Abstract: Aircraft comprising a primary propeller driven in rotation by a motor, the motor having a first assembly and a second assembly movable in rotation relative to each other along an axis of rotation, the primary propeller being secured in rotation to one of said first assembly and second assembly, the first assembly and the second assembly being movable in translation relative to each other along a direction of translation defined by the axis of rotation, between a rest position and a service position, characterized in that said aircraft comprises a locking system, comprising a housing and an indexing element, the housing being formed in one among the first assembly and the second assembly, the indexing element being secured to the other among the first assembly and the second assembly, the locking system having an engaged configuration in which the indexing element is at least partially inserted into the housing.

Abstract: Embodiments of the disclosure relate to a power electronics apparatus. The power electronics apparatus includes at least a first electrically conductive element and a second electrically conductive element. The elements are intended to be at a first electrical potential and at a second electrical potential, respectively. At least a first and second power electronics components are mounted on the first and second elements, respectively, a first portion and a second portion of a sink are mounted on the first conductive element and on the second conductive element, respectively, so as to permit the transfer of heat from each power component to the corresponding portion of the sink through the corresponding conductive element. An electrical insulator is present between each portion of the sink so as to prevent the risk of flashover between the two portions.

Abstract: Methods for determining an operating state of a battery with respect to one or more use profiles include: a step of prior learning during which operational limits of the battery are defined depending on parameters of the battery; the operational limits defining an operational zone in which the battery carries out the one or more use profiles, and a non-operational zone in which the battery does not carry out the one or more use profiles; a step of determining the operating state of the battery for a given use profile in the course of which the parameters of the battery in operation are determined; and a comparison step in which the operational limits and the parameters of the battery are compared and the battery is positioned in the operational or non-operational zone.

Abstract: A sensor is configured to sense the rate of change of a current in order to protect the bridge arms in a power module with power layers and measurement layers. The sensor includes at least three conductors (C1, C2, Cp) and coils. One end of each conductor is connected to a common node, while the other end of each conductor is used respectively as an electrical terminal. The at least three conductors are contained in the same plane, referred to as the primary plane, while each conductor has a plane of symmetry perpendicular to the primary plane, each plane of symmetry passing through the common node and the corresponding terminal. A first conductor and a second conductor are identical and positioned symmetrically relative to a third conductor, and at least one pair of coils is positioned symmetrically relative to a plane of symmetry.

Abstract: The present invention relates to a rotor of an electric machine for use in an aircraft. By forming the shaft of the rotor such that it performs, at least partially, the function of the back iron, components of the rotor can be combined. Further, by forming the rotor components in this manner, an internal shaft with an increased diameter can be used to provide a rotor with greater stiffness than equivalent prior art devices.

Abstract: An electrical filtering system including capacitors and an electrical distribution device including a stack of two electrically conducting layers facing one another and separated by an insulating layer, the stack being mounted on a rigid insulating plate, and said capacitors being mounted on said distribution device, the rigid plate extending in a plane orthogonal to the direction in which the layers are stacked. The distribution device includes a plurality of electrical connections distributed angularly over the outer perimeter of the distribution device and protruding in a plane parallel to the plane in which the rigid plate extends, and extending from the outer perimeter of the distribution device, each of the connections being, on the one hand, connected to at least one capacitor and, on the other hand, intended to be connected to an arm of an electrical inverter mounted on a tubular electrical converter of an electronic control unit.

Abstract: The invention relates to a method for detecting and locating a fault by reflectometry in an electrical circuit, such a method comprising the steps of: —emitting a reflectometry signal in a line of the circuit to be studied; —acquiring an electrical variable of the reflected signal passing through the network; —filtering the acquired signal so as to eliminate signals having a frequency lower than a cutoff frequency, the cutoff frequency having a value between 100 kHz and 1 GHz; —analysing an acquired signal so as to detect a fault.

Abstract: A protection device for an electrical cabinet is divided into a plurality of compartments, the protection device including a rain guard and an air manifold formed as an integral unit. The rain guard is designed to cover a section of an electrical cabinet and thus prevent water from falling on it. The air manifold includes at least one first pipe fluidically connected to a second pipe. Each first pipe intended to be connected to a corresponding air-circulation opening of a compartment, and the second pipe being intended to be connected to an air-circulation means in order thus to allow air to be circulated in the plurality of compartments. A cabinet is provided with such a protection device.

Abstract: Current sensor comprising: one pair, of identical electrical coils with superparamagnetic cores and surrounded by a common shielding braid; a direct current excitation means configured to make a direct current flow in at least one of the coils of the pair of coils and a means of adjusting an intensity of the direct current; a first alternating current excitation means configured to make an alternating current flow at a first frequency in the coils of the pair that the direct current flows through; a second alternating current excitation means configured to make an alternating current flow at a second frequency greater than the first frequency in the two coils of the pair of coils; a means of measuring an electromotive force of the Noel Effect® type at the terminals of the two coils of the pair.

