Patent ID: 8604741

Claim:
A monitoring and control device for an aircraft actuator, comprising: a control module, delivering control signals for the actuator and position signals for the actuator respectively determined according to control messages received from a piloting management system of the aircraft, and at least one first position sensor supplying information concerning a position of the actuator, a monitoring module, delivering actuator position signals and simultaneously receiving the control messages received from the piloting management system of the aircraft, and information relating to the position of the actuator supplied by at least one second position sensor, said control and monitoring modules being capable of assessing a consistency of the signals processed therein and of controlling accordingly an actuator power supply and a disabling module, the actuator being moved by a brushless electric motor, the first position sensor being a Hall-effect type sensor supplying information concerning a rotational positioning of a rotor of the motor, the position of the actuator being determined by the control module based on an initial position datum supplied by the monitoring module, the control module comprising a first simulation module receiving the control messages received from the piloting management system of the aircraft, and simulating a behavior of the actuator and generating a first actuator virtual position signal.