Research and Development of High-Efficiency Hall-Type Ion Engines for Small Spacecrafts

被引：0

作者：

Ikeda, Tomoyuki ^{[1
]}

Sugimoto, Naru ^{[1
]}

Togawa, Kazuya ^{[1
]}

Mito, Yohei ^{[1
]}

Tahara, Hirokazu ^{[1
]}

机构：

[1] Osaka Inst Technol, Dept Mech Engn, Asahi Ku, Osaka 5358585, Japan

来源：

INTERNATIONAL CONFERENCE ON RENEWABLE ENERGY RESEARCH AND APPLICATIONS (ICRERA) | 2012年

关键词：

space propulsion; electric propulsion; Hall thruster; nano satellite; THRUSTER;

D O I：

暂无

中图分类号：

TE [石油、天然气工业]; TK [能源与动力工程];

学科分类号：

0807 ; 0820 ;

摘要：

Development of Hall thrusters for nano, small and low-power satellites below 100W is expected. In lowering Hall thruster power, the cylindrical-type Hall thruster is more advantage than conventional coaxial-type Hall thrusters. In this study, a very low power cylindrical Hall thruster was designed, and the thruster performance was measured. As a result, a stable operation was achieved even with 10W. The specific impulse and the thrust efficiency are 1570sec and 18.1%, respectively, with 66W. Also, the discharge current oscillation was lower compared SPT-type Hall thruster.

引用

页数：6

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