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Sliding mode-based continuous guidance law with terminal angle constraint

Published online by Cambridge University Press:  07 June 2016

S. He  and
D. Lin
S. He*
Affiliation:
School of Aerospace Engineering, Beijing Institute of Technology, Beijing, P.R. China
D. Lin
Affiliation:
School of Aerospace Engineering, Beijing Institute of Technology, Beijing, P.R. China
*
[email protected]
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Abstract

In this paper, sliding mode control and disturbance observer are used to design a new continuous composite guidance law with terminal angle constraint. The robustness and finite-time convergence of the proposed guidance law is established using the Lyapunov stability theory. For performance improvement, a nonlinear disturbance observer, which can be viewed as a ‘patch’ for the original guidance law, is designed to estimate the target manoeuvre. Theoretical analysis and simulation results demonstrate the effectiveness of the proposed method.

Keywords

Sliding mode controldisturbance observerguidance lawimpact anglechattering-free
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1229 , July 2016 , pp. 1175 - 1195
Copyright
Copyright © Royal Aeronautical Society 2016 

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