International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Finite-Time Convergent Guidance Law Based on Second-Order Sliding Mode Control Theory

  • Ji, Yi (School of Aerospace Engineering, Beijing Institute of Technology) ;
  • Lin, Defu (School of Aerospace Engineering, Beijing Institute of Technology) ;
  • Wang, Wei (School of Aerospace Engineering, Beijing Institute of Technology) ;
  • Lin, Shiyao (School of Aerospace Engineering, Beijing Institute of Technology)
  • Received : 2016.12.18
  • Accepted : 2017.08.16
  • Published : 2017.12.30
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Abstract

The complex battlefield environment makes it difficult to intercept maneuvering targets for guided missiles. In this paper, a finite-time convergent (FTC) guidance law based on the second-order sliding mode (SOSM) control theory is proposed to achieve the requirements of stability, accuracy and robustness. More specifically, a second-order sliding mode observer (SMOB) is used to estimate and compensate for the total disturbance of the controlled system, while the target acceleration is extracted from the line-of-sight (LOS) angle measurement. The proposed guidance law can drive the LOS angular rate converge to zero in a finite time, which means that the missile will accurately intercept the target. Numerical simulations with some comparisons are performed to demonstrate the superiority of the proposed guidance law.

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References

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