Numerical Investigation of Discharge Current Path in a Hydrogen MPD Thruster
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- Kawasaki Akira
- Department of Energy Sciences, Tokyo Institute of Technology
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- Kubota Kenichi
- Japan Aerospace Exploration Agency
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- Funaki Ikkoh
- Japan Aerospace Exploration Agency
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- Okuno Yoshihiro
- Department of Energy Sciences, Tokyo Institute of Technology
Bibliographic Information
- Other Title
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- 水素MPDスラスタの放電電流経路に関する数値的検討
- スイソ MPD スラスタ ノ ホウデン デンリュウ ケイロ ニ カンスル スウチテキ ケントウ
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Abstract
For a 10N-class, steady-state, self-field magnetoplasmadynamic (MPD) thruster using hydrogen as the propellant, the distribution of discharge current path has been investigated by means of axisymmetry two-dimensional magnetohydrodynamic (MHD) flow simulation including an electrode sheath model with cathode temperature distributions. The discharge current path concentrates in the downstream region of the thruster, particularly on the anode edge and the cathode tip, because the ionization of hydrogen occurs after the dissociation. This feature is so dominant that the cathode sheath voltage is determined mainly by the temperature at the cathode tip and the discharge current path is hardly affected by the temperature gradient of the cathode. These characteristics are quite different from those for argon MPD thruster.
Journal
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- IEEJ Transactions on Fundamentals and Materials
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IEEJ Transactions on Fundamentals and Materials 136 (3), 141-146, 2016
The Institute of Electrical Engineers of Japan
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Keywords
Details 詳細情報について
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- CRID
- 1390001204598215936
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- NII Article ID
- 130005132226
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- NII Book ID
- AN10136312
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- ISSN
- 13475533
- 03854205
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- NDL BIB ID
- 027160970
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
- KAKEN
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- Abstract License Flag
- Disallowed
