Abstract: In view of the effects of the selection of the engine control law on the integrated fighter / aero-engine performance， the optimization design method of the engine control law based on the integrated fighter / aero-engine performance was carried out. Based on the typical advanced fighter flight mission， the integrated fighter / aero-engine performance design is carried out， and constraint analysis and mission analysis were conducted. Taking the lowest total takeoff weight as the optimization target， the optimal fighter / aero-engine were obtained. The rationality of the design method was verified. The effects of different throttle ratios and different control laws on integrated fighter / aero-engine performance design were respectively studied by using the method of integrated fighter / aero-engine performance. The results show that reasonable aero-engine control law under maximum condition and reasonable aero-engine throttle ratio can effectively expand the constraint feasible region and reduce the fuel consumption of engine and the total take-off weight of aircraft in the integrated fighter / aero-engine performance.

Key words: Aircraft/engine performance integration；Control law；Lift drag characteristic；Uninstalled performance；Installed performance

摘要： 针对发动机控制规律的选取对飞机/发动机性能一体化设计的影响，基于飞机/发动机性能一体化设计方法，开展了发动机控制规律优化设计方法研究。从先进战斗机飞行任务出发，开展了飞机/发动机性能一体化设计方法研究，进行约束分析和任务分析，以起飞总重最低为目标优选飞机/发动机设计方案，验证了设计方法的合理性。采用飞机/发动机性能一体化设计方法，分别研究了不同节流比和不同控制规律设计对飞机/发动机性能一体化设计的影响。研究表明:在飞机/发动机性能一体化设计过程中，采用合理的发动机最大状态控制规律同时选取恰当的发动机节流比，可以有效扩大约束可行域，同时能够降低发动机的燃油消耗量，降低飞机起飞总重。

关键词: 飞机/发动机性能一体化；控制规律；升阻特性；非安装性能；安装性能