引用本文:王婕,宗群,田柏苓,范文茹.基于拟连续高阶滑模的高超声速飞行器再入姿态控制[J].控制理论与应用,2014,31(9):1166~1173.[点击复制]
WANG Jie,ZONG Qun,TIAN Bai-ling,FAN Wen-ru.Reentry attitude control for hypersonic vehicle based on quasi-continuous high order sliding mode[J].Control Theory and Technology,2014,31(9):1166~1173.[点击复制]
基于拟连续高阶滑模的高超声速飞行器再入姿态控制
Reentry attitude control for hypersonic vehicle based on quasi-continuous high order sliding mode
摘要点击 3861  全文点击 2118  投稿时间：2013-08-04  修订日期：2014-04-22
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DOI编号  10.7641/CTA.2014.30819
  2014,31(9):1166-1173
中文关键词  高超声速飞行器  再入姿态控制  拟连续高阶滑模  虚拟控制  制导控制一体化
英文关键词  hypersonic vehicle  reentry attitude control  quasi-continuous high order sliding mode  virtual control  integrated guidance and control
基金项目  国家自然科学基金资助项目(61203012, 61004073, 61203142); 天津市自然科学基金资助项目(12JCZDJC30300); 河北省自然科学基金 资助项目(F2014202206).
作者单位E-mail
王婕* 河北工业大学 控制科学与工程学院 wangjiestudent@gmail.com 
宗群 天津大学 电气与自动化工程学院  
田柏苓 天津大学 电气与自动化工程学院  
范文茹 中国民航大学 航空自动化学院  
中文摘要
      考虑模型参数不确定和外界干扰对再入制导控制性能的影响, 基于拟连续高阶滑模控制策略对高超声速 飞行器的再入制导控制问题进行了研究. 首先, 给出再入制导指令的设计过程. 其次, 基于再入飞行特性对模型进 行简化, 获得面向控制的姿态模型, 在此基础上, 通过引入新的控制变量, 设计解耦滑模面, 实现姿态间的解耦. 再 次, 为了削弱控制抖振, 通过引入虚拟控制, 对系统进行增广, 基于齐次性理论设计拟连续三阶滑模再入姿态控制 器, 确保系统在有限时间实现对制导指令的稳定跟踪. 最后, 六自由度再入飞行器的制导控制一体化仿真结果表明, 本研究给出的控制策略在不影响系统鲁棒性的同时, 能够实现对标称轨迹和再入姿态的综合控制.
英文摘要
      Considering the influence of model parameter uncertainties and external disturbance on the reentry guidance and control, we investigate the guidance and control problem for reentry hypersonic vehicles based on the quasi-continuous high-order sliding mode control strategy. Firstly, the design process of reentry guidance command is introduced. Secondly, the control-oriented attitude model is developed via model reduction based on reentry flight characteristics. On this basis, sliding mode surfaces are designed by introducing new control variables, and then the decoupling for each attitude channel is achieved. Thirdly, in order to reduce the control chattering, the virtual-control is introduced to augment the system, and then a third-order quasi-continuous sliding mode reentry attitude controller is designed based on homogeneity theory which ensures that the system to be able to track the guidance command in finite time. Finally, the integrated guidance and control with six-degrees-of-freedom simulation results demonstrate that the developed control of the nominal trajectory and reentry attitude can be achieved based on the proposed control strategy without the loss of robustness.