Improved pseudo state method for aircraft controller design

An improved method for compensator design in aircraft control applications is presented. A design technique using a pseudo-state equation together with an enlarged system is discussed. This method improves the redesign procedure when the compensator characteristics cannot meet the required specifications. The theoretical basis of the proposed method is investigated, and an algorithm is developed. To prove the effectiveness of the pseudo-state method, an example of an aircraft controller for landing approach is discussed and tested. The simulation results show that the redesign efforts are reduced, and the characteristics of the designed compensators are improved.