| Item type |
会議発表論文 / Conference Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
Numerical calculation of ablation and plasma expansion induced by electric breakdown of spacecraft insulator surface in ambient plasma environment |
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言語 |
en |
| 言語 |
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言語 |
eng |
| キーワード |
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主題Scheme |
Other |
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主題 |
数値シミュレーション |
| キーワード |
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主題Scheme |
Other |
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主題 |
アブレーション |
| キーワード |
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主題Scheme |
Other |
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主題 |
宇宙機帯電 |
| キーワード |
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主題Scheme |
Other |
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主題 |
航空宇宙環境 |
| キーワード |
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主題Scheme |
Other |
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主題 |
宇宙プラズマ |
| キーワード |
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主題Scheme |
Other |
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主題 |
プラズマ膨張 |
| キーワード |
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主題Scheme |
Other |
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主題 |
絶縁破壊 |
| キーワード |
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主題Scheme |
Other |
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主題 |
絶縁体 |
| キーワード |
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主題Scheme |
Other |
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主題 |
アーク放電 |
| キーワード |
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主題Scheme |
Other |
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主題 |
LEO宇宙機 |
| キーワード |
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主題Scheme |
Other |
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主題 |
宇宙機材料 |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
numerical simulation |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
ablation |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
spacecraft charging |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
aerospace environment |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
space plasma |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
plasma expansion |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
electric breakdown |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
insulator |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
arc discharge |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
LEO spacecraft |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
spacecraft material |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_5794 |
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資源タイプ |
conference paper |
| 著者 |
堀川, 晃司
田原, 弘一
増山, 貴久
Horikawa, Koji
Tahara, Hirokazu
Masuyama, Takahisa
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| 著者所属 |
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大阪大学 大学院基礎工学研究科 |
| 著者所属 |
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大阪大学 大学院基礎工学研究科 |
| 著者所属 |
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大阪大学 大学院基礎工学研究科 |
| 著者所属（英） |
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en |
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Osaka University Graduate School of Engineering Science |
| 著者所属（英） |
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en |
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Osaka University Graduate School of Engineering Science |
| 著者所属（英） |
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en |
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Osaka University Graduate School of Engineering Science |
| 出版者 |
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出版者 |
宇宙航空研究開発機構 |
| 出版者（英） |
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出版者 |
Japan Aerospace Exploration Agency (JAXA) |
| 書誌情報 |
宇宙航空研究開発機構特別資料
en : JAXA Special Publication: 9th Spacecraft Charging Technology Conference
巻 JAXA-SP-05-001E,
p. 580-588,
発行日 2005-08-01
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
In the future, LEO spacecraft will be larger and higher powered. Because of the balance of leakage currents through ambient space plasma, their main conductive body will have a higher negative potential without plasma contactor operation. When spacecraft operate with a higher voltage, more intensive electric breakdown, i.e. arcing, is suspected to occur on the surface. In this study, unsteady physical processes inside an arc spot, such as ablation and heating of insulator, and plasma generation and acceleration etc., were studied using Computational Fluid Dynamics (CFD). Direct-Simulation-Monte-Carlo Particle-In-Cell (DSMC-PIC) plasma simulation was also carried out to examine influences of ambient space plasma on plasma expansion processes outside the arc spot. The calculated arc current increased with time; had a peak and then decreased. Inside the arc spot, the calculated plasma resistance rapidly decreased with time; was kept low level and jumped just before extinguishment of arc. As a result the plasma resistance characteristics agreed with the arc current characteristics. The calculated ablation rate rapidly increased with time; had a peak and then gradually decreased, although the calculated arc spot diameter gradually increased with time. Furthermore, the calculated arc spot diameter gradually increased with initial stored energy, although it was smaller than experimental ones. Both the neutral particle number density and the electron number density were the highest near arc initiation and decreased with time. Both the number densities were relatively high inside the arc spot compared with those outside it. The temperature of insulator surface in contact with plasma rapidly increased up to 5,000 K near arc initiation and gradually decreased to 4,000 K. Outside the arc spot, neutral particles in addition to charged particles around spacecraft played an important role in expansion of arc plasma by intensive ionization near the arc spot. Accordingly, high voltage operation of LEO spacecraft might bring drastic degradation of insulator surface by arcing, depending on insulator material properties and ambient plasma conditions. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
1349-113X |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
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収録物識別子 |
AA11984031 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: AA0049206064 |
| レポート番号 |
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内容記述タイプ |
Other |
|
内容記述 |
レポート番号: JAXA-SP-05-001E |
49206064.pdf (2.6 MB)
