Fuzzy control strategy for hypersonic missile autopilot with blended aero-fin and lateral thrust

Abstract

An aerodynamic force and lateral thrust blended control autopilot is designed for the near-space air-breathing hypersonic missile with low overload cruise phase due to angle of attack restriction. The nonlinear longitudinal short-period motion model of a hypersonic missile is built, and several fuzzy control strategies are applied in overload command allocation, so as to decouple the aerodynamic and direct force subsystems. The adaptive sliding mode control approach is proposed for aerodynamic subsystem to handle the model uncertainties and atmospheric environment disturbances. A two-dimensional fuzzy controller is designed for direct force subsystem to reduce the dependence of the accurate model. The simulations show that the proposed blended controller can overcome the effects of disturbances and improve the delay effect by reason of weak aerodynamic to realize satisfied tracking performance. The simulations are also given to illustrate the validity of the blended control law in long period. The results show that the blended controller can achieve a good tracking performance throughout the cruise phase. The maneuverability of this dual-controlled hypersonic missile, with blended aero-fin and divert-control lateral jets, is enhanced obviously in cruise phase.