WEKO3
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水を推進剤とする自己誘起磁場型MPDスラスタの電極形状に関する研究
https://jaxa.repo.nii.ac.jp/records/49533
https://jaxa.repo.nii.ac.jp/records/49533c84088cb-9515-446b-b62e-871844f4d758
名前 / ファイル | ライセンス | アクション |
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SA6000184077.pdf (907.2 kB)
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Item type | 会議発表論文 / Conference Paper(1) | |||||
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公開日 | 2023-05-23 | |||||
タイトル | ||||||
タイトル | 水を推進剤とする自己誘起磁場型MPDスラスタの電極形状に関する研究 | |||||
言語 | ||||||
言語 | jpn | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Study on electrode geometry of a self-field MPD thruster using water propellant | |||||
著者 |
小松, 大介
× 小松, 大介× 各務, 聡× KOMATSU, Daisuke× KAKAMI, Akira |
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著者所属 | ||||||
東京都立大学大学院 | ||||||
著者所属 | ||||||
東京都立大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Metropolitan University | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Metropolitan University | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS) | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS) | |||||
書誌情報 |
令和4年度宇宙輸送シンポジウム: 講演集録 en : Proceedings of Space Transportation Symposium FY2022 発行日 2023-01 |
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会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 令和4年度宇宙輸送シンポジウム(2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)) , 相模原市, 神奈川県 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | This study deals with a water-propellant Magnetoplasma dynamic (MPD) thruster. Though ammonia and hydrogen have been conventionally used as propellants of MPD thrusters, the former is deleterious, the latter embrittles metals, and the both require high-pressure tanks for storage, which complicate the propulsion system. Hence, our group proposed to use water as the propellant. Water is neither toxic nor reactive to materials and requires no high-pressure tank, and hence, the use of water reduces thruster size and costs of ground tests. Furthermore, water is abundant on the earth and available in space because it may be harvestable in celestial objects such as regolith on the moon. In this study, a water MPD thruster was tested at discharge currents ranging from 2 kA to 10 kA to evaluate the dependence of performance on electrode geometry. A ceramic-nozzle anode with an anode radius of 4.8 mm yielded the largest thrust (14 N) and highest thrust efficiency (7 %). ion slip, which was induced by the nozzle divergence, seemed to cause low thrust performance. A circular anode yielded smaller thrust and lower thrust efficiency than the ceramic-nozzle anode. This would be partially attributed to low propellant utilization. | |||||
著者版フラグ | ||||||
出版タイプ | AM | |||||
出版タイプResource | http://purl.org/coar/version/c_ab4af688f83e57aa | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: SA6000184077 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | STEP-2022-025 |