Three-dimensional prescribed-time tracking guidance strategy for terminal angle and field of view control against maneuvering targets

This study presents a three-dimensional (3D) guidance law for intercepting maneuvering targets while satisfying the terminal angle and the field of view (FOV) constraints. First, a line-of-sight (LOS) vector rotation rate profile is developed. The zero-miss distance and the terminal angle constraint can be achieved as long as the desired LOS rotation rate vector can be precisely tracked. Second, a novel feedback guidance law is derived based on the tracking error of LOS rotation rate vector. A prescribed-time disturbance observer (DOB) is employed in the guidance law to compensate for disturbance induced by target maneuvers. Subsequently, the analytical solution of the missile’s relative lead angle is solved to achieve the FOV constraint. Finally, extensive simulation results and comparative evaluations validate the superior performance and robustness of the proposed guidance law. In contrast to prior studies, the proposed guidance law does not require decoupling, linearization, and switching logic, which guarantees smooth guidance commands and facilitates practical implementation.