System comprising a rack and a line replaceable module

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.

CONNECTION, METHOD, EQUIPOTENTIAL SHUNT CONNECTION AND EQUIPOTENTIAL BONDING CURRENT RETURN NETWORK IN A NON-CONDUCTIVE ARCHITECTURE

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 ). Each in-line shunt connector ( 2 ) comprises a central sleeve ( 2 m ) for directly electrically contacting the cable ( 1 ), end portions for installation on the cable ( 1 ) by crimping, and an attachment means ( 2 p ) for attaching to the bracket ( 111 ) of the device. Each of the ends of the sleeve ( 2 m ) have a seal accommodated therein. Each interconnection has two sealed regions, which surround a central contact region formed by means of window-stripping.

Electronic unit with reversible modules

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.

Electronic device comprising a module connected to a PCB and electronic unit comprising such a device

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.

Cooling module and electronic unit comprising such a module

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.

Aircraft having computers distributed in the fuselage

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.

Electronic module with improved moisture protection

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.

ELECTRONIC UNIT WITH REVERSIBLE MODULES

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. 1. An electronic unit comprising a box defining a reception compartment for receiving an electronic module in two mutually opposite directions along 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.2. The electronic unit according to claim 1 , wherein the power supply means comprise a first conductive area and a second conductive area arranged on opposite sides of a middle line of the connection face claim 1 , one of the first and second conductive areas being the positive pole of the electrical power supply of the electronic module claim 1 , the other one of the first and second conductive areas claim 1 , being the negative pole of the electrical power supply of the electronic module.3. The electronic unit according to claim 2 , wherein the conductive areas extend along respective axes parallel to the middle line.4. The electronic unit according to claim 1 , wherein the connection face is coated at least in part by a friction-reducing coating.5. The electronic unit according to claim 1 , wherein the connection means for connecting the electronic module to the electronic unit comprise at least one magnetic coupler.6. The electronic unit ...

Cooling module and electronic unit comprising such a module

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.

ELECTRONIC DEVICE COMPRISING A MODULE CONNECTED TO A PCB AND ELECTRONIC UNIT COMPRISING SUCH A DEVICE

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. 1. 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.2. The printed circuit board according to claim 1 , wherein the electrically insulating material is a silicone claim 1 , and more particularly a silicone for room temperature vulcanization.3. The printed circuit board according to claim 2 , wherein the protective film is a photosensitive film based on epoxy.4. The printed circuit board according to claim 3 , wherein the protective film has thickness lying in the range 25 μm to 100 μm.5. An electronic unit comprising a box defining a compartment containing calculation modules insertable into the main compartment along an insertion axis through a first opening in the box and connectable to connectors carried by a back wall of the compartment to extend in the compartment opposite from the first opening claim 3 , at least one of the calculation modules having pins for engaging in blind metal-plated holes of a printed circuit board extending opposite from the first opening ...

ELECTRONIC MODULE WITH IMPROVED MOISTURE PROTECTION

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. 1. An electronic module including a protective casing defining an internal volume and an electronic circuit board placed in the internal volume , the electronic module including:means for detecting a predetermined environmental condition of the internal volume;means for generating a cold zone inside the internal volume such that the cold zone is separated from the electronic circuit board;a control unit that is connected to the means for detecting an environmental condition and to the means for generating a cold zone, the control unit being adapted to trigger the means for generating a cold 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 circuit board.2. The electronic module as claimed in claim 1 , in which the means for detecting a predetermined environmental condition comprise a first temperature sensor fastened to the electronic circuit board.3. The electronic module as claimed in claim 1 , in which the means for detecting a predetermined ...

SYSTEM COMPRISING A RACK AND A LINE REPLACEABLE MODULE

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. 1. A system comprising a rack and at least one line-replaceable module , the rack comprising a slot for accommodating the line-replaceable module , the rack further comprising a primary transmission circuit comprising a primary antenna , primary emission components arranged to generate an emitted power containing uplink data , and primary reception components arranged to receive downlink data , the line-replaceable module comprising a secondary transmission circuit comprising a secondary antenna , secondary reception components arranged to receive the emitted power and the uplink data , and secondary emission components arranged to generate the downlink data , the emitted power , the uplink data and the downlink data being transmitted via one and the same coupling between the primary antenna and the secondary antenna.2. The system as claimed in claim 1 , wherein the primary emission components comprise a two-phase generator L.3. The system as claimed in claim 2 , wherein the primary emission components further comprise a non-inverting amplifier and an inverting amplifier linked to the two-phase generator L claim 2 , an output of the non-inverting amplifier being connected to a first primary conductor linked to a first terminal of the primary ...

