| Project/Area Number |
16K06899
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Multi-year Fund |
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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 |
Takayanagi Hiroki 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 研究開発員 (70513422)
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| Project Period (FY) |
2016-04-01 – 2020-03-31
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| Project Status |
Completed (Fiscal Year 2019)
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| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2018: ¥780,000 (Direct Cost: ¥600,000、Indirect Cost: ¥180,000)
Fiscal Year 2017: ¥1,690,000 (Direct Cost: ¥1,300,000、Indirect Cost: ¥390,000)
Fiscal Year 2016: ¥2,340,000 (Direct Cost: ¥1,800,000、Indirect Cost: ¥540,000)
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| Keywords | 航空宇宙流体力学 / 発光分光計測 / 輻射解析 / 膨張波管 / 熱流束計測 / 衝撃波管 / 赤外域発光強度スペクトル / 航行宇宙流体力学 / 赤外域発光強度スペクトル計測 / 航空宇宙工学 |
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| Outline of Final Research Achievements |
In this study, we performed infrared radiation intensity measurement around Mars entry capsule model with the expansion tube developed in JAXA Chofu space center. In addition, we evaluated the CO2 number density and temperature distribution by IR radiation spectroscopy coupled with the radiation analysis code, SPRADIAN2. Finally, selected an appropriate test flow condition in order to avoid the IR radiation in the test flow, we could obtain the IR radiation intensity distribution around Mars entry model.
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| Academic Significance and Societal Importance of the Research Achievements |
本研究では調布航空宇宙センターにおいて開発している高速膨張波管を用いて，火星大気突入機模型周りの赤外域放射強度分布計測を実施するとともに膨張波管試験気流における二酸化炭素数密度分布および温度分布を実施し、火星大気突入機周りの流れ場解析に取り組んだ。本研究の結果は我が国における将来の火星大気突入機開発に生かすことができる。
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