Sliding mode guidance law with Field-of-view constraint and impact time control for missiles

Abstract This study introduces an innovative guidance law that allows for controlled impact time while meeting the missile’s field-of-view angle constraints. The equation that shows the missile-target relative movement is first established. A non-singular sliding mode guidance law is designed, leveraging sliding mode control theory. Under the field-of-view constraints, the impact time reaches the desired value, as proven according to the Lyapunov stability theory. The analyses derived from the numerical simulation support that the missile’s field-of-view angle remains within constraints throughout the attack process, and the control commands are smooth without singularities. The research findings hold significant value as a reference for designing multi-missile coordinated attack strategies.