综合飞行/推进控制系统的鲁棒设计方法

Robust method to design the integrated flight/ propulsion control system

基于凸多面体线性系统族镇定方法和航迹准稳态运动概念 ,研究了现代攻击机的综合飞行 /推进控制系统的鲁棒设计方法。该方法根据航迹准稳态运动的条件 ,生成航迹准稳态运动的期望控制量和状态量 ,以航迹准稳态运动为基准运动建立综合系统的线性系统族模型 ,采用凸多面体线性系统族鲁棒镇定方法设计了综合控制系统的反馈调节控制器。数学仿真表明 ,所设计的综合控制系统对攻击机推进系统输出推力的变化具有大范围的鲁棒性 。

The robust design method is proposed to design the integrated flight/ propulsion control system based on stabilization of the convex bound linear system family and the quasi steady state of the flight path. The method is to produce the expected control variables and state variables at the quasi steady state of the flight path on its conditions, to establish the linear system family of the integrated system in which the quasi steady state of the flight path is taken as the baseline motion, and to design the feedback regulator of the integrated control system on the stabilization of the convex bound linear system family. The simulations show that the designed integrated control system has the robust on the large indefinite of the thrust outputted from the propulsion system and attains excellent dynamic performances and tactical performances in the open loop on the thrust. It indicates that the proposed method is available.