Influence of Azimuthally Nonuniform Propellant Flow Rate on Thrust Vector and Discharge Current Oscillation in a Hall Thruster

• FUKUSHIMA Yasuhiro

  Department of Aeronautics and Astronautics, The University of Tokyo

• YOKOTA Shigeru

  Department of Aeronautics and Astronautics, The University of Tokyo

• KOMURASAKI Kimiya

  Department of Aeronautics and Astronautics, The University of Tokyo

• ARAKAWA Yoshihiro

  Department of Aeronautics and Astronautics, The University of Tokyo

Abstract

Discharge current oscillation at the frequency range of 10-100 kHz causes serious problems in using an anode layer type Hall thruster in space. As a new approach to the discharge stabilization, azimuthally nonuniform propellant flows were created in an acceleration channel. A plenum chamber was divided into two rooms to which xenon gas was supplied at different flow rates. As a result, stable discharge was achieved in wider operation conditions with the larger mass flow differential. The oscillation amplitude at the maximum thrust efficiency was decreased by up to 94%. In addition, thrust vector was measured and the deviation angle was found to vary with the differential flow rate and magnetic flux density.

Journal

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7 (ists26), Pb_41-Pb_45, 2009

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Hall Thruster
• Discharge Stabilization
• Thrust Vector Control

Details

• CRID: 1390282680191093120
• NII Article ID: 130000151846
• DOI: 10.2322/tstj.7.pb_41
• ISSN: 13473840
• Web Site: https://www.jstage.jst.go.jp/article/tstj/7/ists26/7_ists26_Pb_41/_pdf
• Text Lang: en
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
• Abstract License Flag: Disallowed