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

基于改进Terminal滑模的导弹大角度机动控制

马悦悦 唐胜景 郭杰

马悦悦, 唐胜景, 郭杰等 . 基于改进Terminal滑模的导弹大角度机动控制[J]. 北京航空航天大学学报, 2016, 42(3): 472-480. doi: 10.13700/j.bh.1001-5965.2015.0189
引用本文: 马悦悦, 唐胜景, 郭杰等 . 基于改进Terminal滑模的导弹大角度机动控制[J]. 北京航空航天大学学报, 2016, 42(3): 472-480. doi: 10.13700/j.bh.1001-5965.2015.0189
MA Yueyue, TANG Shengjing, GUO Jieet al. Large angle maneuvering control for missiles based on improved Terminal sliding mode method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(3): 472-480. doi: 10.13700/j.bh.1001-5965.2015.0189(in Chinese)
Citation: MA Yueyue, TANG Shengjing, GUO Jieet al. Large angle maneuvering control for missiles based on improved Terminal sliding mode method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(3): 472-480. doi: 10.13700/j.bh.1001-5965.2015.0189(in Chinese)

基于改进Terminal滑模的导弹大角度机动控制

doi: 10.13700/j.bh.1001-5965.2015.0189
基金项目: 国家自然科学基金(11202024);航空科学基金(2012ZA720002)
详细信息
    作者简介:

    马悦悦 男,博士研究生。主要研究方向:飞行器总体设计、飞行动力学与控制。Tel.:010-68918678 E-mail:mayy@bit.edu.cn;唐胜景 男,博士,教授,博士生导师。主要研究方向:飞行器总体设计、飞行动力学与控制。Tel.:010-68918678 E-mail:tangsj@bit.edu.cn;郭杰 男,博士,讲师。主要研究方向:飞行器总体设计、飞行动力学与控制。Tel.:010-68912408 E-mail:guojie1981@bit.edu.cn

    通讯作者:

    郭杰,Tel.:010-68912408 E-mail:guojie1981@bit.edu.cn

  • 中图分类号: V249.122;TJ765.2

Large angle maneuvering control for missiles based on improved Terminal sliding mode method

Funds: National Natural Science Foundation of China (11202024);Aeronautical Science Foundation of China (2012ZA720002)
  • 摘要: 针对空空导弹攻击载机尾后目标的大角度机动控制问题,提出一种基于复合滑模面与扰动抑制机制的非奇异Terminal滑模(NTSM)控制器设计方法。首先建立了包含有气动不确定性的直接力控制系统(RCS)空空导弹数学模型,并采用传统NTSM控制方法设计了导弹姿态控制律。然后,在此基础上,针对大角度机动时初始状态远离平衡点的问题,设计了一种复合滑模面以加快系统收敛速度。为解决大攻角下的气动不确定性导致的严重抖振问题,引入了扩张状态观测器(ESO)技术,实现了系统不确定量的在线估计与补偿。对所提方法的稳定性分析证明了系统的有限时间收敛特性。最后,将设计的控制器应用于空空导弹的敏捷转弯大角度机动控制,仿真结果表明新方法可以加快系统收敛速度,并能有效削弱未建模动力学造成的抖振现象。

     

