Model of the plasma discharge in a Hall thruster with heat conduction

被引:43
作者
Ahedo, E [1 ]
Gallardo, JM
Martínez-Sánchez, M
机构
[1] Univ Politecn Madrid, ETSI Aeronaut, E-28040 Madrid, Spain
[2] MIT, Cambridge, MA 02139 USA
关键词
D O I
10.1063/1.1499496
中图分类号
O35 [流体力学]; O53 [等离子体物理学];
学科分类号
070204 ; 080103 ; 080704 ;
摘要
The inclusion of heat conduction into a one-dimensional, macroscopic model of the plasma inside a Hall thruster and in the near plume is found to smooth the temperature profile of previous solutions with a nonconductive model. The spatial structure still consists of reverse-flow, ionization, and acceleration regions. Conductive energy flow, being of the same order of convective flow, has significant effects on the rear part of the channel where it can make impossible the establishment of a steady anode sheath. As a result, there is an upper bound on the plasma reverse flow for the existence of stationary solutions. The analysis of inertial effects on the electron dynamics concludes that the main contribution is the azimuthal electron motion, which can produce extra collisionality, mainly in the near plume. The different contributions to the effective axial diffusion of electrons and the ion temperature are evaluated. A parametric investigation yields the basic scaling laws of the thruster stationary performance. (C) 2002 American Institute of Physics.
引用
收藏
页码:4061 / 4070
页数:10
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