| Project/Area Number |
16K14509
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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 | Japan Aerospace EXploration Agency |
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Principal Investigator |
OGAWA HIROYUKI 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 教授 (60311172)
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| Co-Investigator(Kenkyū-buntansha) |
長野 方星 名古屋大学, 工学研究科, 教授 (10435810)
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| Project Period (FY) |
2016-04-01 – 2018-03-31
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| Project Status |
Completed (Fiscal Year 2017)
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| Budget Amount *help |
¥3,640,000 (Direct Cost: ¥2,800,000、Indirect Cost: ¥840,000)
Fiscal Year 2017: ¥2,340,000 (Direct Cost: ¥1,800,000、Indirect Cost: ¥540,000)
Fiscal Year 2016: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
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| Keywords | 線膨張係数 / 熱伝導率 / 天文衛星 / 熱ひずみ / 光ヘテロダイン干渉計 / 熱的寸法安定性 / 熱物性 / 宇宙機熱制御 |
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| Outline of Final Research Achievements |
In order to achieve a high precise thermal strain design of spacecraft, a simultaneous measurement for a coefficient of thermal expansion (CTE) and a thermal diffusivity has been proposed, and its feasibility was experimentally examined. A new measurement method which consists of a heterodyne interferometry which has a good advantage in high wavelength resolution for the CTE, and periodic heating method for the thermal diffusivity has been developed. First, a measurement accuracy was evaluated with a single crystal silicon. Second, the temperature dependence of the CTE for carbon fiber reinforced plastic was measured, finally, a simultaneous measurement of the CTE and the thermal diffusivity for Al alloy was conducted and its high-accurate measurement was demonstrated.
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