Abstract: A method of characterizing a bundle (1) of electrical cables (2, 3, 4, . . . ), comprising taking into consideration for at least one surface temperature of the cables (Tsurface), firstly of at least one sum of heat fluxes (?1, ?2, . . . , ?n) calculated for each cable (2, 3, 4, . . . ) for the heating effect due to the electrical resistance of each cable passing a respective electric current (i1, i2, . . . , in), and secondly of a heat flux (?s) calculated for the heat given off by the bundle (1) into its environment in order to make the dimensioning of the cables (2, 3, 4, . . . ) compatible with their use.

Abstract: A three-phase/two-phase rotary transformer, includes a first single-phase rotary transformer and a second single-phase rotary transformer, the first transformer including a first body defining a first slot, a first coil in the first slot, a second body defining a second slot, and a second coil in the second slot, the second transformer including a third body defining a third slot, a third coil in the third slot, a fourth body defining a fourth slot, and a fourth coil in the fourth slot, wherein one terminal of the first coil is connected to the midpoint of the third coil, the first body, the first coil, the third body, and the third coil forming a three-phase portion of the transformer, the second body, the second coil, the fourth body, and said fourth coil forming a two-phase portion of the transformer.

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 including a first toroidal coil of axis A in the first slot, a second toroidal coil of axis A in the second slot, and one or more third toroidal coils connected in series, the third coils being wound around one of the legs, and passing via slots in the leg.

Abstract: A method for controlling a converter for converting an n-phase AC input voltage into a DC output voltage, each phase of the AC input voltage being connected to a switch of the converter. The method includes determining the signs of j characteristic voltages (Va, Vb, Vc, Va-Vb, Vb-Vc, Va-Vc, Va+20°, Vb+20°, Vc+20°, Va?20°, Vb?20°, Vc?20°); determining a reference combination (C1-C12, C1-C18), to which the signs of j characteristic voltages (Va, Vb, Vc, Va-Vb, Vb-Vc, Va-Vc, Va+20°, Vb+20°, Vc+20°, Va?20°, Vb?20°, Vc?20°) correspond, by comparing the signs of the j characteristic voltages to data from a reference table; and (c) opening each switch for an opening time (t1, t2, t3) pre-determined according to the reference combination (C1-C12, C1-C18) identified during the determining of the reference combination.

Abstract: An electrical circuit including at least one electrical component, such as a power component, and an electrical flex circuit, and at least one electrical conductor part connecting the electrical component to the flex circuit, the electrical conductor part including at least a first contact portion configured to receive in contact a contact element of the electrical power component and a second contact portion configured to receive in contact a conductive layer of the electrical flex circuit, the extent of the width of the second contact portion corresponding to the width of the flex circuit, and the extent of the length of same being adjusted to provide a contact surface that one of transmitting a density of electrical current of between 4.5 and 5.5 A/mm2 and allowing the electrical circuit to support a current specific to the power component, i.e. between 30 and 80 A.

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 characterised 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 power distribution assembly for an airplane, the assembly including an electric switch device for placing in a Karman fairing of the airplane.

Abstract: The invention concerns an electrical connection member, characterised in that it is capable of detecting discontinuities in an electrical network and comprises a casing having at least three branches, each of the branches comprising, 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 comprising 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: The invention relates to a method for manufacturing a strip of impregnated anodised aluminium, for use in a coil of an electrotechnical component, said coil including an interstitial material providing dielectric cohesion and insulation functions, said interstitial material being suitable for cross-linking, in other words for forming, by chemical reactions between the components thereof when subjected to certain physical conditions, molecular structures being organised in a lattice, the method comprising: a step of applying the precursor mixture of said interstitial material to the anodised aluminium; at least one step of cross-linking the precursor mixture in order to form said interstitial material on the strip of aluminium; characterised in that the anodised aluminium has not been subjected to the sealing of the pores of the alumina formed by anodisation prior to the application of the precursor mixture of said interstitial material.

Abstract: The invention relates to an electrical energy generator system (20) for an aircraft (10), the system comprising a streamlined fairing (21) containing at least one turbine (22) housed in the front portion (21a) of the fairing (21), and an electrical energy generator (23) connected to said turbine. The front portion (21a) of the fairing (21) is fitted with air admission means (26) that are movable between an open position in which the turbine (22) is exposed to the stream of air outside the fairing (21) and a closed position in which the turbine (22) is masked inside the fairing (21). The invention serves to reduce the aerodynamic drag usually 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: An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.

Abstract: An aircraft including an electric starter-generator for each of turbojets, and an undercarriage including an electric motor for taxiing the aircraft, which mutualizes an electricity converter for starting and for taxiing the aircraft. A single electricity converter is configured to be coupled to the electric starter-generator associated with a turbojet or to the electric motor of the undercarriage for taxiing, the coupling take place via an electricity distribution unit.

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: A three-phase-two-phase transformer including a magnetic circuit, three-phase windings, and two-phase windings, wherein the magnetic circuit includes a first column, a second column, and a third column that are magnetically connected together, the three-phase windings including a first winding, a second winding, and a third winding. The two-phase windings include a fourth winding around the first column, a fifth winding around the first column, a sixth winding around the third column, and a seventh winding around the third column, the fourth winding and the seventh winding being connected in series and forming a first two-phase phase, and the fifth winding and the sixth winding being connected in series and forming a second two-phase phase.

Abstract: A coiled power device including a magnetic core including a first leg and a second leg which are parallel to each other, the device including a first coil and a second coil to generate mutual inductance between the coils, the first coil including a first winding of conducting wires around the first leg and a second winding of conducting wires around the second leg, the second coil including at least a third winding of conducting wires around the second leg and a fourth winding of conducting wires around the first leg, the first winding and the fourth winding covering the same portion of the first leg to limit leakage inductance of the coiled power device.

Abstract: A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa.

Abstract: A printed circuit includes a substrate onto which at least one ceramic component is attached so as to enable the heat produced by the ceramic component to be discharged and to prevent cracks in the ceramic component and in the substrate. To this end, the ceramic component is attached onto the substrate using two connectors made of metal matrix composite material. The two connectors further have incisions so as to enable the mechanical stresses exerted in the substrate to be carried over into the connectors.

Abstract: A method of controlling a permanent magnet synchronous machine including a stator and a rotor. The method includes determining an estimated position of the rotor, and determining a second in-phase voltage setpoint that, in alternation, is equal either to a first in-phase voltage setpoint or else to the first in-phase voltage setpoint plus a predetermined periodic signal. The determining an estimated position of the rotor includes determining a coupling term, determining a speed of rotation of the rotor as a function of the coupling term, and determining the estimated position of the rotor by integrating the speed of rotation of the rotor.

Abstract: A three-phase/two-phase rotary transformer including a three-phase portion and a two-phase portion that are movable in rotation relative to each other about an axis A. The three-phase portion includes a first body made of ferromagnetic material and three-phase coils, the two-phase portion including a second body made of ferromagnetic material and two-phase coils. The second body defines a first annular slot of axis A and a second annular slot of axis A, the two-phase coils including 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 first coil and the fourth coil being connected in series, the second coil and the third coil being connected in series.

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.