A 200 W Hall thruster with hollow indented anode

被引：23

作者：

Ding, Yongjie ^{[1
,2
]}

Sun, Hezhi ^{[1
]}

Wei, Liqiu ^{[1
,2
]}

Li, Peng ^{[1
]}

Su, Hongbo ^{[1
]}

Peng, Wuji ^{[1
]}

Yu, Daren ^{[1
,2
]}

机构：

[1] Harbin Inst Technol, Inst Adv Power, Plasma Prop Lab, Harbin 150001, Heilongjiang, Peoples R China

[2] Harbin Inst Technol, Elect Dr & Prop Technol Lab, Harbin 150001, Heilongjiang, Peoples R China

来源：

ACTA ASTRONAUTICA | 2017年 / 139卷

基金：

中国国家自然科学基金;

关键词：

Hall thruster; Hollow indented anode;

D O I：

10.1016/j.actaastro.2017.08.001

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A hollow indented anode is proposed for increasing the neutral gas density in a discharge channel, in order to improve the performance of the thruster. The experimental results show that a hollow indented anode structure can effectively improve the performance, compared to a hollow straight anode under similar operating conditions, in terms of thrust, propellant utilization, ionization rate, and anode efficiency. Furthermore, simulations show that the indented anode can effectively increase the neutral gas density in a discharge channel and on the centerline of the channel, compared to a hollow straight anode. In addition, it can increase the ionization rate in the channel and the pre-ionization in the anode. Therefore, the hollow indented anode could be considered as an important design idea for improving thruster performance.

引用

页码：521 / 527

页数：7

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