Abstract: Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: —an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and— an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

Abstract: The invention relates to a system for sychronising energy sources coupled to an electrical grid supplying at least one electrical load of an aircraft, said system comprising: a main source of electrical energy supplying said electrical load comprising a multi-stage generator, said multi-stage generator comprising: a primary stage comprising a generator with permanent magnets, a secondary stage comprising an excitation, and a tertiary stage comprising a main generator; an auxiliary source of electrical energy supplying said electrical load; and a device for synchronising the main source and the auxiliary source, designed to measure an electrical voltage at the outlet of the primary stage of the main source, and to control the supply of said electrical load by means of the auxiliary source of electrical energy at an electrical voltage slaved to the characteristics of frequency and phase of the electrical voltage of the primary stage.

Abstract: An electric motor nacelle for a vertical take-off and landing (VTOL) aircraft includes a fairing wherein an electric motor is housed equipped with at least one propeller extending outwards from a top face of the fairing, and a cooling device designed to cool the electric motor when the aircraft is in take-off, cruise and landing phases and including a reversible coolant fluid supply and exhaust manifold, designed, alternately: in the cruise phase, to receive a stream of cold fluid generated by the movement of the aircraft and to convey this stream of fluid, through the motor, towards an outlet situated opposite the propeller, and in take-off or landing phase, to receive a stream of hot fluid transmitted by the propeller and having passed through the motor.

Abstract: The invention relates to a member (O1) for measuring a magnitude representative of a common mode voltage (Vres) in an electrical network (1) or in an equipment (E), the network (1) or the equipment (E) comprising at least one first power conductor (C1) and a second power conductor (C2). The measuring member (O1) comprises a sensor formed by two resistive elements (R1, R2) which are intended to be arranged in a bridge between the two power conductors (C1, C2) and have resistance values which are identical to each other. The two resistive elements (R1, R2) are connected at a midpoint (T3). The sensor also comprises a measuring dipole (SH) connected to the midpoint (T3) and to a connection terminal intended to be electrically connected to a common conductor (Cc), of which the electrical network (1) or the equipment (E) has been equipped.

Abstract: A generator drive disconnect device comprising a drive transfer means (100) having a connected configuration, and a disconnected configuration. The disconnect device further comprises a disconnect mechanism, configured to move the drive transfer means from the connected configuration to the disconnected configuration, and a latch mechanism configured to the hold the drive transfer means in the disconnected configuration. The latch mechanism includes a latch member, which is moveable between a retracted position and an extended position, and a biasing mechanism. The biasing mechanism is configured to generate a biasing force to bias the latch member towards the extended position and to apply a reaction force to the latch member to resist movement of the latch member towards the retracted position, the reaction force having a magnitude which increases as a function of the distance of the latch member from the retracted position.

Abstract: Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (VHVDC), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.

Abstract: Current sensor comprising: one pair, of identical electrical coils with superparamagnetic cores and surrounded by a common shielding braid; a direct current excitation means configured to make a direct current flow in at least one of the coils of the pair of coils and a means of adjusting an intensity of the direct current; a first alternating current excitation means configured to make an alternating current flow at a first frequency in the coils of the pair that the direct current flows through; a second alternating current excitation means configured to make an alternating current flow at a second frequency greater than the first frequency in the two coils of the pair of coils; a means of measuring an electromotive force of the Néel Effect® type at the terminals of the two coils of the pair.

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 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: In the field of multi-rotor rotary-wing aircraft a propulsion system for such an aircraft includes a reconfigurable electric network for supplying the electric motors driving the rotors. The system includes: a supply source, a supply bus connected to the supply source, at least four drive units each including an electric motor and its control circuit, and an electrical ring network including: an electrical line which is interrupted at each drive unit and whose ends are connected to the supply bus, and, for each drive unit, a first switch and a second switch that are connected between the control circuit and the electrical line, on either side of the interruption.

Abstract: An aircraft propulsion system includes a turbomachine and at least one electric motor. The motor includes a first half-motor and a second half-motor that include, respectively, a first stator and a second stator cooperating with a common rotor of the motor. The propulsion system further includes at least one first energy source (B) capable of delivering a DC voltage and at least one electric generator (PMG) driven by the turbomachine. The electric generator generates an AC voltage to form a second energy source and is associated with an active rectifier that transforms the AC voltage into a DC voltage. The value of the DC voltage is controlled by the active rectifier, the output of which is connected to the first energy source.