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Optimum aeroelastic design of flapping wing for micro air vehicles
- Source :
- 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. :20-36
- Publication Year :
- 2008
- Publisher :
- 宇宙航空研究開発機構, 2008.
-
Abstract
- 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.<br />資料番号: AA0063824003<br />レポート番号: JAXA-SP-07-008E
Details
- Language :
- English
- ISSN :
- 1349113X
- Database :
- OpenAIRE
- Journal :
- 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
- Accession number :
- edsair.jairo.........66beeef6a79986de30eeb1149bdc5906