期刊
IEEE-ASME TRANSACTIONS ON MECHATRONICS
卷 25, 期 6, 页码 2711-2721出版社
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
DOI: 10.1109/TMECH.2020.2987963
关键词
Vibrations; IEEE transactions; Mechatronics; Biomimetics; Mathematical model; Strain; Actuators; Boundary control; distributed parameter system; rigid-flexible coupled wing; vibration control
类别
资金
- National Natural Science Foundation of China [61933001, 61873298]
- Joint Funds of Equipment Pre-Research and Ministry of Education of China [6141A02033339]
- Beijing Top Discipline for Artificial Intelligent Science and Engineering, University of Science and Technology Beijing
A boundary control approach is used to control a two-link rigid-flexible wing in this article. Its design is based on the principle of bionics to improve the mobility and the flexibility of aircraft. First, a series of partial differential equations (PDEs) and ordinary differential equations (ODEs) are derived through the Hamilton's principle. These PDEs and ODEs describe the governing equations and the boundary conditions of the system, respectively. Then, a control strategy is developed to achieve the objectives including restraining the vibrations in bending and twisting deflections of the flexible link of the wing and achieving the desired angular position of the wing. By using Lyapunov's direct method, the wing system is proven to be stable. The numerical simulations are carried out with the finite difference method to prove the effectiveness of designed boundary controllers.
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