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

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Abstract

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.

Journal

  • JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 50(582), 286-292, 2002-07-05

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

References:  12

Cited by:  1

Codes

  • NII Article ID (NAID)
    10008967912
  • NII NACSIS-CAT ID (NCID)
    AA11307372
  • Text Lang
    JPN
  • Article Type
    Journal Article
  • ISSN
    13446460
  • NDL Article ID
    6222755
  • NDL Call No.
    Z74-B503
  • Data Source
    CJP  CJPref  NDL  J-STAGE 
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