| 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 |
宇宙機表面絶縁材料の繰り返しアーキング特性とそのアブレーション現象の数値計算 |
| 言語 |
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言語 |
jpn |
| キーワード |
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主題Scheme |
Other |
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主題 |
低高度地球周回軌道 |
| キーワード |
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主題Scheme |
Other |
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主題 |
宇宙機構造材料 |
| キーワード |
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主題Scheme |
Other |
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主題 |
表面絶縁体 |
| 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 |
アーク放電 |
| 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 |
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 |
数値解析 |
| キーワード |
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主題Scheme |
Other |
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主題 |
高電圧 |
| キーワード |
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主題Scheme |
Other |
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主題 |
中性粒子 |
| 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 |
low Earth orbit |
| 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 construction material |
| 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 |
surface 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 |
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 |
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 |
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 |
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 |
numerical analysis |
| 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 |
high voltage |
| 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 |
neutral particle |
| 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 |
| アクセス権 |
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アクセス権 |
metadata only access |
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アクセス権URI |
http://purl.org/coar/access_right/c_14cb |
| その他のタイトル（英） |
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その他のタイトル |
Repetitive arcing characteristics on spacecraft surface insulator in ambient plasma environment and numerical calculation of physical phenomena inside its arc spot |
| 著者 |
田原, 弘一
増山, 貴久
堀川, 晃
Tahara, Hirokazu
Masuyama, Takahisa
Horikawa, Koji
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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宇宙科学研究本部 |
| 出版者（英） |
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出版者 |
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) |
| 書誌情報 |
第24回宇宙エネルギーシンポジウム 平成16年度
en : The Twenty-fourth Space Energy Symposium March 7, 2005
p. 92-96,
発行日 2005-06
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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 arcing is suspected to occur on the surface. In this study ground-based experiment was carried out to understand the arcing phenomenon and to examine influences of ambient space plasma on the arcing process. Simulating plasmas were generated by electron cyclotron resonance discharge. When arcing occurred on negatively-biased anodized aluminum sample (AAS) plates in the plasma environment, the time variations in arc current and bias voltage were measured. Arc spot diameter was also measured. The single arcing characteristics showed that both the peak arc current and the total charge emitted by arcing increased with initial charging voltage and neutral particle number density. The diameter of arc spots increased with initial charging voltage although it was almost constant regardless of neutral particle density. The repetitive arcing characteristics showed that the arc rate gradually increased with arcing number. Lots of overlapping arc spot were observed after 1,000 arcings, and its number increased with arcing number. Accordingly, arc tends to occur at a same location as increasing arcing number. Influences of initial charging energy on arcing characteristics were also examined by widely changing capacitance and initial charging voltage. The arc spot diameter widely increased with initial charging energy, and the fitting line could be evaluated. 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 spacecraft capacitance, insulator material properties and ambient plasma conditions. |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: AA0049120019 |