DEVICE FOR COOLING AVIONICS RACKS WITH A HEAT-TRANSFER FLUID

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. 112-. (canceled)13. A device for cooling at least one 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 aircraft 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 of the ventilated cabin.14. The cooling device according to claim 13 , wherein the first heat exchanger comprises first means for forcing an air flow.15. The cooling device according to claim 13 , wherein the second heat exchanger comprises second means for forcing an air flow.16. The cooling device according to claim 14 , wherein the first means and/or second means for forcing an air flow comprise a fan.17. The cooling device according to claim 13 , ...

A METHOD OF CHARACTERIZING A BUNDLE OF ELECTRIC CABLES

A method of characterizing a bundle () of electrical cables ( ), comprising taking into consideration for at least one surface temperature of the cables (T), firstly of at least one sum of heat fluxes (Φ, Φ, . . . , Φ) calculated for each cable ( ) for the heating effect due to the electrical resistance of each cable passing a respective electric current (i, i, . . . , i), and secondly of a heat flux (Φ) calculated for the heat given off by the bundle () into its environment in order to make the dimensioning of the cables ( ) compatible with their use. 1. A method of characterizing a bundle of electrical cables , comprising taking into consideration for at least one surface temperature of the cables , first at least one sum of incoming heat fluxes calculated for each cable for the heating effect due to the electrical resistance of each cable passing a respective electric current , and second an outgoing heat flux calculated for the heat given off by the bundle into its environment in order to make the dimensioning of the cables compatible with their use.2. A method of characterization according to claim 1 , wherein the consideration of said sum of incoming fluxes and said outgoing flux comprises calculating them for a given temperature constituting a constraint to be satisfied and comparing the numerical values as calculated in this way.3. A method of characterization according to claim 1 , wherein the consideration of said sum of incoming fluxes and said outgoing flux comprises solving an equation to obtain the temperatures that are actually reached in operation.4. A method of characterization according to claim 1 , wherein said sum of incoming fluxes and said outgoing flux are compared at the maximum temperature at which the cable can operate without degradation.5. A method of characterization according to claim 1 , wherein said sum of incoming fluxes and said outgoing flux are compared at the maximum operating temperature that guarantees safety for human ...

Aircraft having computers distributed in the fuselage

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.

COOLING DEVICE FOR AVIONIC BAYS WITH HEAT TRANSFER LIQUID

Dispositif de refroidissement (100) d'un module électronique (81, 82) placé dans une baie avionique (80) d'un aéronef (1) comprenant une cabine ventilée (31), le dispositif de refroidissement (100) comprenant : un circuit fermé (10) de circulation d'un liquide caloporteur (11) ;des premiers moyens de circulation du liquide caloporteur (12) dans le circuit fermé (10) ; un premier échangeur thermique (50) comprenant un circuit froid (51) qui est pourvu de premiers moyens de liaison (89, 90) au circuit fermé (10) de liquide caloporteur (11) et qui est thermiquement relié à une source chaude de la baie d'aéronef (80) ; un deuxième échangeur thermique (60) comprenant un circuit chaud (61) pourvu de deuxièmes moyens de liaison (20, 21) au circuit fermé (10) de liquide caloporteur (11) et un circuit froid (62) thermiquement relié à une évacuation d'air (30) de la cabine ventilée (31). Baie avionique et aéronef comprenant une telle baie. Device for cooling (100) an electronic module (81, 82) placed in an avionics bay (80) of an aircraft (1) comprising a ventilated cabin (31), the cooling device (100) comprising: a circuit closed circulation (10) of a heat transfer liquid (11); first means of circulation of the heat transfer liquid (12) in the closed circuit (10); a first heat exchanger (50) comprising a cold circuit (51) which is provided with first connecting means (89, 90) to the closed circuit (10) of coolant liquid (11) and which is thermally connected to a hot source of the aircraft bay (80); a second heat exchanger (60) comprising a hot circuit (61) provided with second connecting means (20, 21) to the closed circuit (10) of coolant liquid (11) and a cold circuit (62) thermally connected to an outlet of air (30) from the ventilated cabin (31). Avionics and aircraft bay comprising such a bay.

