Research on the stability of overload-control for aerodynamic missiles

The overload-control approach was developed and applied to aerodynamic missiles in order to solve the problem of nonminimum phase of the acceleration control. It controlled the overload and the angle acceleration, but it didn´t control the attitude variables in order to acquire high maneuverability. Sliding mode control (SMC) was adopted in this approach to design a control law of the fin deflection. The control law realized an integrative control of the overload and the angle acceleration. Stability analysis for the overload-control system was provided considering the uncertainties of aerodynamic coefficients. The analysis shows that the attitude variables of aerodynamic missiles are asymptotically stable. The validity of the overload-control is demonstrated by numerical simulation.