Effect of Nozzle Temperature on the Performance of a 1 kW H2-N2 Arcjet Thruster

doi:10.1088/1009-0630/12/4/17

IMECH-IR > 等离子体与燃烧中心(2009-2011)

	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)
发表期刊	Plasma Science and Technology
	2010
卷号	12 期号:4 页码:473-477
ISSN	1009-0630
摘要	A 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.
关键词	Arcjet Thruster Nozzle Temperature Energy Conversion Experimental Measurement
学科领域	交叉与边缘领域的力学
DOI	10.1088/1009-0630/12/4/17
URL	查看原文
收录类别	SCI
语种	英语
WOS记录号	WOS:000281989500017
引用统计	被引频次：7[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/43281
专题	等离子体与燃烧中心(2009-2011)
通讯作者	Pan WX(潘文霞)
推荐引用方式 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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