Abstract: An electrical contactor that includes separable contacts that include a first pair of mating contacts and a second pair of mating contacts. The electrical contactor also includes a first portion that includes the first pair of mating contacts and a solenoid plunger that is configured to receive a plunger rod; The electrical contactor additionally includes a second portion that includes the second pair of mating contacts. The plunger rod is configured to be inserted within the solenoid plunger and rotated towards the second portion to be threaded into the second portion to enable the second portion to be pulled up towards the first portion. The second pair of mating contacts are configured to move closer to the first pair of mating contacts until the second pair of mating contacts mate with the first pair of mating contacts to increase a wear allowance to a predetermined desired level.

Abstract: The invention relates to an electronic circuit (1) comprising a plurality of printed circuits (2) connected by at least one bus bar (4), each printed circuit (2) comprising at least two superposed layers enclosing at least a portion of said at least one bus bar (4), so as to cover said at least one bus bar (4).

Abstract: A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tube of a second individual module and the gas inlet opening of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.

Abstract: A system REG for regulating a physical parameter of a real turbomachine system F(p) from a physical setpoint parameter, the regulation system REG comprising a system OPTK for optimising the parameterisation gain K during the regulation, the optimisation system OPTK comprising a stability correction module determining a first gain component K1, a response time correction module determining a second gain component K2, the stability correction module being designed to inhibit the response time correction module when an instability is detected during the regulation of the physical parameter, and a determination module configured to determine the parameterisation gain K as a function of the previously determined first gain component K1 and second gain component K2.

Abstract: An aircraft thruster includes at least a first propeller provided with a plurality of radial blades extending about an axis of rotation of the said first propeller, which is driven in rotation by a first electric motor. An electrical supply of the first electric motor includes power circuits carried by a fairing of the thruster characterized in that the power circuits are arranged in an annular manner in an annular part integral with the fairing of the thruster, this annular part being arranged around the said first propeller.

Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.

Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.

Abstract: The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23?) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.

Abstract: A three-phase autotransformer including three output groups and three inputs each connected to each of the outputs of a respective output group by windings, the windings being configured so that, when each input has a respective input voltage applied thereto, the three input voltages having the same input amplitude, being 120° out of phase with each other and defining a neutral point: for each output group, a main output voltage, taken between a main output of said output group and the neutral point, has an amplitude greater than the input amplitude; and output voltages of the autotransformer belong to a same Reuleaux polygon, each output voltage being associated with a respective output and being equal to a voltage between said output and the neutral point.

Abstract: A liquid fuel supply system for an aircraft engine includes a fuel tank, a suction duct connected to the fuel tank and located higher than the fuel tank, an electric pump, a supply pump that is mechanically driven by an accessory gear box and an outlet of the supply pump being connected to a fuel supply circuit of the engine, and an air expulsion drain. The electric pump is in communication with the suction duct independently of the supply pump, the electric pump is in communication with the air expulsion drain, and the supply pump is in communication with the suction duct independently of the electric pump.

Abstract: An aircraft passenger suite is provided. The suite comprises an aircraft seat for use by a passenger. The suite also comprises a controller for controlling a number of output states of the suite, the controller comprising a logic condition receiver operable to receive a logic condition input. The suite also comprises sensor equipment operable to provide a sensor input to the controller, the sensor input providing an indication of at least one attribute of a passenger of the suite. The sensor equipment comprises one or more of: an image sensor a pressure sensor and a physiological sensor. The controller is configured to control at least one of the output states of the suite based on both the logic condition input and the sensor input.

Abstract: A method for correcting the radial moment weight of a vane includes the step of providing a vane extending along an axis of elongation (Z) between a free end and an opposite root, the vane having a blade made of composite material and having a leading edge. The method further includes the steps of measuring the radial moment weight of the vane and comparing the measured radial moment weight to a reference value and adjusting the radial moment weight of the vane according to the result of the comparison. The vane has at least one adjustment cavity extending along the leading edge and opening into the free end of the vane. The adjustment is carried out by inserting a first material into the adjustment cavity.

Abstract: A component for an acid electrolyte fuel cell or electrolyser provided with an anticorrosion coating, as well as such an acid electrolyte fuel cell or electrolyser, the component including an electrically conductive substrate, and an anticorrosion coating deposited on at least one surface of the substrate, the anticorrosion coating including at least one main tantalum-nitride-based layer doped with one or more dopant elements chosen from the family of the transition metals or lanthanides.

Abstract: An integrated unit for de-icing the propeller blades and the nose of a turbomachine including: a rotary transformer including a static part and a rotary part; a DC-to-AC voltage converter connected at its output to the static part of the rotary transformer and intended to be connected at its input to a DC electrical power supply, and a power switch connected to the rotary transformer and configured to transmit electrical power to at least one pair of propeller blades and to the nose cone of the turbomachine.

Abstract: This method for managing devices installed in a nacelle of a turbine engine, the devices being provided with radio tags and the turbine engine being fitted with a radio frequency identification reader and with at least two time reversal antennae, comprises the following steps: mapping the electromagnetic field inside the closed nacelle matching the known position of the devices with the electromagnetic characteristics of their respective radio tags carrying out an inventory by time reversal focusing of waves.

Abstract: Method for braking an aircraft turbine engine including a fan or a propeller connected to a turbine by a shaft and an electric generator connected to the shaft, the method comprising the following steps: a request to brake the turbine engine by thrust reversal; a calculation of a turbine braking setpoint by a control system; and in response to the braking setpoint, an adjustment by the control system of a resistance of a dissipative load to draw electric power from the electric generator to the dissipative load.

Abstract: A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.

Abstract: A method of assembling together a first part and at least one second part that are made of materials compatible with bonding by molecular adhesion includes a step of pressing a first surface of the first part against a second surface of the second part so as to create molecular bonds at an interface between the parts, and a step of consolidating the interface bonding as created in this way by heat treatment. The consolidation includes a step of emitting a power laser beam towards an impact point forming a portion of the outline of the interface, and a step of moving the impact point along the outline of the interface.

Abstract: Described are energy absorbing assemblies for a passenger seat. The energy absorbing assemblies can include one or more auxetic energy absorbing elements (130), each element including a crushable matrix formed of cells having an auxetic cell geometry that are crushable in a direction of energy capture.

Abstract: A thrust reverser for a propulsion unit, incudes movable grids, two half-assemblies forming part of a secondary stream and, at the six o'clock position, a connecting beam intended to be mounted in cantilever with a fan housing. The half-assemblies are hinged at the twelve o'clock position so as to enable their “butterfly” movement between a flight configuration and a maintenance configuration. The connecting beam includes a connecting member configured to cooperate, in the form of a tenon and groove connection, with the half-assemblies when these are in flight configuration. The reverser also includes, downstream of the connecting member, locks capable of locking the half-assemblies in flight configuration.