Abstract
In this paper, we propose to prevent compressor surge and control rotating speed for UAV turbojet engine. Turbojet engine controller is designed by applying PID control algorithm and it was applied to the linearized turbojet engine model. To prevent any surge or a flame out event during the engine acceleration or deceleration, the PID controller effectively controls the fuel flow input of the control system. PID results are used as the fuel flow control inputs to prevent compressor surge and flame-out for turbojet engine and the controller is designed to converge to the desired speed quickly and safely. Using LabVIEW to perform computer simulations verified the performance of the proposed controller. The simulation result using the designed PID controller verified that quickly converge to the desired speed and properly control fuel flow rate while preventing the surge and flame out event.
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