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A miniature electrothermal thruster using microwave-excited microplasmas: thrust measurement and its comparison with numerical analysis
http://hdl.handle.net/10131/9078
http://hdl.handle.net/10131/9078d033537d-f608-49c2-9bf9-aa96c025e656
名前 / ファイル | ライセンス | アクション |
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JAP2007_101_123307_Takao.pdf (1.4 MB)
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Item type | 学術雑誌論文 / Journal Article(1) | |||||
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公開日 | 2015-03-10 | |||||
タイトル | ||||||
タイトル | A miniature electrothermal thruster using microwave-excited microplasmas: thrust measurement and its comparison with numerical analysis | |||||
言語 | ||||||
言語 | eng | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||
資源タイプ | journal article | |||||
著者 |
Takao, Yoshinori
× Takao, Yoshinori× Eriguchi, Koji× Ono, Kouichi |
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著者(ヨミ) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 714 | |||||
識別子Scheme | e-Rad | |||||
識別子URI | https://kaken.nii.ac.jp/ja/search/?qm=80552661 | |||||
識別子 | 80552661 | |||||
姓名 | タカオ, ヨシノリ | |||||
著者(ヨミ) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19449 | |||||
姓名 | エリグチ, コウジ | |||||
著者(ヨミ) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19450 | |||||
姓名 | オノ, コウイチ | |||||
著者別名 | ||||||
識別子Scheme | WEKO | |||||
識別子 | 714 | |||||
識別子Scheme | e-Rad | |||||
識別子URI | https://kaken.nii.ac.jp/ja/search/?qm=80552661 | |||||
識別子 | 80552661 | |||||
姓名 | 鷹尾, 祥典 | |||||
著者別名 | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19452 | |||||
姓名 | 江利口, 浩二 | |||||
著者別名 | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19453 | |||||
姓名 | 斧, 髙一 | |||||
著者所属 | ||||||
Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University | ||||||
著者所属 | ||||||
Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University | ||||||
著者所属 | ||||||
Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University | ||||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | A microplasma thruster has been developed, consisting of a cylindrical microplasma source 10mm long and 1.5mm in inner diameter and a conical micronozzle 1.0-1.4mm long with a throat of 0.12-0.2mm in diameter. The feed or propellant gas employed is Ar at pressures of 10-100kPa, and the surface-wave-excited plasma is established by 4.0GHz microwaves at powers of <10W. The thrust has been measured by a combination of target and pendulum methods, exhibiting the performance improved by discharging the plasma. The thrust obtained is 1.4mN at an Ar gas flow rate of 60SCCM (1.8mg/s) and a microwave power of 6W, giving a specific impulse of 79s and a thrust efficiency of 8.7%. The thrust and specific impulse are 0.9mN and 51s, respectively, in cold-gas operation. A comparison with numerical analysis indicates that the pressure thrust contributes significantly to the total thrust at low gas flow rates, and that the micronozzle tends to have an isothermal wall rather than an adiabatic. | |||||
書誌情報 |
Journal of Applied Physics 巻 101, 号 12, p. 123307-1-123307-10, 発行日 2007-06-15 |
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ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 00218979 | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA00693547 | |||||
著者版フラグ | ||||||
出版タイプ | VoR | |||||
出版タイプResource | http://purl.org/coar/version/c_970fb48d4fbd8a85 |