Development of a Fault Tolerant Control for Aircraft Electromechanical Actuators

There is a general trend in aerospace industry to increase the use of electrically powered equipment. This trend is usually referred to as “More Electric Aircraft” (MEA) or “Power-by-Wire”. Thus, new approaches to control system design have been developed in order to tolerate component malfunctions while maintaining desirable stability and performance properties. This paper gives an issue on integration of Fault Detection and Diagnosis (FDD) and accommodation scheme for Active Fault-Tolerant Control Systems (AFTCS). The Electromechanical Actuator (EMA) in aircraft will be studied in particular.