JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
48710006.pdf3.08 MB
titleREV熱防御系の設計と飛行後解析
Other TitleDesign and post-flight analysis of REV thermal protection system
Author(jpn)加藤 純郎; 菅野 義就; 奥山 圭一; 上垣 栄一; 山田 哲哉; 鈴木 俊之
Author(eng)Kato, Sumio; Kanno, Yoshitsugu; Okuyama, Keiichi; Uegaki, Eiichi; Yamada, Tetsuya; Suzuki, Toshiyuki
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; 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; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Kawasaki Heavy Industries Ltd. Aerospace Company; Kawasaki Heavy Industries Ltd. Aerospace Company; Kawasaki Heavy Industries Ltd. Aerospace Company; Kawasaki Heavy Industries Ltd. Aerospace Company; Japan Aerospace Exploration Agency Institute of Space and Astronautical Science; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Issue Date2005-03-31
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
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 page77
End page103
Publication date2005-03-31
Languagejpn
AbstractThe re-entry capsule USERS/REV was successfully recovered in May 2003. REV has a heat shield system to protect inner equipments against the severe heating environment during the re-entry. The heat shield system is mainly made of three kinds of layers, i.e., CFRP ablator, felt type insulation material with thermal anchor and an aluminum shell structure. In the design of the heat shield system, contradictory requirements of heat ejection in orbit and heat protection during the re-entry had to be satisfied. Thermal protection performance of the heat shield system was calculated using an ablation analysis code. Thermal stress analysis of the ablator during the reentry was carried out using a large deformation FEM that considers materials non-linearity. For the development of the heat shield system, various kinds of tests such as the arc-heated tests of the ablator and the strain survey test of the heat shield system were carried out. After the recovery of REV, evaluation of the recovered heat shield system was carried out. The temperature time histories in the ablator obtained during the re-entry and the damage of the heat shield system measured after the recovery were compared with the results of ablation analysis and structural analysis, from which the heating environment during the re-entry and the cause of the damage were estimated. The evaluation of the heat shield system design based on the flight results is also described.
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordsthermal protection system; reentry module; recovery vehicle; ablator; heat shield design; spacecraft reentry; aerodynamic heating; CFRP; post-flight analysis; 熱防御システム; リエントリモジュール; 回収機; アブレータ; ヒートシールド設計; 宇宙機再突入; 空力加熱; CFRP; 飛行後解析
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
SHI-NOAA0048710006
Report NoJAXA-RR-04-045
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/37957


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