In the process of robust controller design for aircraft engines, it is difficult to divide the flight envelope region systematically. In this paper, a flight envelope division method for aircraft engines based on thrust fuel consumption characteristics and dynamic pressure fuel consumption 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 boundary points are replaced by the parameters of the corresponding nominal points of each region. By comparing the parameters 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 aircraft engine controller design.