Journal
IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS
Volume 58, Issue 5, Pages 3992-4003Publisher
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
DOI: 10.1109/TAES.2022.3157807
Keywords
Missiles; Lead; Convergence; Quaternions; Kinematics; Trajectory; Numerical simulation; Field-of-view (FOV) constraint; impact angle control; time-varying speed; 3-D guidance
Funding
- National Natural Science Foundation of China [61873031]
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This article proposes a guidance law based on impact angle control, which has the constraints of field-of-view (FOV) and dynamic tracking of impact error. It ensures that the impact error converges to zero before interception and satisfies the FOV constraint. Numerical simulations demonstrate the effectiveness of the proposed guidance law.
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.
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