Hall Thruster Development for Japanese Space Propulsion Programs

• HAMADA Yushi

  Department of Aeronautics and Astronautics, The University of Tokyo

• BAK Junhwi

  Department of Aeronautics and Astronautics, The University of Tokyo

• KAWASHIMA Rei

  Department of Aeronautics and Astronautics, The University of Tokyo

• KOIZUMI Hiroyuki

  Department of Aeronautics and Astronautics, The University of Tokyo

• KOMURASAKI Kimiya

  Department of Aeronautics and Astronautics, The University of Tokyo

• YAMAMOTO Naoji

  Department of Advanced Energy Engineering Science, Kyushu University

• EGAWA Yusuke

  Department of Advanced Energy Engineering Science, Kyushu University

• FUNAKI Ikkoh

  Institute of Space and Astronautical Science, JAXA

• IIHARA Shigeyasu

  IHI Aerospace Co., Ltd.

• CHO Shinatora

  Research and Development Directorate, JAXA

• KUBOTA Kenichi

  Research and Development Directorate, JAXA

• WATANABE Hiroki

  Department of Aerospace Engineering, Tokyo Metropolitan University

• FUCHIGAMI Kenji

  IHI Corporation

• TASHIRO Yosuke

  IHI Aerospace Co., Ltd.

• TAKAHATA Yuya

  Department of Aeronautics and Astronautics, Osaka Institute of Technology

• KAKUMA Tetsuo

  Department of Aeronautics and Astronautics, Osaka Institute of Technology

• FURUKUBO Yusuke

  Department of Aeronautics and Astronautics, Osaka Institute of Technology

• TAHARA Hirokazu

  Department of Aeronautics and Astronautics, Osaka Institute of Technology

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.

Journal

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 60 (5), 320-326, 2017

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Hall Thruster
• In-space Propulsion

Details

• CRID: 1390282679057618688
• NII Article ID: 130006059281
• DOI: 10.2322/tjsass.60.320
• ISSN: 21894205
• ISSN: 05493811
• Web Site: https://www.jstage.jst.go.jp/article/tjsass/60/5/60_T-16-49/_pdf
• Text Lang: en
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed