Abstract: An aircraft including a first electrical distribution busbar and a second electrical distribution busbar extending at least in part in a fuselage of the aircraft, in a longitudinal direction of the fuselage. A first electric generator is connected to the distribution conductors of the first electrical distribution busbar via a first coupling switch directly connected to the first electric generator and to the distribution conductors of the first busbar. A second electric generator is connected to the distribution conductors of the second electrical distribution busbar via a second coupling switch directly connected to the second electric generator and to the distribution conductors of the second busbar. The first coupling switch and the second coupling switch are positioned in the aircraft independently of one another.

Abstract: An aircraft comprising a fuselage (1) subdivided by a floor (2) into a top volume (3) and a bottom value (4) in which girders (5) extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings (6) that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprises a box (101) defining a main compartment containing calculation modules (122) insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors (115) carried by a back wall (116) of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

Abstract: Electronic module comprising a protective casing defining an internal volume and an electronic board placed in the internal volume, the electronic module comprising: means, for detecting a predetermined environmental condition of the internal volume, means for generating a cool zone inside the internal volume, which means are arranged such that the cool zone is separated from the electronic board; a control unit that is linked to the means for detecting an environmental condition and to the means for generating a cool zone and arranged to trigger the means for generating a cool zone when the means for detecting a predetermined environmental condition in the internal volume detect an environmental condition that is liable to result in the moisture in the air contained in the internal volume condensing on the electronic board.

Abstract: A system comprising a rack and at least one line replaceable module, the rack further comprising a primary transmission circuit comprising a primary antenna, primary emission components designed to generate an emitted power containing uplink data, and primary receiving components designed to receive downlink data, the line replaceable module comprising a secondary transmission circuit comprising a secondary antenna, secondary receiving components designed to receive the emitted power and the uplink data, and secondary emission components designed to generate the downlink data, the emitted power, the uplink data and the downlink data being transmitted via a shared coupling between the primary antenna and the secondary antenna.

Abstract: An electronic unit comprising a box defining a reception compartment for receiving an electronic module along two mutually opposite directions of an insertion axis, the compartment including electrical power supply means for powering the electronic module and connection means for connecting the electronic unit to the electronic module, these means extending onto a connection face forming part of the reception compartment and extending parallel to the insertion axis. An electronic module for mounting in a compartment of an electronic unit of the invention.

Abstract: A device for cooling an electronic module placed in an avionics rack of an aircraft comprising a ventilated cabin, the cooling device comprising: a closed circuit for circulating a heat-transfer fluid; first means for circulating the heat-transfer fluid in the closed circuit; a first heat exchanger comprising a cold circuit which is provided with first means for connecting to the closed circuit for circulating a heat-transfer fluid and which is thermally connected to a hot source of the avionics rack; a second heat exchanger comprising a hot circuit provided with second means for connecting to the closed circuit for circulating a heat-transfer fluid and a cold circuit thermally connected to an air exhaust from the ventilated cabin. An avionics rack and an aircraft comprising such a rack.

Abstract: A printed circuit board including at least one blind metal-plated hole, for receiving a pin of the printed circuit board being covered by a first layer of a protective film on which there extends a second layer of electrically insulating flexible material, the first layer and second layer are for piercing by the pins when they are engaged in the metal-plated holes, the first and second layers being for claming between a support of the pins and the printed circuit board. An electronic unit including such a device. A method of fabricating a printed circuit card for such a device.

Abstract: A cooling module including a first air inlet, a second air inlet, and an air discharge vent, the module having two check valves, each mounted in register with a respective inlet and arranged to allow air to pass towards the inside of the module and to oppose a flow of air in the opposite direction. An electronic unit including such a box.

Abstract: A system comprising a rack and at least one line replaceable module, the rack further comprising a primary transmission circuit comprising a primary antenna, primary emission components designed to generate an emitted power containing uplink data, and primary receiving components designed to receive downlink data, the line replaceable module comprising a secondary transmission circuit comprising a secondary antenna, secondary receiving components designed to receive the emitted power and the uplink data, and secondary emission components designed to generate the downlink data, the emitted power, the uplink data and the downlink data being transmitted via a shared coupling between the primary antenna and the secondary antenna.

Abstract: Electronic module comprising a protective casing defining an internal volume and an electronic board placed in the internal volume, the electronic module comprising: means, for detecting a predetermined environmental condition of the internal volume, means for generating a cool zone inside the internal volume, which means are arranged such that the cool zone is separated from the electronic board; a control unit that is linked to the means for detecting an environmental condition and to the means for generating a cool zone and arranged to trigger the means for generating a cool zone when the means for detecting a predetermined environmental condition in the internal volume detect an environmental condition that is liable to result in the moisture in the air contained in the internal volume condensing on the electronic board.

Abstract: A printed circuit board including at least one blind metal-plated hole, for receiving a pin of the printed circuit board being covered by a first layer of a protective film on which there extends a second layer of electrically insulating flexible material, the first layer and second layer are for piercing by the pins when they are engaged in the metal-plated holes, the first and second layers being for claming between a support of the pins and the printed circuit board. An electronic unit including such a device. A method of fabricating a printed circuit card for such a device.

Abstract: An electronic unit comprising a box defining a reception compartment for receiving an electronic module along two mutually opposite directions of an insertion axis, the compartment including electrical power supply means for powering the electronic module and connection means for connecting the electronic unit to the electronic module, these means extending onto a connection face forming part of the reception compartment and extending parallel to the insertion axis. An electronic module for mounting in a compartment of an electronic unit of the invention.

Abstract: A cooling module including a first air inlet, a second air inlet, and an air discharge vent, the module having two check valves, each mounted in register with a respective inlet and arranged to allow air to pass towards the inside of the module and to oppose a flow of air in the opposite direction. An electronic unit including such a box.

Abstract: An aircraft comprising a fuselage (1) subdivided by a floor (2) into a top volume (3) and a bottom value (4) in which girders (5) extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings (6) that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprises a box (101) defining a main compartment containing calculation modules (122) insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors (115) carried by a back wall (116) of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

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 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: The object of the invention is to produce equipotential connections that are electrically efficient in terms of resistivity between portions of a current-return network in a non-conductive architecture, such as an airplane fuselage. The approach adopted by the invention is to impart an equipotential-bonding function to an aluminum cable having a large cross section, said bond being electrically connected, via direct contact, to as many devices as is physically possible to connect thereby. According to one embodiment, an electrical connection assembly of an aircraft fuselage (100) having a composite skin comprises in-line shunt connections (2) for electrically interconnecting an aluminum-alloy-based cable (1) of large cross section acting as an equipotential connection to brackets (113, 141) for primary current-return networks and to brackets (111) for electrical devices via connectors (202).