Microjet engines are a class of gas turbine engines that have a simple structure and are widely used in industry, especially in aerial systems. In this type of engines, only engine spool speed and exhaust gas temperature are measured by the sensors. In the present research, the design of a selector control structure is carried out to control microjet engines. In this controller, using the variables of engine spool speed, exhaust gas temperature, and throttle degree, the value of the requested thrust is provided, and the limitations governing engine speed, turbine temperature, combustion chamber blow-out, and compressor surge margin are maintained. Since selector controllers belong to the category of switching control systems and the issue of stability is very important for these structures, in this research, a method is presented to ensure the stability of the proposed controller scheme. To evaluate the operation of the presented strategy, a simulation study is carried out for the controller in connection with the thermodynamic model of a microjet engine. The results show the powerful performance of the controller in achieving the desired thrust and maintaining the engine’s limits in fault-free conditions and also in the presence of actuator fault.
