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Effect of Nozzle Temperature on the Performance of a 1 kW H2-N2 Arcjet Thruster
Pan WX(潘文霞); Huang HJ(黄河激); Wu CK(吴承康)
Source PublicationPlasma Science and Technology
2010
Volume12Issue:4Pages:473-477
ISSN1009-0630
AbstractA 1 kW-class arcjet thruster was ¯red in a vacuum chamber at a pressure of 18 Pa. A gas mixture of H2 : N2 = 2.8 : 1.5 in volume at a total °ow rate of 4.3 slm was used as the propellant with an input power ¯xed at 860 W. The time-dependent thrust, nozzle temperature and inlet pressure of the propellant were measured simultaneously. Results showed that with the increase in nozzle temperature the thrust decreased and various losses increased. The physical mechanisms involved in these effects are discussed.
KeywordArcjet Thruster Nozzle Temperature Energy Conversion Experimental Measurement
Subject Area交叉与边缘领域的力学
DOI10.1088/1009-0630/12/4/17
URL查看原文
Indexed BySCI
Language英语
WOS IDWOS:000281989500017
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/43281
Collection等离子体与燃烧中心(2009-2011)
Corresponding AuthorPan WX(潘文霞)
Recommended Citation
GB/T 7714
Pan WX,Huang HJ,Wu CK. Effect of Nozzle Temperature on the Performance of a 1 kW H2-N2 Arcjet Thruster[J]. Plasma Science and Technology,2010,12(4):473-477.
APA 潘文霞,黄河激,&吴承康.(2010).Effect of Nozzle Temperature on the Performance of a 1 kW H2-N2 Arcjet Thruster.Plasma Science and Technology,12(4),473-477.
MLA 潘文霞,et al."Effect of Nozzle Temperature on the Performance of a 1 kW H2-N2 Arcjet Thruster".Plasma Science and Technology 12.4(2010):473-477.
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