| 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 |
Ground-based experiment of electric breakdown of spacecraft insulator surface in ambient plasma environment |
|
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 |
|
主題 |
アーク放電 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
低高度地球周回軌道 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
LEO衛星 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
地上実験 |
| キーワード |
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|
主題Scheme |
Other |
|
主題 |
絶縁破壊 |
| キーワード |
|
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主題Scheme |
Other |
|
主題 |
宇宙機設計 |
| キーワード |
|
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主題Scheme |
Other |
|
主題 |
航空宇宙環境 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
表面絶縁体 |
| キーワード |
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言語 |
en |
|
主題Scheme |
Other |
|
主題 |
arc discharge |
| キーワード |
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|
言語 |
en |
|
主題Scheme |
Other |
|
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 |
|
主題 |
LEO satellite |
| キーワード |
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|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
ground-based experiment |
| キーワード |
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|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
electric breakdown |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
spacecraft design |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
aerospace environment |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
surface insulator |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_5794 |
|
資源タイプ |
conference paper |
| 著者 |
田原, 弘一
増山, 貴久
堀川, 晃司
Tahara, Hirokazu
Masuyama, Takahisa
Horikawa, Koji
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| 著者所属 |
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|
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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） |
|
|
|
en |
|
|
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） |
|
|
|
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） |
|
|
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. 58-64,
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 |
|
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. Accordingly, high voltage operation of LEO spacecraft might bring drastic degradation of AAS by arcing, depending on ambient plasma conditions and spacecraft capacitance. |
| ISSN |
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収録物識別子タイプ |
ISSN |
|
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 |
|
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: AA0049206007 |
| 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 |
49206007.pdf (2.8 MB)
