Terminal Sliding Mode And LMI Based Control With Application To Aero-engine

With the advent of the higher requirements for the aero-engine’s performanceand the difficulty of the establishment of model in aero-engine system, as well as thequite complicate of the work environment of this system, the control methods of suchsystem, however, turn into a direction where there are more advance control methods,including progressively multivariable, intelligent and robustness. Compared withother sliding mode control methods, the terminal sliding mode control (TSMC) ismore sufficient to avoid the presence of local sliding mode that exists on each of theswitching hyper-plane. The states of such control system, therefore, could gainentrance to the terminal sliding mode within the expected dynamic response.Moreover, it is also possible to guarantee the entire control system’s globalasymptotical stability due to the fact that the control method could efficiently promotethe control performance along with weakening the chattering.In this paper, the work principles of aero-engine are introduced and analyzedfirstly. Through calibrating sectional model for each of the engine components, it isconvenient to establish the component-level model of some aero-engine system. Inthis scenario, it is beneficial to realize the study of control theory after the appropriateprocessing of component-level model, and the linearization of the state space model,as well as the theoretical basis for the research of the control system following.Secondly, terminal sliding mode controller is designed on the basis of LMI combinedwith the linear matrix inequality and terminal sliding mode theory. A dynamiccompensator is considered to accomplish the real-time compensation of the dynamicsystems all over the optimal design of the terminal sliding mode control. Theparameters of controller are selected from the LMI toolbox of Matlab. Subsequently,the controller which is obtained from section four and five is used in the context of theconstant model system and time-varying model system of aero-engine, respectively.The stability of model reference sliding mode control system with mismatcheduncertainties is also analyzed. Simulation results show that the designed controllerbased on LMI can be well controlled and more effective than that of the way ofgeneral terminal sliding mode control. The system not only possesses strongrobustness of both the disturbance and model parameters of the mode control system,but also is capable of effectually weakening the chattering phenomenon of terminalsliding mode control system.In addition, for the sake of making the study of the control of aero-engine systemfar more practical, some problems for convenient engineering applications arediscussed, including the validity in the entire flight envelope and certain degree ofphysical simulation based upon the LMI in terminal sliding mode controller.