Affiliations: [a] Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin, China
| [b] China Aerospace Science and Industry Corporation, Beijing, China
| [c]
Beijing Institute of Electrical and Mechanical Engineering, Beijing, China
| [d] Department of Control Engineering, Naval Aeronautical and Astronautical University, Yantai, Shangdong, China
Correspondence:
[*]
Corresponding author. Yiyin Wei, Research Center of Control Theory and Application, Harbin Institute of Technology, Harbin, China & China Aerospace Science and Industry Corporation, 100074 Beijing, China. E-mail: hmrhit@163.com.
Abstract: With the continuous expansion of aircraft flying envelope and the extensive application of new structural materials, the flexibility of the aircraft increases. Under the actual flight conditions, the elastic vehicle will be elastically deformed under aerodynamic force which will produce elastic vibration. In addition to the rigid body movement of the inertia vehicle, the inertial measurement element of the control system will introduce the structural elastic vibration noise into the control system. Under certain unfavorable conditions, the control system will increase the amplitude of the vibration, resulting in the final destruction of the structure of the aircraft. In the engineering application, the elastic noise in the control signal is generally suppressed by the structural notch filter. However, when the structural bending frequency is low and the bandwidth is close to the control system, the suppression effect of the structural notch filter to the elastic noise will be reduced. By combining the fuzzy sliding mode control method with the classical attitude control structure, the longitudinal attitude controller is designed for the static unstable elastic aircraft, and the equilibrium state of the system at the origin is proved to be consistent and stable by using the Lyapunov stability analysis method. The time-domain response characteristics of the designed controller and the stability of the program signal under disturbing conditions are verified by the fixed-point simulation. The simulation results show the effectiveness and robustness of the controller.
Keywords: Fuzzy sliding mode control, robustness, active control, hypersonic aircraft
