Abstract: A device for centering and guiding a shaft of an aircraft turbine engines. The device includes an outer ring of a rolling bearing, the ring extending about a main axis and having orifices arranged around the axis; an annular bearing support extending about the main axis and at least partially about the ring, the support having orifices and openings arranged about the axis; and a series of studs for linking the ring to the support, the studs being distributed about the main axis and having elongation axes substantially parallel to the main axis, the body of each of the studs passing through one of the openings. Some of the studs, have bodies that pass with a first positive clearance and a second virtually zero clearance through the first openings, the first and second clearances being configured so that the device has different displacement amplitudes.

Abstract: A device for centering and guiding a shaft of an aircraft turbine engine, the device including an outer ring of a rolling bearing, the ring extending about an axis; an annular bearing support extending about the axis and at least partially about the ring; at least one series of connecting elements for linking the ring to the support, the connecting elements being interposed between an inner cylindrical rim of the ring and an outer cylindrical rim of the support that extends about the inner rim, and each having a first radially outer end for linking to the outer cylindrical rim and a second radially inner end for linking to the inner cylindrical rim, the ring, the support and the connecting elements being integrally formed, the connecting elements being enclosed in an annular housing that is radially delimited by the rims and laterally enclosed by an annular web.

Abstract: A device for centering and guiding a shaft of an aircraft turbine engine is provided. The device includes an outer ring of a rolling bearing extending about an axis and having orifices, an annular bearing support extending about the axis and at least partially about the ring, the support having orifices and a series of studs for connecting the ring to the support. The studs can be distributed about the axis and extend parallel to the axis. The ends of first studs can be engaged without clearance in the orifices, and ends of second studs can be engaged with clearances in the orifices of the ring and/or of the support, the clearances being configured so that the device has different stiffnesses in at least two directions perpendicular to the axis.

Abstract: A turbomachine including a rotary body including a motor shaft supplying mechanical power, and at least one magnetic drive pump including at least: one stator delimiting an annular inner space and including a first and a second flange, a rotor arranged in the inner space between the first and second flanges and capable of driving fluid, the rotor being able to rotate about an axis of rotation, a pair of magnets having opposite polarities coaxially arranged on the rotor with the axis of rotation, a magnet arranged on the first flange in order to co-operate with one of the magnets of the pair of magnets of the rotor, a magnetic rotator for rotating the rotor arranged on the second flange, the second flange being non-magnetic.

Abstract: A drive arrangement for a vehicle, the drive arrangement comprising a rotatable interface arranged to be mounted to the vehicle, wherein the rotatable interface is rotatably coupled to a mounting arm to allow continuous rotation of the mounting arm in a clockwise and anti clockwise direction that is substantially perpendicular to the longitudinal and transverse axis of the vehicle; and a first electric motor having a stator and a rotor, wherein the stator is coupled to the mounting arm to allow the axis of the rotor to be substantially perpendicular to the rotational axis of the rotatable interface, wherein the rotor is arranged to be coupled to a wheel of the vehicle to allow the electric motor to provide drive torque to the wheel.

Abstract: The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).

Abstract: According to one aspect, a method includes identifying a first signal, which carries or otherwise includes data, to be provided to a system by a vehicle. The method includes determining a first amount of bandwidth, the first amount of bandwidth being associated with the signal, determining a second amount of bandwidth, the second amount of bandwidth being an available bandwidth associated with a plurality of modems included on the vehicle to enable the vehicle to communicate with the system, and dividing the first signal into a first plurality of portions based at least on the first amount of bandwidth and the second amount of bandwidth. The first plurality of portions is provided to the plurality of modems for transmission from the vehicle to the system, and is transmitted to the system using the plurality of modems and a plurality of channels associated with the plurality of modems.

Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.

