Powered flight of HAYABUSA in deep space

Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Tetsuya Yamada, Yukio Shimizu, Jun'ichiro Kawaguchi

研究成果: Conference contribution

19 被引用数 (Scopus)


The electron cyclotron resonance ion engine, "μ10,"" has a long life and high reliability because of electrodeless plasma generation in both the ion generator and the neutralizer. Four μ10, each generating a thrust of 8 mN, specific impulse of 3,200 seconds, and consuming 350 W of electric power, propel the "HAYABUSA" asteroid explorer that was launched on May 2003. After vacuum exposure and several runs of bailing to reduce residual gas, the ion engine system established continuous acceleration. Delta-V Earth Gravity Assist, a new orbit change scheme that uses electric propulsion with a high specific impulse was applied to change from a terrestrial orbit to an asteroid-based orbit. In 2005, HAYABUSA, using solar electric propulsion, managed to successfully cover the distance between 0.86 AU and 1.7 AU in the solar system, as well as rendezvous with, land on, and lift off from the asteroid Itokawa. During the 3-year flight, the ion engine system generated a delta-V of 1,400 m/s while consuming 22 kg of xenon propellant and operating for 25,900 hours.

ホスト出版物のタイトルCollection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷版)1563478188, 9781563478185
出版ステータスPublished - 2006
イベントAIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference - Sacramento, CA, United States
継続期間: 2006 7 92006 7 12


名前Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference


ConferenceAIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
国/地域United States
CitySacramento, CA

ASJC Scopus subject areas

  • 宇宙惑星科学
  • エネルギー(全般)
  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学
  • 機械工学


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