A Simple Differential Sliding Mode Design for the Overload Control of Missile System

Abstract

A simple differential sliding mode control law was designed for the missile overload control system without considering the uncertainties of air-dynamic coefficients. The sliding mode was composed of overload error and the differential error of overload. Finally, a numerical simulation was down and it testified that it is unable to make the system stable with only pure overload control strategy. Although the sliding mode was arrived , Oscillation phenomenon was caused by the poles in imaginary axis.