Design and Simulation of Model Predictive Control for Turbojet Engine Fuel Control of The Missile

In this article, Design and simulation of model predictive control for turbojet engine fuel control of the missile has been proposed. Operational and structural constraints of the engine are controller design challenges. The control system must make sure that the engine always works in full health condition, i.e. without acceleration of the shaft speed, staling compressor, ignition of the combustion chamber, turbine temperature increase etc. In this regard, a controller is needed which can take into account these constraints while obtaining a suitable control signal. Using the model predictive control as well as taking into the account the limitations of various parameters such as rotational speed, turbine inlet temperature, stalactite compressor, etc. the control of turbojet engine fuel for a linear model of this engine at a functional point has been investigated. In the final section, the performance results of this controller has been compared with the results of Min-Max controller and indicated that in the predictive control, in addition to producing optimized the optimal control signal, all constraints are in the desired range.