The realization of the three dimensional guidance law using modified augmented proportional navigation

This paper deals with 3D missile guidance law and presents the general optimal solution of the state equation which includes the target maneuver as Gauss-Markov processing, and the solution has the form of the augmented proportional navigation guidance. The main result is about the transformation between the Cartesian coordinates on which both the guidance law and the filter are based and the polar coordinates in real missile guidance and radar measurement information. The adjustment of estimated target acceleration by trigonometric functions and extended Kalman filter is proposed as a solution to this problem. It is shown that this proposed transformation is valid in real 3D guidance problem by comparison with the conventional method through computer simulation