International Journal of Frontiers in Engineering Technology, 2022, 4(7); doi: 10.25236/IJFET.2022.040709.
Qifan Zhang1, Xia Jiang2
1Faculty of Information Science and Engineering, China University of Petroleum-Beijing, Beijing, 102249, China
2Faculty of Automation and Electrical Engineering, Tianjin University of Technology and Education, Tianjin, China
In recent years, bionic flapping wing aircraft is widely used in battlefield reconnaissance and flight patrol, making it a popular research in the field of UAV. However, because the wing and body forces are complex and conventional method calculation and modeling are difficult, so it is urgent to study the flight control of flapping aircraft. In this paper, the rigid body dynamics modeling method is used firstly to analyze the wing motion, establish the dynamic model of the wing aircraft, and then the PID control model is used to control the suspended motion state of the wing aircraft, and at last control simulation using Simulink. The results show that the mean value of the angular velocity fluctuation with PID control is 32.6% of the value without control, and the change rate is 38.2% of the value without control. The attitude adjustment process is more stable and the performance is better.
Flapping wing aircraft; Angular speed; Attitude Angle; PID
Qifan Zhang, Xia Jiang. Implementation and Simulation of Hovering Control Model for Flapping Wing Aircraft. International Journal of Frontiers in Engineering Technology (2022), Vol. 4, Issue 7: 41-47. https://doi.org/10.25236/IJFET.2022.040709.
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