Abstract: A drive arrangement for a vehicle, the drive arrangement comprising a rotatable interface arranged to be mounted to the vehicle, wherein the rotatable interface is rotatably coupled to a mounting arm to allow continuous rotation of the mounting arm in a clockwise and anti clockwise direction that is substantially perpendicular to the longitudinal and transverse axis of the vehicle; and a first electric motor having a stator and a rotor, wherein the stator is coupled to the mounting arm to allow the axis of the rotor to be substantially perpendicular to the rotational axis of the rotatable interface, wherein the rotor is arranged to be coupled to a wheel of the vehicle to allow the electric motor to provide drive torque to the wheel.

Abstract: A double wishbone suspension system for an in-wheel electric motor comprises an upper arm having a first end pivotally coupled to an upper portion of a motor mounting plate and two spaced apart second ends, the upper arm second ends are respectively coupled to first and second suspension mounting points; a lower arm having a first end pivotally coupled to a lower portion of the mounting plate and two spaced apart second ends, the lower arm second ends are respectively coupled to third and fourth suspension mounting points; a first coupling member having a first end pivotally coupled between the lower arm first second ends and a first coupling member second end is pivotally coupled to a second coupling element first end, wherein a second coupling member second end is pivotally coupled to the mounting plate between the first ends of the upper and lower arms.

Abstract: A system for aircraft maintenance is disclosed, such as for monitoring parts mounted in a turbojet engine, the turbojet engine being accommodated in a nacelle compartment delimited by a nacelle wall. The system can verify parts, each of the parts being equipped with an RFID tag. The verification system includes an inner antenna accommodated in the nacelle compartment, the inner antenna being arranged to allow the exchange of radio frequency signals with each RFID tag, an interface device including an access point located outside the nacelle compartment, the interface device being arranged to be able to be connected to an interrogator device arranged to communicate with the RFID tag, and a transmission line connecting the interface device to the inner antenna.

Abstract: The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).

Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.

Abstract: An event-recording circuit for recording electrical events experienced by an internal circuit in a semiconductor device is disclosed. The event-recording circuit is coupled to the internal circuit via a spark gap circuit. The spark gap circuit includes one or more encapsulated air-gap structures that are fabricated using a process flow that matches, or is adapted from, a process flow used in fabricating the semiconductor device. The event-recording circuit further includes a recording device that has an electrical property that is changed by a signal passed by the spark gap circuit, such as an ESD or EOS signal. Accordingly, a test may be performed to determine the presence, and in some cases the extent, of the change to the electrical property in a failure analysis of the semiconductor device.

Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.

Abstract: A propulsion assembly includes an engine surrounded by a nacelle, structure for draining the fluids from the engine and structure for guiding said fluids to a retention box. The retention box is arranged outside the engine and has a cavity for storing drained fluids. The retention box is fixed to a cowling of the nacelle and supported thereby.

Abstract: The present invention relates to an aircraft comprising a fuselage, a lateral support wing (1) and propulsion assembly (100) mounted under the wing, the wing comprising at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream, and the propulsion assembly comprising a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans (102, 104) are attached directly to one of the said spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (?) with the axis of the fuselage, the two offset fans (102, 104) are axially offset from one another.

Abstract: Pot with an undercut that includes a bottom wall (5), a side wall (6) that is closed on itself and connected to the bottom wall (5), with an opening providing access to the interior of the pot. The outside surface of the side wall of the pot has a non-symmetrical undercut shape for rotation around the vertical direction (Z). The outside surface has at least one vertical demolding plane (P) such that an undercut value of the pot with respective side ends of the pot, with a maximum side spacing of the outside surface in relation to the vertical demolding plane (P), is less than a maximum undercut value of the pot on the circumference of the outside surface of the pot.

Abstract: A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop.

Abstract: A propulsion assembly includes an engine surrounded by a nacelle, a means for draining the fluids from the engine and a means for guiding said fluids to a retention box. The retention box is arranged outside the engine and has a cavity for storing drained fluids. The retention box is fixed to a cowling of the nacelle and supported thereby.