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一致性约束下末制导系统最大可容许模式决策延迟

项盛文 范红旗 达凯 付强

项盛文, 范红旗, 达凯, 付强. 一致性约束下末制导系统最大可容许模式决策延迟. 自动化学报, 2022, 48(6): 1448−1456 doi: 10.16383/j.aas.c200717
引用本文: 项盛文, 范红旗, 达凯, 付强. 一致性约束下末制导系统最大可容许模式决策延迟. 自动化学报, 2022, 48(6): 1448−1456 doi: 10.16383/j.aas.c200717
Xiang Sheng-Wen, Fan Hong-Qi, Da Kai, Fu Qiang. Maximal admissible mode decision delay under consistency constraint in terminal guidance system. Acta Automatica Sinica, 2022, 48(6): 1448−1456 doi: 10.16383/j.aas.c200717
Citation: Xiang Sheng-Wen, Fan Hong-Qi, Da Kai, Fu Qiang. Maximal admissible mode decision delay under consistency constraint in terminal guidance system. Acta Automatica Sinica, 2022, 48(6): 1448−1456 doi: 10.16383/j.aas.c200717

一致性约束下末制导系统最大可容许模式决策延迟

doi: 10.16383/j.aas.c200717
详细信息
    作者简介:

    项盛文:国防科技大学博士. 主要研究方向为图像处理, 制导, 导航与控制. E-mail: xiangsw224@163.com

    范红旗:国防科技大学研究员. 主要研究方向为雷达信号处理, 目标跟踪, 导引控制, 信息融合. 本文通信作者. E-mail: fanhongqi@nudt.edu.cn

    达凯:国防科技大学博士. 主要研究方向为雷达信号处理, 多传感器多目标跟踪, 信息融合. E-mail: dktm131@163.com

    付强:国防科技大学教授. 主要研究方向为雷达信号处理与目标识别. E-mail: fuqiang1962@vip.sina.com

Maximal Admissible Mode Decision Delay Under Consistency Constraint in Terminal Guidance System

More Information
    Author Bio:

    XIANG Sheng-Wen Ph.D. at National University of Defense Technology. His research interest covers image processing, guidance, and navigation and control

    FAN Hong-Qi Professor at National University of Defense Technology. His research interest covers radar signal processing, target tracking, guidance and control, and information fusion. Corresponding author of this paper

    DA Kai Ph.D. at National Univer-sity of Defense Technology. His research interest covers radar signal processing, multisensor multitarget tracking, and information fusion

    FU Qiang Professor at National University of Defense Technology. His research interest covers radar signal processing and target recognition

  • 摘要: 对于大机动目标拦截问题, 模式决策器是基于逻辑的集成估计导引系统(Integrated estimation and guidance, IEG)中的一个重要组件. 为了保证系统的估计精度和制导性能, 模式决策器的模式延迟应尽可能小. 本文针对末制导场景, 首先推导了离散时间系统零控脱靶量的估计误差模型, 然后在一致性约束条件下给出了系统最大可容许模式决策延迟的数值计算方法. 本文的研究结果可为IEG系统中模式决策器的设计提供指标参考.
  • 图  1  平面拦截几何

    Fig.  1  Planer interception geometry

    图  2  一个典型的基于逻辑的IEG制导系统框架[18]

    Fig.  2  A typical logic-based IEG guidance system frame[18]

    图  3  目标模式切换和模式决策器输出示意图

    Fig.  3  Diagram of target's mode switch and mode decision-maker's outputs

    图  4  $ t_{{\rm sw}} = 2.0 \;{\rm{s}}$$ \Delta m = 10 \;{\rm{g}}$下的$ \chi _k^2 $

    Fig.  4  $ \chi _k^2 $ under $ t_{{\rm sw}} = 2.0 \;{\rm{s}}$ and $ \Delta m = 10 \;{\rm{g}}$

    图  5  $t_{{\rm{sw}}} = 1.0 \;{\rm{s}}$时不同机动幅度下的$ \chi _k^2 $

    Fig.  5  $ \chi _k^2 $ under different maneuver magnitude for $t_{{\rm{sw}}} = 1.0 \;{\rm{s}}$

    图  6  $ \Delta m = 20 \;{\rm{g}}$时不同机动时刻下的$ \chi _k^2 $

    Fig.  6  $ \chi _k^2 $ under different maneuver time for $ \Delta m = 20 \;{\rm{g}}$

