JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
48710004.pdf1.88 MB
Other TitleValidation and post-flight analysis of the ablation analysis code
Author(jpn)加藤 純郎; 奥山 圭一; 山田 哲哉
Author(eng)Kato, Sumio; Okuyama, Keiichi; Yamada, Tetsuya
Author Affiliation(jpn)川崎重工業 航空宇宙カンパニー; 川崎重工業 航空宇宙カンパニー; 宇宙航空研究開発機構 宇宙科学研究本部
Author Affiliation(eng)Kawasaki Heavy Industries Ltd. Aerospace Company; Kawasaki Heavy Industries Ltd. Aerospace Company; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science
Issue Date2005-03-31
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication titleUSERS REVカプセルの開発研究および飛行後解析
Research and Development of USERS REV Capsule and its Post-flight Analysis
Start page31
End page54
Publication date2005-03-31
AbstractA computer code for charring ablation and thermal response analysis has been developed for simulation of one-dimensional transient thermal behavior of multi-layer stack of isotropic charring ablation materials used for re-entry capsules. A mathematical model of charring ablation including governing equations is summarized. Analytical solutions of several thermal response problems with or without ablation agreed very well with numerical results that are obtained with the charring ablation analysis code. Arc-heated tests of CFRP ablator models were carried out and measured results including temperature response data were compared with the simulation results of the ablation analysis code. The test results and the simulation results agreed very well. Measurements of the successfully recovered USERS/REV ablator were carried out. The measured results of the in-depth temperature history in the ablator, the char depth, the surface recession, etc. agreed well with the simulation results using the ablation analysis code. These results show that the ablation analysis code based on the present mathematical model are available for the thermal response prediction of CFRP ablator used in the re-entry capsules such as USERS/REV.
DescriptionJAXA Research and Development Report
Keywordsspacecraft reentry; USERS capsule; ablation analysis code; computer program; aerodynamic heating; thermal protection; mathematical model; ablation; CFRP; post-flight analysis; 宇宙機再突入; USERSカプセル; アブレーション解析コード; 計算機プログラム; 空力加熱; 熱防御; 数学モデル; アブレーション; CFRP; 飛行後解析
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-04-045

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