An optimal, proportional-plus-integral/tracking control law for aircraft applications

An Optimal Proportional-plus-Integral/Tracking control law is formulated. The control law has a Command Augmentation System configuration suitable for implementation on a digital computer on-board an aircraft. The proposed configuration offers the flexibility for choosing a feedforward matrix incorporating a set of additional control elements and for shaping the transient response without affecting the steady state tracking property. Assuming the system is open loop stable, then in the presence of a "Jam" the disengaged system will maintain the steady state tracking property which is desirable for aircraft continuing their mission.