航空发动机全飞行包线稳态划分方法研究

航空发动机在鲁棒控制器设计过程中存在飞行包线区域难以系统划分的问题，为此，提出基于推力耗油率特性和基于动压耗油率特性的航空发动机飞行包线划分法。根据某型涡扇发动机在全包线范围内稳态工作时的推力、耗油率及动压特性，结合大气条件的客观规律，通过两种划分方法将飞行包线划分为65 个区域，用每个区域对应标称点的参数代替其周围小偏差区域和边界点参数。通过对该发动机全包线内各区域标称点与边界点参数的对比，证明两种方法均对全飞行包线划分有效，可为后续航空发动机控制器设计提供理论基础。

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 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.