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

作　　者：陈福红[1] 马大为[1] 杨必武[2] 朱忠领[1] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094 [2]第二炮兵装备研究院,北京100085

出　　处：《兵工学报》2012年第6期641-646,共6页Acta Armamentarii

基　　金："十二五"国防基础科研项目(B2620110005)

摘　　要：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 .

关 键 词：自动控制技术 火箭炮 全局滑模 永磁同步电动机 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]