ABSTRACT
The main goal of this research is to derive the complete closed-form solutions of threedimensional ideal proportional navigation (3D IPN) for nonmaneuvering and maneuvering targets. IPN is a guidance law by which the commanded missile acceleration is applied in the direction perpendicular to the relative velocity between the missile and the target, and the acceleration magnitude is proportional to the product of line-of-sight (LOS) rate and relative speed. Three coupled nonlinear second-order dynamic equations modeling the relative motion are solved analytically without any linearization for performance and trajectory analysis. Properties of 3D IPN such that capture region, range-to-go, time-to-go, and two aspect angles within the spherical coordinates are all obtained in closed form.
