According to the aeroengine nonlinear and time-varying features in the entire flight envelope

the design method of parameters-adaptive PID controller was put forward

and two kinds of parameter estimators including least-squares method and corrected-parameter method for on-line identification and tuning were investigated.The two control algorithms were compared through the simulation with aeroengine linear or component-level nonlinear models.The results show that the control system using corrected-parameter adaptive PID controller is stable and the control algorithm is simple and adaptable to the entire flight envelope.The corrected-parameter adaptive PID controller was implemented to an aeroengine FADEC system

and its advantages were validated by ground test and flight test.