Adaptive backstepping-based flight control system using integral filters |
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| Authors: | Chao-Yong Li Wu-Xing Jing Chang-Sheng Gao |
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| Institution: | 1. Jiangsu Provincial Key Laboratory of Networked Collective Intelligence, School of Mathematics, Southeast University, Nanjing 211189, China;2. School of Science, Guangxi Key Laboratory of Hybrid Computation and IC Design Analysis, Guangxi University for Nationalities, Nanning 530006, China;3. NAAM Research Group, Department of Mathematics, Faculty of Science, King Abdulaziz University, Jeddah, Saudi Arabia;4. Department of Mathematics, Quaid-I-Azam University, Islamabad, Pakistan;1. Equipment Management and Safety Engineering College, Air Force Engineering University, Xi’an, Shaanxi 710051, PR China;2. Delft Center for Systems and Control, Delft University of Technology, CD Delft 2628, Netherlands;3. Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi’an, Shaanxi 710038, PR China;4. National Defence University, Beijing 101416, PR China |
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| Abstract: | A backstepping control design procedure for uncertain nonlinear flight control system expressible in parameter-strict feedback form is presented in this paper. The proposed backstepping procedure, in association with sliding model control technique, exploits the possibility of avoiding, under certain suitable assumptions, the overparameterization problem existing in the classical backstepping process. In particular, a sliding-model-based integral filter is introduced to facilitate the development of the derivation of the virtual inputs, thus reducing the computational load with regard to the standard backstepping procedure. Moreover, in simulations, the control parameters in the resulted controller are optimally tuned using a genetic algorithm so as to show the full potential of the proposed control system. |
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