Micro turbojet engines can be found in some small-scale airplanes, mainly in Unmanned Aerial Vehicles (UAVs), but they also have other applications. Although they are not widely used, their simplicity and similitude to more complex gas turbine systems make them suitable as technology demonstrators for validating concepts in real engine environments. The present paper discusses the development of a Linear Quadratic Integral control for a specific micro turbojet, the PD-60R. In contrast to the conventional approaches, a novel thrust parameter, the Turbofan Power Ratio, is introduced. Despite its original designation, this parameter also performs correctly also in the given engine. The research focuses on its advantages over conventional thrust parameters as well as PID control systems. The authors also provide a detailed description of the Hardware-in-the-Loop test, which showed the applicability of the currently investigated solution in real microcontroller devices.