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针对含有参数不确定性、干扰和响应延迟的控制系统鲁棒性设计问题,采用状态反馈控制方法设计控制系统,使得闭环控制系统在保证渐进稳定的同时满足H∞性能指标要求。建立导弹控制系统的线性离散模型,将提出的基于时滞不确定理论的设计方法应用于导弹俯仰-偏航通道的自动驾驶仪设计。通过仿真计算,验证了提出的控制系统设计方法在气动参数摄动±30%且时滞时间为1个采样周期时,能够保证导弹自动驾驶仪快速稳定地跟踪参考输入,具有良好的抗干扰特性,并且能够解决由于不确定性和响应延迟引起的不稳定问题。
In order to solve the problem of robust design of control system with parameter uncertainty, disturbance and response delay, a state feedback control method is used to design the control system so that the closed-loop control system meets the H∞ performance requirement while ensuring asymptotic stability. The linear discrete model of the missile control system is established. The proposed design method based on the uncertain theory of delay is applied to the design of the autopilot of missile pitch-yaw channel. The simulation results show that the proposed control system design method can ensure the missile autopilot to track the reference input quickly and stably when the aerodynamic parameters perturb ± 30% and the lag time is one sampling period , And can solve the instability caused by uncertainty and response delay.