Modeling the flapping motion via quasi-steady approach and controlling the longitudinal dynamics of a flapping wing mav

Date

2021-09-10

Author

Çalış, Özgün
Kurtuluş, Dilek Funda
ARIKAN, KUTLUK BİLGE

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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An aerodynamic model in order to simulate and control the flapping-wing micro air vehicle based on the quasi-steady approach and blade element theory is developed to calculate the instantaneous aerodynamic forces and moments. The system dynamics of a 2-D flapping-wing MAV in hover mode are modeled. Control simulations are done for hover, take-off, forward flight and landing conditions. Linear Quadratic Regulator (LQR) and Coefficient Diagram Method (CDM) are used to stabilize the flapping-wing system. The effectiveness of the controllers are compared in the means of disturbance rejection, response speed, and controller response. By using the stroke plane angle and the flapping frequency as the control inputs, six state variables of the system are stabilized. Position commands are tracked with an integral tracker at low-speed flights.

URI

http://aiac.ae.metu.edu.tr/paper.php?No=AIAC-2021-110
https://hdl.handle.net/11511/95304

Conference Name

11th Ankara International Aerospace Conference

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

Ö. Çalış, D. F. Kurtuluş, and K. B. ARIKAN, “Modeling the flapping motion via quasi-steady approach and controlling the longitudinal dynamics of a flapping wing mav,” presented at the 11th Ankara International Aerospace Conference, Ankara, Türkiye, 2021, Accessed: 00, 2022. [Online]. Available: http://aiac.ae.metu.edu.tr/paper.php?No=AIAC-2021-110.