留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

基于预测碰撞点的剩余飞行时间估计方法

李辕 赵继广 白国玉 闫梁

李辕, 赵继广, 白国玉, 等 . 基于预测碰撞点的剩余飞行时间估计方法[J]. 北京航空航天大学学报, 2016, 42(8): 1667-1674. doi: 10.13700/j.bh.1001-5965.2015.0509
引用本文: 李辕, 赵继广, 白国玉, 等 . 基于预测碰撞点的剩余飞行时间估计方法[J]. 北京航空航天大学学报, 2016, 42(8): 1667-1674. doi: 10.13700/j.bh.1001-5965.2015.0509
LI Yuan, ZHAO Jiguang, BAI Guoyu, et al. Method of time-to-go estimation based on predicted crack point[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(8): 1667-1674. doi: 10.13700/j.bh.1001-5965.2015.0509(in Chinese)
Citation: LI Yuan, ZHAO Jiguang, BAI Guoyu, et al. Method of time-to-go estimation based on predicted crack point[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(8): 1667-1674. doi: 10.13700/j.bh.1001-5965.2015.0509(in Chinese)

基于预测碰撞点的剩余飞行时间估计方法

doi: 10.13700/j.bh.1001-5965.2015.0509
基金项目: 国家“863”计划
详细信息
    作者简介:

    李辕,男,博士研究生。主要研究方向:航天任务分析与设计。Tel.:010-66364196。E-mail:bartholomew_lee@hotmail.com;赵继广,男,博士,教授,博士生导师。主要研究方向:航天任务分析与设计。Tel.:010-66364196。E-mail:zjgbeijing@126.com

    通讯作者:

    赵继广,Tel.:010-66364196,E-mail:zjgbeijing@126.com

  • 中图分类号: TJ765;TJ761.7

Method of time-to-go estimation based on predicted crack point

  • 摘要: 分别针对顺轨与逆轨拦截飞行轨迹的特点,设计了相应的剩余飞行时间(TGO)估计方法。该方法通过对弹目碰撞点的预测,降低了发射条件差异对TGO估计精度的影响。首先对线性比例导引运动方程进行变形,得到拦截弹飞行轨迹关于弹目距离的一阶微分方程,基于预测碰撞点,对不同初始发射角造成的积分结果误差进行修正,得出了2种拦截模式下的TGO解析表达式。通过与3种现有估计方法对比分析,验证了提出方法的实时性和估计精度,且能够优化制导性能。

     

