火箭炮交流伺服系统全局滑模控制

Global Sliding Mode Control for Rocket Launcher AC Servo System

针对某火箭炮位置伺服系统参数变化范围大,冲击力矩强等特点,提出了一种全局滑模控制方法,并结合伺服系统数学模型对其进行了稳定性证明,同时对于控制律中的高阶微分项,引入微分估计器来获取其高精度估计值。仿真结果表明,该控制方法不仅能够有效抑制抖振,保证系统的响应速度和控制精度,并且对参数摄动和负载扰动具有很强的鲁棒性。

Aimed at wide parameter variations and strong impact moment in a rocket launcher position servo system, a global sliding mode control method was presented. Its stability was proved by using the system＇ s mathematic model. And, for the high-order derivative term in the control law, a derivative esti- mator was introduced to obtain the high accuracy estimation. The simulation results show that the pro- posed approach can inhibit the chattering problem effectively, guarantee the response speed and control accuracy, and possess a strong robustness to parameter perturbation and load disturbance .