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High-Specific-Impulse Electrostatic Thruster with Argon Propellant
http://hdl.handle.net/2237/00032258
http://hdl.handle.net/2237/00032258959bcdfb-62b7-45d1-9f24-0f77b816bc11
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
JPP-B37675_AUTHOR_submitted (990.2 kB)
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| Item type | 学術雑誌論文 / Journal Article(1) | |||||
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| 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× Matsuba, Toshihiro× Iwakawa, Akira× 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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| 著者版フラグ | ||||||
| 値 | author | |||||
