Park, Moonsoo;
(2024)
Integrated system modelling approach for developing mini flapping wing aerial vehicles.
Doctoral thesis (Ph.D), UCL (University College London).
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Abstract
This thesis studies the mathematical modelling for motor-actuated and piezoelectric beam-type actuator-driven mini-flapping wing aerial vehicles (MFAV). The investigated systems are composed of three essential components: the actuator, transmission, and wings. By integrating the characteristic equations governing these parts, the mechanical responses of the systems are thoroughly examined. MATLAB and Simulink are employed to conduct simulations, enabling in-depth exploration of the energy flow within the electromechanical system and their optimisations under realistic loads. The developed electromechanical models for motor-actuated MFAVs effectively capture the system's behaviour by considering the commercial DC gear motor and the flapping mechanism. The system's losses are modelled using the Coulomb friction model, enabling prediction of the system's energetic requirements which is not possible otherwise. The model also allows examination of the impact of adding elastic storage elements to the system. Optimal crank and connecting rod lengths are identified through trend analysis, and the system's performance under varying operational conditions is evaluated. A comparison between slider-crank and direct drive systems offers valuable insights into their respective advantages and drawbacks, revealing the direct drive model's superior performance in terms of average lift and system efficiency. A mathematical model for piezoelectric bimorph actuators is established and its effectiveness is confirmed using Ansys. The model serves as the basis for developing a comprehensive mathematical model for piezoelectric bimorph-actuated MFAV. The model includes the wing morphology and aerodynamic effects encompassing translation, added mass effect, and rotation around the leading edge axis. Lastly, optimisation is performed, and the maximum stress in the piezoelectric actuator is examined to ensure structural integrity. The analysis focuses on the net lift, and stroke and pitch angles of the wing. The optimised system’s performance is assessed under different voltages. Additionally, the influence of aerodynamic coefficients and the flexural hinge on the piezoelectric bimorph-actuated flapping wing system is established.
| Type: | Thesis (Doctoral) |
|---|---|
| Qualification: | Ph.D |
| Title: | Integrated system modelling approach for developing mini flapping wing aerial vehicles |
| Open access status: | An open access version is available from UCL Discovery |
| Language: | English |
| Additional information: | Copyright © The Author 2024. Original content in this thesis is licensed under the terms of the Creative Commons Attribution-NonCommercial 4.0 International (CC BY-NC 4.0) Licence (https://creativecommons.org/licenses/by-nc/4.0/). Any third-party copyright material present remains the property of its respective owner(s) and is licensed under its existing terms. Access may initially be restricted at the author’s request. |
| UCL classification: | UCL UCL > Provost and Vice Provost Offices > UCL BEAMS UCL > Provost and Vice Provost Offices > UCL BEAMS > Faculty of Engineering Science UCL > Provost and Vice Provost Offices > UCL BEAMS > Faculty of Engineering Science > Dept of Mechanical Engineering |
| URI: | https://discovery.ucl.ac.uk/id/eprint/10188575 |
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