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Volume 41 Issue 12
Dec.  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(12): 2256-2268.
ZHANG Jiao, YANG Xu, LIU Yuanxianget al. Guidance law with impact angle constraints based on extended disturbance observer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(12): 2256-2268. doi: 10.13700/j.bh.1001-5965.2015.0013(in Chinese)
Citation: ZHANG Jiao, YANG Xu, LIU Yuanxianget al. Guidance law with impact angle constraints based on extended disturbance observer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(12): 2256-2268. doi: 10.13700/j.bh.1001-5965.2015.0013(in Chinese)
shu

Guidance law with impact angle constraints based on extended disturbance observer

doi: 10.13700/j.bh.1001-5965.2015.0013

  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

  • Received Date: 05 Jan 2015
  • Rev Recd Date: 18 Apr 2015
  • Publish Date: 20 Dec 2015
    Abstract
  • Aimed at the requirement for intercepting maneuvering targets with impact angle constraint, based on the technology of extended disturbance observer (EDO), a novel finite-time convergence guidance law was presented. Considering the relative motion between missile and target, the time-varying uncertainty of missile velocity and the unknown target acceleration were regarded as the disturbance, which is estimated and compensated by EDO. The fast tracking differentiator was introduced to solve the immeasurability problem of the desired line of sight angle rate. Moreover, the domain of sliding mode capturability was introduced to the performance evaluation of guidance law. The simulation experiments of different interception scenarios and different forms of maneuvering target were carried out. The simulation results show that the proposed guidance law has good interception performance and robustness, and it is of less missile acceleration and higher guidance accuracy, which is more helpful for the realization in engineering.

     

