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Volume 42 Issue 4
Apr.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(4): 669-676.
ZHOU Weidong, CHEN Yankui, XIONG Shaofenget al. Chattering-free sliding mode guidance law with impact angle constraint[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(4): 669-676. doi: 10.13700/j.bh.1001-5965.2015.0290(in Chinese)
Citation: ZHOU Weidong, CHEN Yankui, XIONG Shaofenget al. Chattering-free sliding mode guidance law with impact angle constraint[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(4): 669-676. doi: 10.13700/j.bh.1001-5965.2015.0290(in Chinese)
shu

Chattering-free sliding mode guidance law with impact angle constraint

doi: 10.13700/j.bh.1001-5965.2015.0290
  • 1.

    School of Automation, Harbin Engineering University, Harbin 150001, China

  • 2. School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 10008

  • 3. Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds:  National Natural Science Foundation of China (61102107, 61374208)
  • Received Date: 08 May 2015
  • Rev Recd Date: 29 May 2015
  • Publish Date: 20 Apr 2016
    Abstract
  • Taking into account both the autopilot dynamics and impact angle constraint,a novel chattering-free sliding mode control guidance law for homing missile to intercept a target performing evasive maneuvers was proposed. Firstly, we establish the guidance system state equation by differentiating the line-of-sight (LOS) angle three times. Secondly, a new sliding mode control system is put forward based on guidance system state equation, and we choose full-order TSM (terminal sliding mode)manifold to avoid the singularity of TSM, and introduce the sliding mode switching term compensating the unknown bounded disturbance in the derivative of controller to eliminate the chattering phenomenon. Finally, we apply the new sliding mode control in designing the guidance law, which enforces the LOS angle convergence to desired value in finite time. Compared with the existing finite time guidance laws, this guidance law can not only compensate for the effects of the autopilot lag but also eliminate chattering phenomenon of controller effectively. The numerical simulation verifies the effectiveness of the proposed method in the design of guidance law.

     

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    • References(19)
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