Aircraft single-jet engine with hydro-mechanical fuel flow controller

The paper deals with an aircraft twin-spool single-jet engine equipped with a hydro-mechanical indirect action fuel control unit. From aircraft pilot's point of view, engine's control (or command) means its power lever (throttle) displacement, proportional to the desired thrust level. Considering the engine as controlled object and its thrust the most important operation effect, from the multitude of engine's parameters only its rotational speed(s) is (are) measurable and proportional to its thrust, so engine's speed has become the most important controlled parameter. Engine's operation is due to fuel's burning in its combustor, so the studied engine's control system is based on fuel injection dosage, but it could have other inputs, such as exhaust nozzle's effective area. Based on such an architecture, one has determined the embedded system model; some Simulink-Matlab simulations are performed, concerning embedded system quality (its output parameters time behavior) and some conclusions concerning engine's parameters are revealed.