ELECTRONIC DEVICE COMPRISING A MODULE CONNECTED TO A PCB AND ELECTRONIC UNIT COMPRISING SUCH A DEVICE

Aircraft comprising an electrical power distribution network.

Aéronef comportant un réseau de distribution de puissance électrique. L’aéronef (1) comporte un premier jeu de barres de distribution électrique (B1) et un deuxième jeu de barres de distribution électrique (B2) s’étendant au moins en partie dans un fuselage (2) de l’aéronef, selon une direction longitudinale du fuselage. Un premier générateur électrique (G1a) est relié aux conducteurs de distribution (B1a, B1b) du premier jeu de barres de distribution électrique (B1) par l’intermédiaire d’un premier commutateur de couplage (C1a) relié directement au premier générateur électrique et aux conducteurs de distribution du premier jeu de barres. Un deuxième générateur électrique (G2a) est relié aux conducteurs de distribution (B2a, B2b) du deuxième jeu de barres de distribution électrique (B2) par l’intermédiaire d’un deuxième commutateur de couplage (C2a) relié directement au deuxième générateur électrique et aux conducteurs de distribution du deuxième jeu de barres. Le premier commutateur de couplage (C1a) et le deuxième commutateur de couplage (C2a) sont positionnés dans l’aéronef indépendamment l’un de l’autre. Figure pour l’abrégé : Fig. 2 Aircraft comprising an electrical power distribution network. The aircraft (1) comprises a first set of electrical distribution bars (B1) and a second set of electrical distribution bars (B2) extending at least partly in a fuselage (2) of the aircraft, according to a longitudinal direction of the fuselage. A first electrical generator (G1a) is connected to the distribution conductors (B1a, B1b) of the first electrical distribution busbar (B1) via a first coupling switch (C1a) directly connected to the first electrical generator and to the distribution conductors of the first busbar. A second electrical generator (G2a) is connected to the distribution conductors (B2a, B2b) of the second electrical distribution busbar (B2) via a second coupling switch (C2a) connected directly to the second electrical generator and to the distribution ...

ELECTRONIC UNIT WITH INVERSE MODULES

Unité électronique (100) comprenant un boîtier (101) délimitant un compartiment de réception (104) d'un module électronique (124) selon deux sens opposés l'un à l'autre d'une direction d'introduction (P'), le compartiment comprenant des moyens d'alimentation électrique (125,) du module électronique (124) et des moyens de connexion (166.1-166.12, 167.1-167.4) de l'unité électronique (100,) au module électronique (124), ces moyens débouchant sur une face de branchement (160) appartenant au compartiment de réception (104) s'étendant parallèlement à la direction d'introduction (P'). Module électronique (124, 224, 324, 424) destiné à être montée dans un compartiment (104, 204, 304, 404) d'une unité électronique (100, 200, 300, 400) selon l'invention. An electronic unit (100) comprising a housing (101) delimiting a receiving compartment (104) of an electronic module (124) in two directions opposite to each other of an insertion direction (P '), the compartment comprising power supply means (125,) of the electronic module (124) and connection means (166.1-166.12, 167.1-167.4) of the electronic unit (100,) to the electronic module (124), these means opening onto a branch face (160) belonging to the receiving compartment (104) extending parallel to the insertion direction (P '). Electronic module (124, 224, 324, 424) intended to be mounted in a compartment (104, 204, 304, 404) of an electronic unit (100, 200, 300, 400) according to the invention.

Device, system and method for the electrical protection of an aircraft.

