Abstract: A method for managing the propulsive power of an aircraft, the aircraft extending longitudinally along an axis X from the rear forwards and comprising at least two lateral propulsion systems each comprising a fan, each lateral propulsion system having a fan rotation speed N2 and at least one rear propulsion system configured to ingest a boundary layer of said aircraft, the rear propulsion system comprising a fan having a fan rotation speed N3, the management system comprising, during a cruising phase P4, a step of adjusting the rotation speed N3 of the rear propulsion system according to the following formula N3=a*N2 in which a is a constant.

Abstract: An air intake includes a substantially cylindrical inner wall, a substantially cylindrical outer wall, a front lip connecting the inner wall and the outer wall, a front mounting flange, and a support structure. The front mounting flange is configured to cooperate with a rear flange of a wall of an aircraft engine. The support structure is configured to be secured to the wall of the aircraft engine at a location longitudinally downstream of the mounting flange. The outer wall includes a downstream end configured to be positioned in a junction area flush with a front end of a fan external cowl. A portion of the outer wall being configured to bear at least against the support structure. The support structure is configured to be secured to the wall of the aircraft engine so that a load path passes directly from the outer wall towards the fan casing.

Abstract: An aircraft turbomachine module having two tubular casings equipped with first and second annular flanges assembled by studs received in the first flange and receiving nuts on the back of the second flange, each stud having an intermediate stretch of hexagonal shape cooperating with a locking plate. The locking plate can have a first orifice received on the intermediate stretch by at least two opposite walls, and a transverse body which is immobilized to prevent the rotation of the plate and that of the stud. Each plate can be fitted on two immediately adjacent studs and the body can have, for this purpose, a second orifice opposite the first orifice and which is received on an intermediate stretch of an immediately adjacent stud and cooperates with the intermediate stretch of hexagonal shape of the stud.

Abstract: A blade comprising a blade body made of fiber-reinforced organic-matrix composite material and a leading edge shield made of a material having a better resistance to point impacts than the composite material of the blade body, the leading edge shield being assembled on the blade body and including a pressure side fin and an suction side fin connected by a thicker central part, the blade including an aerodynamic airfoil height and a chord length, the suction side fin having a first length projected onto the chord between 10 and 18% of the chord length, the first length being disposed between 70 and 80% of the aerodynamic airfoil height, a second length projected onto the chord between 18 and 26% of the chord length, the second length being disposed between 85 and 95% of the aerodynamic airfoil height.

Abstract: A fuse pin valve includes a housing, a piston, and a mechanical fuse, such as a fuse pin. As assembled, the piston is movably disposed in the housing and is retained in a static position by the fuse pin. Upon a certain pressure (e.g., an abnormal pressure) acting on the piston, the fuse pin fails, thereby releasing the piston to move from a first or start position to second or end position. In the start position of the piston, the valve is in a first operational state (e.g., a closed state). In the end position of the piston, the valve is in a second operational state (e.g., an open state, fully open states, etc.). In other embodiments, in the start position of the piston the valve is in an open state, and in the end position of the piston the valve is in a closed state.

Abstract: The present invention relates to a blade (3) of a fan (1), made of composite material, of a turbomachine. On a portion (15) of the blade (7) which extends from a lower limit (16) located at a predetermined distance (d) from the shank (6) of the blade equal to at least 80% of the predetermined height (h) to the top (11) of the blade (7), a dihedral angle (D) measured at at least one predefined point on the chord of the blade (3), located on the chord of the blade (3) at the upstream end (13a) of the nose (13) of the shield (12), is greater than or equal to ?3° and less than or equal to 0°.

Abstract: Systems and methods are described herein for providing content recommendations to a user based on an elapsed playback time of the current content on the user device. A recommendation server having memory and a processor can be used to compare an elapsed playback time of the current content and compare the elapsed playback time with one or more threshold values. If the elapsed playback time is less than a first threshold, anticorrelated content with respect to the current content can be recommended and presented on or using the user device.

Abstract: The invention relates to a device (D) for detecting a fault in an electrical network (1), comprising at least one electrical equipment (E) which is electrically connected to a first power conductor (C1) and to a second power conductor (C2), the electrical network (1) being provided with a common conductor (Cc). The device comprises a first measuring member (O1) of the common mode voltage present on the power conductors (C1, C2) and a second measuring member (O2) of a current flowing in the power conductors (C1, C2). The device also comprises a calculator (UP) configured to determine over a determined observation period a mixed energy (Emix) transported in the measurement region from the first variable (Vres) and the second variable (Inet). The invention also relates to an equipment, a localization system and a method for detecting a fault in an electrical network.

Abstract: Method for generating an OFDM training sequence, device and computer program product. The OFDM training sequence consists of at least two OFDM symbols, and the OFDM training sequence comprises at least two OFDM sub-carriers, the method comprising a step of partitioning the OFDM sub-carriers into at least two separate groups comprising at least one sub-carrier, a number of groups being smaller than a number of sub-carriers. The method comprises steps, carried out independently for each group, of generating an elementary sequence associated with a group by combining the sub-carriers of the group, the elementary sequence having a duration equal to a duration of one of the at least two symbols.

