Design of optimal guidance law for interception ballistic missile during the boost phase

This paper studied a direct hit optimal guidance law of interception,aiming at the characteristics of acceleration high,flight velocity rapid and reaction time short for ballistic missile during the boost phase.Relative motion equations of interception missile and ballistic missile were founded;the performance index function was designed to reach undershoot quantity least and energy minimum.The optimal guidance law of defense missile launched by airplane was designed for interception ballistic missile during the boost phase.Simulations showed that the guidance law designed satisfied the required index,reaching the aim to direct hit the target.The correctness and effectiveness of the optimal guidance law were proved.