Design and Implementation of Hovering Flapping Wing Micro Air Vehicle
In this paper, a prototype of a hovering flapping wing micro air vehicle is developed. The aerodynamic force of the prototype at different flapping frequencies and pitch angles is measured, and a hovering flight control scheme for the vehicle is designed based on the measured results. Finally, a flight test of the prototype is carried out. The tail deflection of the prototype is controlled by a micro linear rudder, and the pitch attitude of the prototype is adjusted during flight. The hovering flight within a certain range is realized. The feasibility of the hovering flight control scheme of flapping wing micro air vehicle is verified.
KeywordsFlapping Wing Micro Air Vehicle Hovering Attitude control
The work described in this paper was supported by the National Natural Science Foundation of China (No. U1613227), the Natural Science Foundation of Guangdong Province of China (No. 2018A030310045), the Basic Research Program of Science and Technology Project of Shenzhen (No. JCYJ20170307151117299), the China Postdoctoral Science Foundation(No. 2018M641828), the DGUT innovation center of robotics and intelligent equipment of China (No. KCYCXPT2017006) and the KEY Laboratory of Robotics and Intelligent Equipment of Guangdong Regular Institutions of Higher Education (No. 2017KSYS009).
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