Optimal guidance law with multiple terminal constrains for penetrating guided weapon

In order to study the terminal guidance problem of penetrating guided weapon, the guidance model with multiple terminal constraints based on first-order missile dynamics was established. The common optimal solution was deduced by state feedback law, and three typical optimal guidance laws were obtained by the relationship between different terminal constraints and penalty function. Then, advanced proportional navigation guidance law(APN), trajectory shaping guidance law with impact position and angle constraints (TSGPA), and optimal guidance law with multiple terminal constrains (OGLMTC) were obtained based on small angle assumption according to the information of typical guidance and control system. Theoretical analysis and typical simulations show that TSGPA and OGLMTC can control the missile to meet the dual and multiple terminal constraints concerning terminal location angel and accelaration respectively, and the two guidance laws can provide reference to engineering problem.