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Microwave-excited microplasma thruster with helium and hydrogen propellants
http://hdl.handle.net/10131/9070
http://hdl.handle.net/10131/9070d626fa10-66ee-4dd3-a199-a4545599f75b
名前 / ファイル | ライセンス | アクション |
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PHPAEN186063505_1.pdf (4.0 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 | Microwave-excited microplasma thruster with helium and hydrogen propellants | |||||
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 |
Takahashi, Takeshi
× Takahashi, Takeshi× Takao, Yoshinori× Ichida, Yugo× Eriguchi, Koji× Ono, Kouichi |
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著者(ヨミ) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19337 | |||||
姓名 | タカハシ, タケシ | |||||
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 | 19339 | |||||
姓名 | イチダ, ユウゴ | |||||
著者(ヨミ) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19340 | |||||
姓名 | エリグチ, コウジ | |||||
著者(ヨミ) | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19341 | |||||
姓名 | オノ, コウイチ | |||||
著者別名 | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19342 | |||||
姓名 | 高橋, 岳志 | |||||
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 | 19344 | |||||
姓名 | 市田, 有吾 | |||||
著者別名 | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19345 | |||||
姓名 | 江利口, 浩二 | |||||
著者別名 | ||||||
識別子Scheme | WEKO | |||||
識別子 | 19346 | |||||
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 | ||||||
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 | Microplasma thruster of electrothermal type has been investigated with feed or propellant gases of He and H2. The thruster consisted of an azimuthally symmetric microwave-excited microplasma source 1.5 mm in diameter and 10 mm long with a rod antenna on axis, and a converging-diverging micronozzle 1 mm long with a throat 0.2 mm in diameter. Surface wave-excited plasmas were established by 4.0-GHz microwaves at powers of ≤ 6 W, with the sourcepressure in the range 0.5-12 kPa at flow rates of 2-70 sccm. The microplasma generation, micronozzle flow, and thrust performance with He were numerically analyzed by using a two-dimensional fluid model, coupled with an electromagnetic model for microwaves interacting with plasmas in the source region. In experiments, the plasma electron density and gas temperature in the microplasma source were measured at around the top of the microwaveantenna, or just upstream of the micronozzle inlet, by optical emission spectroscopy with a small amount of additive gases of H2 and N2. In the case of He propellant, the Stark broadening of H Balmer-βββ line and the vibronic spectrum of N2 2nd positive (0, 2) band indicated that the electron density was in the range (2-5)×10 19m-3(2-5)×10 19m-3()(2-5)×10 19m-3() and the gas or rotational temperature was in the range 600-700 K. The thrust performance was also measured by using a target-type microthrust stand, giving a thrust in the range 0.04-0.51 mN, a specific impulse in the range 150-270 s, and a thrust efficiency in the range 2%-12%. These experimental results were consistent with those of numerical analysis, depending on microwave power and gas flow rate. Similar plasma characteristics and thrust performance were obtained with H2 propellant, where the specific impulse of ≤ 450 s was more than 1.5 times higher than that with He, owing to a difference in mass between He and H2. A comparison with previous studies with Ar propellant [T. Takahashi et al., Phys. Plasmas16, 083505 (2009)] indicated that in the presence as well as absence of plasma discharge, the specific impulse was enhanced by more than 3-5 times with light-mass propellants He and H2 as has been known for large-scale propulsion systems. Thus, it follows that in the microplasma thruster of electrothermal type, the high diffusivity and thermal conductivity of He and H2 in the microplasma source of high surface-to-volume ratios do not lead to a deterioration of the thrust performance, primarily owing to a more significant thermal energy gain due to elastic collisions between electrons and heavy particles in He and H2. | |||||
書誌情報 |
Physics of Plasmas 巻 18, 号 6, p. 063505-1-063505-12, 発行日 2011-06-23 |
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ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1070664X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA10987555 | |||||
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 |