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高超声速飞行器全局有限时间姿态控制方法

刘海东 包为民 李惠峰 龚春叶 廖宇新

刘海东, 包为民, 李惠峰, 等 . 高超声速飞行器全局有限时间姿态控制方法[J]. 北京航空航天大学学报, 2016, 42(9): 1864-1873. doi: 10.13700/j.bh.1001-5965.2015.0547
引用本文: 刘海东, 包为民, 李惠峰, 等 . 高超声速飞行器全局有限时间姿态控制方法[J]. 北京航空航天大学学报, 2016, 42(9): 1864-1873. doi: 10.13700/j.bh.1001-5965.2015.0547
LIU Haidong, BAO Weimin, LI Huifeng, et al. Attitude control method within finite time globally for hypersonic vehicles[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(9): 1864-1873. doi: 10.13700/j.bh.1001-5965.2015.0547(in Chinese)
Citation: LIU Haidong, BAO Weimin, LI Huifeng, et al. Attitude control method within finite time globally for hypersonic vehicles[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(9): 1864-1873. doi: 10.13700/j.bh.1001-5965.2015.0547(in Chinese)

高超声速飞行器全局有限时间姿态控制方法

doi: 10.13700/j.bh.1001-5965.2015.0547
详细信息
    作者简介:

    刘海东,男,博士研究生,工程师。主要研究方向:导航、制导与控制。Tel.:010-68752726,E-mail:liuhaidong84@126.com;李惠峰女,博士,教授,博士生导师。主要研究方向:导航、制导与控制。Tel.:010-82339276,E-mail:lihuifeng@buaa.edu.cn

    通讯作者:

    李惠峰,Tel.:010-82339276,E-mail:lihuifeng@buaa.edu.cn

  • 中图分类号: V448.22+2

Attitude control method within finite time globally for hypersonic vehicles

  • 摘要: 以高超声速飞行器6自由度模型为研究对象,设计了一种基于终端滑模的全局有限时间姿态控制方法。在控制器设计中,通过动态逆实现对俯仰、偏航和滚转通道的解耦处理。在考虑模型不确定性和外部干扰的情况下,终端滑模变结构控制方法用于保证系统的鲁棒性。同时,通过改进指数趋近律,实现闭环系统在滑模面趋近阶段和沿滑模面滑动阶段均是有限时间收敛的。基于李雅普诺夫稳定性理论,控制器的全局有限时间收敛特性得到证明。仿真实验结果验证了高超声速飞行器全局有限时间姿态控制方法的有效性。

     

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出版历程
  • 收稿日期:  2015-08-26
  • 网络出版日期:  2016-09-20

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