引用本文:卜祥伟,吴晓燕,陈永兴,白瑞阳.基于非线性干扰观测器的高超声速飞行器滑模反演控制[J].控制理论与应用,2014,31(11):1473~1479.[点击复制]
BU Xiang-wei,WU Xiao-yan,CHEN Yong-xing,BAI Rui-yang.Nonlinear-disturbance-observer-based sliding mode backstepping control of hypersonic vehicles[J].Control Theory and Technology,2014,31(11):1473~1479.[点击复制]
基于非线性干扰观测器的高超声速飞行器滑模反演控制
Nonlinear-disturbance-observer-based sliding mode backstepping control of hypersonic vehicles
摘要点击 2645  全文点击 1647  投稿时间：2014-03-30  修订日期：2014-06-22
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DOI编号  10.7641/CTA.2014.40260
  2014,31(11):1473-1479
中文关键词  高超声速飞行器  滑模反演控制  1阶低通滤波器  改进滑模微分器  非线性干扰观测器
英文关键词  hypersonic vehicles  sliding mode backstepping control  low-pass first order filter  improved sliding mode differentiator  nonlinear disturbance observer
基金项目  航空科学基金资助项目(20130196004); 陕西省自然科学基础研究计划资助项目(2012JM8020).
作者单位E-mail
卜祥伟* 空军工程大学 防空反导学院 buxiangwei1987@126.com 
吴晓燕 空军工程大学 防空反导学院  
陈永兴 空军工程大学 防空反导学院  
白瑞阳 空军工程大学 防空反导学院  
中文摘要
      针对高超声速飞行器非线性、强耦合和参数不确定弹性体模型, 提出了一种基于非线性干扰观测器的滑模反演控制方法. 将飞行器曲线拟合模型分解为速度子系统和高度相关子系统并表示为严格反馈形式, 分别采用滑模和反演方法设计实际控制量与虚拟控制量. 采用1阶低通滤波器获取虚拟控制量的导数, 解决了传统反演控制方法“微分项膨胀”问题. 基于改进滑模微分器设计了一种新型非线性干扰观测器, 以此对模型不确定项进行估计和补偿. 仿真结果表明, 该控制器对模型不确定性和气动弹性影响具有鲁棒性, 且实现了对速度和高度参考输入的稳定跟踪.
英文摘要
      A nonlinear-disturbance-observer-based sliding mode backstepping controller is designed for flexible hypersonic vehicles with the characters of nonlinearity, strong couplings and parameter uncertainties. The vehicle curve-fitted model is decomposed as velocity subsystem and altitude-related subsystem, and is expressed as strict feedback form. The actual control laws and virtual control laws are designed based on the design procedures of sliding mode control and backstepping control, respectively. Low-pass first order filter is introduced to obtain the derivatives of virtual control laws, which avoids the explosion of differentiation terms in the traditional backstepping control. A new nonlinear disturbance observer designed based on improved sliding mode differentiator is introduced to estimate and compensate the model uncertainties. Simulation results demonstrate the effectiveness of this controller in tracking velocity and altitude commands in the presence of model uncertainty and aeroelasticity.