Missile guidance law design based on free-time convergent error dynamics

TL;DR

This paper introduces a novel guidance law design method using free-time convergent error dynamics, allowing flexible convergence time independent of initial conditions, with applications to missile guidance constraints.

Contribution

It proposes a unified approach for guidance law design based on free-time convergent error dynamics, enabling adjustable convergence time and handling multiple guidance constraints.

Findings

Guidance laws with free-time convergence are derived for various constraints.

The proposed method's effectiveness is validated through simulation comparisons.

The approach offers theoretical insights into differences from existing guidance laws.

Abstract

The design of guidance law can be considered a kind of finite-time error-tracking problem. A unified free-time convergent guidance law design approach based on the error dynamics and the free-time convergence method is proposed in this paper. Firstly, the desired free-time convergent error dynamics approach is proposed, and its convergent time can be set freely, which is independent of the initial states and the guidance parameters. Then, the illustrative guidance laws considering the leading angle constraint, impact angle constraint, and impact time constraint are derived based on the proposed free-time convergent error dynamics respectively. The connection and distinction between the proposed and the existing guidance laws are analyzed theoretically. Finally, the performance of the proposed guidance laws is verified by simulation comparison.