Predefined-Time Spatial-Temporal Cooperative Guidance Law With Leader-Follower Strategy

In this article, a 3-D cooperative guidance law using a leader-follower strategy is proposed for a multimissile simultaneous attack on a maneuvering target at an adjustable impact time and desired impact angles. Since the missile terminal guidance phase spans a very short time, predefined-time conve...

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Bibliographic Details
Published in:IEEE transactions on aerospace and electronic systems Vol. 61; no. 3; pp. 6053 - 6069
Main Authors: Wang, Xu, Cai, Yuanli, Deng, Yifan, Jiang, Haonan
Format: Journal Article
Language:English
Published: New York IEEE 01.06.2025
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subjects:
adaptive control
Aerospace and electronic systems
asymptotic stability
Communication networks
Consensus protocol
Control methods
Control theory
Convergence
Design
Design parameters
Disturbance observers
Initial conditions
Line of sight
Lyapunov methods
Maneuvering targets
Missile control
Missile tracking
Missiles
multi-agent systems
Navigation
numerical simulation
Simulation
Sliding mode control
Stability analysis
State observers
Terminal guidance
Topology
Upper bound
ISSN:0018-9251, 1557-9603
Online Access:Get full text
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Summary:In this article, a 3-D cooperative guidance law using a leader-follower strategy is proposed for a multimissile simultaneous attack on a maneuvering target at an adjustable impact time and desired impact angles. Since the missile terminal guidance phase spans a very short time, predefined-time convergence theory is introduced to design guidance laws. The convergence time of the guidance error is designed as a tunable parameter and can be predefined arbitrarily regardless of the initial conditions or other design parameters. First, an impact-time control guidance law with predefined-time convergence is presented for the leader missile to hit the target at any prespecified impact time. Next, based on the predefined-time adaptive sliding-mode control method, an impact-angle control guidance law is designed to attack the maneuvering target at the desired line-of-sight angles without estimation of the target's acceleration, ensuring that the impact-angle errors converge to a small neighbor of zero at the predefined time. To address the inaccessibility of followers to the leader state under a directed communication topology, a predefined-time cooperative guidance scheme consisting of a distributed state observer and a tracking controller is, subsequently, developed. It utilizes information from neighboring missiles to reach a consensus regarding relative distance and radial relative velocity between the leader and followers, which ensures the simultaneous attack of the missile cluster. A stability analysis of the proposed methods is conducted with Lyapunov theory. The numerical simulation results demonstrate the effectiveness of the proposed cooperative guidance laws.
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ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2024.3524216