A guidance law for air defence missile trajectory tracking

Based on the Lyapunov stability theory,a sliding surface is structrued by using nominal optimal trajectory parametersA new guidance law of the trajectory tracking is proposed The mathematic theorem and the derivation procedure of the guidance law are given in detailThe digital computer trajectory simulation of twodimensional missile guidance problem is performed The results demonstrate that the proposed guidance law of the trajectory tracking can make the missile tracking nominal optimal trajectory fast