JAXA Repository / AIREX 未来へ続く、宙(そら)への英知

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title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
Other TitleResearch on development and performance improvement of electron-emitting film for spacecraft charging mitigation
Author(jpn)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
Author(eng)Sumida, Takahiro; Khan, Arifur R.; Masui, Hirokazu; Iwata, Minoru; Toyoda, Kazuhiro; Cho, Mengu; Mizuguchi, Yoshifumi; Hatta, Shinji; Fujita, Tatsuhito
Author Affiliation(jpn)九州工業大学; 九州工業大学; 九州工業大学; 九州工業大学; 九州工業大学; 九州工業大学; モレックス喜入; MUSCATスペース・エンジニアリング; 宇宙航空研究開発機構研究開発本部
Author Affiliation(eng)Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Molex Kiire; MUSCAT Space Engineering; Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)(ARD)
Issue Date2010-02
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構宇宙科学研究本部
Publication titleSpace Energy Symposium
宇宙エネルギーシンポジウム
Volume29
Publication date2010-02
Languagejpn
eng
AbstractAs 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.
DescriptionOriginal contains color illustrations
Meeting Information: The twenty-ninth Space Energy Symposium (February 26, 2010, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara)
形態: カラー図版あり
会議情報: 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)
形態: CD-ROM1枚
Note: One CD-ROM
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
NCIDAN10324356
SHI-NOAA0064737012
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/19683


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