Aerodynamic force and lateral thrust blended control for hypersonic missile using fuzzy control algorithm

For the air-breathing hypersonic missile with low overload in cruise phase due to angle of attack restriction, an aerodynamic force and lateral thrust blended control autopilot is designed, which based on fuzzy control theory. The non-linear system model in the longitudinal plane 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. In view of the model uncertainties and atmospheric environment disturbances, the adaptive sliding mode control approach is proposed for aerodynamic subsystem. And a two-dimension fuzzy controller is designed for direct force subsystem to reduce the dependence of the accurate model. Simulation results show that the proposed blended controller can overcome the effects of disturbances, and improve the delay effect by reason of weak aerodynamic to realize satisfying tracking performance. The maneuverability of this dual controlled hypersonic missile, with blended aero-fin and divert-control lateral jets, is enhanced obviously in cruise phase, while the angle of attack changing in permissible range.