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Three-dimensional robust nonlinear cooperative guidance law for spatiotemporal coordination under stringent input constraint

Published online by Cambridge University Press:  19 March 2025

K. Zhao Open the ORCID record for K. Zhao [Opens in a new window] ,
J. Song Open the ORCID record for J. Song [Opens in a new window] ,
J. Yu  and
Y. Liu
K. Zhao
Affiliation:
School of Astronautics, Beihang University (BUAA), Beijing, China
J. Song*
Affiliation:
School of Astronautics, Beihang University (BUAA), Beijing, China
J. Yu
Affiliation:
School of Astronautics, Beihang University (BUAA), Beijing, China
Y. Liu
Affiliation:
School of Automation Science and Electrical Engineering, Beihang University (BUAA), Beijing, China
*
Corresponding author: J. Song; Email: [email protected]
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Abstract

A three-dimensional robust nonlinear cooperative guidance law is proposed to address the challenge of multiple missiles intercepting manoeuvering targets under stringent input constraints and thruster failure. The finite-time convergence theory is used to design a distributed nonlinear sliding mode guidance law, ensuring that the system converges in finite time, with the upper limit of convergence time related to the initial state. A nonlinear sliding surface is adopted to mitigate actuator saturation issues. Then, considering thruster failure, a robust cooperative guidance law is further introduced, ensuring mission completion through the reconstruction of the guidance law. The closed-loop system is proven to be stable using Lyapunov theory, and the influence of hyperparameters on the cooperative guidance law is analysed. Additionally, the results of numerical simulations and hardware-in-the-loop experiments demonstrate the effectiveness and robustness of the proposed algorithm in dealing with stringent input saturation and various disturbances.

Keywords

robust cooperative guidance lawfinite-time convergence theorynonlinear sliding mode guidance lawhardware-in-the-loop
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 18
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Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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