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

Abstract

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