Dispositif, système et procédé de protection électrique d’un aéronef. Le dispositif (10) de protection électrique d’un aéronef (1), est un dispositif de protection différentielle d’au moins un circuit électrique comprenant un ensemble de conducteurs électriques (w1, w2). Il comprend une unité de traitement (12) configurée pour calculer une différence entre les courants circulant dans ces conducteurs électriques. Si cette différence excède un seuil prédéterminé correspondant à une courbe de protection différentielle, l’unité de traitement (12) commande l’ouverture d’un interrupteur (Sw) pour interdire la circulation de courants électriques dans les conducteurs électriques. En l’absence d’activation d’un mode de maintenance, ladite courbe de protection différentielle correspond à une première courbe de protection différentielle (20) dimensionnée pour permettre le fonctionnement d’équipements électriques de l’aéronef lors de l’exploitation en vol ou au sol de l’aéronef. Sinon, elle correspond à une deuxième courbe de protection différentielle (22) dimensionnée pour permettre la protection d’opérateurs de maintenance de l’aéronef. Figure pour l’abrégé : Fig. 2 Device, system and method for the electrical protection of an aircraft. The electrical protection device (10) of an aircraft (1) is a differential protection device for at least one electrical circuit comprising a set of electrical conductors (w1, w2). It comprises a processing unit (12) configured to calculate a difference between the currents flowing in these electrical conductors. If this difference exceeds a predetermined threshold corresponding to a differential protection curve, the processing unit (12) controls the opening of a switch (Sw) to prevent the flow of electric currents in the electrical conductors. In the absence of activation of a maintenance mode, said differential protection curve corresponds to a first differential protection curve (20) sized to allow the operation of electrical equipment of ...

SYSTEM AND METHOD FOR GENERATING PNEUMATIC ENERGY IN AN AIRCRAFT

Device for cooling avionics racks with a heat-transfer fluid

Aircraft comprising an electric power distribution network

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.

System comprising a rack and a line replaceable module

A system comprising a rack and at least one line replaceable module, the rack further comprising a primary transmission circuit (1) comprising a primary antenna (2), primary emission components (7, 8) designed to generate an emitted power containing uplink data (18), and primary receiving components (26, 27, 28) designed to receive downlink data (68), the line replaceable module comprising a secondary transmission circuit (40) comprising a secondary antenna (41), secondary receiving components (45, 51, 54, 52) designed to receive the emitted power and the uplink data, and secondary emission components (61, 62, 63) 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 (2) and the secondary antenna.

DATA EXCHANGE PROCESS IN AN AIRCRAFT AND CONTROL UNIT

Un procédé d'échange de données dans un système (100) d'échange de données embarqué dans un aéronef, ledit système (100) comprenant : • une étape de réception par une première unité de contrôle (20) de données émises par un premier organe émetteur selon un premier protocole élémentaire, • une étape d'encapsulation desdites données reçues par la première unité de contrôle (20) selon un protocole global, • une étape de transfert des données entre la première et une deuxième unité de contrôle (20) selon le protocole global, • une étape de désencapsulation des données par la deuxième unité de contrôle (20) selon le protocole global de manière à obtenir des données selon le premier protocole élémentaire, et • une étape de transfert des données à un premier organe récepteur (10) par la deuxième unité de contrôle (20) selon le premier protocole élémentaire. A method for exchanging data in a data exchange system (100) on board an aircraft, said system (100) comprising: a step of reception by a first control unit (20) of data sent by a first transmitter unit according to a first elementary protocol, • a step of encapsulating said data received by the first control unit (20) according to a global protocol, • a step of transferring data between the first and a second control unit (20) according to the global protocol, • a step of de-encapsulating the data by the second control unit (20) according to the global protocol so as to obtain data according to the first elementary protocol, and • a step of transferring the data to a first receiving unit (10) by the second control unit (20) according to the first elementary protocol.

connection process with equipotential bonding of a current return network, in-line equipotential bypass connection, and current return network.

ELECTRONIC DEVICE COMPRISING A MODULE CONNECTED TO A PCB AND ELECTRONIC UNIT COMPRISING SUCH A DEVICE

Dispositif électronique comprenant au moins un module électronique comprenant des broches (151) destinées à être engagées dans des trous métallisés (152) d'une plaque de circuit imprimé (118), la plaque de circuit imprimé (118) étant recouverte d'une couche de matériau souple électriquement isolant (153) qui est percée par les broches (151) lorsque celles-ci sont engagées dans les trous métallisés (152) et est serrée entre un support (150) des broches et la plaque de circuit imprimé (118). Unité électronique comprenant un tel dispositif.

