Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream of the gas generator and configured to generate a main gas flow, of which one portion flows in a stream from the gas generator to form a primary flow, and of which another portion flows in a stream around the gas generator to form a secondary flow. The gas generator includes a low pressure body having a rotor driving the fan by means of a crown of a mechanical planetary reduction gear. The turbine engine further includes an electrical machine mounted coaxially around the reduction gear and having a rotor rotated by the crown of the reduction gear, and a stator extending around the rotor of the electrical machine.

Abstract: A starting/generating system for an aircraft turbine engine, the starting/generating system comprising at least one brushless drive motor/generator, at least one control module and at least one power module, the power module being configured to supply/receive electric power from the brushless drive motor/generator, the control module being connected to the brushless drive motor/generator by a control cable in order to control its operation, in which system the power module is configured to be mounted in the housing of the non-pressurized zone so as to be located adjacent to the brushless drive motor/generator and the control module is configured to be mounted in a pressurized zone of the aircraft, the control module being connected to the power module by a two-way communication cable in order to control its operation.

Abstract: A module for operating a carrier of one or more substrates to be treated in a vacuum deposition method includes a frame provided with a plate receiving, on a first side, an electronic assembly comprising radio transmitter/receiver electronics, a processor card, motor controller electronics and a battery for supplying power to the module. The processor card has a program memory with a program for controlling the motor controller electronics according to data received from a remote apparatus provided with a radio transmitting/receiving device for communicating with the module's radio transmitter/receiver electronics and, on a second side, a device for operating the carrier, which device is provided with a first motor for rotating the carrier about a first axis parallel to the plate and with a second motor for rotating the carrier about a second axis perpendicular to the plate.

Abstract: A turbine shaft of a turbomachine extending along a longitudinal axis (A) includes a main tubular portion with a length L1 and a maximum outer main diameter. The shaft further includes a secondary tubular segment with a length L2 and a maximum outer secondary diameter greater than the maximum outer main diameter. The secondary tubular segment extends radially from the shaft such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A). The secondary tubular segment includes a weak point that is configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, and thus cause retraction of the turbine.

Abstract: A device for measuring the mass flow rate, including a flow pipe; a first set of actuators which are arranged in a first plane including a first transverse cross section of the pipe and perpendicular to the fluid flow path, these being configured to move selectively in the first plane; a control circuit configured to control a movement of the first and second actuators so that the cross-sectional area for flow through the pipe in the first plane remains constant; a measurement sensor measuring a force or a stress in a direction perpendicular to the flow path, in the vicinity of the actuators of the first set along the flow path; a computation device configured to calculate the mass flow rate passing through the flow pipe as a function of the force or stress measured by the sensor.

Abstract: A bogey undercarriage having at least two axles, each carrying at least two wheels, wherein at least one of the axles carries a wheel fitted with a rotary drive device and no brake device, while the other wheels are provided with brake devices and no movement devices is provided. A braking method applied to such an undercarriage is also provided.

Abstract: A speed reducer, particularly of an aircraft, includes a central sun gear mounted to rotate with a drive shaft about a rotation axis X, an annular ring gear coaxial with the X axis, and a plurality of planet gears arranged about the X axis and mounted to be movable on a planet carrier. The planet gears engages the sun gear and the annular ring gear, which extends around the planet gears. The speed reducer further includes a lubricant recovery device having a pipe for recovering lubricant discharged from the reducer by centrifuging. The recovery device has scoops mounted to pivot about a pivot axis P on a movable member of the speed reducer that rotates about the X axis between a deployed state and a rest state.

Abstract: An aircraft turbine engine includes a turbine shaft having a first axis of rotation, a propulsion propeller having a second axis of rotation parallel to and spaced from the first axis, and a mechanical reduction gear coupled to the turbine shaft and rotating the propeller. The reduction gear has a sun gear connected to the turbine shaft, a ring gear, and at least two planet gears, each including a first external toothing that is meshed with an external toothing of the sun gear. A second external toothing is located within the ring gear and is meshed with an internal toothing of the ring gear.

Abstract: An electric circuit for measuring a current flowing in a conductor comprising: 2×N coils, N being an integer greater than or equal to 2, connected in series together; and a common mode filtering element associated with each of the 2×N coils, each filtering element being placed in parallel with the associated coil and being able to accomplish common mode filtering of the 2×N coils, a core of the 2×N coils having a relative permeability less than 10, and among the 2×N coils, N coils being wound in a direction opposite to the winding direction of the N other coils.

Abstract: A method for the non-destructive inspection of an aeronautical component having a step of obtaining a plurality of digital images of a unit area of the aeronautical component, a step of estimating a characteristic image representative of the unit area, each pixel of the characteristic image having a characteristic vector, a step of dividing the characteristic image into a plurality of micro prediction zones, a step of comparing the characteristic vector of each pixel in each micro prediction zone with a previously estimated local statistical model of the micro prediction zone, the local model of a micro prediction zone being obtained by means of a learning algorithm from characteristic vectors of pixels in a micro learning zone of the annotated characteristic image which includes the micro prediction zone.

