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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

High-Specific-Impulse Electrostatic Thruster with Argon Propellant

http://hdl.handle.net/2237/00032258
http://hdl.handle.net/2237/00032258
959bcdfb-62b7-45d1-9f24-0f77b816bc11
名前 / ファイル ライセンス アクション
JPP-B37675_AUTHOR_submitted.pdf JPP-B37675_AUTHOR_submitted (990.2 kB)
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 High-Specific-Impulse Electrostatic Thruster with Argon Propellant
言語 en
著者 Ichihara, Daisuke

× Ichihara, Daisuke

WEKO 99189

en Ichihara, Daisuke

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Matsuba, Toshihiro

× Matsuba, Toshihiro

WEKO 99190

en Matsuba, Toshihiro

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Iwakawa, Akira

× Iwakawa, Akira

WEKO 99191

en Iwakawa, Akira

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Sasoh, Akihiro

× Sasoh, Akihiro

WEKO 99192

en Sasoh, Akihiro

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アクセス権
アクセス権 open access
アクセス権URI http://purl.org/coar/access_right/c_abf2
権利
言語 en
権利情報 Copyright © 2020 by Daisuke Ichihara, Toshihiro Matsuba, Akira Iwakawa, and Akihiro Sasoh. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. 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
内容記述タイプ Abstract
内容記述 In this study, an electrostatic thruster was newly developed, in which a diverging magnetic field with a cusp around a cathode was applied by using two solenoid coils. The effects of the magnetic field strength on thrust performance under a similar applied-magnetic-field configuration were investigated. Because of its light weight and lower price, argon was used as a propellant. By increasing the magnetic field strength, the thrust efficiency was improved owing to the suppression of the discharge current while an almost constant thrust was maintained. A specific impulse of 3800 s with thrust efficiency greater than 30% was obtained; the corresponding mass-averaged exhaust velocity exceeded the value by full-potential electrostatic acceleration of singly charged ions. From the thrust performance, ion beam current, and ion energy distribution function that were experimentally measured under the representative operation condition, 32% of the ion beam current and 43% of the total thrust were evaluated as the contribution of doubly charged ions.
言語 en
出版者
出版者 American Institute of Aeronautics and Astronautics
言語 en
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
出版タイプ
出版タイプ AM
出版タイプResource http://purl.org/coar/version/c_ab4af688f83e57aa
DOI
関連タイプ isVersionOf
識別子タイプ DOI
関連識別子 https://doi.org/10.2514/1.B37675
ISSN(print)
収録物識別子タイプ PISSN
収録物識別子 1533-3876
書誌情報 en : Journal of Propulsion and Power

巻 36, 号 2, p. 256-263, 発行日 2020-03
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