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Non-smooth guidance law with terminal angular constraints for missiles against surface targets

Guidance law with terminal angular constraints is considered for an air-to-surface missile against a surface target. To guarantee the finite-time convergence property, a non-smooth continuous guidance law is designed in the engagement of the missile against a non-maneuvering target. By taking the target’s maneuver as an external disturbance input, the designed guidance law is also applicable to a maneuvering target, which is justified through the performance analysis using the input-to-state stability theory. Simulation is conducted, and the simulation results verify the theory proposed in the paper.