準定常MPD推進機の噴出プラズマ流の状態 Feature of Exhaust Plasma Flows for a Quasi-Steady MPD Thruster

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The quasi-steady MPD thruster MY-III was operated to study the exhaust plasma plume characteristics. Both emission spectroscopic and rotatable double probe measurements were made to evaluate electron temperatures, plasma number densities and plasma flow directions. The plasma was slightly expanded radially outward downstream within the extrapolation line of the divergent nozzle regardless of gas species and discharge current although it was intensively expanded outside the line. Both the electron temperature and the plasma number density decreased radially outward at a constant axial position. The angle of radial expansion decreased with discharge current. The angle for H<SUB>2</SUB> was relatively small compared with cases for Ar. Nozzle angle was expected to influence the downstream flow characteristics although a core flow, i.e., the cathode jet, with a high temperature and a large plasma density existed on the central axis.

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  • 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 50(582), 286-292, 2002-07-05

    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)
    10008967912
  • 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
    6222755
  • 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  CJP引用  NDL  J-STAGE 
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