アブレーション解析コードと飛行後解析

Material type: 文書・図像類

Author: 加藤, 純郎ほか

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)：: A computer code for charring ablation and thermal response analysis has been developed for simulation of one-dimensional transient thermal behavior of...

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Material Type: 文書・図像類
Title: アブレーション解析コードと飛行後解析
Author/Editor: 加藤, 純郎
奥山, 圭一
山田, 哲哉
Kato, Sumio
Okuyama, Keiichi
Yamada, Tetsuya
Author Heading: 加藤, 純郎
奥山, 圭一
山田, 哲哉
Kato, Sumio
Okuyama, Keiichi
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: Validation and post-flight analysis of the ablation analysis code
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: 31-54
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: jpn
Subject Heading: 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
spacecraft reentry
USERS capsule
ablation analysis code
computer program
aerodynamic heating
thermal protection
mathematical model
ablation
post-flight analysis
Target Audience: 一般
Note (General): A 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.
資料番号: AA0048710004
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