Abstract: In order to find out the effects of flight control on the output response of turboshaft engine under the condition of variable rotor speed， based on the integrated simulation platform of variable rotor speed helicopter / transmission mechanism / engine， considering the existence of system uncertainties， an incremental nonlinear dynamic inverse flight controller was proposed and designed to improve the control effect of the system. The controller mainly includes angle rate controller， attitude angle controller and track controller. Due to the physical limitation of the actuator， the pseudo control module was introduced to improve the stability of the system. The simulation results of a typical flight mission show that， compared with the incremental nonlinear dynamic inverse flight controller， the pseudo control module can not only significantly improve the flight control effect， reduce the overshoot of climb speed by more than 50%， but also effectively reduce the overshoot of the power turbine speed by about 9.0%， which is helpful to enhance the dynamic control quality of the engine.

Key words: Turboshaft engine;Variable rotor speed;Incremental nonlinear dynamic inversion;Pseudo-control hedging;Engine output response

摘要： 为探明变旋翼转速条件下飞行控制对涡轴发动机输出响应的影响，在变旋翼转速直升机/传动机构/发动机综合仿真平台的基础上，考虑系统不确定因素的存在，提出并设计了增量式非线性动态逆飞行控制器，提高对系统的控制效果，控制器主要包括角速率控制器、姿态角控制器和航迹控制器；由于执行机构的物理限制，引入伪控制模块，以提高系统的稳定性。典型飞行任务下的仿真结果表明：相对于增量式非线性动态逆飞行控制器而言，伪控制模块不仅可显著提升飞行控制效果，使爬升速度的超调量减小50%以上，还可有效减小动力涡轮转速的超调量9.0%左右，有助于增强发动机的动态控制品质。

关键词: 涡轴发动机;变旋翼转速;非线性增量式动态逆;伪控制模块;发动机输出响应