Impact Time Control Guidance with Finite-Time Convergence Based on Pure Proportional Navigation

Abstract

A finite-time-convergent impact time control guidance law based on pure proportional navigation is proposed for interception of stationary target. The proposed guidance law achieves impact time control by tracking desired look angle. The desired look angle is defined to satisfy the time-to-go condition at each instant by pure proportional navigation. The guidance law can deal with feasible impact times for all initial conditions without any linearisation and approximation. The finite-time convergence of tracking error ensures that the missile can intercept the target while maintaining the characteristics of pure proportional navigation. Numerical simulation is performed to verify the properties and performance of the proposed guidance law.