International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Adaptive nonsingular sliding mode based guidance law with terminal angular constraint

  • He, Shaoming (School of Aerospace Engineering, Beijing Institute of Technology) ;
  • Lin, Defu (School of Aerospace Engineering, Beijing Institute of Technology)
  • Received : 2014.04.01
  • Accepted : 2014.06.18
  • Published : 2014.06.30
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Abstract

In this paper, a new adaptive nonsingular terminal sliding mode control theory based impact angle guidance law for intercepting maneuvering targets was documented. In the design procedure, a new adaptive law for target acceleration bound estimation was presented, which allowed the proposed guidance law to be used without the requirement of the information on the target maneuvering profiles. With the aid of Lyapunov stability criteria, the finite-time convergent characteristics of the line-of-sight angle and its derivative were proven in theory. Numerical simulations were also performed under various conditions to demonstrate the effectiveness of the proposed guidance law.

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References

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