REV熱防御系の設計と飛行後解析

• Material Type: 文書・図像類
• Title: REV熱防御系の設計と飛行後解析
• Author/Editor: 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
• Author Heading: 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
• Publication, Distribution, etc.: 宇宙航空研究開発機構
• Publication Date: 2005-03-31
• Publication Date (W3CDTF): 2005-03-31
• Alternative Title: Design and post-flight analysis of REV thermal protection system
• Periodical title: 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
• No. or year of volume/issue: JAXA-RR-04-045
• Volume: JAXA-RR-04-045
• Pages: 77-103
• ISSN (Periodical Title): ISSN : 1349-1113
• Text Language Code: jpn
• Subject Heading: 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
• Target Audience: 一般
• Note (General): 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
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2322&item_no=1&attribute_id=31&file_no=1
• Access Restrictions: 限定公開
• Data Provider (Database): 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
• Original Data Provider (Database): 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