| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2019: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2018: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2017: ¥2,210,000 (Direct Cost: ¥1,700,000、Indirect Cost: ¥510,000)
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| Outline of Final Research Achievements |
An experimental device using an oxy-hydrogen gas torch to simulate an unsteady aerodynamic heating environment during atmospheric entry flights was developed. This device provided a broad range of heat flux and surface temperature conditions, as in existing high-temperature plasma wind tunnels. Moreover, embedded ablation sensor measurements were possible under the time-varying heat flux environment, which is challenging to do in the existing wind tunnel. In the present study, the time history of surface temperature encountered during a space vehicle's atmospheric entry condition was experimentally simulated using the developed device. The results showed a significant difference in the ablation phenomenon between the time-varying and time-constant heating history. The ground testing procedure demonstrated the reproduction of realistic entry flight ablation behavior and the detection of unsteady ablation with embedded ablation sensor measurements.
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