偏转弹头导弹控制系统设计与仿真

Control System Design and Simulation of Missile with Deflectable Nose Control

根据弹头的可偏转特性,利用无根多刚体系统动力学方法建立了偏转弹头导弹的动力学模型,并对通道间的耦合特性及弹头偏转对弹体运动的影响进行了分析。在此基础上,将通道间的耦合及弹头偏转对弹体运动的影响作为干扰项处理,将气动参数的非线性变化等效为标称参数的摄动,利用变结构控制理论设计了偏转弹头导弹的控制器。仿真结果表明,所设计的变结构控制器能够有效地减小和消除俯仰、偏航通道对滚转通道的耦合作用以及弹头偏转对弹体运动的影响,较好地抑制了导弹气动参数的摄动,具有较高的稳态精度和良好的动态性能。

According to the deflectable characteristics of missile nose, the kinetic model was established utilizing the rootless multi-rigid body system dynamics, the coupling characteristic of different channels and the influence of nose deflection on missile body were also analyzed. In allusion to the coupling of different channels, the influences of nose deflection on body motion and the nonlinear variation of missile aerodynamic parameters, the variable structure controller of the deflectable nose missile was designed in the condition that the coupling and influence of nose on body were seen as disturbance. Simulation results indicate that the variable structure controller can effectively reduce and eliminate the coupling effect of different channels and the influence of nose deflection on missile body.