Abstract: Electrical circuit for measuring a current flowing in a conductor comprising: a first pair of Rogowski-type coils connected in series, the Rogowski-type coils of the first pair being able to operate in a first frequency band; a second pair of Rogowski-type coils connected in series, the Rogowski-type coils of the second pair being able to operate in a second frequency band, the second frequency band comprising at least partly frequencies higher than the frequencies of the first frequency band; and a means for electrically shielding the first pair of coils, and wherein a core of the Rogowski-type coils of the first and second pairs has a relative permeability of less than 10 and wherein one coil of each pair comprises at least one multi-turn winding, the other coil of the pair comprising at least one multi-turn winding.

Abstract: A turbomachine part or assembly of parts includes a first blade and a second blade, and platform from which the first blade and the second blade extend, The platform has, between a pressure side of the first blade and a suction side of the second blade a non-axisymmetric surface defining at least one fin, and a transverse section of the fin is asymmetric. The transverse section includes a first and a second oblique faces joining at a dorsal edge, the first oblique face is oriented toward the pressure side of the first blade, the second oblique face is oriented toward the suction side of the second blade, and the first oblique face has a steeper slope than the second oblique face.

Abstract: The invention relates to a method for controlling an aircraft taxi system, comprising the steps of: generating a traction command (Com) to control an electric motor of a wheel drive actuator; detecting whether or not an external brake command, intended to control braking of the wheel via the brake, is generated; if an external braking command is generated, producing a predetermined minimum command (Cmp) to control the electric motor so that the drive actuator applies a strictly positive predetermined minimum motor torque to the wheel during braking; detecting whether a speed of the aircraft becomes zero and, if so, inhibiting the predetermined minimum command (Cmp) so that the drive actuator applies zero torque to the wheel.

Abstract: The invention relates to a housing (30) for managing access to an industrial network (10), to which industrial equipment (U1, U2, U3) is connected, the management housing (30) comprising: —a channel (30a) for access to an internet-type data network, said channel (30a) for access to the data network comprising a cut-off unit (33); —a channel (30b) for controlling the channel (30a) for access to the data network, said control channel (30a) comprising a controller (31) configured to control the cut-off unit (33) so as to allow communication between the industrial network and the data network, the cut-off unit comprising a cut-off relay that can be activated by means of a control signal emitted by the controller (31).

Abstract: A device for unlocking a system for closing a container by means of a tie, such as a rope or strap, in particular a tie tensioned between closing eyelets, includes a cutting tool (O) capable of cutting the tie in order to unlock the closing system. It also includes an actuation member linked to the cutting tool, the actuation member being capable of being manipulated manually by a user in order to cause the cutting tool (O) to move into a position for severing the tie.

Abstract: A method for monitoring an aircraft turboshaft engine including a vibration sensor capable of outputting a vibration signal and a spark plug. The method includes, based on the vibration signal output by the vibration sensor, a step of determining a level of vibration of the turboshaft engine as well as a step of determining an indicator of spark plug wear.

Abstract: A composite part (sandwich or monolithic), including a rigid outer surface, to which is integrated an electronic instrumentation circuit, the electronic instrumentation circuit including a piezoelectric transducer, connected to a coil, an electronic control circuit, connected to a coil positioned facing the coil. The coil is printed on an insulating layer, printed directly on the rigid outer surface, the coil is printed on an insulating layer, covering the coil and the transducer, conducting tracks are printed on an insulating layer printed on at least one portion of the coil to be connected to it, the electronic control circuit being attached to the rigid outer surface and being connected to the tracks.

Abstract: A method for controlling the clearance between the blade tips of a high-pressure turbine of a gas turbine aircraft engine and a turbine shroud, including the controlling of a valve delivering a stream of air to the turbine shroud, this method further including the following steps: the detection of a transient acceleration phase of the engine; the receiving of an item of data representative of the gas temperature at the outlet of the combustion chamber of the engine; a valve opening command, to deliver the air stream to the turbine shroud or to increase the flow rate of the delivered air stream, if the transient acceleration phase is detected and if the gas temperature at the outlet of the combustion chamber is greater than a first temperature threshold corresponding to a degraded clearance characteristic of an aged engine, this threshold being less than an operating limit temperature of the engine.

Abstract: A turbomachine blade including a body that extends mainly in a plane defined by a main axis and a longitudinal direction, which is defined by a lower surface wall, an upper surface wall, a leading edge located at a first longitudinal end of the body and a trailing edge located at a second longitudinal end of the body, wherein the body of the blade includes a plurality of first pipes that extend mainly along the direction of the main axis, for circulation of a gas flow, and a plurality of second pipes that extend mainly along the longitudinal direction, for circulation of a second gas flow.

Abstract: A method for processing flight data having been recorded during three or more flights of an aircraft by a flight data recorder including obtaining two signature vectors with respective sizes, the two signature vectors corresponding to two different flights among the three or more flights, determining a similarity matrix, the components of which quantify the proximity between the two flight signature vectors, each component allowing identifying, for each element of a first signature, an element of the other signature which is closest, the proximity between two components of the signature vectors being a distance weighted by a mean value of the neighboring components of the similarity matrix, repeating the obtaining and determining in order to compare, two by two, all the flight signatures so as to obtain three or more similarity matrices, and processing said similarity matrices in order to evaluate the similarity between two flights.