Optimum aeroelastic design of flapping wing for micro air vehicles
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説明
A method is presented for the optimum aeroelastic design of a flapping wing employing lifting-surface theory as an aerodynamic tool and the complex method as the optimization algorithm. The method is applied to the optimum design of a flapping wing of a Kite Hawk (Milvus migrans) UAV (Unmanned Aerial Vehicle) and the optimum thickness distribution of the main-spar is determined. As the result of the optimization, a high propulsive efficiency of 75 percent is attained considering only dihedral flapping of the main spar. By evaluating the viscous effect for this optimum design using a three-dimensional Navier-Stokes code, the effectiveness of the design is confirmed.
資料番号: AA0063824003
レポート番号: JAXA-SP-07-008E
収録刊行物
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- 宇宙航空研究開発機構特別資料 = JAXA Special Publication: Proceedings of Lectures and Workshop International: Recent Advances in Multidisciplinary Technology and Modeling
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宇宙航空研究開発機構特別資料 = JAXA Special Publication: Proceedings of Lectures and Workshop International: Recent Advances in Multidisciplinary Technology and Modeling JAXA-SP-07-008E 20-36, 2008-02-29
宇宙航空研究開発機構
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詳細情報 詳細情報について
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- CRID
- 1050574036195373824
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- NII論文ID
- 120006829083
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- NII書誌ID
- AA11984031
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- ISSN
- 1349113X
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- Web Site
- http://id.nii.ac.jp/1696/00005652/
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- 本文言語コード
- en
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- 資料種別
- conference paper
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- データソース種別
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- IRDB
- CiNii Articles