Three-dimensional guidance law with terminal impact angle constraint

Based on the dynamics and kinematics of the relative motion between missile and target for missile guidance, under the assumptions that the target is stationary, and the velocity of missile is a constant, and according to the error between the real impact angle and the designated impact angle, the desired kinematics of LOS (line of sight) is analyzed and designed. Then, a three-dimensional guidance law is designed by using Lyapunov stability theory. Finally, the missile is guided to impact the target by the designed guidance law. Simulation results are given.