液体窒素浸漬試験による複合材料製極低温推進剤タンクの熱応力軽減設計の検証

Material type: 文書・図像類

Author: 吉村, 彰記ほか

Publisher: 宇宙航空研究開発機構(JAXA)

Publication date: 2013-02-28

Material Format: Digital

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Note (General)：: Drastic structural weight reduction is needed in order to make possible the practical reusable space transportation system. Utilization of carbon fibe...

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Material Type: 文書・図像類
Title: 液体窒素浸漬試験による複合材料製極低温推進剤タンクの熱応力軽減設計の検証
Author/Editor: 吉村, 彰記
小笠原, 俊夫
末益, 博志
Yoshimura, Akinori
Ogasawara, Toshio
Suemasu, Hiroshi
Author Heading: 吉村, 彰記
小笠原, 俊夫
末益, 博志
Yoshimura, Akinori
Ogasawara, Toshio
Suemasu, Hiroshi
Publication, Distribution, etc.: 宇宙航空研究開発機構(JAXA)
Publication Date: 2013-02-28
Publication Date (W3CDTF): 2013-02-28
Alternative Title: Validation of thermal stress reduction design of CFRP cryogenic propellant tank by LN2 immersion test
Periodical title: 宇宙航空研究開発機構研究開発資料 = JAXA Research and Development Memorandum
No. or year of volume/issue: JAXA-RM-12-012
Volume: JAXA-RM-12-012
Pages: 1-8
ISSN (Periodical Title): ISSN : 1349-1121
Text Language Code: jpn
Subject Heading: Composite Materials
Structural Design
Structural Analysis
Cryogenic Tank
Thermal Stress
Target Audience: 一般
Note (General): Drastic structural weight reduction is needed in order to make possible the practical reusable space transportation system. Utilization of carbon fiber reinforced plastic (CFRP) to the structural material of cryogenic propellant tank can significantly reduce the structural weight. However, at the cryogenic temperature, significant thermal stress occurs between the metallic mouthpiece (boss) and the CFRP tank wall because of the large difference of the coefficients of the thermal expansion (CTE). The thermal stress causes the debonding between the boss and the wall, and it may lead to the catastrophic failure of the whole tank structure. Recently, the design method which can relax the thermal stress was proposed by Suemasu and his colleagues. However, the method was not demonstrated experimentally yet. Therefore in the present study, four types of cryogenic composite tank specimen were manufactured. Two specimens were designed by the proposed method. The specimens were cooled down to cryogenic temperature (-190 C) by immersing them into the liquid nitrogen pool. The test results demonstrated the validity of the method. The results showed that we could design the practical CFRP cryogenic tank by the proposed method.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA0061882000
レポート番号: JAXA-RM-12-012
Access Restrictions: 限定公開
Periodical Title (NCID): AA11983593
https://ci.nii.ac.jp/ncid/AA11983593
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