舵机动态响应下导弹阻尼回路稳定性

针对导弹控制参数稳定区域的研究大多忽略了舵机的动态响应过程对参数稳定区域的影响，首先建立了阻尼驾驶仪控制的导弹动力学方程以及舵机的动力学方程，然后考虑舵机的稳态响应和动态响应，应用劳斯判据给出了非旋转弹阻尼反馈增益与舵机控制参数的动态关系。为推导旋转弹阻尼反馈增益的稳定区域，分析了舵机在准弹体坐标系下的表达式，然后采用复姿态角方法和Lyapunov稳定性判据，给出了旋转弹动态稳定性条件。最后以某一导弹飞行参数为例进行了仿真，验证了本文所得出的稳定性条件的有效性。

Stability of missile damping loop under actuator dynamic response

Most of the researches on the stability region of missile control parameters ignore the influence of the dynamic response process of the actuator. In this paper, the dynamic equations of the missile and the actuator are established firstly. Considering the steady-state response and dynamic response of the actuator, applying the Routh criterion, the dynamic relationship between the damping feedback gain of the non-spinning missile and the control parameters of the actuator is given. In order to deduce the stability region of the damping feedback gain of the spinning missile, the expression of the actuator in the quasi-body coordinate system is analyzed, then the dynamic stability condition of the spinning missile is given by using the complex attitude angle method and Lyapunov stability criterion. Finally, a missile flight parameter is taken as an example to verify the effectiveness of the stability conditions.