The capture region of TPN guidance law for orbital pursuit-evasion with limited maneuverability

This work studies the capture region of true proportional navigation (TPN) guidance law for orbital pursuit-evasion, which is a new research view compared with prior method used in orbital pursuit-evasion. The three-dimensional relative dynamic equations in line of sight (LOS) rotation coordinate system is derived and demonstrated firstly. Then nonlinear transformation is used in the dynamic equations so as to acquire the relative motion equation. The optimal strategies of both two satellites are determined and the expression of the capture-escape analytic equation is proposed. The capture and escape region of orbital pursuit-evasion is defined, and the numerical simulation is also performed to show the capture and escape region intuitively. Finally, two examples of orbital pursuit-evasion simulation are performed, which verify the effectiveness of the analytic method of this paper in orbital pursuit-evasion.