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Volume 42 Issue 3
Mar.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(3): 472-480.
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)
shu

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

doi: 10.13700/j.bh.1001-5965.2015.0189

  • 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)
  • Received Date: 01 Apr 2015
  • Publish Date: 20 Mar 2016
    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.

     

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