カスプとダイバージェントノズル状の外部磁場をもつパルス作動型電磁プラズマ加速アークジェット推進機の性能とプラズマ特性 Performance and Plasma Characteristics of Pulsed Magneto-Plasma-Dynamic Arcjet Thrusters with Cusp and Divergent-Nozzle Applied-Magnetic-Fields

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A two-stage magnetic field with cusp and divergent shapes was applied in a magneto-plasma-dynamic (MPD) thruster discharge chamber. The thrust efficiency intensively increased with enhanced thrust and unchanged discharge voltage because of more effective ionization/heating and swirl acceleration due to the applied magnetic field. When the magnetic field became much stronger and the arc current became much higher, the thrust approached the self-magnetic thrust. As a result, an optimum magnetic field strength existed. The plasma flow was observed by a high-speed camera, and plasma density, temperature and velocity were measured with electrostatic probes. Through the magnetic nozzle the exhausted plasma rotated and spreaded radially-outward, and the plasma density decreased near the central axis. Accordingly, the plasma characteristics agreed with the measured thrust performance, considering intensive plasma heating due to Hall current and swirl acceleration, i.e. conversion from azimuthal kinetic energy to axial kinetic energy.

収録刊行物

  • 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences  

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 54(632), 392-396, 2006-09-05 

    一般社団法人 日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10018428892
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    13446460
  • NDL 記事登録ID
    8513955
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  NDL  J-STAGE 
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