An Improved Pseudo State Method for Aircraft Controller Design

This paper presents an improved method for compensator design in the aircraft control applications. A design technique introducing the pseudo state equation together with the enlarged system is discussed. This proposed method improves the redesign procedure when the compensator characteristics can not meet the required specifications. Theoretical basis of the proposed method is investigated, and algorithm is organized. To prove the effectiveness of the pseudo state method, an example of aircraft controller for ladning approach is discussed and tested. The simulation results show that the redesign efforts are reduced, and the characteristics of the designed compensators are improved.