METHOD FOR EXCHANGING DATA IN AN AIRCRAFT AND CONTROL UNIT

Un procédé d'échange de données dans un système (100) d'échange de données embarqué dans un aéronef, ledit système (100) comprenant : • une étape de réception par une première unité de contrôle (20) de données émises par un premier organe émetteur selon un premier protocole élémentaire, • une étape d'encapsulation desdites données reçues par la première unité de contrôle (20) selon un protocole global, • une étape de transfert des données entre la première et une deuxième unité de contrôle (20) selon le protocole global, • une étape de désencapsulation des données par la deuxième unité de contrôle (20) selon le protocole global de manière à obtenir des données selon le premier protocole élémentaire, et • une étape de transfert des données à un premier organe récepteur (10) par la deuxième unité de contrôle (20) selon le premier protocole élémentaire. A method of exchanging data in a system (100) for exchanging data on board an aircraft, said system (100) comprising: • a step of reception by a first control unit (20) of data transmitted by a first transmitter according to a first elementary protocol, • a step of encapsulating said data received by the first control unit (20) according to a global protocol, • a step of transferring data between the first and a second control unit (20) according to the global protocol, • a step of de-encapsulation of the data by the second control unit (20) according to the global protocol so as to obtain data according to the first elementary protocol, and • a step of transferring the data to a first receiving organ (10) by the second control unit (20) according to the first elementary protocol.

Electronic module with improved moisture protection

Electronic module (100) comprising a protective casing (21) defining an internal volume (22) and an electronic board (10) placed in the internal volume (22), the electronic module (100) comprising: - means (30, 31) for detecting a predetermined environmental condition of the internal volume (22); - means (50) for generating a cool zone inside the internal volume (22), which means are arranged such that the cool zone is separated from the electronic board (10); - a control unit (40) that is linked to the means (30, 31) for detecting an environmental condition and to the means (50) for generating a cool zone and arranged to trigger the means (50) for generating a cool zone when the means for detecting a predetermined environmental condition in the internal volume (22) detect an environmental condition that is liable to result in the moisture in the air contained in the internal volume (22) condensing on the electronic board (10).

Connection method, equipotential shunt connection and equipotential bonding current return network in a non-conductive architecture

ELECTRONIC UNIT WITH INVERSE MODULES

SYSTEM COMPRISING A BAY AND A REPLACEABLE MODULE ONLINE

Système comportant une baie et au moins un module remplaçable en ligne, la baie comprenant en outre un circuit de transmission primaire (1) comportant une antenne primaire (2), des composants d'émission primaires (7, 8) agencés pour générer une puissance émise contenant des données montantes (18), et des composants de réception primaires (26, 27, 28) agencés pour recevoir des données descendantes (68), le module remplaçable en ligne comprenant un circuit de transmission secondaire (40) comportant une antenne secondaire (41), des composants de réception secondaires (45, 51, 54, 52) agencés pour recevoir la puissance émise et les données montantes, et des composants d'émission secondaires (61, 62, 63) agencés pour générer les données descendantes, la puissance émise, les données montantes et les données descendantes étant transmises via un même couplage entre l'antenne primaire (2) et l'antenne secondaire. System comprising a bay and at least one in-line replaceable module, the bay further comprising a primary transmission circuit (1) having a primary antenna (2), primary emission components (7, 8) arranged to generate a power transmitted signal containing rising data (18), and primary receiving components (26,27,28) arranged to receive downstream data (68), the on-line replaceable module including a secondary transmission circuit (40) having a secondary antenna (41), secondary receive components (45, 51, 54, 52) arranged to receive the transmitted power and the upstream data, and secondary transmit components (61, 62, 63) arranged to generate the downstream data, the transmitted power, the rising data and the downstream data being transmitted via the same coupling between the primary antenna (2) and the secondary antenna.

Aircraft having computers distributed in the fuselage

Procede de caracterisation d'un toron de cables electriques

Procédé de caractérisation d'un toron (1) de câbles électriques (2, 3, 4...), comprenant la considération pour au moins une température de surface des câbles (Tsurface), d'une part d'une somme de flux thermiques (Φ1, Φ2,... Φn) calculés pour chaque câble (2, 3, 4...) pour l'effet d'échauffement dû à la résistance électrique du câble parcouru par un courant électrique (i1, i2, ... in), et d'autre part d'un flux thermique (Φs) calculé pour la chaleur dégagée dans son environnement par le toron (1), pour rendre compatibles le dimensionnement des câbles (2, 3, 4...) et leur utilisation.

