A Simple Differential Sliding Mode Design for the Overload Control of Missile System
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.
W. G. Zhang et al., "A Simple Differential Sliding Mode Design for the Overload Control of Missile System", Applied Mechanics and Materials, Vols. 66-68, pp. 207-211, 2011