketry article is a stub. You can help Wikipedia by expanding it. |