Circular Guidance Law against Ground Stationary Target in Specified Impact Angle

Since to impact the ground stationary target in a specified angle is required for some guided missiles, a circular guidance law which only uses the line-of-sight angle information for terminal velocity direction control is derived. The idea of this approach is to guide the missile flying in a series of arcs determined by the specified impact angles and the real-time positions of the missile and the target. Based on the simple geometry principles, the required velocity inclination angle can be quickly worked out, which is then used for guidance command generation. Simulation results show that compared with the typical optimal guidance law, the circular guidance law presented which is less sensitive to guidance cycle than guidance order delay, is more favorable for overhead-attack motion.