Système d’alimentation électrique de charges électriques d’un aéronef.

Système d’alimentation électrique de charges électriques d’un aéronef. Le système d’alimentation électrique (10) d’un ensemble de charges électriques d’un aéronef (1) comprend une carte de protection (12) équipée d’un ensemble de protections électriques (S1, S2 … SN) et un ensemble de liaisons électriques (30) configuré pour relier des sorties de protections électriques équipant la carte de protection à l’ensemble de charges électriques. Le système comprend en outre au moins une interface (22) entre les protections électriques (S1, S2 … SN) équipant la carte de protection (12) et l’ensemble de liaisons électriques (30), cette interface étant configurée pour relier au moins deux sorties de protections électriques à une même charge électrique, l’interface (22) étant indépendante de la carte de protection (12). Figure pour l’abrégé : Fig. 2

Aeronef ayant des calculateurs repartis dans le fuselage

Aéronef comprenant un fuselage (1) divisé par un plancher (2) en un o volume supérieur (3) et un volume inférieur (4) dans lequel s'étendent des poutrelles (5) supportant le plancher et délimitant avec le fuselage et le plancher deux logements latéraux (6) qui ont une section transversale sensiblement triangulaire et qui s'étendent parallèlement à une direction longitudinale du fuselage. Des unités de calcul (100) sont disposées dans les logements latéraux et comprennent chacune un boîtier (101) définissant un compartiment principal contenant des modules de calcul (122) insérables dans le compartiment principal selon une direction df insertion par une ouverture de celui- ci et raccordables à des connecteurs (115) portés par une paroi de fond (116) du compartiment pour déboucher dans le compartiment principal à l' opposé de l' ouverture, la direction d' insertion étant sensiblement parallèle à la direction longitudinale du fuselage.

Procede de caracterisation d'un toron de cables electriques

Procédé de caractérisation d'un toron (1) de câbles électriques (2, 3, 4...), comprenant la considération pour au moins une température de surface des câbles (Tsurface), d'une part d'une somme de flux thermiques (F1, F2,... Fn) calculés pour chaque câble (2, 3, 4...) pour l'effet d'échauffement dû à la résistance électrique du câble parcouru par un courant électrique (i1, i2,... i,n), et d'autre part d'un flux thermique (Fs) calculé pour la chaleur dégagée dans son environnement par le toron (1), pour rendre compatibles le dimensionnement des câbles (2, 3, 4...) et leur utilisation.

Procédé de caractérisation d'un toron de câbles électriques

Procédé de caractérisation d'un toron (1) de câbles électriques (2, 3, 4...), comprenant la considération pour au moins une température de surface des câbles (T surface ), d'une part d'une somme de flux thermiques (Φ 1 , Φ 2 ,... Φ n ) calculés pour chaque câble (2, 3, 4...) pour l'effet d'échauffement dû à la résistance électrique du câble parcouru par un courant électrique (i 1 , i 2 ,... i, n ), et d'autre part d'un flux thermique (Φ s ) calculé pour la chaleur dégagée dans son environnement par le toron (1), pour rendre compatibles le dimensionnement des câbles (2, 3, 4...) et leur utilisation.

Procédé de caractérisation d'un toron de câbles électriques

Procédé de caractérisation d'un toron (1) de câbles électriques (2, 3, 4...), comprenant la considération pour au moins une température de surface des câbles (T surface ), d'une part d'une somme de flux thermiques (Φ 1 , Φ 2 ,... Φ n ) calculés pour chaque câble (2, 3, 4...) pour l'effet d'échauffement dû à la résistance électrique du câble parcouru par un courant électrique (i 1 , i 2 ,... i, n ), et d'autre part d'un flux thermique (Φ s ) calculé pour la chaleur dégagée dans son environnement par le toron (1), pour rendre compatibles le dimensionnement des câbles (2, 3, 4...) et leur utilisation.

Aircraft comprising an electric power distribution network

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.

Module de refroidissement et unite electronique comportant un tel module

Module de refroidissement comprenant une première entrée d'air, une deuxième entrée d'air et un évent d'évacuation d'air, le module comprenant deux clapets anti-retour montés chacun devant une des entrées et agencés pour autoriser un passage d'air vers l'intérieur du module et s'opposer à une circulation d'air en sens opposé. Unité électronique comprenant un tel boîtier.