大攻角飞行导弹控制器μ综合设计

导弹在大攻角飞行条件,由于非线性气动力和参数不确定等原因,其通道间存在强烈的耦合,经典的三通道控制器独立设计方法很难获得满意的系统性能.在设计大攻角飞行控制系统时,采用μ综合设计方法,通过仿真结果表明采用μ综合设计理论设计的控制器具有很好的鲁棒性能.

Design of Control System for Missile at High Angle of Attack Using μ-Synthesis

Under the high angle of attack, because of the nonlinear dynamics and the parameter uncertainty, serious coupling existed within the channels of the missile. The control system for missile at hight angle of attack using μ-synthesis is design in this paper. The simulation shows the well robust performance.