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Volume 42 Issue 9
Sep.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(9): 1857-1863.
LI Xinsan, WANG Lixin, WANG Mingjian, et al. Cooperative guidance law based on MPSC and CPN guidance method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(9): 1857-1863. doi: 10.13700/j.bh.1001-5965.2015.0592(in Chinese)
Citation: LI Xinsan, WANG Lixin, WANG Mingjian, et al. Cooperative guidance law based on MPSC and CPN guidance method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(9): 1857-1863. doi: 10.13700/j.bh.1001-5965.2015.0592(in Chinese)
shu

Cooperative guidance law based on MPSC and CPN guidance method

doi: 10.13700/j.bh.1001-5965.2015.0592
  • 1.

    Department of Control Engineering, Rocket Military Engineering University, Xi'an 710025, China

  • 2. Petty Officer Academy, Rocket Military Engineering University, Qingzhou 262500, China

Funds:

National Natural Science Foundation of China (61203354) 

  • Received Date: 10 Sep 2015
  • Publish Date: 20 Sep 2016
    Abstract
  • Cooperative guidance of multiple missiles satisfying terminal impact angle constraints is considered. A suboptimal guidance law is presented using the recently proposed model predictive spread control (MPSC) method and cooperative proportional navigation (CPN) guidance law. The basic principle of the MPSC method is given and the MPSC guidance law is designed on the assumption that the control is considered to be a function of quadratic formulation. The MPSC method requires a control history to begin the algorithmic sequence. Guess control history is computed using the CPN technique, subject to constraint on impact time. A stationary target is attacked by two missiles in the simulation. It is observed from the simulation that the impact time error and terminal impact angle error are within the specified convergence tolerance. The terminal impact angle constraint is well satisfied in salvo attack scenario.

     

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    • References(20)
  • [1]
    LEE J I,JEON I S,TAHK M J.Guidance law using augmented trajectory-reshaping command for salvo attack of multiple missiles[C]//UKACC International Control Conference 2006.Glasgow:UKACC,2006:766-771.
    [2]
    邹丽,孔繁峨,周锐,等.多导弹分布式自适应协同制导方法[J].北京亚洲成人在线一二三四五六区学报,2012,38(1):128-132.ZOU L,KONG F E,ZHOU R,et al.Distributed adaptive cooperative guidance for multi-missile salvo attack[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(1):128-132(in Chinese).
    [3]
    孙雪娇,周锐,吴江,等.多导弹分布式协同制导与控制方法[J].北京亚洲成人在线一二三四五六区学报,2014,40(1):120-124.SUN X J,ZHOU R,WU J,et al.Distributed cooperative guidance and control for multiple missiles[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(1):120-124(in Chinese).
    [4]
    范作娥,于德海,顾文锦.带落角约束和目标机动补偿的三维制导律[J].系统工程与电子技术,2011,33(8):1856-1859.FAN Z E,YU D H,GU W J.Three-dimensional guidance law with impact angle constraint and maneuvering target compensation[J].Systems Engineering and Electronics,2011,33(8):1856-1859(in Chinese).
    [5]
    JEON I S,LEE J I,TAHK M J.Impact-time-control guidance law for anti-ship missiles[J].IEEE Transactions on Control Systems Technology,2006,14(2):260-266.
    [6]
    LEE J I,JEON I S,TAHK M J.Guidance law to control impact time and angle[J].IEEE Transactions on Aerospace and Electronic Systems,2007,43(1):301-310.
    [7]
    张友安,马培蓓.带有攻击角度和攻击时间控制的三维制导[J].航空学报,2008,29(4):1021-1026.ZHANG Y A,MA P B.Three-dimensional guidance law with impact angle and impact time constraints[J].Acta Aeronautica et Astronautica Sinica,2008,29(4):1021-1026(in Chinese).
    [8]
    PADHI R,KOTHARI M.Model predictive static programming:A computationally efficient technique for suboptimal control design[J].International Journal of Innovative Computing,Information and Control,2009,5(2):399-411.
    [9]
    DWIVEDI P N,BHATTACHARYA A,PADHI R.Suboptimal midcourse guidance of interceptors for high speed targets with alignment angle constraint[J].Journal of Guidance,Control,and Dynamics,2011,34(3):860-877.
    [10]
    OZA H B,PADHI R.Impact-angle-constrained suboptimal model predictive static programming guidance of air-to-ground missiles[J].Journal of Guidance,Control,and Dynamics,2012,35(1):153-164.
    [11]
    MAITY A,OZA H B,PADHI R.Generalized model predictive static programming and its application to 3D impact angle constrained guidance of air-to-surface missiles[C]//2013 American Control Conference(ACC).Piscataway,NJ:IEEE Press,2013:4999-5004.
    [12]
    CANNON M.Efficient nonlinear model predictive control algorithms[J].Annual Reviews in Control,2004,28(2):229-237.
    [13]
    SLEGERS N,COSTELLO M.Model predictive control of a parafoil and payload system[J].Journal of Guidance,Control,and Dynamics,2005,28(4):816-821.
    [14]
    PADHI R,CHAWLA C,DAS P G.Partial integrated guidance and control of interceptors for high-speed ballistic targets[J].Journal of Guidance,Control,and Dynamics,2014,37(1):149-163.
    [15]
    赵启伦,陈建,董希旺,等.拦截高超声速目标的异类导弹协同制导律[J].航空学报,2016,37(3):936-948.ZHAO Q L,CHEN J,DONG X W,et al.Cooperative guidance law for heterogeneous missiles intercepting hypersonic weapon [J].Acta Aeronautica et Astronautica Sinica,2016,37(3):936-948(in Chinese).
    [16]
    张爱梅,江加和.基于相互通信的多导弹协同制导[J].应用科技,2015,42(2):1-6.ZHANG A M,JIANG J H.Cooperative guidance for multi-missiles based on mutual communication [J].Applied Science and Technology,2015,42(2):1-6(in Chinese).
    [17]
    ZHAO S Y,ZHOU R,WEI C.Design and feasibility analysis of a closed-form guidance law with both impact angle and time constraints[J].Journal of Astronautics,2009,30(3):1064-1085.
    [18]
    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.
    [19]
    JEON I S,LEE J I,TAHK M J.Homing guidance law for cooperative attack of multiple missiles[J].Journal of Guidance,Control,and Dynamics,2010,33(1):275-280.
    [20]
    方研,马克茂,陈宇青.带有攻击角度和时间约束的协同制导律设计[J].系统仿真学报,2014,26(10):2434-2441.FANG Y,MA K M,CHEN Y Q.Cooerative guidance laws with constraints on impact time and terminal angle[J].Journal of System Simulation,2014,26(10):2434-2441(in Chinese).
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