一种改进积分滑模面在飞控中的应用  

Application of Improved Integral Sliding Surface to Flight Control System

作　　者：李鹏[1] 孙未蒙[1] 李文强[1] 郑志强[1] 

机构地区：[1]国防科技大学自动控制系,湖南长沙410073

出　　处：《控制工程》2010年第3期269-271,289,共4页Control Engineering of China

基　　金：国家自然科学基金资助项目(60374006);国防科技大学博士研究生创新基金资助项目(B070304)

摘　　要：针对传统积分型滑模面容易产生积分饱和从而导致超调量大的缺点,在Seshagiri和Khalil设计的条件积分型滑模面的基础上,提出了一种改进积分型滑模面,其可以根据系统的状态通过调节因子对积分项进行削弱来防止积分饱和。同时对调节因子的取值范围进行了讨论。并将改进积分型滑模面应用到导弹的俯仰角速度跟踪滑模控制器设计中,对舵机输出受到干扰的情况进行了仿真。理论分析和仿真研究表明,改进积分型滑模面形式简单,便于工程实现,在其基础上设计的滑模控制器在受到类似脉冲干扰的情况下几乎没有超调和具有较短的调节时间。To the shortcoming of integrator windup in the conventional integral sliding surface,an improved integral sliding surface is proposed,based on the conditional sliding surface designed by Seshagiri and Khalil.The integral action is reduced through adjust factor when the sliding variable is out of the boundary layer.The improved integral sliding surface is applied to a missile pitch-rate tracking sliding mode controller design.Theoretical analysis and simulation results show that the improved integral sliding surface is easy to design for engineering applications,and the sliding mode controller based on improved integral sliding surface has no overshoot and has short settling times when suffering additive impulse-like disturbance.

关 键 词：积分饱和 改进积分型滑模面 滑模控制 俯仰角速度跟踪 

分 类 号：TP27[自动化与计算机技术—检测技术与自动化装置]