Design of a Pitch Orientation Control System for Aircraft Control in Stall Region

This paper discusses a situation where a pole as well as a zero of Aircraft-short period T.F. is likely to move to R.H. s plane. The conventional pitch orientation control system would then be inadequate to provide stable control. A modification to the system is suggested in the form of dynamic compensators in the feedforward and feedback paths. Design approach to decide the coefficients of the compensators is given. It is shown that by scheduling just one of the 8 coefficients it may be possible to provide stable control when the pole-zero combination is laying in the L.H. plane as well as when the combination is laying in the R.H. s plane.