Study on steady state division method of aircraft engine full flight envelope

In the process of robust controller design for aircraft engines, it is difficult to divide the flight envelope re-gion systematically. In this paper, the flight envelope division methods for aircraft engines based on thrust fuel con-sumption rate characteristics and dynamic pressure fuel consumption rate characteristics is proposed. According to the thrust, fuel consumption and dynamic pressure characteristics of a turbofan engine during steady-state operation within the full envelope, combined with the objective law of atmospheric conditions, the flight envelope is divided into 65 regions by two division methods, and the parameters of the surrounding small deviation regions and bound-ary points are replaced by the parameters of the corresponding nominal points of each region. By comparing the pa-rameters of nominal points and boundary points within the full envelope of the engine, the results show that both methods are effective for the full flight envelope division, which provides a theoretical basis for the subsequent air-craft engine controller design.