Active Control of Flapping Wings Using Wing Deformation

スポンサーリンク

概要

• 論文の詳細を見る

• A new method for the attitude control of a flapping-wing aircraft is proposed. In this method, the variations in wing deformation, that is, the feathering angle and the camber, are controlled by pulling the wing at a certain point with a thread connected to a servomotor. The experimental setup for verifying the practicability of this method was developed, and aerodynamic forces and wing deformation were measured. It was concluded that thread control caused effective wing deformation, and the variation in the deformation generated the pitching moment that controls the attitude of a flapping-wing aircraft.

• 社団法人 日本航空宇宙学会の論文
• 2009-08-04

著者

• SUNADA Shigeru

  Department of Aerospace Engineering, Osaka Prefecture University

• Ohtsuka Yukio

  Graduate School Of Engineering Osaka Prefecture University

• TOKUTAKE Hiroshi

  Department of Aerospace Engineering, Osaka Prefecture University

• Sunada Shigeru

  Department Of Aerospace Engineering Osaka Prefecture University

• Tokutake Hiroshi

  Department Of Aerospace Engineering Osaka Prefecture University

関連論文

• Attitude Control of a Small UAV Using a Flow Sensor System
• Optical Measurement of the Deformation, Motion, and Generated Force of the Wings of a Moth, Mythimna Separata : Walker
• Application of Moving Horizon Method to States Estimation from Flight Test Data
• Active Control of Flapping Wings Using Wing Deformation
• Disturbance Observer Based on Multipoint Feedback
• Fluid Dynamic Forces Acting on Rectangular Plate with Hole in Stokes Flow
• Characteristics of Rotary Wings in Hovering Mode at an Ultra-Low Reynolds Number
• Analysis of Flapping Motion of Rotors of Small Coaxial Helicopter
• Navigation of Small and Lightweight Helicopter
• Disturbance Observer Based on Multipoint Feedback
• Disturbance Preview Controller and Its Application to a Small UAV

もっと見る 閉じる

スポンサーリンク