Abstract: A method detects and localizes a failure of a measurement acquisition channel in an acquisition system including two redundant acquisition channels for the measurement of a physical quantity in an environment. The method uses a processor with a memory storing a model including modeled values of the physical quantity based on measurements of other physical quantities in the environment. The method includes detecting a symptomatic error of a defective acquisition channel when a deviation between the measured values of the two channels reaches a detection threshold, waiting to let the acquisition system evolve for a certain period, and localizing the defective channel among the two channels, when the deviation of the values measured between the channels reaches a localization threshold different from the detection threshold. The localization is made from the comparison of the measured value of each of the channels with a modeled value of the physical quantity.

Abstract: A casting slurry for the manufacture of shell molds, including powder particles and a binder, further including a surfactant. Use of such a casting slurry for the manufacture of a shell mold.

Abstract: A method of assembling a member and a cap of a vane using a tool which allows the application of a pressing force of the cap against the member during a step of polymerisation by heating a resin for bonding these components. To this end, the tool includes an inflatable bladder and a pocket which surrounds the bladder and the vane so that the inflated bladder applies the pressing force. The heating can be carried out by resistors which are mounted in the bladder and/or using a device for supplying external heat.

Abstract: A configuration system (80) arranged to configure an aircraft in a single-pilot mode and a two-pilot mode, comprising: acquisition means (84) and authentication means (83) arranged to acquire and authenticate a configuration order that defines the selected mode and controls the configuration system (80) to configure the aircraft in the selected mode; first activation means (85) arranged to activate equipment dedicated to piloting by a single-pilot on board when the aircraft is configured in single-pilot mode, and to deactivate dedicated equipment when the aircraft is configured in two-pilot mode; verification means (87) arranged to, when the aircraft is configured in the single-pilot mode, verify that single-pilot flight conditions are met and inform the sole pilot on board and a ground station of the results of these checks.

Abstract: A gear element includes a support (3) on which first rollers (10a) and second rollers (10b), which are intended for engaging with the teeth of a neighboring gear element (2), are alternately mounted. Each roller (10a, 10b) is mounted for rotation about its longitudinal axis (X?) via rotary guide means (20) cooperating with end portions of the rollers (10a, 10b). The rotary guide means (20) of the first rollers (10a) and the rotary guide means (20) of the second rollers (10b) are staggered in the vicinity of an outer periphery of the support (3).

Abstract: Aircraft landing gears include at least one wheel, an electric taxiing system including an electric taxiing motor, brakes capable of slowing down or stopping the rotation of the wheel, and a cooling system for cooling the electric taxiing motor and the brakes. The cooling system includes ventilation means capable of mixing a first air flow originating from the brakes and a second air flow originating from outside the landing gear and of ventilating the electric taxiing motor with a mixture of the two air flows.

Abstract: The invention relates to a motorizing device (1) for moving an aircraft (A) provided with a landing device (L) having wheels (W) on the ground, the motorizing device comprising at least one electric motor (2) having an output shaft provided with means for its rotational connection to at least one of the wheels (W) of the landing device for driving said wheel in rotation, and an electronic control unit (3) connected on the one hand to the motor to control it and on the other hand to a control interface (4) from which the aircraft pilot can transmit control signals which the electronic control unit (3) is arranged to transform into motor control signals, characterized in that the control unit is arranged to implement a first control law having determined dynamics to promote an aircraft movement speed and a second control law having dynamics to promote aircraft manoeuvrability.

Abstract: A weaving installation includes a loom that receives a series of strands, and at least one device for measuring the diameter of a strand having a defined number of filaments. The device includes a diaphragm having an external ring forming a support on which a series of strips forming an iris are fixed. The strips are movable and allow a substantially circular space with variable dimensions to be defined at the center of the iris. The diaphragm is configured to adjust the dimensions of the space so as to allow a strand of the loom to pass through it, and to encircle the profile of the strand so as to allow the number of filaments in the strand to be determined.

Abstract: An assembly of a device for three-dimensional printing by metal deposition comprising a conduit for guiding a metal wire and opening inside an enclosure under an inert atmosphere. The device has means for injecting an inert gas into the conduit of the head.

Abstract: A cell storage box for storing a battery cell includes a first end provided with a safety valve and a second end. The cell storage box includes a metal case having a bottom wall and side walls, and a thermally insulating support arranged in the metal case. The thermally insulating support includes a shoulder raised relative to the bottom wall of the metal case, a side bearing wall configured such that the cell rests against the at least one side bearing wall so as to keep the cell at a first distance from the at least one side wall of the metal case, and an opening arranged below the shoulder in order to allow smoke and gas to escape during a runaway of the cell.

Abstract: A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.