Command Filter Based Robust Nonlinear Control of Hypersonic Aircraft with Magnitude Constraints on States and Actuators

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• 作者：Bin Xu (1)
  Shixing Wang (2) (3)
  Daoxiang Gao (4)
  Yu Zhang (5)
  Zhongke Shi (6)
  
• 关键词：Hypersonic aircraft ; Command filter ; State constraint ; Input saturation
• 刊名：Journal of Intelligent and Robotic Systems
• 出版年：2014
• 出版时间：January 2014
• 年：2014
• 卷：73
• 期：1-4
• 页码：233-247
• 全文大小：1,321 KB
• 作者单位：Bin Xu (1)
  Shixing Wang (2) (3)
  Daoxiang Gao (4)
  Yu Zhang (5)
  Zhongke Shi (6)
  
  1. School of Automation, Northwestern Polytechnical University, Xi鈥檃n, China
  2. Department of Control Engineering, Naval Aeronautical and Astronautical University, Yantai, China
  3. Department of Computer Science and Technology, Tsinghua University, Beijing, China
  4. School of Engineering, Beijing Forestry University, Beijing, China
  5. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou, China
  6. School of Automation, Northwestern Polytechnical University, Xi鈥檃n, China
  
• ISSN：1573-0409

文摘

The command filter based robust nonlinear controller is designed for the longitudinal dynamics of a generic hypersonic aircraft in presence of parametric model uncertainty and magnitude constraints on the states and actuators. The functional subsystems are transformed into the linearly parameterized form and the controller is proposed based on dynamic inversion and adaptive gain. Since the dynamics are with cascade structure, the states are considered as virtual control and the signal is filtered to produce the limited command signal and its derivative. To eliminate the effect of the constraint, the auxiliary error compensation design is employed and the parameter projection estimation is proposed based on the compensated tracking error. The uniformly ultimately boundedness is guaranteed for the closed-loop control system. Simulation results show that the proposed approach achieves good tracking performance.