Abstract: The disclosure herein describes an aircraft assembly tracker system including a user interface configured to display an aircraft part under assembly and overlay one or more zones on the displayed part. The user interface operates on a computing device. The zones represent different panels to be affixed to the aircraft during assembly and their shape displayed on the user interface is identical to the shape of their corresponding panel being affixed to the physical aircraft part. The aircraft assembly tracker system monitors the assembly progress of each zone and automatically alerts aircraft assembly workers when the zone is ready for closure.

Abstract: The disclosure herein describes an aircraft assembly tracker system including a user interface configured to display an aircraft part under assembly and overlay one or more zones on the displayed part. The user interface operates on a computing device. The zones represent different panels to be affixed to the aircraft during assembly and their shape displayed on the user interface is identical to the shape of their corresponding panel being affixed to the physical aircraft part. The aircraft assembly tracker system monitors the assembly progress of each zone and automatically alerts aircraft assembly workers when the zone is ready for closure.

Abstract: A method of managing an electrical power supply outage on board an aircraft, including the following operations: —detection of an electrical power supply outage, —measurement of a duration of the power supply outage by measuring a discharge time of a capacitor and comparing this measured duration with a threshold duration, —saving a long outage indication when the duration of the outage is greater than a threshold duration. The disclosed embodiments also relates to a system implementing this method and including: —a circuit for detecting an electrical power supply outage, —a circuit for measuring a duration of the power supply outage, and—a circuit for managing indications able to manage emissions of signals according to the measured duration of the power supply outage.

Abstract: A device for controlling an electromechanical actuator includes an electric motor and an actuator operated by the electric motor. It also includes a digital signal processor (DSP) providing data of reference voltages (Ud—ffw, Uq—ffw) on the basis of an decoupled electrical model of the motor. The processor has at least one Park transformation module receiving measurement data for the currents of at least two supply phases of the motor (i_mot—2, i_mot—3) and a datum for the estimated angle of the motor (?estimated) and transforming them into data regarding the component of current with stator current axis (id) and the component of current in quadrature with the stator current (iq).

Abstract: A method of managing an electrical power supply outage on board an aircraft, including the following operations: —detection of an electrical power supply outage, —measurement of a duration of the power supply outage by measuring a discharge time of a capacitor and comparing this measured duration with a threshold duration, —saving a long outage indication when the duration of the outage is greater than a threshold duration. The disclosed embodiments also relates to a system implementing this method and including: —a circuit for detecting an electrical power supply outage, —a circuit for measuring a duration of the power supply outage, and—a circuit for managing indications able to manage emissions of signals according to the measured duration of the power supply outage.

Abstract: A device for controlling an electromechanical actuator includes an electric motor and an actuator operated by the electric motor. It also includes a digital signal processor (DSP) providing data of reference voltages (Ud—ffw, Uq—ffw) on the basis of an decoupled electrical model of the motors. The processor has at least one Park transformation module receiving measurement data for the currents of at least two supply phases of the motor (i_mot_2, i_mot_3) and a datum for the estimated angle of the motor (?estimated) and transforming them into data regarding the component of current with stator current axis (id) and the component of current in quadrature with the stator current (iq).