Field-of-View Constrained Three-Dimensional Impact Angle Control Guidance for Speed-Varying Missiles

This article develops a three-dimensional (3-D) impact angle control guidance law with the field-of-view (FOV) constraint. The impact error is defined as the difference between the predicted impact angle by proportional navigation guidance and the desired impact angle. The derived guidance command e...

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Published in:IEEE transactions on aerospace and electronic systems Vol. 58; no. 5; pp. 3992 - 4003
Main Authors: Wang, Jianan, Ding, Xiangjun, Chen, Yadong, Wang, Chunyan, Xin, Ming
Format: Journal Article
Language:English
Published: New York IEEE 01.10.2022
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subjects:
3-D guidance
Constraints
Convergence
Errors
Field of view
Field-of-view (FOV) constraint
Guidance (motion)
Guided missiles
Impact angle
impact angle control
Impact prediction
Interception
Kinematics
Lead
Missile control
Missiles
Numerical simulation
Proportional navigation
Quaternions
Terminal guidance
time-varying speed
Trajectories
Trajectory
ISSN:0018-9251, 1557-9603
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Abstract This article develops a three-dimensional (3-D) impact angle control guidance law with the field-of-view (FOV) constraint. The impact error is defined as the difference between the predicted impact angle by proportional navigation guidance and the desired impact angle. The derived guidance command enables the impact angle error trajectory to follow a desired impact angle error dynamic. It can guarantee that the impact error converges to zero before the time of interception. Meanwhile, zero terminal guidance command is achieved, and the FOV constraint is always met during the guidance process. Furthermore, the trajectory of a guided missile is not affected by the variation of missile speed even under the FOV constraint, which reveals that the impact angle control performance is independent of time-varying missile speed. Numerical simulations are conducted to demonstrate the effectiveness of the proposed guidance law.
AbstractList This article develops a three-dimensional (3-D) impact angle control guidance law with the field-of-view (FOV) constraint. The impact error is defined as the difference between the predicted impact angle by proportional navigation guidance and the desired impact angle. The derived guidance command enables the impact angle error trajectory to follow a desired impact angle error dynamic. It can guarantee that the impact error converges to zero before the time of interception. Meanwhile, zero terminal guidance command is achieved, and the FOV constraint is always met during the guidance process. Furthermore, the trajectory of a guided missile is not affected by the variation of missile speed even under the FOV constraint, which reveals that the impact angle control performance is independent of time-varying missile speed. Numerical simulations are conducted to demonstrate the effectiveness of the proposed guidance law.
Author Ding, Xiangjun
Wang, Jianan
Xin, Ming
Chen, Yadong
Wang, Chunyan
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  email: xin@missouri.edu
  organization: Department of Mechanical and Aerospace Engineering, University of Missouri, Columbia, MO, USA
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SubjectTerms 3-D guidance
Constraints
Convergence
Errors
Field of view
Field-of-view (FOV) constraint
Guidance (motion)
Guided missiles
Impact angle
impact angle control
Impact prediction
Interception
Kinematics
Lead
Missile control
Missiles
Numerical simulation
Proportional navigation
Quaternions
Terminal guidance
time-varying speed
Trajectories
Trajectory
Title Field-of-View Constrained Three-Dimensional Impact Angle Control Guidance for Speed-Varying Missiles
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