Abstract: An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Abstract: A rotating machine assembly includes a rotating machine that has a cover that defines an outer surface of the rotating machine and a stator disposed within the cover. The stator is stationary with respect to the cover. The rotating machine also includes a shaft rotatably disposed at least partially within the cover so as to define a rotation axis. The shaft Includes a first end that is connectable to an aircraft engine and a second end that is opposite the first end. The rotating machine also includes a rotor attached to the shaft, the rotor being movable with respect to the stator and a power module including at least one MOSFET that periodically reverses an electrical current direction of the rotor. The power module includes the at least one MOSFET Is disposed within the cover.

Abstract: A generator arranged to be driven by an aircraft engine, the generator comprising a stator and a rotor. The stator comprises a stator core and a plurality of slots longitudinally extending in a direction of a longitudinal axis of the stator, for receiving conductors to form windings of the stator, and a plurality of power channels. Each power channel comprises a set of windings having at least a first phase winding including a first set of coils comprising a plurality of conductors wound in a lap winding configuration, the first set of coils having a split phase belt such that the first set of coils comprises at least a first coil and a second coil, the first coil being mechanically shifted with respect to the second coil by a predetermined number of slots of the stator. The rotor comprises a permanent magnet adapted to reduce eddy-current losses.

Abstract: An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.

Abstract: A system for controlling an aircraft power network including at least a first propulsion assembly having at least one left-hand starter-generator and a second propulsion assembly having at least one right-hand starter-generator as well as other electrical motors, the system including first and second power electronics boxes each including at least two so-called generic control boards for controlling the power network, each of these at least two generic control electronics boards being connected by a fast communication link to separate first and second data switches, the first and second data switches of the first power electronics box being respectively connected to the first and second data switches of the second power electronics box by a first fast communication bus.

Abstract: Aircraft electric propulsion system including: a motor including a hollow rotor, and a power and control electronics device, in which the power and control electronics device includes at least two ring-shaped electrical tracks each including at least two inverters, the inverters being connected to each other in parallel, wherein the electrical tracks delimit a hollow circular part of the power and control electronics device, the hollow circular part being placed in the axis of the hollow rotor of the motor.

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: A system for cooling the brakes of a brake system of a landing gear of an aircraft, including: a compressor configured to generate a pressurized airflow, the compressor including at least one air outlet, and an air jet pump including: a pump tube including a first end connected to the air outlet and a second end, the pump tube being designed to carry the pressurized airflow between the first and second ends, and a plurality of injectors connected to the second end of the pump tube, and configured to inject the pressurized airflow.

Abstract: An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.

Abstract: The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

Abstract: A door hinge for an electrical cabinet includes a pathway for receiving an electrical harness, the hinge including two parts that are connected together and are rotatable with respect to one another about a pivot axis, the hinge including a duct that extends along the pivot and is designed to receive an intermediate section of the harness along the pivot axis, the duct including a longitudinal slot for the lateral insertion of the intermediate section of the harness into the duct while the intermediate section extends parallel to the duct. An electrical cabinet includes such a door hinge.

Abstract: The present invention relates to a generator input shaft assembly comprising a generator input shaft (160) arranged to receive a drive input to the generator, and a disconnect input shaft (120) arranged to deliver a drive input from the generator input shaft to a disconnectable drive transfer means (116). The disconnectable drive transfer means is configured to transfer rotational drive from the generator input shaft assembly to a rotor (110) of the generator. The generator input shaft assembly is configured such that the generator input shaft can: float axially relative to the disconnect input shaft and/or drive the disconnect input shaft with an axis of rotation of the generator input shaft non-parallel to an axis of rotation of the disconnect input shaft, so as to compensate for a misaligned input to the generator input shaft. Other aspects of the invention relate to a generator and a system comprising the generator input shaft assembly.

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.