WEKO3
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衛星帯電防止用受動型電子エミッタの研究開発と性能改善
https://jaxa.repo.nii.ac.jp/records/7984
https://jaxa.repo.nii.ac.jp/records/7984bbf8cace-6aee-42fd-9893-86a29335250b
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | 衛星帯電防止用受動型電子エミッタの研究開発と性能改善 | |||||
言語 | ||||||
言語 | jpn | |||||
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 | |||||
アクセス権 | ||||||
アクセス権 | metadata only access | |||||
アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Research on development and performance improvement of electron-emitting film for spacecraft charging mitigation | |||||
著者 |
澄田, 貴大
× 澄田, 貴大× 増井, 博一× 岩田, 稔× 豊田, 和弘× 趙, 孟佑× 水口, 善文× 八田, 真児× 藤田, 辰人× Sumida, Takahiro× Khan, Arifur R.× Masui, Hirokazu× Iwata, Minoru× Toyoda, Kazuhiro× Cho, Mengu× Mizuguchi, Yoshifumi× Hatta, Shinji× Fujita, Tatsuhito |
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著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
九州工業大学 | ||||||
著者所属 | ||||||
モレックス喜入 | ||||||
著者所属 | ||||||
MUSCATスペース・エンジニアリング | ||||||
著者所属 | ||||||
宇宙航空研究開発機構研究開発本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology | ||||||
著者所属(英) | ||||||
en | ||||||
Molex Kiire | ||||||
著者所属(英) | ||||||
en | ||||||
MUSCAT Space Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)(ARD) | ||||||
出版者 | ||||||
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) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙エネルギーシンポジウム en : Space Energy Symposium 巻 29, 発行日 2010-02 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 第29回宇宙エネルギーシンポジウム(2010年2月26日, 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス) | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The twenty-ninth Space Energy Symposium (February 26, 2010, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara) | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | As geo-stationary (GEO) satellite bus voltage is increasing due to the size of the satellites, the number of solar array failures due to spacecraft charging is also increasing. It is believed that the failures are initiated by the potential difference between cover glasses and the spacecraft chassis that sharply drops negatively under substorm plasma environment. The potential difference leads to an electrostatic discharge (ESD). If the spacecraft chassis potential can be maintained near zero potential even when the spacecraft encounters the substorm, the danger of discharge can be greatly reduced. We are developing an electron emitter that emits electrons from the conductor by developing enhanced electric field at the triple junction that occur simultaneously while the spacecraft charging. The emitter is composed of a polymer on top of copper plate. Parts of the copper plate are exposed through the polymer creating the triple junctions that are the source of electron emission.This emitter operates in a completely passive fashion. It has a number of advantages over other spacecraft charging mitigation methods; compact in size, lightweight, powerless, cableless and low cost. As the emitter is expected to operate for a long time in orbit, it needs resistance to prolonged space environment exposure and performance upgrading. At this symposium, we reported the resistance of electron emitter to high electron irradiation and the operational simulation. In the ground test, the emitters were biased to a highly negative potential with respect to a grounded vacuum chamber and exposed to electron beam. Through this test, the emission current from each sample emitter is evaluated. We also simulated the operation of the ELF using MUSCAT (Multi-Utility Spacecraft Charging Analysis Tool) to find the best arrangement. | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: カラー図版あり | |||||
内容記述 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 形態: CD-ROM1枚 | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Physical characteristics: Original contains color illustrations | |||||
内容記述(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Note: One CD-ROM | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10324356 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0064737012 |