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Cooperative guidance law for intercepting a hypersonic target with impact angle constraint

Published online by Cambridge University Press:  17 January 2022

S. Liu Open the ORCID record for S. Liu [Opens in a new window] ,
B. Yan Open the ORCID record for B. Yan [Opens in a new window] ,
R. Liu ,
P. Dai ,
J. Yan  and
G. Xin
S. Liu
Affiliation:
Unmanned System Research Institute, Northwestern Polytechnical University, Xi’an710072, China
B. Yan*
Affiliation:
School of Astronautics, Northwestern Polytechnical University, Xi’an710072, China
R. Liu
Affiliation:
School of Astronautics, Northwestern Polytechnical University, Xi’an710072, China
P. Dai
Affiliation:
School of Astronautics, Northwestern Polytechnical University, Xi’an710072, China
J. Yan
Affiliation:
Unmanned System Research Institute, Northwestern Polytechnical University, Xi’an710072, China
G. Xin
Affiliation:
Aerospace System Engineering Shanghai, Shanghai201100, China
*
E-mail: yanbinbin@nwpu.edu.cn
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Abstract

The cooperative guidance problem of multiple inferior missiles intercepting a hypersonic target with the specific impact angle constraint in the two-dimensional plane is addressed in this paper, taking into consideration variations in a missile’s speed. The guidance law is designed with two subsystems: the direction of line-of-sight (LOS) and the direction of normal to LOS. In the direction of LOS, by applying the algebraic graph theory and the consensus theory, the guidance command is designed to make the system convergent in a finite time to satisfy the goal of cooperative interception. In the direction of normal to LOS, the impact angle is constrained to transform into the LOS angle at the time of interception. In view of the difficulty of measuring unknown target acceleration information in real scenarios, the guidance command is designed by utilising a super-twisting algorithm based on a nonsingular fast-terminal sliding mode (NFTSM) surface. Numerical simulation results manifest that the proposed guidance law performs efficiently and the guidance commands are free of chattering. In addition, the overall performance of this guidance law is assessed with Monte Carlo runs in the presence of measurement errors. The simulation results demonstrate that the robustness can be guaranteed, and that overall efficiency and accuracy in intercepting the hypersonic target are achieved.

Keywords

Cooperative guidanceConsensus theorySuper-twisting algorithmHypersonic targets
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1300 , June 2022 , pp. 1026 - 1044
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Copyright
© The Author(s), 2022. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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