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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

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.

Acknowledgement

Supported by : Natural Science Foundation of China

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