Nonlinear Three-Dimensional Guidance for Impact Time and Angle Control With Field-of-View Constraint

This article presents a nonlinear 3-D guidance law for homing missiles with a field-of-view (FOV) constraint to achieve impact time and angle control against a stationary target. Specifically, a guidance error vector and its nonlinear error dynamics are first developed. The desired impact time and a...

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Bibliographic Details
Published in:IEEE transactions on aerospace and electronic systems 2024-02, Vol.60 (1), p.264-279
Main Authors: Wang, Pengyu, Lee, Chang-Hun, Liu, Yuhan, Tahk, Min-Jea
Format: Article
Language:English
Subjects:
3-D guidance
Aerodynamics
Decoupling
Estimation
Field of view
Field-of-view (FOV) constraint
Geometry
Guidance (motion)
homing missile
impact angle
impact time
Iterative methods
Kinematics
Missiles
Nonlinear dynamics
Orthogonality
Switches
Three-dimensional displays
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Summary:This article presents a nonlinear 3-D guidance law for homing missiles with a field-of-view (FOV) constraint to achieve impact time and angle control against a stationary target. Specifically, a guidance error vector and its nonlinear error dynamics are first developed. The desired impact time and angle can be satisfied as long as the guidance error converges to zero before the interception. The proposed nonlinear error dynamics is then enhanced with an auxiliary function to address the FOV constraint, and the prescribed-time control technique is employed to obtain a feedback guidance law. The guidance framework in this article is rigorously derived under the original 3-D missile-target kinematics model, without decoupling the engagement geometry into two mutually orthogonal planes. Furthermore, different from the existing similar studies, the proposed guidance law does not require explicit time-to-go estimation and numerical iterations, which avoids estimation error and allows for convenient implementation.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2023.3322123