Abstract: A method of stabilizing a DC electricity network, the network including a DC voltage source powering electrical loads that are connected in parallel to terminals of the voltage source and each of which is to receive a current or voltage setpoint. The method stabilizes the network by regulating setpoints applied to the loads by a virtual stabilization impedance generated at terminals of each load, the virtual impedances being dimensioned to stabilize the network in desired operating points and in given configurations of the network including a state in which at least one load is inactive or has failed and a state in which the stabilization of a load is inactive. Each virtual impedance is generated by a non-linear regulation loop acting on the setpoint for the corresponding load.

Abstract: A method of manufacturing a load buss array assembly includes placing a plurality of load conductors within a thermally conductive substrate, placing a portion of a load connector within the thermally conductive substrate, and electrically connecting the load conductors to the portion of the load connector within the thermally conductive substrate.

Abstract: The invention relates to an assistance device (17) for an electrical power generation system (11) of an aircraft, said system (11) comprising a generator (13), a regulator (14) and a contactor (15) comprising contacts and an actuator for opening/closing the contacts which is controlled by said regulator (14) and arranged between the generator (13) and a distribution architecture (12), the assistance device being characterized in that it is connected to at least one power source (18) which is separate from the generator (13) and the regulator (14), and in that it comprises means for closing the contactor which are suitable for connecting the power source (18) to the actuator (23) of the contactor (15) in order to provide the current necessary for closing said contactor (15).

Abstract: A switching assembly includes an operating assembly and a fixed contact assembly including a first fixed contact, a second fixed contact, a third fixed contact, a fourth fixed contact, and a number of terminals. The number of terminals includes a first terminal, a second terminal, and a third terminal. The switching assembly also includes a movable contact assembly that includes a first movable contact and a second movable contact. The first movable contact is movable between a first position and a second position. The second movable contact is movable between a first position and a second position. The operating assembly is coupled to the movable contact assembly and moves the first and second movable contact assemblies between the first and second positions. The switching assembly also includes a shunt assembly including a number of shunts. The shunt assembly is configured in one of a series configuration or a parallel configuration.

Abstract: An electrical connection member capable of detecting discontinuities in an electrical network is provided. The connection member includes a casing having at least three branches, each of the branches including, at the end of same, at least one terminal for electrical connection to a respective piece of equipment, and least one main conductor linking two terminals at the ends of two branches in the casing, at least one secondary conductor linking at least one terminal of the end of the third branch in the casing, and including an electrical coupler designed to inject an electrical test signal from the secondary conductor into the main conductor, and to transmit, to the secondary conductor, an electrical response signal generated by the reflection of the electrical test signal against a discontinuity encountered in the electrical network.

Abstract: An actuator or generator device includes an AC rotary electric machine having an electrical connection for transferring electrical energy to the terminals of the stator of the machine, the device including a transformer.

Abstract: A device for supplying electrical power to an aircraft on the ground, including two electric generators driven by an auxiliary power unit. The first generator is connected by a connection/disconnection mechanism to an aircraft network and to an electric taxiing network, to supply either an AC voltage to the aircraft network when it is connected to the aircraft network, or an AC voltage or a power to the taxiing network when it is connected to the taxiing network. The second generator is connected by the connection/disconnection mechanism to the aircraft or taxiing networks to supply the AC voltage to one of those networks.

Abstract: A power contactor that includes a number of inputs for a number of power sources, a number of outputs for a number of loads, a number of separable contacts for each pair of the number of inputs and the number of outputs, and an electromagnetic coil. The power contactor also includes a control circuit structured to control the electromagnetic coil to cause the number of separable contacts to open or close, and a plurality of plug-in pins. Each of the plug-in pins is for a corresponding one of the number of inputs and the number of outputs, and is structured to plug into a backplane socket. The power contactor also includes an electrically insulating housing electrically insulating each of the plug-in pins from the other the plug-in pins.

Abstract: An electrical energy generator system for an aircraft, the system including a streamlined fairing containing at least one turbine housed in the front portion of the fairing, and an electrical energy generator connected to said turbine. The front portion of the fairing is fitted with air admission means that are movable between an open position in which the turbine is exposed to the stream of air outside the fairing and a closed position in which the turbine is masked inside the fairing. The system may serve to reduce the aerodynamic drag caused by turbulence present at a wing tip for a conventional wing having sharp edges during stages of takeoff, climbing, and cruising; and during stages of descent it makes it possible to recover the kinetic and potential energy that has been accumulated by the aircraft during its stages of climbing and cruising.

Abstract: The invention relates to a method of measuring the temperature of a coiled component comprising the injection of a known DC current into a gauge wire (1) made of resistive material, the resistance of the gauge wire varying with temperature according to a known law, the measurement of potential difference between the terminals (7a, 7b) of said gauge wire, and a step of calculation transforming the potential difference into a mean temperature of the gauge wire, said gauge wire (1) being wound inside the coil, and arranged as a series of “outbound” turns (5) and a series of “inbound” turns (6) associated pairwise with a geometry and a position that are substantially equal. It also relates to a component made in order to be able to implement this method and the measurement device as a whole.