  • [1] THUKRAL A, INNOCENTI M.A sliding mode missile pitch autopilot synthesis for high angle of attack maneuvering[J].IEEE Transactions on Control Systems Technology,1998,6(3):359-371.
    [2] MCFARLAND M B, CALISE A J.Neural networks and adaptive nonlinear control of agile antiair missiles[J].Journal of Guidance,Control,and Dynamics,2000,23(3):547-553.
    [3] KANG S, KIM H J,LEE J I,et al.Roll-pitch-yaw integrated robust autopilot design for a high angle-of-attack missile[J].Journal of Guidance,Control,and Dynamics,2009,32(5):1622-1628.
    [4] RYU S M, WON D Y,LEE C H,et al.High angle of attack missile autopilot design by pole placement approach[C]//The 3rd International Symposium on Systems and Control in Aeronautics and Astronautics.Piscataway,NJ:IEEE Press,2010:535-539.
    [5] KIM K U, KANG S,KIM H J,et al.Realtime agile-turn guidance and control for an air-to-air missile[C]//AIAA Guidance,Navigation,and Control Conference.Reston:AIAA,2010.
    [6] RATLIFF R T, RAMSEY J A,WISE K A,et al.Advances in agile maneuvering for high performance munitions[C]//AIAA Guidance,Navigation,and Control Conference.Reston:AIAA,2009.
    [7] KIM Y, KIM B S,PARK J H.Aerodynamic pitch control design for reversal of missile's flight direction[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2014,228(9):1519-1527.
    [8] KIM Y,KIM B S. Pitch autopilot design for agile missiles with uncertain aerodynamic coefficients[J].IEEE Transactions on Aerospace and Electronic Systems,2013,49(2):907-914.
    [9] YANG L, YANG J Y.Nonsingular fast terminal sliding-mode control for nonlinear dynamical systems[J].International Journal of Robust and Nonlinear Control,2011,21(16):1865-1879.
    [10] 李升波,李克强, 王建强,等.非奇异快速的终端滑模控制方法[J].信息与控制,2009,38(1):1-8. LI S B,LI K Q,WANG J Q,et al.Nonsingular and fast terminal sliding mode control method[J].Information and Control,2009,38(1):1-8(in Chinese).
    [11] 胡庆雷,姜博严, 石忠.基于新型终端滑模的航天器执行器故障容错控制[J].航空学报,2013,34(1):1-9. HU Q L,JIANG B Y,SHI Z.Novel terminal sliding mode based fault tolerant attitude control for spacecraft under actuator faults[J].Acta Aeronautica et Astronautica Sinica,2013,34(1):1-9(in Chinese).
    [12] LEE C H, KIM T H,TAHK M J.Agile missile autopilot design using nonlinear backstepping control with time-delay adaptation[J].Transactions of the Japan Society for Aeronautical and Space Sciences,2014,57(1):9-20.
    [13] WISE K A, BROY D J.Agile missile dynamics and control[J].Journal of Guidance,Control,and Dynamics,1998,21(3):441-449.
    [14] SIMON J M, BLAKE W B.Missile Datcom:High angle of attack capability[C]//The 24th Atmospheric Flight Mechanics Conference.Reston:AIAA,1999.
    [15] ABNEY E J, MCDANIEL M A.High angle of attack aerodynamic predictions using Missile Datcom[C]//The 23rd AIAA Applied Aerodynamics Conference.Reston:AIAA,2005,2:1111-1129.
    [16] HAN J Q. From PID to active disturbance rejection control[J].IEEE Transactions on Industrial Electronics,2009,31(3):900-906.
    [17] 马悦悦,唐胜景, 郭杰,等.基于自抗扰与模糊逻辑的大攻角控制系统设计[J].系统工程与电子技术,2013,35(8):1711-1716. MA Y Y,TANG S J,GUO J,et al.High angle of attack control system design based on ADRC and fuzzy logic[J].Systems Engineering and Electronics,2013,35(8):1711-1716(in Chinese).
    [18] KORI D K, KOLHE J P,TALOLE S E.Extended state observer based robust control of wing rock motion[J].Aerospace Science and Technology,2014,33(1):107-117.
    [19] GUO B Z, ZHAO Z L.On the convergence of an extended state observer for nonlinear systems with uncertainty[J].Systems & Control Letters,2011,60(6):420-430.
    [20] FENG Y, YU X H,MAN Z H.Non-singular terminal sliding mode control of rigid manipulators[J].Automatica,2002,38(12):2159-2167.
    [21] 张巍巍,王京. 基于指数趋近律的非奇异Terminal滑模控制[J].控制与决策,2012,27(6):909-913. ZHANG W W,WANG J.Nonsingular terminal sliding model control based on exponential reaching law[J].Control and Decision, 2012,27(6):909-913(in Chinese).
    [22] ANTHONY T C, WIE B,CARROLL S.Pulse-modulated control synthesis for a flexible spacecraft[J].Journal of Guidance,Control,and Dynamics,1990,13(6):1014-1022.
  • 加载中
计量
  • 文章访问数:  993
  • HTML全文浏览量:  75
  • PDF下载量:  5
  • 被引次数: 0
出版历程
  • 收稿日期:  2015-04-01
  • 网络出版日期:  2016-03-20

目录

    /

    返回文章
    返回
    常见问答