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带碰撞角约束的三维有限时间滑模制导律

赵曜 李璞 刘娟 陈喆 刘向东

赵曜, 李璞, 刘娟, 等 . 带碰撞角约束的三维有限时间滑模制导律[J]. 北京航空航天大学学报, 2018, 44(2): 273-279. doi: 10.13700/j.bh.1001-5965.2017.0087
引用本文: 赵曜, 李璞, 刘娟, 等 . 带碰撞角约束的三维有限时间滑模制导律[J]. 北京航空航天大学学报, 2018, 44(2): 273-279. doi: 10.13700/j.bh.1001-5965.2017.0087
ZHAO Yao, LI Pu, LIU Juan, et al. Finite-time sliding mode control based 3D guidance law with impact angle constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(2): 273-279. doi: 10.13700/j.bh.1001-5965.2017.0087(in Chinese)
Citation: ZHAO Yao, LI Pu, LIU Juan, et al. Finite-time sliding mode control based 3D guidance law with impact angle constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(2): 273-279. doi: 10.13700/j.bh.1001-5965.2017.0087(in Chinese)

带碰撞角约束的三维有限时间滑模制导律

doi: 10.13700/j.bh.1001-5965.2017.0087
详细信息
    作者简介:

    赵曜  男, 博士, 工程师。主要研究方向:制导及精度总体设计

    通讯作者:

    赵曜, E-mail:shine3y9r@126.com

  • 中图分类号: V448

Finite-time sliding mode control based 3D guidance law with impact angle constraints

More Information
  • 摘要:

    针对导弹对地面静止目标的打击问题,提出了一种三维有限时间滑模制导律。利用Lyapunov方法证明了该制导律能够控制导弹以期望的纵向和侧向碰撞角对目标进行精确打击。该方法具有以下4点优势:无需对系统模型作解耦或线性化处理,可以同时对纵向和侧向碰撞角进行约束,可以得到解析的制导指令,闭环系统对外部扰动和参数不确定性具有不敏感特性。仿真结果验证了该制导方法能够保证较高的终端精度和较强的鲁棒性。

     

  • 图 1  不同发射角条件下仿真结果

    Figure 1.  Simulation results with different launch angles

    图 2  本文制导律蒙特卡罗仿真结果

    Figure 2.  Results of Monte Carlo simulation with proposed guidance law

    图 3  文献[17]制导律蒙特卡罗仿真结果

    Figure 3.  Results of Monte Carlo simulation with guidance law in Ref. 17]

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出版历程
  • 收稿日期:  2017-02-21
  • 录用日期:  2017-05-05
  • 刊出日期:  2018-02-20

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