Microplasma thruster for ultra-small satellites: Plasma chemical and aerodynamical aspects
A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm in diameter and ~10 mm long, being operated at around atmospheric pressures; the micronozzle was a converging-diverging type, having a throat...
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Published in: | Pure and applied chemistry Vol. 80; no. 9; pp. 2013 - 2023 |
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Main Authors: | , , , |
Format: | Journal Article |
Language: | English |
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Berlin
De Gruyter
01-09-2008
Walter de Gruyter GmbH |
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Abstract | A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm in diameter and ~10 mm long, being operated at around atmospheric pressures; the micronozzle was a converging-diverging type, having a throat ~0.2 mm in diameter and ~1 mm long. Numerical and experimental results with Ar as a working gas demonstrated that this miniature electrothermal thruster gives a thrust of >1 mN, a specific impulse of ~100 s, and a thrust efficiency of ~10 % at a microwave power of <10 W, making it applicable to attitude-control and station-keeping maneuver for a microspacecraft of <10 kg. |
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AbstractList | A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm in diameter and ~10 mm long, being operated at around atmospheric pressures; the micronozzle was a converging-diverging type, having a throat ~0.2 mm in diameter and ~1 mm long. Numerical and experimental results with Ar as a working gas demonstrated that this miniature electrothermal thruster gives a thrust of >1 mN, a specific impulse of ~100 s, and a thrust efficiency of ~10 % at a microwave power of <10 W, making it applicable to attitude-control and station-keeping maneuver for a microspacecraft of <10 kg. |
Author | Takahashi, Takeshi Eriguchi, Koji Ono, Kouichi Takao, Yoshinori |
Author_xml | – sequence: 1 givenname: Yoshinori surname: Takao fullname: Takao, Yoshinori organization: Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University, Yoshida-Honmachi, Sakyo-ku, Kyoto 606-8501, Japan – sequence: 2 givenname: Takeshi surname: Takahashi fullname: Takahashi, Takeshi organization: Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University, Yoshida-Honmachi, Sakyo-ku, Kyoto 606-8501, Japan – sequence: 3 givenname: Koji surname: Eriguchi fullname: Eriguchi, Koji organization: Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University, Yoshida-Honmachi, Sakyo-ku, Kyoto 606-8501, Japan – sequence: 4 givenname: Kouichi surname: Ono fullname: Ono, Kouichi organization: Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto University, Yoshida-Honmachi, Sakyo-ku, Kyoto 606-8501, Japan |
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Cites_doi | 10.2514/4.866586 10.1007/978-3-7091-0547-4 10.1143/JJAP.45.8235 10.1063/1.2188594 10.1023/A:1024514719608 10.1088/0963-0252/12/2/319 10.1016/j.tsf.2005.08.066 10.2514/4.989032 10.1063/1.2399886 10.1063/1.2749336 10.1016/j.tsf.2005.08.045 10.1016/j.vacuum.2006.01.053 10.2514/1.9247 10.1063/1.1428784 10.1063/1.2335612 10.1063/1.1849816 10.1116/1.582265 10.1063/1.2214127 10.1063/1.2360781 10.1063/1.1753658 10.1143/JJAP.41.2199 10.1088/0963-0252/15/2/006 10.1116/1.581428 |
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Snippet | A microplasma thruster has been developed of electrothermal type using azimuthally symmetric microwave-excited microplasmas. The microplasma source was ~2 mm... |
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SubjectTerms | electric propulsion Energy conversion efficiency microdischarge micronozzle flow microplasma microplasma jets Microplasmas micropropulsion Microspacecraft microthrusters nano- and pico-satellites Organic chemistry plasma thrusters Power efficiency Small satellites Specific impulse surface wave-excited plasma |
Title | Microplasma thruster for ultra-small satellites: Plasma chemical and aerodynamical aspects |
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