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Research On The Control Problem Of Distributed Structure Morphing Wings

Posted on:2017-07-27Degree:MasterType:Thesis
Country:ChinaCandidate:X Z YuFull Text:PDF
GTID:2322330509962888Subject:Control theory and control engineering
Abstract/Summary:PDF Full Text Request
The design of conventional fixed wing aircraft cannot meet the requirements of complex flight missions. With the development of new intelligent materials, structure technology and distributed control technology, the research of morphing wing aircraft has received extensive attention. Morphing wing aircraft can change the shape of wing to achieve the best flight performance. In this paper, a new type of distributed structural morphing wing is designed to simulate the morphing wing aircraft, and its dynamic modeling and dynamic shape control are studied.First, based on the tension structure, a distributed structure is designed and its dynamic model is established. By using the theory of mechanics, two kinds of methods are used to establish the nonlinear dynamic model, and the results of the two methods are consistent. The morphing wing distributed structure is designed and its nonlinear dynamic model is established by using analytical mechanics theory.Then, based on the nonlinear dynamic model of morphing wing distributed structure, two nonlinear controllers are designed, that is, the feedback linearization controller and the sliding mode controller with filter. In theory, the stability of the two controllers is proved. The performance of the controllers is verified by simulation in two cases, that is, if the system including the uncertainties and the small disturbance. Through the comparison of the simulation curves, the two kinds of nonlinear controllers can be well controlled, and the sliding mode controller with filter has the better robustness.Finally, the cooperative control of morphing wing tension structure is researched. Based on the T-S fuzzy theory, the T-S fuzzy model is present. According to the Lyapunov stability criterion and pole assignment theory, the T-S fuzzy controller is designed, and the stability and the strong robustness of the T-S fuzzy controller are verified by simulations. In the T-S fuzzy model, the coordination term is added to be the improved fuzzy model. Based on the improved fuzzy model, the cooperative controller is designed. Through the simulation, the effectiveness of the controller is verified.
Keywords/Search Tags:morphing wing aircraft, tension structure, feedback linearization control, sliding model control, fuzzy control, cooperative control
PDF Full Text Request
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