Nonsingular Sliding Mode Guidance Law for Impact Time Control With Field-of-View Constraint

In this paper, a new missile impact time control guidance law using sliding mode control technology is proposed, aiming at intercepting stationary targets. The research focuses on improving the time-to-go estimation method, abandoning the small-angle assumption to achieve a more accurate estimation, and innovatively incorporating the field-of-view (FOV) constraint into the design of the guidance law. The guidance law ensures the missile’s seeker remains within the specified FOV even with large initial lead angles, improving stability and enhancing launch flexibility in complex environments. By selecting reasonable control parameters, the impact time error and lead angle of the missile converge rapidly, boosting guidance efficiency. Lyapunov stability theory verifies its reliability and safety, and the absence of singularities in the guidance command significantly enhances the system’s stability and robustness. The simulation results show that the proposed guidance law is adaptable to varieties of working conditions and exhibits excellent performance. Compared with the existing method, the guidance law satisfies the impact time control and FOV constraint even when the missile is launched at a large initial lead angle. This feature makes the guidance law show significant potential in the field of salvo attack.