  • [1] RYOO C,CHO H,TAHK M.Time-to-go weighted optimal guidance with impact angle constraints[J].IEEE Transactions on Control Systems Technology,2006,14(3):483-492.
    [2] KIM K B,KIM M,CHOI J W.Modified receding horizon guidance law with information on small accurate time-to-go[J].IEEE Transactions on Aerospace and Electronic Systems,2000,36(2):725-729.
    [3] TANAKA A,MAEDA H.Studies on the time-to-go indexing control scheme for an automatic aircraft landing system[J].Transactions of the Japan Society for Aeronautical and Space Sciences,1973,16(31):1-18.
    [4] WHANG I,RA W.Time-to-go estimation filter for anti-ship missile application[C]//Society of Instrument and Control Engineers (SICE).Piscataway,NJ:IEEE Press,2008:247-250.
    [5] YORK R,PASTRICK H.Optimal terminal guidance with constraints at final time[J].Journal of Spacecraft and Rockets,1977,14(6):381-382.
    [6] JEON I,LEE J,TAHK M.Impact-time-control guidance law for anti-ship missiles[J].IEEE Transactions on Control Systems Technology,2006,14(2):260-266.
    [7] LIU P,SUN R,LI W.Homing guidance law with falling angle and flying time control[J].Journal of Harbin Institute of Technology,2014,21(1):55-61.
    [8] KIM T H,LEE C H,TAHK M J.Time-to-go polynomial guidance with trajectory modulation for observability enhancement[J].IEEE Transactions on Aerospace and Electronic Systems,2013,49(1):55-73.
    [9] 马国欣,张友安,李君.带导引头视场限制的多约束导引律及剩余时间估计[J].系统工程与电子技术,2014,36(8):1609-1613.MA G X,ZHANG Y A,LI J.Guidance law with multiple constraints and seeker field-of-view limit and the time-to-go estimation[J].Systerms Engineering and Electronics,2014,36(8):1609-1613(in Chinese).
    [10] 李辕,闫梁,赵继广,等.顺轨拦截模式剩余飞行时间估计方法研究[J].航空学报,2015,36(9):3032-3041.LI Y,YAN L,ZHAO J G,et al.Method of time-to-go estimation for head-pursuit interception mode[J].Acta Aeronautica et Astronautica Sinica,2015,36(9):3032-3041(in Chinese).
    [11] 刘剑锋,庄志洪.利用导引头测角信息进行遭遇段剩余飞行时间估计的算法[J].兵工学报,2006,27(1):27-31.LIU J F,ZHUANG Z H.The algorithm of time-to-go using angle information provided by seeker during missile-target encounter[J].Acta Armamentarii,2006,27(1):27-31(in Chinese).
    [12] RIGGS J T L.Linear optimal guidance for short range air-to-air missile[C]//Proceedings of National Aerospace and Electronics Conference NAECON'79.Piscataway,NJ:IEEE Press,1979:757-764.
    [13] HULL D G,RADKE J J,MACK R E.Time-to-go prediction for homing missiles based on minimum-time intercepts[J].Journal of Guidance,Control,and Dynamics,1991,14(5):865-871.
    [14] DHANANJAY N,GHOSE D.Accurate time-to-go estimation for proportional navigation guidance[J].Journal of Guidance,Control,and Dynamics,2014,37(4):1378-1383.
    [15] TAHK M,RYOO C,CHO H.Recursive time-to-go estimation for homing guidance missiles[J].IEEE Transactions on Aerospace and Electronic Systems,2002,38(1):13-24.
    [16] 常青,邢超,李言俊.利用导弹轴向加速度估算剩余飞行时间的新方法[J].弹箭与制导学报,2002,22(4):112-114.CHANG Q,XING C,LI Y J.A new method for time-to-go using the acceleration along the axis of missile[J].Journal of Projectiles Rockets Missiles and Guidance,2002,22(4):112-114(in Chinese).
    [17] 张友安,马国欣.大前置角下比例导引律的剩余时间估计算法[J].哈尔滨工程大学学报,2013,34(11):1409-1414.ZHANG Y A,MA G X.Time-to-go estimation algorithm for the proportional navigation guidance law with a large lead angle[J].Journal of Harbin Engineering University,2013,34(11):1409-1414(in Chinese).
    [18] PRASANNA H M,GHOSE D.Retro-proportional-navigation:A new guidance law for interception of high-speed targets[J].Journal of Guidance,Control,and Dynamics,2012,35(2):377-386.
    [19] SHIMA T.Intercept-angle guidance[J].Journal of Guidance,Control,and Dynamics,2011,34(2):484-492.
    [20] TAL S,GOLAN O M.Head pursuit guidance[J].Journal of Guidance,Control,and Dynamics,2007,30(5):1437-1444.
    [21] ZARCHAN P.Tactical and strategic missile guidance[M].3rd ed.Reston:AIAA,2002:15.
    [22] YUAN P,CHERN J.Ideal proportional navigation[J].Journal of Guidance,Control,and Dynamics,1992,15(5):1161-1165.
  • 加载中
计量
  • 文章访问数:  689
  • HTML全文浏览量:  0
  • PDF下载量:  496
  • 被引次数: 0
出版历程
  • 收稿日期:  2015-07-31
  • 刊出日期:  2016-08-20

目录

    /

    返回文章
    返回
    常见问答