A methodology is presented to design aeroengine output dynamic feedback controller.When the state and output matrices of a control system are perturbed

the controller designed in this way can lead the system to be quadratic stable.When disturbances are equal to zero

the system will be of quadratic disturbance-restraining performance when the perturbation of the matrices does not exist.The problem is simplified into a standard output dynamic feedback control problem on the basis of two theorems about quadratic stability and disturbance-restraining performance.From the two theorems

an augmented plant is derived.With the augmented plant

the controller is designed by using control theory.For an example

the flight envelope of the engine is divided into 12 subregions

and in each subregion the simulation under different flying conditions is given.It is shown that the dynamic performance of the control system meets the design target and the robustness of stability is good.