Remote control law synthesis with two-point guidance for surface-to-air missile on the basis of optimal control theory and differential of kinematic parameters

Abstract

The paper presents a synthesis method of guidance law for missile systems in general and a synthesis method of two-point guidance law for remote control missiles in particular that are based on applications of the optimal control theory and differential of kinematic parameters. The method not only proves the new guidance law clearly about mathematics, but also points out solutions to realize the guidance law for remote control missile systems with optimal coefficients.