@inproceedings{oai:jaxa.repo.nii.ac.jp:00015031,
 author = {田中, 太朗 and 青木, 雄一郎 and 末益, 博志 and 永尾, 陽典 and Tanaka, Taro and Aoki, Yuichiro and Suemasu, Hiroshi and Nagao, Yosuke},
 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25回)(2009年12月4日、宇宙航空研究開発機構宇宙科学研究本部), 25th Symposium on Aerospace Structure and Materials (December 4, 2009. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, kanagawa Japan, The objectives of the present study are to clarify the failure mechanism of stiffened panel under compressive load. The compression tests of the stiffened panels with and without impact damage were conducted. The experiment showed that the failure started from the debonding between the stiffener flange and skin panel due to the significant bending caused by the buckling. A simultaneous unstable damage propagation in the transverse direction all the through-width of panel to the final failure occurred following the debondlng. It showed that the key of the compressive strength of the buckled stiffened panels was the debonding between the skin panel and the flange of the stiffener. Following the fact, bending tests for specimens with three different thickness of skin panels were carried out to reveal the mechanism of the onset and the growth of skin/stiffener debondlng. Owing to the singular nature of the stress at the bonded edge, a limiting energy release rate as zero crack length was used. Only the energy release rate, showing some correlation with the failure loads obtained, was not sufficient to explain the onset of the debonding., 資料番号: AA0064732009},
 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 = {補強部材の剥離発生メカニズムに関する一考察},
 volume = {25},
 year = {2010}
}