@inproceedings{oai:jaxa.repo.nii.ac.jp:00003424,
 author = {永井, 弘人 and 中村, 俊介 and 室園, 昌彦 and 小野, 幸生 and 宇田, 暢秀 and Nagai, Hiroto and Nakamura, Shunsuke and Murozono, Masahiko and Ono, Kosei and Uda, Nobuhide},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of the First International Symposium on Flutter and its Application},
 month = {Mar},
 note = {First International Symposium on Flutter and its Application (May 15-17, 2016. Mielparque-tokyo), Minato-ku, Tokyo, Japan, We have conducted aeroelastic analysis for the resonant type elastic flapping wing and investigated the effect of planform and thickness of the plate on the vibrational and aerodynamic characteristics. The resonant type elastic flapping wing consists of a CFRP rod and EPP plate. When a small oscillation is input to the wing base, bending and torsional wing deformation are produced passively due to aeroelastic phenomenon. To search an optimal design parameters of the wing to maximize thrust coefficient, parametric studies have been conducted with respect to the plate thickness, span location with the maximum chord, chord length at wing base, and chord length at wing tip. From these calculation, an optimal structure of the elastic wing have been obtained, which generates larger thrust coefficient than the initial value. When the resonant type elastic flapping wing have an optimal wing structure, both first and second mode have coupling mode shape of spanwise bending and torsion, and the first and second natural frequencies are close to each other. Such an optimal wing can produce an appropriate wing kinematics with the phase difference of near 90 deg by coupling the two vibrational modes. These results indicate that it is possible to conduct approximative optimal design only by using vibrational analysis without any aeroelastic analysis, which can save the calculation cost of numerical optimization., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630046031, レポート番号: JAXA-SP-16-008E},
 pages = {303--312},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Structural design of aeroelastic flapping wing},
 volume = {JAXA-SP-16-008E},
 year = {2017}
}