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带落角约束的新型二阶滑模三维制导律

史绍琨 赵久奋 崇阳 杨奇松 尤浩

史绍琨, 赵久奋, 崇阳, 等 . 带落角约束的新型二阶滑模三维制导律[J]. 北京航空航天大学学报, 2019, 45(3): 614-623. doi: 10.13700/j.bh.1001-5965.2018.0387
引用本文: 史绍琨, 赵久奋, 崇阳, 等 . 带落角约束的新型二阶滑模三维制导律[J]. 北京航空航天大学学报, 2019, 45(3): 614-623. doi: 10.13700/j.bh.1001-5965.2018.0387
SHI Shaokun, ZHAO Jiufen, CHONG Yang, et al. Novel second-order sliding mode control based 3D guidance law with impact angle constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(3): 614-623. doi: 10.13700/j.bh.1001-5965.2018.0387(in Chinese)
Citation: SHI Shaokun, ZHAO Jiufen, CHONG Yang, et al. Novel second-order sliding mode control based 3D guidance law with impact angle constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(3): 614-623. doi: 10.13700/j.bh.1001-5965.2018.0387(in Chinese)

带落角约束的新型二阶滑模三维制导律

doi: 10.13700/j.bh.1001-5965.2018.0387
详细信息
    作者简介:

    史绍琨  男, 硕士研究生。主要研究方向:飞行器总体、结构分析与飞行力学

    赵久奋  男, 博士, 硕士生导师。主要研究方向:飞行器总体、结构分析与飞行力学

    通讯作者:

    赵久奋, E-mail:xiangcdx1994@163.com

  • 中图分类号: V488.13

Novel second-order sliding mode control based 3D guidance law with impact angle constraints

More Information
  • 摘要:

    针对导弹在三维空间中攻击地面机动目标问题,提出了一种带落角约束的三维有限时间制导律。为提高收敛速度和抑制抖振现象,基于非齐异快速终端滑模面和二阶滑模控制理论设计了含耦合项的非奇异快速终端二阶滑模三维制导律,设计过程中无需对系统模型作线性化处理并且避免了奇异问题的出现。针对目标机动信息和视线角耦合带来的总扰动,设计了非齐次干扰观测器进行估计并补偿。并对制导律的稳定性和有限时间收敛特性进行了严格的数学证明。仿真验证了本文提出制导律的有效性和优越性。

     

  • 图 1  弹目相对运动关系

    Figure 1.  Relative motion relationship between missile and target

    图 2  3枚导弹攻击目标仿真结果

    Figure 2.  Simulation results of 3 missiles attacking targets

    图 3  3种制导律仿真对比结果

    Figure 3.  Simulation result comparison of 3 guidance laws

    表  1  导弹初始参数和期望落角

    Table  1.   Initial parameters and expected impact angles of missiles

    导弹 初始坐标/km θm0/(°) φm0/(°) qεd/(°) qβd/(°)
    M1 (0, 10, 0) -25 -20 -30 -30
    M2 (2, 12, 1) -10 -30 -60 -20
    M3 (-2, 9, 3) 10 10 -70 -60
    下载: 导出CSV

    表  2  3枚导弹攻击目标主要仿真参数

    Table  2.   Main simulation parameters of 3 missiles attacking targets

    导弹 脱靶量/m 视线倾角误差/(°) 视线偏角误差/(°) 飞行时间/s
    M1 0.206 9 0.011 6 0.025 7 29.768 0
    M2 0.077 6 0.010 0 0.025 0 29.979 0
    M3 0.296 2 0.029 3 0.015 9 30.362 0
    下载: 导出CSV

    表  3  3种制导律仿真主要参数对比

    Table  3.   Main simulation parameters comparison of 3 guidance laws

    制导律 脱靶量/m 视线倾角误差/(°) 视线偏角误差/(°) 飞行时间/s
    SO-NFTSMG 0.206 9 0.011 6 0.025 7 29.768 0
    NTSMG1 0.268 1 0.023 6 0.026 1 29.706 0
    NTSMG2 0.242 3 0.011 4 0.027 3 29.923 0
    下载: 导出CSV
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出版历程
  • 收稿日期:  2018-06-27
  • 录用日期:  2018-07-27
  • 网络出版日期:  2019-03-20

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