Hall Thruster Development for Japanese Space Propulsion Programs

Yushi HAMADA; Junhwi BAK; Rei KAWASHIMA; Hiroyuki KOIZUMI; Kimiya KOMURASAKI; Naoji YAMAMOTO; Yusuke EGAWA; Ikkoh FUNAKI; Shigeyasu IIHARA; Shinatora CHO; Kenichi KUBOTA; Hiroki WATANABE; Kenji FUCHIGAMI; Yosuke TASHIRO; Yuya TAKAHATA; Tetsuo KAKUMA; Yusuke FURUKUBO; Hirokazu TAHARA

doi:10.2322/tjsass.60.320

Yushi HAMADA, Junhwi BAK, Rei KAWASHIMA, Hiroyuki KOIZUMI, Kimiya KOMURASAKI, Naoji YAMAMOTO, Yusuke EGAWA, Ikkoh FUNAKI, Shigeyasu IIHARA, Shinatora CHO, Kenichi KUBOTA, Hiroki WATANABE, Kenji FUCHIGAMI, Yosuke TASHIRO, Yuya TAKAHATA, Tetsuo KAKUMA, Yusuke FURUKUBO, Hirokazu TAHARA

Author information

Yushi HAMADA
Department of Aeronautics and Astronautics, The University of Tokyo
Junhwi BAK
Department of Aeronautics and Astronautics, The University of Tokyo
Rei KAWASHIMA
Department of Aeronautics and Astronautics, The University of Tokyo
Hiroyuki KOIZUMI
Department of Aeronautics and Astronautics, The University of Tokyo
Kimiya KOMURASAKI
Department of Aeronautics and Astronautics, The University of Tokyo
Naoji YAMAMOTO
Department of Advanced Energy Engineering Science, Kyushu University
Yusuke EGAWA
Department of Advanced Energy Engineering Science, Kyushu University
Ikkoh FUNAKI
Institute of Space and Astronautical Science, JAXA
Shigeyasu IIHARA
IHI Aerospace Co., Ltd.
Shinatora CHO
Research and Development Directorate, JAXA
Kenichi KUBOTA
Research and Development Directorate, JAXA
Hiroki WATANABE
Department of Aerospace Engineering, Tokyo Metropolitan University
Kenji FUCHIGAMI
IHI Corporation
Yosuke TASHIRO
IHI Aerospace Co., Ltd.
Yuya TAKAHATA
Department of Aeronautics and Astronautics, Osaka Institute of Technology
Tetsuo KAKUMA
Department of Aeronautics and Astronautics, Osaka Institute of Technology
Yusuke FURUKUBO
Department of Aeronautics and Astronautics, Osaka Institute of Technology
Hirokazu TAHARA
Department of Aeronautics and Astronautics, Osaka Institute of Technology

Keywords: Hall Thruster, In-space Propulsion

JOURNAL FREE ACCESS

2017 Volume 60 Issue 5 Pages 320-326

DOI https://member-cnki-net-s-1416.res.gxlib.org.cn:443/rwt/1416/https/MSYXTLUQPJUB/10.2322/tjsass.60.320

Details

Abstract

Three different types of high power Hall thrusters—anode layer type, magnetic layer type with high specific impulse, and magnetic layer type with dual mode operation (high thrust mode and high specific impulse mode)—have been developed, and the thrust performance of each thruster has been evaluated. The thrust of the anode layer type thruster is in the range of 19–219 mN, with power in the range of 325–4500 W. The thrust of the high specific impulse magnetic layer type thruster was 102 mN, with specific impulse of 3300 s. The thrust of the bimodal operation magnetic layer thruster was 385 mN with specific impulse of 1200 s, and 300 mN with specific impulse of 2330 s. The performance of these thrusters demonstrates that the Japanese electric propulsion community has the capability to develop a thruster for commercial use.

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