小惑星探査機「はやぶさ」搭載マイクロ波放電式イオンエンジンの初期運用  [in Japanese] Initial Operation of Microwave Discharge Ion Engines Onboard "HAYABUSA" Asteroid Explorer  [in Japanese]

Access this Article

Search this Article

Author(s)

Abstract

The microwave discharge ion engine generates plasmas of the main ion source as well as the neutralizer using 4GHz microwave without discharge electrodes and hollow cathodes, so that long life and durability against oxygen and air are expected. MUSES-C “HAYABUSA” spacecraft installing four microwave discharge ion engines was launched into deep space by M-V rocket on May 9, 2003. After vacuum exposure and several runs of baking for reduction of residual gas the ion engine system established the continuous acceleration of the spacecraft toward an asteroid. The Doppler shift measurement of the communication microwave revealed the performance of ion engines, which is 8mN thrust force for a single unit with 3,200sec specific impulse at 23mN/kW thrust power ratio. At the beginning of December 2003 the accumulated operational time exceeded 7,000 hours and units.

Journal

  • JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 52(602), 129-134, 2004-03-05

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

References:  11

Cited by:  4

Codes

  • NII Article ID (NAID)
    10012680638
  • NII NACSIS-CAT ID (NCID)
    AA11307372
  • Text Lang
    JPN
  • Article Type
    Journal Article
  • ISSN
    13446460
  • NDL Article ID
    6889158
  • NDL Source Classification
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL Call No.
    Z74-B503
  • Data Source
    CJP  CJPref  NDL  J-STAGE 
Page Top