An Adaptive Velocity Pursuit Guidance Law Considering the Dynamics of Missile Autopilot

摘要

This paper presents an adaptive velocity pursuit guidance law considering the dynamic characteristics of the missile autopilot. The design model of the velocity pursuit guidance system in the pitch plane is firstly established, where the autopilot dynamics assumed to be of known structure but known parameters is explicitly considered. By adopting the dynamic surface control method, an adaptive nonlinear guidance law is further designed so that the missile can obtain high guidance accuracy. The stability analysis of the closed-loop system is also conducted by employing the Lyapunov theory. The numerical simulation confirms the usefulness of the proposed guidance law design scheme.