@inproceedings{oai:jaxa.repo.nii.ac.jp:00015068,
 author = {末益, 博志 and 和羅, 貴之 and 青木, 雄一郎 and Suemasu, Hiroshi and Wara, Takayuki and Aoki, Yuichiro},
 book = {宇宙構造・材料シンポジウム, Symposium on Aerospace Structure and Materials},
 month = {Mar},
 note = {宇宙構造・材料シンポジウム(第24回)(2008年12月12日、宇宙航空研究開発機構宇宙科学研究本部), 24th Symposium on Aerospace Structure and Materials (December 12, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, Debonding problem of cryogenic carbon fiber reinforced composite vessels with aluminium liner subjected to thermal stress and internal pressure is studied fracture-mechanically by using a finite element analysis. The dome portions of the vessel whose shape is derived based on the orthotropic membrane theory [1] are assumed to be axi-symmetric and the geometric nonlinearity is considered. The energy release rate is obtained by using virtual crack closure technique. The energy release rate due to the thermal stress is found to be significant to cause debonding at the cap portion. For types of shapes are studied to show the feasibility of the reduction of the energy release rate by the design of the boss shape., 資料番号: AA0064731009},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {極低温用フィラメントワインディング圧力容器の口金部のはく離に関する一考察},
 volume = {24},
 year = {2009}
}