IMECH-IR  > 等离子体与燃烧中心(2009-2011)
Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters
Wang HX; Chen X; Pan WX(潘文霞); Murphy AB; Geng JY; Jia SX
Source PublicationPlasma Science and Technology
2010
Volume12Issue:6Pages:692-701
ISSN1009-0630
AbstractA modelling study is performed to compare the plasma °ow and heat transfer char- acteristics of low-power arc-heated thrusters (arcjets) for three di®erent propellants: hydrogen, nitrogen and argon. The all-speed SIMPLE algorithm is employed to solve the governing equa- tions, which take into account the e®ects of compressibility, Lorentz force and Joule heating, as well as the temperature- and pressure-dependence of the gas properties. The temperature, veloc- ity and Mach number distributions calculated within the thruster nozzle obtained with di®erent propellant gases are compared for the same thruster structure, dimensions, inlet-gas stagnant pressure and arc currents. The temperature distributions in the solid region of the anode-nozzle wall are also given. It is found that the °ow and energy conversion processes in the thruster nozzle show many similar features for all three propellants. For example, the propellant is heated mainly in the near-cathode and constrictor region, with the highest plasma temperature appear- ing near the cathode tip; the °ow transition from the subsonic to supersonic regime occurs within the constrictor region; the highest axial velocity appears inside the nozzle; and most of the input propellant °ows towards the thruster exit through the cooler gas region near the anode-nozzle wall. However, since the properties of hydrogen, nitrogen and argon, especially their molecular weights, speci¯c enthalpies and thermal conductivities, are di®erent, there are appreciable di®er- ences in arcjet performance. For example, compared to the other two propellants, the hydrogen arcjet thruster shows a higher plasma temperature in the arc region, and higher axial velocity but lower temperature at the thruster exit. Correspondingly, the hydrogen arcjet thruster has the highest speci¯c impulse and arc voltage for the same inlet stagnant pressure and arc current. The predictions of the modelling are compared favourably with available experimental results.
Subject Area电磁流体力学和等离子体动力学
DOI10.1088/1009-0630/12/6/11
URL查看原文
Indexed BySCI
Language英语
WOS IDWOS:000286172000011
Citation statistics
Cited Times:10[WOS]   [WOS Record]     [Related Records in WOS]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/43284
Collection等离子体与燃烧中心(2009-2011)
Corresponding AuthorWang HX
Recommended Citation
GB/T 7714
Wang HX,Chen X,Pan WX,et al. Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters[J]. Plasma Science and Technology,2010,12(6):692-701.
APA Wang HX,Chen X,潘文霞,Murphy AB,Geng JY,&Jia SX.(2010).Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters.Plasma Science and Technology,12(6),692-701.
MLA Wang HX,et al."Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters".Plasma Science and Technology 12.6(2010):692-701.
Files in This Item:
File Name/Size DocType Version Access License
Modeling study to co(4875KB) 开放获取LicenseView Application Full Text
Related Services
Recommend this item
Bookmark
Usage statistics
Export to Endnote
Google Scholar
Similar articles in Google Scholar
[Wang HX]'s Articles
[Chen X]'s Articles
[潘文霞]'s Articles
Baidu academic
Similar articles in Baidu academic
[Wang HX]'s Articles
[Chen X]'s Articles
[潘文霞]'s Articles
Bing Scholar
Similar articles in Bing Scholar
[Wang HX]'s Articles
[Chen X]'s Articles
[潘文霞]'s Articles
Terms of Use
No data!
Social Bookmark/Share
File name: Modeling study to compare the flow and heat transfer characteristics of low-power hydrogen, nitrogen and argon arc-heated thrusters.pdf
Format: Adobe PDF
This file does not support browsing at this time
All comments (0)
No comment.
 

Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.