导弹气动力／侧向推力混合控制特性研究

Research on Blended Control System of Missile with Lateral Thrust and Aerodynamic Fin

建立了具有气动力和侧向推力混合控制的导弹动力学模型。提出了将控制系统分成控制律和复合逻辑两部分进行设计的方法，并分析了姿控发动机到导弹质心距离对控制效果的影响。

The blended dynamic model of missile with aerodynamic fin and lateral thrust was developed. A controller, including the aerodynamic control surface and pulse type lateral jets, was developed. It was divided into two parts： the control law and the blended logic. The control law can be designed easily as before, and the blended logic commands the two actuators. Effect of the distance between motors and the center of gravity of the interceptor had been discussed.