Thrust Performance of a Low Power Hall Thruster

• YAMAMOTO Naoji

  Department of Advanced Energy Engineering Science, Kyushu University

• EZAKI Toru

  Department of Advanced Energy Engineering Science, Kyushu University

• NAKASHIMA Hideki

  Department of Advanced Energy Engineering Science, Kyushu University

Abstract

For the application of Hall thrusters to small satellites, we have been developing a low power Hall thruster. As an initial test, we evaluated the thrust performance of a 50 W class miniature Hall thruster developed at Kyushu University. The outer diameter and the length of the acceleration channel are 18 mm and 7 mm, respectively. A torsional type thrust stand was developed, since the estimated thrust is 1-3 mN, which is too small to be measured by means of a conventional pendulum type thrust stand for Hall thrusts. The uncertainty of this thrust stand is less than 10% at 2 mN with calibration. The thrust, the discharge current, specific impulse and the thrust efficiency at xenon mass flow rate of 0.30 mg/s and discharge voltage of 125 V were 1.7 mN, 0.35 A, 600 sec and 11.4%, respectively. The thrust increased with an increase in discharge voltage and the thrust became 3.1 mN at discharge voltage of 250 V.

Journal

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

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 10 (ists28), Tb_9-Tb_12, 2012

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Hall Thruster
• Miniature Propulsion
• Thrust Stand

Details

• CRID: 1390282680296521856
• NII Article ID: 130002136605
• DOI: 10.2322/tastj.10.tb_9
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/10/ists28/10_Tb_9/_pdf
• Text Lang: en
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed