Numerical Analysis on the Plasma Behavior of a Hydrogen MPD Thruster at the Critical Current
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- Tauchi Shitan
- 連絡先著者(Corresponding author):s.tauchi@ac.jaxa.jp 総合研究大学院大学物理科学研究科宇宙科学専攻
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- Kawasaki Akira
- 名古屋大学大学院工学研究科
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- Nakane Masakatsu
- 日本大学理工学部
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- Kubota Kenichi
- 宇宙航空研究開発機構
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- Funaki Ikkoh
- 宇宙航空研究開発機構
Bibliographic Information
- Other Title
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- 臨界電流における水素MPDスラスタのプラズマ挙動に関する数値解析
- リンカイ デンリュウ ニ オケル スイソ MPD スラスタ ノ プラズマ キョドウ ニ カンスル スウチ カイセキ
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Abstract
<p>For a self-field magnetoplasmadynamic (MPD) thruster using hydrogen propellant, plasma flows were numerically simulated with a model including the ion-slip effect. To clarify the thruster behavior near the critical current, the discharge current and the propellant mass flow rate were set to 5 or 10 kA (critical current) and 0.4 g/s, respectively. At the critical current, current paths protruded toward a downstream region due to an increased Hall parameter when compared with the lower current case. In conjunction with this, the pressure was higher in the vicinity of the cathode tip and the ion-slip parameter exceeded unity in the discharge chamber at the critical current. Significant ion-slip heating occurred in the supersonic region, which resulted in limited amount of gas dynamic thrust. </p>
Journal
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- JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 67 (5), 159-166, 2019
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Details 詳細情報について
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- CRID
- 1390001277365968256
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- NII Article ID
- 130007723959
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- NII Book ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL BIB ID
- 030034950
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- Abstract License Flag
- Disallowed