New Look-Angle Tracking Guidance Strategy for Impact Time and Angle Control

Abstract

This paper presents a new guidance strategy for a certain class of homing missiles subject to various terminal constraints and lateral acceleration limit. To achieve zero miss distance in the presence of various terminal impact constraints, a planar engagement scenario of missiles is considered to develop a feedback guidance law of tracking a time-varying look angle that is modeled as an inverse tangent function. The proposed strategy can be applied to both the impact time control and the impact time and angle control guidance problems. Furthermore, it does not require any forms of time-to-go estimation, numerical iterations, and linearization procedures. Numerical simulations are conducted to validate the effectiveness, robustness, and energy efficiency of the proposed guidance strategy in comparison with other existing guidance strategies.