| Project/Area Number |
15K14251
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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 | Tottori University (2016)
Nagoya University (2015) |
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Principal Investigator |
SAKAI TAKEHARU 鳥取大学, 工学(系)研究科(研究院), 教授 (90323047)
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| Co-Investigator(Renkei-kenkyūsha) |
ISHIDA Yuichi 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 主任研究開発員 (20371114)
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| Project Period (FY) |
2015-04-01 – 2017-03-31
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| Project Status |
Completed (Fiscal Year 2016)
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| Budget Amount *help |
¥3,900,000 (Direct Cost: ¥3,000,000、Indirect Cost: ¥900,000)
Fiscal Year 2016: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
Fiscal Year 2015: ¥1,820,000 (Direct Cost: ¥1,400,000、Indirect Cost: ¥420,000)
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| Keywords | アブレーション / 輻射加熱 / 低密度炭素材 / 空力加熱 / アーク加熱風洞 / 数値シミュレーション / 航空宇宙工学 / アブレ－ション / 低密度熱防御材 / 数値解析 / 炭素多孔質材 / 高温 / 輻射伝熱 |
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| Outline of Final Research Achievements |
Thermal response of carbon-based and char materials in an aerodynamic heating environment was studied experimentally and numerically. Radiative transfer in the materials was modeled using an effective radiative conductivity, which was evaluated through a radiative extinction coefficient deduced from a ray-tracing calculation using the X-ray CT models of the materials. Aerodynamic heating experiments were made using JAXA arcjet wind tunnel facilities, and the thermal response of the material’s test specimen was numerically simulated using the radiative conductivity model. Comparison of in-depth temperature between calculation and measurement showed that overall trends in the measured time history of the temperatures was reproduced for all the materials examined in this study when the radiative conductivity was included in the calculation, suggesting that the radiative transfer within the low density carbon material can be modeled by the proposed method in this study.
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