JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
61882000.pdf1.32 MB
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
Other TitleValidation of thermal stress reduction design of CFRP cryogenic propellant tank by LN2 immersion test
Author(jpn)吉村, 彰記; 小笠原, 俊夫; 末益, 博志
Author(eng)Yoshimura, Akinori; Ogasawara, Toshio; Suemasu, Hiroshi
Author Affiliation(jpn)宇宙航空研究開発機構研究開発本部複合材技術研究センター(JAXA); 宇宙航空研究開発機構研究開発本部複合材技術研究センター(JAXA); 上智大学理工学部機能創造理工学科
Author Affiliation(eng)Advanced Composite Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Advanced Composite Research Center, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA); Department of Engineering and Applied Sciences, Faculty of Science and Technology, Sophia University
Issue Date2013-02-28
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発資料
JAXA research and development memorandum
VolumeJAXA-RM-12-012
Start page1
End page8
Publication date2013-02-28
Languagejpn
eng
AbstractDrastic 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.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
KeywordsComposite Materials; Structural Design; Structural Analysis; Cryogenic Tank; Thermal Stress
Document TypeTechnical Report
JAXA Category研究開発資料
ISSN1349-1121
NCIDAA11983593
SHI-NOAA0061882000
Report NoJAXA-RM-12-012
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/14869


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.