基于NESO的高超声速拦截弹解耦控制研究  

Decoupling Control of a Hypersonic Intercept Missile Based on NESO

作　　者：白辰[1] 熊子豪 任章[1] 

机构地区：[1]北京航空航天大学飞行器控制一体化技术重点实验室,北京100191

出　　处：《导航定位与授时》2016年第5期46-50,共5页Navigation Positioning and Timing

基　　金：国家自然科学基金(91316304;61333011;61121003;61101004)

摘　　要：针对高超声速拦截弹姿态控制问题,提出了基于非线性扩张状态观测器(NESO)的解耦控制方法。根据Tornambe的分散鲁棒控制理论,把耦合项和不确定性视为广义不确定项,构造基于NESO的估计和补偿信号并加入到闭环控制律中。理论推导证明了该方法可以保证闭环系统跟踪误差一致有界。在高超声速拦截弹模型上进行了仿真验证,并与传统的分通道反馈控制方法进行对比,结果表明所设计解耦控制方法得到了更好的控制效果,在较大程度上消除了通道耦合和不确定性的影响。According to attitude control of a hypersonic intercept missile, a decoupling control approach based on Nonlinear Extended States Observer（NESO） is proposed. Decoupling control is realized through the decentralized control theory. The system coupling terms and uncertainties are estimated by NESO and added into the control law for compensation. Theoretical analysis proves that the tracking errors of the closed-loop system are consistently hounded. Simulations are carried on through the hypersonic intercept missile model comparing the proposed method and the traditional sub-channel control method. The results show that the tracking effectiveness of the proposed method is better and the impact caused by coupling and uncertainties is eliminated.

关 键 词：高超声速拦截弹 解耦控制 NESO 不确定性 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]