传统发动机稳态抗扰控制器在设计时，控制性能指标未能充分考虑被控对象及干扰信号的典型特征，如可作为反馈用的传感器和执行机构数量有限、干扰能量只集中在有限频域等因素，往往抗扰控制器设计的较为保守，并不总能获得满意的抗扰性能。本文提出一种可以在有限频域内采用几何图解法进行性能改进的稳态抗扰控制器设计方法“几何设计法”，该方法可以直观地在复平面上定义闭环系统各输出量在有限频域内的控制性能指标以及控制量在受限情况下的系统抗扰性能极限，从而使用图解法的形式来解决有限频域抗扰控制器的求取问题。仿真结果表明，发动机在巡航稳态工况下，面对能量主要集中在2~16 rad/s有限频域的大气湍流马赫数干扰时，基于几何设计法设计的抗扰控制器相比传统混合灵敏度H_∞控制器，风扇折合转速抗扰百分比提升30%以上的同时，推力抗扰百分比提升了15%以上。

In the design process of traditional engine steady-state disturbance rejection controller， the control performance index fails to fully consider the typical characteristics of the controlled object and disturbance signal. For example， the number of sensors and actuators that can be used as feedback is limited， and the disturbance energy is only concentrated in the finite frequency domain. Therefore， it is not always possible to obtain satisfactory control performance. In this study， a design method of steady-state disturbance rejection controller called “Geometric Design Method” is proposed， which can improve the performance by using the geometric analysis method in the finite frequency domain. This method can intuitively define the control performance index of closed-loop system output in finite frequency domain and the output disturbance rejection performance limit when the control signal is in the limited condition. Thus， the graphical method is used to solve the problem of obtaining the disturbance rejection controller in the finite frequency domain. The simulation shows that when the aeroengine encounters the Mach number disturbance of atmospheric turbulence whose energy is mainly concentrated in 2-16 rad/s finite frequency domain under cruise steady-state conditions， compared with the traditional mixed sensitivity H_∞ controller， the disturbance rejection percentage of the corrected fan speed and the thrust is increased by more than 30% and 15%， respectively.