A Sliding Mode Guidance Law with Impact Time and Field-of-View Constraints

This paper proposes a guidance law for controlling the missile's impact time by using sliding mode control theory for stationary targets. Field-of-view constraint is considered into the design of the guidance law, which ensures that the missile's seeker remains within the specified field-of-view. Through the selection of appropriate control parameters, the impact time error and lead angle of the missile converge rapidly, significantly improving guidance efficiency. The stability of the guidance law is rigorously verified through Lyapunov stability theory. Moreover, the absence of singularities in the guidance command further enhances the system's stability and robustness. Simulation results demonstrate that the proposed guidance law exhibits adaptability to various situations and achieves superior performance. The guidance law satisfies both impact time and field-of-view constraints, and this property highlights its significant potential in collaborative attack applications.