Stable inversion for exact and stable tracking controllers: a flight control example

Output tracking for missile flight control is challenging due to the nonminimum phase problem. Among existing methods for output tracking, the regulation approach usually leads to large transient errors and the dynamic inversion approach results in unbounded internal dynamics for nonminimum phase systems. By using a stable inversion approach, this paper presents a new missile autopilot controller that achieves an exact and stable output tracking without any transient or steady state errors and internal vibration.