Research and development of high-efficiency hall-type ion engines for small spacecrafts

Author

Ikeda, Takashi ; Sugimoto, Naozo ; Togawa, K. ; Mito, Y. ; Tahara, H.

Author_Institution

Dept. of Mech. Eng., Osaka Inst. of Technol., Omiya, Japan

fYear

2012

fDate

11-14 Nov. 2012

Firstpage

1

Lastpage

6

Abstract

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.

Keywords

Hall effect devices; artificial satellites; ion engines; Hall type ion engine; cylindrical Hall thruster; discharge current oscillation; nanosatellite; power 10 W; power 66 W; spacecraft; time 1570 s; Coils; Current measurement; Discharges (electric); Magnetic fields; Oscillators; Propulsion; Satellites; Hall thruster; electric propulsion; nano satellite; space propulsion;

fLanguage

English

Publisher

ieee

Conference_Titel

Renewable Energy Research and Applications (ICRERA), 2012 International Conference on

Conference_Location

Nagasaki

Print_ISBN

978-1-4673-2328-4

Electronic_ISBN

978-1-4673-2329-1

Type

conf

DOI

10.1109/ICRERA.2012.6477452

Filename

6477452