2011 Fiscal Year Final Research Report
Prediction accuracy evaluation of analysis method for ablation thermal protection system using a general-purpose ablative materials
| Project/Area Number |
22760630
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
SUZUKI Toshiyuki 独立行政法人宇宙航空研究開発機構, 研究開発本部, 研究員 (20392839)
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| Project Period (FY) |
2010 – 2011
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| Keywords | 航空宇宙流体力学 / アブレーション熱防御システム |
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| Research Abstract |
Thermal characteristics of CFRP ablative materials that were developed for a general-purpose are successfully obtained. Thermal properties of the CFRP ablator were measured. The experimental data obtained in the arcjet wind tunnel were analyzed numerically. The thermal response of ablative TPS of the Hayabusa capsule is calculated along the most probable reentry trajectory by using the analysis method. The calculated results are compared with the flight data obtained at the present time. It is found that a reasonable agreement is obtained between the calculated surface temperature and the temperature values estimated from the ground observation. The present analysis method was also applied to the analysis of a lightweight ablator.
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[Journal Article]
Author(s)
Toshiyuki Suzuki, Kazuhisa Fujita, Takeharu Sakai, Kei-ichi Okuyama, Sumio Kato, and Seiji Nishio
Peer Reviewed
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