Abstract
The problem of impact time control guidance with field-of-view constraint is addressed based on time-varying sliding mode control. The kinematic conditions that satisfy the impact time control with field-of-view constraint are defined, and then a novel time-varying sliding surface is constructed to achieve the defined conditions. The sliding surface contains two unknown coefficients: one is tuned to achieve the global sliding surface to satisfy the impact time constraint and zero miss distance, and the other is tuned to guarantee the field-of-view constraint. The guidance law is designed to ensure the realization of the global sliding mode. On this basis, the guidance law is modified to a closed-loop structure, and the maximum detection capability of the seeker is utilized to a greater extent. Under the proposed guidance law, neither the small angle assumption nor time-to-go estimation is needed. The guidance command is continuous and converges to 0 at the desired impact time. Simulation results demonstrate the effectiveness and superiority of the proposed guidance law.
Highlights
With the development of modern defense systems, single missile penetration is increasingly difficult
In [1], an impact time control guidance (ITCG) law is derived based on linearized formulation and optimal control theory
This guidance law is a combination of the proportional navigation guidance (PNG) law and the feedback of impact time error
Summary
With the development of modern defense systems, single missile penetration is increasingly difficult. In [21], the desired lead angle is designed as a virtual variable that can realize impact time control with FOV constraint, and the virtual variable is tracked by the actual lead angle based on terminal sliding mode control. The kinematic conditions satisfying the impact time control with FOV constraint are defined, and a time-varying sliding surface with two unknown coefficients is designed. The kinematic conditions for impact time control guidance with FOV constraint can be defined as. One coefficient is tuned to obtain the global sliding surface to meet the impact time constraint and zero miss distance, and the other is tuned to meet the FOV constraint. Impact time control and zero miss distance can be achieved under guidance law (13) and global sliding surface (11). It should be noted that the method proposed in this paper needs to avoid the initial lead angle being 0, and there is an explanation of this issue in the singularity analysis
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