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: 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: 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: 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 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: The invention relates to a method for converting alternating current into direct current implemented by a conversion device that comprises a three-phase bridge in which at least one arm is comprised of a first switch and of a second switch mounted in series, with the method comprising a step of regulating the direct voltage output by the conversion device, characterized in that it comprises a transition step which precedes the regulation step, with the transition step comprising the formation of signals for controlling first and second switches capable of limiting the amplitude of the inrush currents when switching the conversion device to the alternative network.

Abstract: A method for cooling an electricity generator (50) for delivering electricity to a first rotor (60), the first rotor being suitable for being rotated relative to a stationary structure, the method being characterized in that the electricity generator is placed in a chamber (62) arranged inside the first rotor, and in that it comprises the following steps: a) transferring heat produced by the generator to a cooling fluid, thereby vaporizing the fluid in an evaporator (64); b) transporting the vaporized fluid to a condenser; and c) condensing the fluid in the condenser, the heat delivered by the fluid being transmitted to the air surrounding the condenser.

Abstract: A method and architecture processing electrical energy regenerated from an aircraft, to address drawbacks posed by customary solutions for dissipating low energy of resistors, conventionally ceramics, which require a significant volume of ceramic and an additional power converter. The method and architecture return energy to an electric generator to convert the energy into mechanical energy. The architecture includes a reversible electric generator, driven by a thermal machine and configured to deliver an AC voltage, electric actuators, and a voltage converter circuit with multiple links. The circuit includes AC voltage rectifiers for voltage originating from the generator and power converters arranged on the multiple links to drive as many electric actuators. The converter circuit also includes a mechanism for electrical energy inverse transmission applied to the generator operating in a motor mode.

Abstract: An aircraft engine including: a stator; a main shaft; a first rotor; a second rotor; a transmission mechanism; a first electrical apparatus supported by the first rotor and a second electrical apparatus supported by the second rotor; at least one first field winding supported by the stator; a control unit configured to circulate direct electric current in the first field winding; at least one first armature winding supported by the first rotor and connected to the first electrical apparatus and at least one second armature winding supported by the second rotor and connected to the second electrical apparatus.

Abstract: The protection device for providing protection against short-circuits upstream from an electrical power supply module having an inlet filter with at least one capacitor and an inductor and having a converter with components associated with a plurality of freewheel diodes includes at least one auxiliary winding and a dissipator element associated with the inlet filter, thereby making it possible to provide an inlet filter of small size without over dimensioning the freewheel diodes.