@inproceedings{oai:jaxa.repo.nii.ac.jp:00007984,
 author = {澄田, 貴大 and 増井, 博一 and 岩田, 稔 and 豊田, 和弘 and 趙, 孟佑 and 水口, 善文 and 八田, 真児 and 藤田, 辰人 and Sumida, Takahiro and Khan, Arifur R. and Masui, Hirokazu and Iwata, Minoru and Toyoda, Kazuhiro and Cho, Mengu and Mizuguchi, Yoshifumi and Hatta, Shinji and Fujita, Tatsuhito},
 book = {宇宙エネルギーシンポジウム, Space Energy Symposium},
 month = {Feb},
 note = {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), The twenty-ninth Space Energy Symposium (February 26, 2010, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara), 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., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0064737012},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 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},
 volume = {29},
 year = {2010}
}