A miniaturized ion thruster and neutralizer with microwave discharge

Masahiko Tanisho, Hiroshi Kataharada, Naoji Yamamoto, Hideki Nakasima

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

2 被引用数 (Scopus)

抄録

A 18 mm-diameter microwave discharge ion engine and a 7 mm-diameter microwave discharge cylindrical neutralizer for space propulsion has been developed. In order to improve the thrust performance of a miniature microwave discharge ion engine, the dependence of its thrust performance on antenna shapes was investigated. At present as for the ion engine performance parameters, the propellant utilization efficiency, the ion production cost and the thrust were 0.72, 770 W/A and 0.66 mN, respectively at input 2.45 GHz microwave power of 8 W and Xe gas flow rate of 0.2 seem with a star type antenna. As for the neutralizer, in order to improve the performance, the dependence of its performance on the magnetic induction was investigated. The maximam extracted electron current of 6 mA was obtained at Ar gas flow rate of 0.1 seem and input microwave power of 4 W.

本文言語英語
ホスト出版物のタイトルInternational Astronautical Federation - 56th International Astronautical Congress 2005
ページ4553-4557
ページ数5
7
出版ステータス出版済み - 2005
イベントInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, 日本
継続期間: 10 17 200510 21 2005

その他

その他International Astronautical Federation - 56th International Astronautical Congress 2005
Country日本
CityFukuoka
Period10/17/0510/21/05

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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