Powered flight of electron cyclotron resonance ion engines on hayabusa explorer

Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Tetsuya Yamada, Yukio Shimizu, Ju N.Ichiro Kawaguchi

研究成果: Article査読

80 被引用数 (Scopus)

抄録

The electron cyclotron resonance ion engine has long life and high reliability because of electrodeless plasma generation in both the ion generator and the neutralizes Four μ 10s, each generating a thrust of 8 mN, specific impulse of 3200 s, and consuming 350 W of electric power, propelled the Hayabusa asteroid explorer launched on May 2003. After vacuum exposure and several baking runs to reduce residual gas, the ion engine system established continuous acceleration. Electric propelled 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 solar distance between 0.86 and 1.7 AU. It rendezvoused with, landed on, and lifted off from the asteroid Itokawa. During the 2-year flight, the ion engine system generated a delta-V of 1400 m/s while consuming 22 kg of xenon propellent and operating for 25,800 h.

本文言語English
ページ(範囲)544-551
ページ数8
ジャーナルJournal of Propulsion and Power
23
3
DOI
出版ステータスPublished - 2007
外部発表はい

ASJC Scopus subject areas

  • 航空宇宙工学
  • 燃料技術
  • 機械工学
  • 宇宙惑星科学

フィンガープリント

「Powered flight of electron cyclotron resonance ion engines on hayabusa explorer」の研究トピックを掘り下げます。これらがまとまってユニークなフィンガープリントを構成します。

引用スタイル