Decoupling of the longitudinal modes of advanced aircraft

In this study, the pitch and flight-path angle of a multimode aircraft have been independently controlled, via static state feedback, using the input-output decoupling with simultaneous arbitrary pole assignment technique. The satisfactory closed-loop performance is illustrated by simulation for an AFTI F-16 aircraft. However, the present technique basically differs from that of eigenstructure assignment on the starting point. Based on this difference several results have been obtained which enabled the desirable damping and settling time to be achieved.