Regular Papers

International Journal of Control, Automation and Systems 2016; 14(1): 99-114

Published online February 11, 2016

https://doi.org/10.1007/s12555-014-0155-8

© The International Journal of Control, Automation, and Systems

Adaptive Nonsingular Fast Terminal Sliding Mode Guidance Law with Impact Angle Constraints

Junhong Song, Shenmin Song*, and Huibo Zhou

Harbin Institute of Technology

Abstract

This paper considers the terminal guidance problem of missiles intercepting maneuvering targets with impact angle constraints. Based on an advanced nonsingular fast terminal sliding mode control scheme and adaptive control, an adaptive nonsingular fast terminal sliding mode guidance law is proposed in the presence of the target acceleration as an unknown bounded external disturbance. In the design procedure, an adaptive law is presented to estimate the unknown upper bound of the external disturbance. Theoretical analysis shows that the proposed guidance law can guarantee the finite-time convergence in both the reaching phase and the sliding phase by applying a Lyapunov-based approach. Numerical simulations are presented to demonstrate the effectiveness of the proposed guidance law. Although the proposed guidance law is developed for the constant speed missiles, by the extensive numerical simulations with a realistic missile model, the performance is shown to be equally good for the varying speed missiles."

Keywords Adaptive control, finite-time convergence, guidance law, missile, terminal sliding mode.

Article

Regular Papers

International Journal of Control, Automation and Systems 2016; 14(1): 99-114

Published online February 1, 2016 https://doi.org/10.1007/s12555-014-0155-8

Copyright © The International Journal of Control, Automation, and Systems.

Adaptive Nonsingular Fast Terminal Sliding Mode Guidance Law with Impact Angle Constraints

Junhong Song, Shenmin Song*, and Huibo Zhou

Harbin Institute of Technology

Abstract

This paper considers the terminal guidance problem of missiles intercepting maneuvering targets with impact angle constraints. Based on an advanced nonsingular fast terminal sliding mode control scheme and adaptive control, an adaptive nonsingular fast terminal sliding mode guidance law is proposed in the presence of the target acceleration as an unknown bounded external disturbance. In the design procedure, an adaptive law is presented to estimate the unknown upper bound of the external disturbance. Theoretical analysis shows that the proposed guidance law can guarantee the finite-time convergence in both the reaching phase and the sliding phase by applying a Lyapunov-based approach. Numerical simulations are presented to demonstrate the effectiveness of the proposed guidance law. Although the proposed guidance law is developed for the constant speed missiles, by the extensive numerical simulations with a realistic missile model, the performance is shown to be equally good for the varying speed missiles."

Keywords: Adaptive control, finite-time convergence, guidance law, missile, terminal sliding mode.

IJCAS
May 2024

Vol. 22, No. 5, pp. 1461~1759

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