@inproceedings{oai:jaxa.repo.nii.ac.jp:00036837,
 author = {石川, 隆司 and 林, 洋一 and 松嶋, 正道 and Ishikawa, Takashi and Hayashi, Yoichi and Matsushima, Masamichi},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {May},
 note = {実際の航空機構造材に一般的に使用されるT字型炭素繊維/ポリマー複合材料(CFRP)補強部材の線形座屈応力および座屈後挙動に対する数値および実験結果の比較を示した。単純な仮定にもとづいて座屈状態後の極限強度を数値的に推定した。使用したソフトウエアは市販コードNISA-2である。Rayleigh-Ritz法のような補助的な数値解析法も用いた。試験した補強部材はCF(炭素繊維)/エポキシおよびCF/PEEK(ポリエーテルエーテルケトン)製のものである。航空機構造材の大幅な軽量化には後者の材料が有力な候補であった。, A comparison between numerical and experimental results for linear buckling stress and postbuckling behavior of T-shaped Carbon Fiber Reinforced Plastics (CFRP) composite stiffeners used commonly in actual aircraft structures was described. The ultimate strength after buckled state based on rather simple assumptions was numerically estimated. The software used is the commercial level code, NISA-2. Some auxiliary numerical analysis method such as Rayleigh-Ritz method was also used. The tested stiffeners were made of CF (Carbon Fiber)/epoxy and CF/PEEK (Polyether Ether Ketone). The latter material was a potential candidate for a drastic weight reduction of aircraft structure., 資料番号: AA0000440014, レポート番号: NAL SP-31},
 pages = {155--162},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {Analysis and experiments of postbuckling behavior of T-shaped CFRP stiffeners},
 volume = {31},
 year = {1996}
}