Design and test of a 100 μN-class thrust stand for a miniature water ion thruster with CubeSat, transactions of Japan society for aeronautical and space sciences

• NAKAGAWA Yuichi

  Department of Aeronautics and Astronautics, The University of Tokyo

• TOMITA Daiki

  Department of Aeronautics and Astronautics, The University of Tokyo

• KOIZUMI Hiroyuki

  Department of Advanced Energy, The University of Tokyo

• KOMURASAKI Kimiya

  Department of Aeronautics and Astronautics, The University of Tokyo

書誌事項

タイトル別名

• Design and Test of a 100 μN-class Thrust Stand for a Miniature Water Ion Thruster with CubeSat

抄録

The electric propulsion system for CubeSat is required to achieve various missions. A miniature water ion thruster for CubeSats has been proposed and tested. To investigate the effect of the dissociation of water on its performance, a direct thrust measurement is required. In this study, a 100 μN-class thrust stand for 10 kg units was designed and integrated. It was calibrated using weights whose mass was measured in advance and achieved the measurement of the thrust of the miniature ion thruster using water. The range of measured thrust was 60–140 μN, and the average of its uncertainty was ±7.6 %. The thrust coefficients were around 0.9, similar to or slightly less than that of xenon. This shows that the dissociation of water has little effect on the thrust.

収録刊行物

• 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 16 (7), 673-678, 2018

  一般社団法人 日本航空宇宙学会

キーワード

• Ion Thruster
• Liquid Propellant
• Water
• CubeSat
• Nanosatellite

詳細情報

• CRID: 1390564238038162176
• NII論文ID: 130007504900
• DOI: 10.2322/tastj.16.673
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/16/7/16_673/_pdf
• 本文言語コード: en
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• 抄録ライセンスフラグ: 使用不可