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

doi:10.13700/j.bh.1001-5965.2015.0189

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

北京理工大学宇航学院, 飞行器动力学与控制教育部重点实验室, 北京 100081

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
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- 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

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

Key Laboratory of Dynamics and Control of Flight Vehicle of Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Funds: National Natural Science Foundation of China (11202024);Aeronautical Science Foundation of China (2012ZA720002)

摘要

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。
- 空空导弹 /
- 大角度机动 /
- Terminal滑模控制 /
- 复合滑模面 /
- 扩张状态观测器(ESO)
Abstract: Based on compound sliding surface and disturbance rejection mechanism, a novel design approach of nonsingular Terminal sliding mode (NTSM) controller is proposed for large angle maneuvering control during an air-to-air missile intercepting a target in the rear hemisphere of the carrier. Firstly, the mathematical model of an air-to-air missile equipped with reaction-jet control system (RCS) is established considering the aerodynamic uncertainties. Subsequently, a missile attitude control law is designed by the traditional NTSM method. On this basis, taking original states far from equilibrium during large angle maneuvering into account, a compound sliding surface is adopted to accelerate the convergence of control system. To solve the problem of severe chattering caused by the aerodynamic uncertainties at high angle of attack, extended state observer (ESO) methodology is introduced to online estimate and compensate the system uncertainties. Furthermore, the stability analysis to the proposed method demonstrates the finite time convergence property of the control system. Eventually, the designed controller is applied to the large angle maneuvering control for agile turn of air-to-air missile. Simulation results reveal that the proposed method is able to make the convergence faster and effectively attenuate chattering caused by unmodeled dynamics.
- air-to-air missile /
- large angle maneuvering /
- Terminal sliding mode control /
- compound sliding surface /
- extended state observer (ESO)

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参考文献(22)

[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.