    图  7  不同$ \Delta m $条件下MAMDD与模式切换时刻

    Fig.  7  MAMDD with mode switch time for different $ \Delta m $

    表  1  符号说明

    Table  1  Description of symbols

    变量名称变量描述
    P导弹
    E目标
    $\tau_{\rm p}$,$\tau_{\rm e}$导弹和目标控制系统的时间常数
    $a_{\rm p}^{\max},a_{\rm e}^{\max}$导弹和目标最大横向加速度
    ${V_{\rm p}},{V_{\rm e}}$导弹和目标的飞行速度
    ${u_{\rm p}},{u_{\rm e}}$导弹和目标的横向加速度指令
    $r$弹目相对距离
    ${t_{\rm sw}}$目标模式切换时刻
    $t$仿真时间
    ${t_{\rm f}}$终止时刻
    ${t_{\rm go}}$剩余飞行时间
    g重力加速度, $9.8\;{\rm{m} }/{{\rm{s}}^2}$
    $m$目标的运动模式
    ${m_1},{m_2}$目标在模式切换时刻前后的运动模式
    $\Delta m$目标运动模式改变量, $\Delta m = {m_2} - {m_1}$
    $T$采样时间间隔
    ${\sigma _\theta }$测角精度
    ${\sigma _a}$导弹加速度测量精度
    ${s_w}$目标指令加速度误差的功率谱密度
    $\Delta t$目标运动模式辨识延迟
    ${\boldsymbol{\tilde x}}$状态估计误差
    ${\boldsymbol{\xi }},{\Sigma}$状态估计误差的均值和方差
    $\mu ,{\sigma ^2}$ZEM估计误差的均值和方差
    $\chi_k^2$检验统计量
    下载: 导出CSV

    表  2  仿真参数

    Table  2  Simulation parameters

    参数类型参数名称单位值 (范围)
    弹目参数$ {V_{\rm p}} $m/s2300
    $ {V_{\rm e}} $m/s2700
    $ a_{\rm p}^{{\max}} $g30
    $ a_{\rm e}^{{\max}} $g15
    $ {\tau _{\rm p}} $s0.2
    $ {\tau _{\rm e}} $s0.2
    观测参数$ T $s0.01
    $ {\sigma _\theta } $mrad5
    $ {\sigma _a } $$ {\rm{m}}/{\rm{s}}^2 $1
    场景参数$ r_0 $m15000
    $ {\phi_{\rm p}}(0) $rad$ \pi/18 $
    $ {\phi_{\rm e}}(0) $rad$ > \pi /2 $且满足碰撞三角形
    目标机动方式随机乒乓
    估计器参数$ s_w $$ {\rm{g}}^2/{\rm{Hz}} $1
    初估计误差$ {{\boldsymbol{\tilde x}}_0} = {[0,0,0,0]^{\rm T}} $
    初估协方差阵${ {{P} }_0} = \left[ \begin{aligned}\;\;0\;\;0\;\;\;\;\;\;0\;\;\;\;\;\;\;\;0\;\;\\\;\;0\;\;0\;\;\;\;\;\;0\;\;\;\;\;\;\;\;0\;\;\\\;\;0\;\;0\,\;\;{ { {(a_{\rm e}^{ {\max} })}^2} }\;\;\;0\;\;\\\;\;0\;\;0\;\;\;\;\;\;0\;\;\;\;\;\;\;\;0\;\; \end{aligned}\right]$
    下载: 导出CSV

    表  3  两种方法MAMDD对比

    Table  3  Comparison of MAMDD with two methods

    $t_{{\rm{sw}}}$ (s)捕获区约束MAMDD (s)一致性约束MAMDD (s)
    $ \Delta m = 5 \;{\rm{g}}$
    0.61.350.64
    1.20.940.53
    1.80.580.54
    2.20.370.60
    2.60.18$ \infty $
    $ \Delta m = 10 \;{\rm{g}}$
    0.60.940.39
    1.20.650.28
    1.80.410.28
    2.20.260.29
    2.60.12$ \infty $
    $ \Delta m = 15 \;{\rm{g}}$
    0.60.720.29
    1.20.500.20
    1.80.320.19
    2.20.200.25
    2.60.09$ \infty $
    $ \Delta m = 20 \;{\rm{g}}$
    0.60.580.24
    1.20.410.16
    1.80.260.15
    2.20.160.16
    2.60.080.19
    $ \Delta m = 30 \;{\rm{g}}$
    0.60.420.17
    1.20.300.11
    1.80.190.10
    2.20.120.11
    2.60.050.13
    下载: 导出CSV
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出版历程
  • 收稿日期:  2020-09-05
  • 录用日期:  2020-12-01
  • 网络出版日期:  2020-12-22
  • 刊出日期:  2022-06-02

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