引用本文:张波,祝小平,周洲,彭新潮.输入有约束时的飞翼布局无人机姿态控制[J].控制理论与应用,2015,32(6):725~733.[点击复制]
ZHANG Bo,ZHU Xiao-ping,ZHOU Zhou,PENG Xin-chao.Attitude control for fly wing unmanned aerial vehicle with input constraints[J].Control Theory and Technology,2015,32(6):725~733.[点击复制]
输入有约束时的飞翼布局无人机姿态控制
Attitude control for fly wing unmanned aerial vehicle with input constraints
摘要点击 2194  全文点击 1112  投稿时间：2014-07-17  修订日期：2015-02-11
查看全文  查看/发表评论  下载PDF阅读器
DOI编号  10.7641/CTA.2015.40672
  2015,32(6):725-733
中文关键词  无人机  非线性控制系统  反步控制  线性矩阵不等式(LMIs)  输入约束  扩张状态观测器
英文关键词  unmanned aerial vehicles (UAV)  nonlinear control systems  backstepping  linear matrix inequalities (LMIs)  input constraints  extended state observer
基金项目  国防预研项目(513250201)资助.
作者单位E-mail
张波 西北工业大学 无人机特种技术重点实验室 hugh123go@mail.nwpu.edu.cn 
祝小平* 西北工业大学 无人机研究所 zhouzhou@nwpu.edu.cn 
周洲 西北工业大学 无人机特种技术重点实验室  
彭新潮 总参四部 驻西安地区军事代表办事处  
中文摘要
      针对大展弦比飞翼布局无人机的刚体运动与弹性运动耦合动力学模型, 研究了输入有约束时的无人机姿态控制问题, 提出了一种采用扩张状态观测器的反步滑模控制方法. 首先, 采用扩张状态观测器实时估计气动弹性模态和外界未知干扰的影响, 并引入跟踪微分器避免了控制律中项数膨胀问题. 然后, 针对飞翼布局无人机多操纵面的配置和输入约束, 给出了基于LMI的在线舵面分配算法. 最后, 针对指令滤波和输入约束情况下控制指令的滞后问题, 设计了辅助补偿器对控制指令进行补偿. 根据Lyapunov稳定性理论证明了该控制方法能够保证姿态跟踪误差收敛至有界, 仿真表明存在复合干扰和输入约束时该方法具有良好的姿态跟踪性能.
英文摘要
      Considering the coupling between the rigid motion and the elastic motion in the dynamic model of an unmanned aerial vehicle with high-aspect-ratio fly wing configuration, we investigate its attitude control under input constraints, and propose a backstepping sliding-mode control method by employing the extended state observer. The extended state observer estimates effects of the aeroelastic mode and unknown disturbance in realtime. A tracking differentiator is introduced to alleviate the term explosion in the control law. According to the allocation of multiple control surfaces in the aerial vehicle with high-aspect-ratio fly wing configuration and the input constraints, we put forward an online allocation algorithm for the allocation of control surfaces, based on the linear-matrix-inequality (LMI). An auxiliary compensator is applied to provide compensation for the control command with time-delay due to the filter and input constraints. Applying Lyapunov stability theorem, we prove that the attitude tracking error will converge to a bounded value. Simulation results show that good performances in attitude tracking control are achieved when disturbances and constraints exist.