Performance test of micro ion thruster using microwave discharge

Yoshiyuki Takao, Hiroshi Kataharada, Takashi Miyamoto, Hirokazu Masui, Naoji Yamamoto, Hideki Nakashima

Research output: Contribution to journalArticle

7 Citations (Scopus)

Abstract

Several types of electric propulsions have been developed and used for artificial satellites on geostationary orbit keeping or planetary exploration. A series of small-scale satellites is recently expected to be used instead of traditional large-scale satellites for reducing launch cost and risk. The trend towards needs of small spacecraft requires micro thrusters with high specific impulse. In this study, a micro ion engine utilizing a microwave discharge plasma was fabricated and was tested. This ion engine comprises some components, such as electrostatic grids, antenna, and microwave power supply, which decide its performance. The performance dependence on the components was examined under several experimental conditions. The typical performance parameters of the engine were ion production cost of 770 V, propellant utilization efficiency of 72%, and thrust of 0.66 mN in conditions of input 2.45 GHz microwave power of 8 W and propellant (xenon gas) flow rate of 0.2 sccm with a star type antenna.

Original languageEnglish
Pages (from-to)1239-1243
Number of pages5
JournalVacuum
Volume80
Issue number11-12
DOIs
Publication statusPublished - Sep 7 2006

All Science Journal Classification (ASJC) codes

  • Instrumentation
  • Condensed Matter Physics
  • Surfaces, Coatings and Films

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