火箭炮交流伺服系统全局滑模控制

陈福红;马大为;杨必武;朱忠领

兵工学报 ›› 2012, Vol. 33 ›› Issue (6) : 641-646.

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  • 主管：中国科学技术协会

    主编：许毅达

    ISSN 1000-1093

    　

  • 主办：中国兵工学会

    出版：《兵工学报》 编辑部

    CN 11-2176/TJ

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兵工学报 ›› 2012, Vol. 33 ›› Issue (6) : 641-646. DOI: 10.3969/j.issn.1000-1093.2012.06.001
论文

火箭炮交流伺服系统全局滑模控制

  • 陈福红1,马大为1,杨必武2,朱忠领1
作者信息 +

Global Sliding Mode Control for Rocket Launcher AC Servo System

  • CHEN Fu-hong1, MA Da-wei1, YANG Bi-wu2， ZHU Zhong-ling1
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文章历史 +

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。

Abstract

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 estimator was introduced to obtain the high accuracy estimation. The simulation results show that the proposed 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

Key words

automatic control technology / rocket launcher / global sliding mode control / permanent magnet synchronous motor

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陈福红,马大为,杨必武,朱忠领. 火箭炮交流伺服系统全局滑模控制. 兵工学报. 2012, 33(6): 641-646 https://doi.org/10.3969/j.issn.1000-1093.2012.06.001
CHEN Fu-hong1, MA Da-wei1, YANG Bi-wu2， ZHU Zhong-ling1. Global Sliding Mode Control for Rocket Launcher AC Servo System. Acta Armamentarii. 2012, 33(6): 641-646 https://doi.org/10.3969/j.issn.1000-1093.2012.06.001

基金

“十二五”国防基础科研项目(B2620110005)

参考文献

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