A device for verifying wiring connections during the assembly of a wire harness. The wire harness comprises a connector having an array of terminals and a plurality wires connected to individual ones of the terminals. The device comprises a transmitter for applying different signals to different terminals for emitting a corresponding electromagnetic signal from a wire connected to that terminal. Each electromagnetic signal has an associated identifying characteristic. A detector is used to receive the electromagnetic signals emitted from the wires connected to terminals, and a processor generates an output which is used to identify the received electromagnetic signals based on their detected identifying characteristics. A method of assembling a wire harness using the device is also disclosed.

The invention relates to a method (1) for monitoring a rotating machine (100) of an aircraft, wherein a measurement signal is acquired from the rotating machine. According to the invention, instantaneous frequencies (f.sub.K(t)) of sinusoidal components of the measurement signal are estimated, and, using a computing module (12), a plurality of successive iterations are carried out in each of which: complex envelopes of the components are updated (C1), parameters of a model of a noise of the signal are updated (C21) on the basis of the envelopes, whether the model has converged from the preceding iteration to the present iteration is tested (C4), with a view to: o if not, carrying out a new iteration, o if so, performing a computation (D) of the complex envelopes on the basis of the iterations that have been carried out.

A method for detecting an electrical arc in an electrical system including analyzing a reflectogram representative of a spatial distribution of impedance in said electrical system and, when an electric arc is identified in the reflectogram, incrementing a detection counter by one unit.

A power distribution system and method can include a controller and a set of power-using devices. Each power-using device in the set can include a sensor configured to measure a parameter and transmit a sensor signal representing the parameter to the controller, and the controller can respond to the transmitted sensor signal.

The present invention relates to an electronic test device for at least one avionic function to be tested, intended to be embedded in an aircraft, the aircraft comprising at least one avionic equipment item, the test device being intended to be connected to the at least one avionic equipment item and comprising: an acquisition module, configured to acquire flight data from the at least one avionic equipment item, and a computing module, configured to compute simulated output data, from acquired flight data and via an implementation of the avionic function to be tested, the avionic function to be tested being able, from the flight data, to deliver the output data.

In an aspect a system for energy tracking in an electric aircraft. A system includes at least a battery pack. At least a battery pack includes a plurality of battery modules. A system includes a sensing device. A sensing device is configured to detect a battery parameter of at least a battery module of a plurality of battery modules. A sensing device is configured to generate battery data as a function of a detected battery parameter of at least a battery module. A system includes a computing device. A computing device is in electronic communication with a sensing device. A computing device is configured to receive battery data from a sensing device. A computing device is configured to determine an energy amount of a plurality of battery packs as a function of battery data.

There is provided an aircraft engine printed circuit board assembly generally having a functional circuit contributing to the operation of an aircraft engine. The functional circuit has a first substrate portion, a first electronic component supported by the first substrate portion, and a first electrical conductor supported by the first substrate portion and leading to the first electronic component. The aircraft engine printed circuit board assembly generally has a monitoring circuit having a second substrate portion, a second electronic component supported by the second substrate portion, a second electrical conductor supported by the second substrate portion and leading to the second electronic component, the second electrical conductor having a shorter life expectancy than the first electrical conductor, and a detector monitoring an indicator of operativeness of the second electrical conductor, in which the first electrical conductor and the second electrical conductor are both exposed to the same environment.

A system includes three switches each having a single pole and dual throws. The respective single pole is on a supply side of the each respective switch. The dual throws are on a load side of each respective switch, and include a respective normally open (NO) throw and a respective normally closed (NC) throw. A first voltage detector is connected from the single pole of the first switch to the NC throw of the third switch. A second voltage detector is connected from the single pole of the second switch to the NC throw of the first switch. A third voltage detector is connected from the single pole of the third switch to a NC throw of the second switch.

A DC electrical network intended to supply electricity to an electrical load via an electric power source. A first pole of the electric power source is linked to first ends of two first electrical lines, second ends of which are linked to one another, and also to a first pole of the electrical load via two stages of a contactor. A second pole of the electric power source is linked to first ends of two second electrical lines, second ends of which are linked to one another, and also to a second pole of the electrical load via two other stages of the contactor. The electrical network further comprises a processing unit configured to control the contactor to open if current measurements correspond to currents flowing in opposite directions through the two first electrical lines or through the two second electrical lines.

A method, device, and system for detecting a current leak in a traction power rail. Magnetic or electrical properties of the rail are measured. The measurements are performed using a rail instrument that senses the properties around the rail at various times while the instrument is being moved down the rail, such as using a cart or train. The rail instrument may be a flux concentrator or open Rogowski coil. The locations of the rail, about which the readings are taken by the rail instrument, may be determined and correlated with the measurements themselves. The method may comprise measuring the magnetic field of the rail along a length of the rail, and identifying a leak based on differences between the magnetic field measurements. The system may comprise a cart comprising the rail instrument and a location instrument.