Abstract:

A new method,combined with the statespace model theory and the linear matrix inequality (LMI), is applied to design a controller to improve the control performance of the aeroengine for the sake of studying its uncertainty and instability during the actual operation. Taking the turbojet engine model as the control object, a dynamic compensator is introduced to improve the performance of aero-engine system through the optimal design of the terminal sliding mode control on the basis of the LMI. Furthermore, the improved power rate reaching law is used to validate the performance simulation of the dynamic system. It is shown that the proposed method not only smoothes the variance ratio of fuel and nozzle outlet area, but also holds the stable and robustness of the system. Our results based on LMI are better than the general terminal sliding mode control for the aero-engine.

Key words: linear matrix inequality;aero-engine;terminal sliding mode control;dynamic compensator