PID Control Synthesis For Aeroengine Based On Static Output Feedback

Aeroengine is a complex nonlinear system, the features of which have great changes in different working conditions. The robust controller for single nominal point is very difficult to ensure the engine with good performances under various working conditions. With the development of aeroengine, the aeroengine becomes more and more complex. Many parameters need be controlled. Therefore, the aeroengine system is established as a linear parameter-varying (LPV) model in this thesis. The different controller is called by using the LPV model with time-varying gain parameter. This thesis presents an improved static output feedback controller design method in order to solve the parameters of controller of MIMO system.Firstly, the model of aeroengine can be expressed as linear parameter-varying (LPV) model in this thesis. Then the model is transformed into convex polytopic model.Secondly, the form of aeroengine PID controller is transformed into static output feedback form. By using the linear matrix inequality (LMI) method the static output feedback controller can be designed to meet H∞ performance and the poles of the closed-loop system are placed in a given region.Thirdly, the PID controller parameters are obtained by the static output feedback controller gain. The global continuous variable gain PID controller can be obtained by comprehensiving vertex controller.Finally, the thesis builds the simulation model and program based on the Matlab environment and the simulation verifys the validity of the design method. Simulation results demonstrate that the proposed robust controller can achieves asymptotic tracking with good robusness properties. Conclusion and prospect are given at last of the end of this paper.