アーク加熱風洞によるREVアブレータの研究開発

Material type: 文書・図像類

Author: 奥山, 圭一ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2005-03-31

Material Format: Digital

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Note (General)：: REV was the first reentry capsule developed through pure domestic technology and successfully recovered. REV is thermally protected against the severe...

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Material Type: 文書・図像類
Title: アーク加熱風洞によるREVアブレータの研究開発
Author/Editor: 奥山, 圭一
加藤, 純郎
山田, 哲哉
Okuyama, Keiichi
Kato, Sumio
Yamada, Tetsuya
Author Heading: 奥山, 圭一
加藤, 純郎
山田, 哲哉
Okuyama, Keiichi
Kato, Sumio
Yamada, Tetsuya
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: Research and development of REV ablator in arc windtunnel
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: 55-75
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: jpn
Subject Heading: アーク加熱風洞
風洞試験
空力加熱
アブレータ
回収機
リエントリモジュール
CFRP
USERSカプセル
USERSミッション
arc wind tunnel
wind tunnel test
aerodynamic heating
ablator
recovery vehicle
reentry module
USERS capsule
USERS mission
Target Audience: 一般
Note (General): REV was the first reentry capsule developed through pure domestic technology and successfully recovered. REV is thermally protected against the severe aerodynamic heating by carbon-phenolic ablator material. The present paper describes the feature of the heating test in the arc wind tunnel and the ablator characteristics clarified during the research and development process of the REV heat shield. Because the heat flux anticipated on the stagnation surface is about 2 MW/sq m, the dominant surface recession mechanism is identified to be in the reaction control region. The thermochemical reaction data have been acquired through three arc-heater facilities with different enthalpy level for calibration and tuning of the ablation analysis code. The thermomechanical behavior of the ablator under the high heat flux environment such as delamination, or spallation also has been investigated for functional safety of the heat shield.
資料番号: AA0048710005
レポート番号: JAXA-RR-04-045
Access Restrictions: 限定公開
Periodical Title (NCID): AA1192675X
https://ci.nii.ac.jp/ncid/AA1192675X
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