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    • References(27)
  • [1]
    Kim M,Grider K V.Terminal guidance for impact attitude angle constrained flight trajectories[J].IEEE Transactions on Aerospace and Electronic Systems,1973,9(6):852-859.
    [2]
    Kim B S,Lee J G,Han H S.Biased PNG law for impact with angular constraint[J].IEEE Transactions on Aerospace and Electronic Systems,1998,34(1):277-288.
    [3]
    Ryoo C K,Cho H,Tahk M J.Optimal guidance laws with terminal impact angle constraint[J].Journal of Guidance,Control,and Dynamics,2005,28(4):724-732.
    [4]
    Ryoo C K,Cho H,Tahk M J.Time-to-go weighted optimal guidance with impact angle constraints[J].IEEE Transactions on Control Systems Technology,2006,14(3):483-492.
    [5]
    Ohlmeyer E J,Philips C A.Generalized vector explicit guidance[J].Journal of Guidance,Control,and Dynamics,2006,29(2):261-268.
    [6]
    Jeon I S,Lee J I.Optimality of proportional navigation based on nonlinear formulation[J].IEEE Transactions on Aerospace and Electronic Systems,2010,46(4):2051-2055.
    [7]
    Utkin V.Variable structure systems with sliding modes[J].IEEE Transactions on Automatic Control,1977,22(2):212-222.
    [8]
    贾庆忠,刘永善,刘藻珍.电视制导侵彻炸弹落角约束变结构反演制导律设计[J].宇航学报,2008,29(1):208-214. Jia Q Z,Liu Y S,Liu Z Z.Variable-structure backstepping guidance law with terminal angular constraint for video guided penetrating bomb[J]. Journal of Astronautics, 2008, 29(1): 208-214(in Chinese).
    [9]
    Harl N,Balakrishnan S N.Impact time and angle guidance with sliding mode control[J].IEEE Transactions on Control Systems Technology, 2012, 20(6): 1436-1449.
    [10]
    Sun W M,Zheng Z Q.3D variable structure guidance law based on adaptive model-following control with impact angular constraint[C]// Proceedings of the 26th Chinese Control Conference.Piscataway, NJ:IEEE Press,2007: 61-66.
    [11]
    Zhang Z X,Li S H,Luo S.Terminal guidance laws of missile based on ISMC and NDOB with impact angle constraint[J]. Aerospace Science and Technology, 2013, 31(1): 30-41.
    [12]
    王晓芳,郑艺裕,林海.基于扰动观测器的终端角约束滑模导引律[J].系统工程与电子技术,2014,36(1): 111-116. Wang X F,Zheng Y Y, Lin H.Sliding mode guidance law with impact angle constraint based on disturbance observer[J].Systems Engineering and Electronics,2014,36(1):111-116(in Chinese).
    [13]
    孙胜,张华明,周荻.考虑自动驾驶仪动特性的终端角度约束滑模导引律[J].宇航学报,2013,34(1):69-78. Sun S,Zhang H M,Zhou D.Sliding mode guidance law with autopilot lag for terminal angle constrained trajectories[J].Journal of Astronautics,2013,34(1):69-78(in Chinese).
    [14]
    Zhou D,Qu P P,Sun S.A guidance law with terminal impact angle constraint accounting for missile autopilot[J].Journal of Dynamic Systems Measurement and Control,2013,135(5):051009.
    [15]
    Kumar S R,Rao S,Ghose D.Sliding-mode guidance and control for all-aspect interceptors with terminal angle constraints[J].Journal of Guidance,Control,and Dynamics,2012,35(4):1230-1246.
    [16]
    Kumar S R,Rao S,Ghose D.Nonsingular terminal sliding mode guidance with impact angle constraints[J].Journal of Guidance,Control,and Dynamics,2014,37(4):1114-1130.
    [17]
    Xiong S F,Wang W H,Liu X D,et al.Guidance law against maneuvering targets with intercept angle constraint[J].ISA Transactions,2014,53(4):1332-1342.
    [18]
    熊少锋,王卫红,刘晓东,等.考虑导弹自动驾驶仪动态特性的带攻击角度约束制导律[J].控制与决策,2014,30(4):585-592. Xiong S F,Wang W H,Liu X D,et al.Impact angle guidance law considering missile's dynamics of autopilot[J].Control and Decision,2014,30(4):585-592(in Chinese).
    [19]
    张运喜,孙明玮,陈增强.滑模变结构有限时间收敛制导律[J].控制理论与应用,2012,29(11):1413-1418. Zhang Y X,Sun M W,Chen Z Q.Sliding mode variable structure finite-time convergence guidance law[J].Control Theory & Applications,2012,29(11):1413-1418(in Chinese).
    [20]
    王钊,李世华,费树岷.非奇异终端滑模导引律[J].东南大学学报,2009,39(1):87-90. Wang Z,Li S H,Fei S M.Nonsingular terminal sliding mode guidance law[J].Journal of Southeast University,2009,39(1):87-90(in Chinese).
    [21]
    熊少锋,王卫红,王森.带攻击角度约束的非奇异快速终端滑模制导律[J].控制理论与应用,2014,31(3):269-278. Xiong S F,Xang W H,Wang S.Nonsingular fast terminal sliding-mode guidance with intercept angle constraint[J].Control Theory & Applications,2014,31(3):269-278(in Chinese).
    [22]
    Chen W H.Nonlinear disturbance observer-enhanced dynamic inversion control of missiles[J].Journal of Guidance,Control,and Dynamics,2003,26(1):161-166.
    [23]
    Chen X S,Yang J,Li S H,et al.Disturbance observer based multi-variable control of ball mill grinding circuits[J].Journal of Process Control,2009,19(7):1205-1213.
    [24]
    Xia Y Q,Chen R F,Pu F,et al.Active disturbance rejection control for drag tracking in mars entry guidance[J].Advances in Space Research,2014,53(5):853-861.
    [25]
    韩京清.自抗扰控制技术[M].北京:国防工业出版社,2008:56-66. Han J Q.Active disturbance rejection control technique[M].Beijing:National Defence Industry Press,2008:56-66(in Chinese).
    [26]
    Guo B Z,Zhao Z L.On convergence of tracking differentiator[J].International Journal of Control,2011,84(4):693-701.
    [27]
    Bhat S P,Bernstein D S.Finite-time stability of continuous autonomous systems[J].SIAM Journal of Control and Optimization,2000,38(8):751-766.
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