2009 Fiscal Year Final Research Report
Control of weakly-ionized flow around reentry spacecraft and a feasibility study for its application
| 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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| Keywords | 宇宙往還機 / 高温弱電離気体 / 流れの制御 |
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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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