Integrated guidance and control backstepping design of blended control missile based on adaptive fuzzy sliding mode control

An integrated guidance and control law is proposed for dual-control missiles based on the backstepping sliding mode design approach. A command filter is introduced to eliminate the computation explosion problem of conventional backstepping design method. An adaptive fuzzy approximator is employed to approximate the system uncertain functions, and a sliding mode surface is constructed to compensate the effects of approximate error and bounded disturbances. The controller parameters are adjusted adaptively on-line to guarantee the robustness of the system. A numerical example is provided. The simulation results show that the integrated guidance and control approach has robustness to disturbances and improves the control performance while ensuring the operating stability of system when a target maneuvers with high acceleration.