Abstract: An electrical control and power supply system for at least one helicopter motor/generator, the system including a first DC/AC converter selectively delivering AC electrical power to the at least one motor/generator, depending on respective positions of contactors of a connection matrix actuated from an electronic control circuit, the first DC/AC converter powered with DC by a DC power supply device that includes either a circuit for rectifying an AC voltage delivered via a contactor by a starter/generator of an APU, or a voltage booster DC/DC converter powered from a battery via a contactor. The connection matrix further includes a contactor connecting the first DC/AC converter in parallel with the second DC/AC converter to make it possible, once at least one of the motors/generators has started, to inject additional power from the starter/generator of the APU.

Abstract: A DC-DC voltage converter including a main switch formed by a normally ON switch element connected in series with a normally OFF switch element including a control circuit, a load in series with the main switch, the main switch and the load being configured to be connected to terminals of a DC voltage source. A voltage source, that can be used for controlling is obtained by connecting a main peak detector circuit to the mid-point of the main switch. The control circuit of the normally OFF switch element can be supplied with the DC voltage that makes the entire device self-supplied. Such a converter can, for example, find application in aeronautics.

Abstract: A circuit interrupter apparatus for plug-in connection to a panel board. The circuit interrupter apparatus includes a line terminal for plug-in connection with a line power member provided as part of the panel board, a load terminal for plug-in connection with a load power member provided as part of the panel board, a moveable contact moveable between a closed position, where the line terminal is electrically coupled to the load terminal, and an open position, where the line terminal is not electrically coupled to the load terminal. The circuit interrupter apparatus also includes a sensor module for a plug-in connection to a number of signal conductors provided as part of the panel board. The sensor module detects whether the moveable contact is in the closed position or the open position and output a signal to at least one of the signal conductors indicating a current position of the moveable contact.

Abstract: A method electrically connects by crimping electrical conductors in a connector for equipotential connection of a planar and flexible layer formed by the conductors, to metal components. The method includes positioning the electrical conductors in individual longitudinal and parallel cells which are formed between two planar walls of the connector, crimping the conductors crimped in a crimping zone by simultaneous transverse punching of at least one wall of the connector, and forming by the transverse punching at least one corresponding transverse groove line on the at least one connector wall and, by load transfer, on each of the conductors to electrically connect the conductors.

Abstract: An electrical power supply including an asynchronous machine, an arrangement for driving a rotor of the asynchronous machine in rotation by a rotor of an engine, and an electrical connection for powering electrical equipment by the rotor of the asynchronous machine. The asynchronous machine is configured to receive AC electrical power via a stator of the asynchronous machine, and it presents, over a predetermined range of drive speeds of the rotor of the asynchronous machine under drive by the rotor of the engine, efficiency in transferring electrical power from the stator to the rotor that is privileged relative to the efficiency with which rotary mechanical power is converted into electrical power.

Abstract: An electronic device with cooling of a heat dissipation source, by a liquid metals spreader, the device including at least one heat dissipation source, at least one spreader through which at least one liquid metal circulation channel passes forming a loop routed below a heat dissipation source, at least one heat sink, and at least one electromagnetic pump moving the liquid metal in the at least one channel such that the liquid metal absorbs heat dissipated by a heat dissipation source and transports the absorbed heat to be evacuated by the heat sink. Each spreader includes at least two plates made of an electrical insulating material located on each side of at least one bar made of deformable material.

Abstract: A front-fan turbojet engine including at least one fluid circuit and an air/fluid heat exchanger by which the fluid is cooled by air external to the turbojet engine and a splitter for splitting a flow downstream of the fan between a primary flow and a secondary flow. The heat exchanger is associated with a thermoelectric generator including a first and a second thermal exchange surface, of which the first surface is in thermal contact with the airflow and the second surface is in thermal contact with the fluid to be cooled in the exchanger.

Abstract: A three-phase transformer including a primary portion and a secondary portion, the primary portion including a first body made of ferromagnetic material and primary coils, the secondary portion including a second body made of ferromagnetic material and secondary coils, the first body defining a first annular slot of axis A and a second annular slot of axis A. The primary coils include a first toroidal coil of axis A in the first slot, a second toroidal coil of axis A in the first slot, a third toroidal coil of axis A in the second slot, and a fourth toroidal coil of axis A in the second slot, the second coil and the third coil being connected in series.

Abstract: An electrical power supply device for an aircraft on the ground, the device including two electricity generators driven by an auxiliary power unit, wherein the first generator is connected by a selective connection/disconnection mechanism to an aircraft network and to an electrical taxiing network, and is configured to deliver either a first AC voltage to the aircraft network when it is connected to that network, or an AC voltage or a power to the taxiing network when it is connected to that network, and wherein the second generator is connected by the connection/disconnection mechanism to the aircraft network to deliver the first AC voltage to that network solely when the first generator is powering the taxiing network.

Abstract: A method of manufacturing a backplane module includes providing a thermally conductive substrate, and applying a predetermined volume of epoxy extending between a first electrical component disposed on the thermally conductive substrate and a second electrical component disposed on the thermally conductive substrate to create an electrical pathway therebetween.