A scheme of an acceleration adaptive fuel control is put forward for helicopter turboshaft engine.The scheme is based on GG/P *2 closed loop control with adaptive control rule

which corrects the demand of og/P *2 closed loop control PID with surge flag detected by sensed compressor discharge pressure during the engine acceleration

since the engine performance deterioration or damage will initiate the surge in this time.This scheme also provides altitude compensation and surge recovery P *2.It requires only modifying a litte the hardware of an existing FADEC

but mainly the fuel control microcomputer software

so it is easy to upgrade an existing FADEC to the adaptive control level.