临近空间高超声速飞行器匹配化滑模姿态控制  

Matched sliding mode attitude control of near-space hypersonic vehicle

作　　者：郭建国[1] 张添保 周军[1] 王国庆[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《系统工程与电子技术》2017年第9期2081-2086,共6页Systems Engineering and Electronics

基　　金：国家自然科学基金(61473226)资助课题

摘　　要：针对临近空间高超声速飞行器非匹配不确定性姿态控制问题,提出一种新型匹配化滑模姿态控制系统设计方法。首先将含有非匹配不确定性的模型进行匹配化变换,得到匹配的不确定性模型。采用扩张干扰观测器估计不确定项,用来补偿系统输出量的微分。其次,基于干扰观测器及频域滤波器设计了一种渐近收敛的复合微分器,用来获取系统输出的一阶导数。在此基础上,采用变结构控制方法,提出了一种匹配化滑模姿态控制方法。最后,通过数字仿真验证了该方法的有效性,并与反步法进行了对比,对比结果表明本文的方法具有更好的快速性及鲁棒性。A novel matched sliding mode attitude control method is proposed for near-space hypersonic vehicle with mismatched uncertainties.Firstly,a model with matched uncertainties is derived from matching transformation,and the derivative of system output is compensated by the estimated uncertainties from an extended disturbance observer.Secondly,a compound derivator with asymptotic stability is designed based on the disturbance observer and the frequency domain filter to obtain the derivative of system output.A novel matched sliding mode attitude control method is proposed based on variable structure control theory.Finally,the performances are assessed through a numerical simulation,and the proposed attitude control system has faster tracking performance and better robustness compared with the backstepping control system.

关 键 词：临近空间高超声速飞行器 非匹配不确定性 扩张干扰观测器 微分器 滑动模态 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]