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  1. B200 工学部/工学研究科
  2. B200a 雑誌掲載論文
  3. 学術雑誌

Central and External Cathode Operations in a Diverging-Magnetic-Field Electrostatic Thruster

http://hdl.handle.net/2237/00032257
c91bc3ab-e5ab-4da2-95b0-2fe321c3b798
名前 / ファイル ライセンス アクション
JPP-B37636_AUTHOR_1_Revised.pdf JPP-B37636_AUTHOR_1_Revised (1.3 MB)
Item type 学術雑誌論文 / Journal Article(1)
公開日 2020-05-26
タイトル
タイトル Central and External Cathode Operations in a Diverging-Magnetic-Field Electrostatic Thruster
著者 Ichihara, Daisuke

× Ichihara, Daisuke

WEKO 99185

Ichihara, Daisuke

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Nakagawa, Yoshiya

× Nakagawa, Yoshiya

WEKO 99186

Nakagawa, Yoshiya

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Iwakawa, Akira

× Iwakawa, Akira

WEKO 99187

Iwakawa, Akira

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Sasoh, Akihiro

× Sasoh, Akihiro

WEKO 99188

Sasoh, Akihiro

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権利
権利情報 Copyright © 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-3876 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
抄録
内容記述 The effects of hollow cathode position on thrust performances of a diverging-magnetic-field electrostatic thruster, which had a diverging magnetic field between a ring anode and a hollow cathode, were investigated. The hollow cathode was located in either a central or an external configuration. Based on the discharge current and direct thrust measurements, electrostatic and magnetic hybrid plasma acceleration was observed in the central cathode operation and even in the external cathode operation especially when magnetic field strength was less than 315 mT. However, the operating points were different: low discharge voltage×large discharge current in the central cathode operation, and high discharge voltage×small discharge current in the external cathode operation. This difference comes from electron-Hall parameter; the estimated electron-Hall parameter was about 50 in the central cathode operation, which was much lower than that of 3000 in the external cathode operation. By combining electromagnetic acceleration, the generated thrust can increase even with lower electron-Hall parameter operation. As a result, similar thrust performances were achieved in both cathode positions. Because of the hybrid plasma acceleration method, thrust density reached 50  N/m^2, which is comparable or even higher than that of the conventional electrostatic thrusters.
内容記述タイプ Abstract
内容記述
内容記述 Published Online:14 Nov 2019
内容記述タイプ Other
出版者
出版者 American Institute of Aeronautics and Astronautics
言語
言語 eng
資源タイプ
資源タイプresource http://purl.org/coar/resource_type/c_6501
タイプ journal article
DOI
関連識別子
識別子タイプ DOI
関連識別子 https://doi.org/10.2514/1.B37636
ISSN(print)
収録物識別子タイプ ISSN
収録物識別子 1533-3876
書誌情報 Journal of Propulsion and Power

巻 36, 号 1, p. 68-77, 発行日 2020-01
著者版フラグ
値 author
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