REV熱防御系の設計と飛行後解析

• 資料種別: 規格・テクニカルリポート類
• タイトル: REV熱防御系の設計と飛行後解析
• 著者・編者: 加藤, 純郎; 菅野, 義就; 奥山, 圭一; 上垣, 栄一; 山田, 哲哉; 鈴木, 俊之; Kato, Sumio; Kanno, Yoshitsugu; Okuyama, Keiichi; Uegaki, Eiichi; Yamada, Tetsuya; Suzuki, Toshiyuki
• 著者標目: 加藤, 純郎; 菅野, 義就; 奥山, 圭一; 上垣, 栄一; 山田, 哲哉; 鈴木, 俊之; Kato, Sumio; Kanno, Yoshitsugu; Okuyama, Keiichi; Uegaki, Eiichi; Yamada, Tetsuya; Suzuki, Toshiyuki
• 出版事項: 宇宙航空研究開発機構
• 出版年月日等: 2005-03-31
• 出版年（W3CDTF）: 2005-03-31
• 並列タイトル等: Design and post-flight analysis of REV thermal protection system
• タイトル（掲載誌）: 宇宙航空研究開発機構研究開発報告: USERS REVカプセルの開発研究および飛行後解析 = JAXA Research and Development Report: Research and Development of USERS REV Capsule and its Post-flight Analysis
• 巻号年月日等（掲載誌）: JAXA-RR-04-045
• 掲載巻: JAXA-RR-04-045
• 掲載ページ: 77-103
• ISSN（掲載誌）: ISSN : 1349-1113
• 本文の言語コード: jpn
• 件名標目: 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; thermal protection system; reentry module; recovery vehicle; ablator; heat shield design; spacecraft reentry; aerodynamic heating; post-flight analysis
• 対象利用者: 一般
• 一般注記: 出版タイプ： NA; The 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.; 資料番号: AA0048710006; レポート番号: JAXA-RR-04-045
• 掲載誌（NCID）: AA1192675X; https://ci.nii.ac.jp/ncid/AA1192675X
• 連携機関・データベース: 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• 提供元機関・データベース: 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