| Project/Area Number |
26630450
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| Research Category |
Grant-in-Aid for Challenging Exploratory Research
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
Funaki Ikkoh 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 准教授 (50311171)
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| Co-Investigator(Kenkyū-buntansha) |
HORISAWA Hideyuki 東海大学, 工学部, 教授 (30256169)
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| Research Collaborator |
OSHIO Yuya 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, プロジェクト研究員
HIGASHIURA Kohsuke 法政大学, 大学院理工学研究科, 大学院生
KUBO Kai 法政大学, 大学院理工学研究科, 大学院生
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| Project Period (FY) |
2014-04-01 – 2016-03-31
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| Project Status |
Completed (Fiscal Year 2015)
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| Budget Amount *help |
¥3,770,000 (Direct Cost: ¥2,900,000、Indirect Cost: ¥870,000)
Fiscal Year 2015: ¥1,690,000 (Direct Cost: ¥1,300,000、Indirect Cost: ¥390,000)
Fiscal Year 2014: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
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| Keywords | 航空宇宙工学 / 推進・エンジン / レーザー / マイクロスラスタ / イオン液体 |
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| Outline of Final Research Achievements |
Experimental study of laser micro-thruster was conducted. Targeting at laser thruster without any valve to supply propellant, metal as well as liquid propellant were employed and it was tested by a system consisting of propellant target and a thrust stand mounting the propellant target, both of which were installed inside a vacuum chamber. When infrared laser beam was irradiated from outside the vacuum chamber, the propellant was found to released as a plasma jet. From the result, the concept of laser micro-thruster with variable thrust level was demonstrated, but it should work in a more wide condition to directly apply the system to accurate spacecraft attitude control.
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