A miniaturized ion thruster and neutralizer with microwave discharge

Masahiko Tanisho, Hiroshi Kataharada, Naoji Yamamoto, Hideki Nakasima

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

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.

Original languageEnglish
Title of host publicationInternational Astronautical Federation - 56th International Astronautical Congress 2005
Pages4553-4557
Number of pages5
Volume7
Publication statusPublished - 2005
EventInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, Japan
Duration: Oct 17 2005Oct 21 2005

Other

OtherInternational Astronautical Federation - 56th International Astronautical Congress 2005
CountryJapan
CityFukuoka
Period10/17/0510/21/05

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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