| Project/Area Number |
21226019
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| Research Category |
Grant-in-Aid for Scientific Research (S)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Tokyo University of Agriculture and Technology (2010-2013)
Kyushu University (2009) |
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Principal Investigator |
SHINOHARA Shunjiro 東京農工大学, 工学(系)研究科(研究院), 教授 (10134446)
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| Co-Investigator(Kenkyū-buntansha) |
TANIKAWA Takao 東海大学, 総合科学技術研究所, 教授 (70207174)
HADA Tohru 九州大学, 大学院総合理工学研究院, 教授 (30218490)
FUNAKI Ikkoh 宇宙航空研究開発機構, 宇宙科学研究所, 准教授 (50311171)
NISHIDA Hiroyuki 東京農工大学, 大学院工学研究院, 准教授 (60545945)
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| Co-Investigator(Renkei-kenkyūsha) |
YAMAGATA Yukihiko 九州大学, 大学院総合理工学研究院, 准教授 (70239862)
INOMOTO Michiaki 東京大学, 大学院新領域創成科学研究科, 准教授 (00324799)
TAKAHASHI Kazunori 東北大学, 工学研究科, 准教授 (80451491)
ONISHI Naofumi 東北大学, 工学研究科, 准教授 (20333859)
KUWAHARA Daisuke 東京農工大学, 大学院工学研究院, 助教 (60645688)
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| Project Period (FY) |
2009-05-11 – 2014-03-31
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| Project Status |
Completed (Fiscal Year 2013)
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| Budget Amount *help |
¥208,910,000 (Direct Cost: ¥160,700,000、Indirect Cost: ¥48,210,000)
Fiscal Year 2013: ¥17,680,000 (Direct Cost: ¥13,600,000、Indirect Cost: ¥4,080,000)
Fiscal Year 2012: ¥20,540,000 (Direct Cost: ¥15,800,000、Indirect Cost: ¥4,740,000)
Fiscal Year 2011: ¥22,230,000 (Direct Cost: ¥17,100,000、Indirect Cost: ¥5,130,000)
Fiscal Year 2010: ¥57,330,000 (Direct Cost: ¥44,100,000、Indirect Cost: ¥13,230,000)
Fiscal Year 2009: ¥91,130,000 (Direct Cost: ¥70,100,000、Indirect Cost: ¥21,030,000)
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| Keywords | 航空宇宙工学 / プラズマ・核融合 / ロケット / ヘリコンプラズマ / 無電極 / 加速 / モデル化 / 熱流体工学 / ヘリコン |
|---|
| Research Abstract |
Fuel cost using electric propulsion is better (specific impulse is higher) than chemical one. The contact erosion between a plasma and electrodes, producing and accelerating the plasma, leads to a lifetime shortage. To overcome this, our study had "electrodeless" conditions.
Helicon sources have been developed and characterized: The largest (smallest) diameter of 74 (0.3) cm was achieved, and the scalings of the production efficiency have been established. Roles of a helicon and a TG waves were examined. We have proposed many acceleration schemes: A helicon source alone showed the maximum specific impulse of 3,000 s and the maximum ratio of thrust to power of 16 mN/kW. The excited magnetic field penetration and the ion velocity increase were found in the RMF scheme. Methods such as REF and PA/ICR were also advanced. We have developed the two-dimensional measurement systems using laser induced fluorescence and high-resolution spectroscopy, and the various types of the thrust stands.
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| Assessment Rating |
Verification Result (Rating)
A
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