| Citation: | WANG Liangyu, XU Haojun, LI Yinghui, et al. Reconfigurable design method of flight control law under icing conditions[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(3): 606-613. doi: 10.13700/j.bh.1001-5965.2018.0358(in Chinese)
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For the flight safety of icing aircraft, the nonlinear icing effect model was built based on the linear icing effect model, and then the nonlinear longitudinal dynamics model of icing aircraft was established. Through the combination of feedback linearization and fuzzy control theory, the reconfigurable design of longitudinal control law under icing condition was completed, which ensures the dynamic response characteristic and promotes the anti-interference ability of the controller, allowing the aircraft to fly under icing condition. The simulation of the aircraft longitudinal dynamic response under various icing severity and interference conditions was carried out, and then by comparison with the conventional PID control, the effectiveness and anti-interference ability of the designed control law are verified. The results show that the dynamic response of each state parameter under the designed control law can converge quickly and greatly and track the pitch angle instructions faster and more accurately. In addition, the anti-interference capability and dynamic performance of the designed control law are better than those of the conventional PID control.
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