| Project/Area Number |
18206087
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| Research Category |
Grant-in-Aid for Scientific Research (A)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
ABE Takashi Japan Aerospace Exploration Agency, 宇宙科学研究本部, 教授 (60114849)
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| Co-Investigator(Kenkyū-buntansha) |
OTSU Hirotaka 龍谷大学, 理工学部, 准教授 (20313934)
MATSUDA Atsushi 独立行政法人宇宙航空研究開発機構, 宇宙科学研究本部, プロジェクト研究員 (80415900)
KATSURAYAMA Hiroshi 独立行政法人宇宙航空研究開発機構, 宇宙科学研究本部, プロジェクト研究員 (80435809)
FUNAKI Ikko 独立行政法人宇宙航空研究開発機構, 宇宙科学研究本部, 准教授 (50311171)
ISHIKAWA Motoo 筑波大学, システム情報工学研究科, 教授 (90109067)
FUJINO Takayasu 筑波大学, システム情報工学研究科, 講師 (80375427)
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| Co-Investigator(Renkei-kenkyūsha) |
YAMADA Kazuhiko 独立行政法人宇宙航空研究開発機構, 宇宙科学研究本部, 助教 (20415904)
FURUDATE Michiko 東北大学, 大学院・工学系研究科, 助教 (70443992)
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| Project Period (FY) |
2006 – 2009
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| Project Status |
Completed (Fiscal Year 2009)
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| Budget Amount *help |
¥48,620,000 (Direct Cost: ¥37,400,000、Indirect Cost: ¥11,220,000)
Fiscal Year 2009: ¥6,110,000 (Direct Cost: ¥4,700,000、Indirect Cost: ¥1,410,000)
Fiscal Year 2008: ¥11,310,000 (Direct Cost: ¥8,700,000、Indirect Cost: ¥2,610,000)
Fiscal Year 2007: ¥14,950,000 (Direct Cost: ¥11,500,000、Indirect Cost: ¥3,450,000)
Fiscal Year 2006: ¥16,250,000 (Direct Cost: ¥12,500,000、Indirect Cost: ¥3,750,000)
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| Keywords | 宇宙往還機 / 高温弱電離気体 / 流れの制御 / 電磁力アクチュエータ / 高温非平衡流れ / 電磁カアクチュエータ / 高温弱電離流れ / 電磁力アクチュエーター / 電磁アクチュエータ |
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| Research Abstract |
The spacecraft reentering into the atmosphere experiences a sever aerodynamic heating caused by the hot plasma flow around it. For flight safety, it is required to mitigate such a sever heating environment in addition to developing a heat protection system for the spacecraft. Because the hot plasma is influenced by the existence of the electromagnetic field, we conducted a feasibility study to make use of the electromagnetic force to mitigate such a severe heating environment. The present result shows that such a mitigation is feasible by making use of an appropriate static magnetic field configuration around the spacecraft. Furthermore, it is shown that an appropriate flight experiment to validate such a measure is feasible.
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