An aero-engine full flight envelope robust control system with control law

For the purpose of practical application, based on the previous work of full envelope dividing and H-infinity loop-shaping control algorithm, the design of full flight envelope robust control system considering the change of control law was researched. In this paper, the full flight envelope was divided into eight regions based on the temperature and pressure of the engine inlet and H-infinity loop-shapingmethodologywas adopted to design the nominal points´ controller aiming at acceleration and deceleration processes, augment transients and steady state process respectively. In order to fulfill full envelope control task, the designed controllers with the change of control law in different nominal points were scheduled following the change of altitude and Mach number where the engine experienced. Further, for decreasing the disturbance occur in the switch between the controllers of different sub-regions, the bumpless switch logic based on the technology called ´inertia delayed to soften the switch´ was constructed creatively in MATLAB/Simulink which could be coded automatically with the help of RTW. From the results of hardware in-the-loop simulations on the real-time simulation platform, the states of aero-engine in full flight envelope are following the command from power lever, and the bumplesses which reach to almost 5 percents of the current values could be reduced effectively.