A three-dimensional Missile Guidance Law with Angle Constraint Based on Sliding Mode Control

According to the relative moving relations of missiles against target in three dimensional space, a novel variable structure guidance law with terminal angle constraints is proposed based on the Lyapunov stability theory. The guidance law cannot only be of stronger robustness against changes of parameters and external disturbance, but also can control the terminal azimuth of a missile. The proposed guidance law only uses the information for the target acceleration bound; the precise measurement of target acceleration of maneuver is not required. Finally, the simulation results are presented to show the validity of the proposed method.