The invention relates to a method for encapsulating a printed circuit board, the method comprising at least: • at least one electronic component (3); and • at least one connector (4) having at least one first portion (5) electrically connected to the printed circuit board (2) and comprising at least: • a first overmoulding step, during which at least one portion of the printed circuit board (2) and the electronic component (3) are covered with a first covering layer (8); • a first cooling step, during which the first covering layer (8) is cooled; • a second overmoulding step, during which the first covering layer (8) and the first portion (5) of the connector (4) are covered with a second covering layer (9); and • a second cooling step, during which the second covering layer (9) is cooled.
B29C 45/14 - Moulage par injection, c.-à-d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule ferméAppareils à cet effet en incorporant des parties ou des couches préformées, p. ex. moulage par injection autour d'inserts ou sur des objets à recouvrir
B29C 45/16 - Fabrication d'objets multicouches ou polychromes
H05K 3/28 - Application de revêtements de protection non métalliques
B29K 21/00 - Utilisation de caoutchouc non spécifié ou élastomères non spécifiés comme matière de moulage
B29K 71/00 - Utilisation de polyéthers comme matière de moulage
B29K 77/00 - Utilisation de polyamides, p. ex. polyesteramides, comme matière de moulage
B29K 81/00 - Utilisation de polymères contenant dans la chaîne principale uniquement du soufre avec ou sans azote, oxygène ou carbone comme matière de moulage
2.
MULTILAYER MATERIAL COMPRISING AT LEAST ONE CREEP ZONE
The present invention relates to a multilayer material (1a, 1b, 1c) comprising at least: - a first layer (2); - a second layer (3); and - a third layer (4), characterised in that it comprises a first creep zone (5) of at least one portion of the first layer (2) through at least one portion of the second layer (3), and in that the third layer (4) comprises at least one composite material comprising: -a reinforcing textile and - a matrix.
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 25/08 - Produits stratifiés composés essentiellement de caoutchouc naturel ou synthétique comprenant du caoutchouc comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
B32B 25/10 - Produits stratifiés composés essentiellement de caoutchouc naturel ou synthétique adjacent à une couche fibreuse ou filamenteuse
B32B 25/16 - Produits stratifiés composés essentiellement de caoutchouc naturel ou synthétique comprenant des polydiènes ou poly-halodiènes
B32B 27/30 - Produits stratifiés composés essentiellement de résine synthétique comprenant une résine vinyliqueProduits stratifiés composés essentiellement de résine synthétique comprenant une résine acrylique
B32B 27/38 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines époxy
3.
METHOD FOR CONTROLLING A POWER CONVERTER, AND ASSOCIATED DEVICE AND AIRCRAFT
The invention relates to a control device (20) for a power converter of an aircraft, wherein the power converter is connected to a DC voltage source and to input terminals of an electrical load. The control device comprises: - initialisation means (39); - first determination means (33); - second determination means (34); - control means (37); - third determinination means (35); - comparison means (38); and - fourth determination means (36).
H02M 7/48 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
H02M 1/00 - Détails d'appareils pour transformation
4.
DEVICE FOR SECURE ACTUATION OF A CONTAINER FOR PROVISION OF PRESSURIZED GAS IN AN AIRCRAFT
The invention relates to a device for secure actuation of a container for provision of gaseous oxygen in an aircraft, in order to distribute this oxygen to a user, said container (1) being intended to store the pressurized oxygen at a first oxygen pressure and having an opening (2) sealed by a seal (9); the device comprising a manifold (4) fluidically connected to said seal (9) and configured to receive an oxygen flow from said opening (2) when the seal (9) is pierced, said manifold (4) comprising an oxygen flow circuit (11) fluidically connected to said seal (10) and having an outlet (14) at a second oxygen pressure, lower than the first pressure, and an expansion valve (13) having means (12, 15, 16) for oxygen pressure regulation between the opening (2) and said outlet (14) during a flow; and an actuator (7) provided in the opening (2) and configured to pierce said seal (9) when triggered, so as to enable a flow of oxygen through the opening (2) from the container (1) and towards the outlet (14), the oxygen flow circuit (11) comprising a calibrated orifice (17) provided at the outlet (14) and configured to prevent any accumulation of oxygen at a third pressure between the first and second pressures in the event of oxygen flowing to said outlet (14) in the absence of triggering of the actuator (7).
An assembly includes an inner wall delimiting a cavity, the inner wall having a first surface facing the cavity, and a second surface opposite the first surface with respect to the cavity, and a sealing device attached to the second surface and including a sealing layer including a material expandable when an opening is formed in the inner wall, and a guide attached to the sealing layer so as to exert a stress on the sealing layer to control a direction of expansion of the material of the sealing layer. The sealing layer has a first face and a second face, and the guide includes a first film attached to the first face and a second film attached to the second face.
The invention relates to a sensor (1) capable of allowing a measurement of a dielectric permittivity of a medium, in particular a fuel in a tank, comprising: - a support (3), - insulating fixing elements (17), - a plurality of plates (7) comprising at least a first plate (7a) and a second plate (7b) which are parallel and aligned along a stacking axis (X), - at least one first support column (11) connecting the first plate (7a) to one of the insulating fixing elements (17), - at least one second support column (13) connecting the second plate (7b) to one of the insulating fixing elements (17), - at least one additional plate (7c), and - at least one spacer column (15) connecting the additional plate to a plate which is the second closest neighbour. The support (3) and the plates (7) are made of a same first metal material and the spacer column (15) is made of a second metal material.
G01F 23/263 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme en mesurant des variables physiques autres que les dimensions linéaires, la pression ou le poids, selon le niveau à mesurer, p. ex. par la différence de transfert de chaleur de vapeur ou d'eau en mesurant les variations de capacité ou l'inductance de condensateurs ou de bobines produites par la présence d'un liquide ou d'un matériau solide fluent dans des champs électriques ou électromagnétiques en mesurant les variations de capacité de condensateurs
G01N 27/22 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant l'impédance en recherchant la capacité
7.
METHOD FOR OPTIMISING THE ELECTRICAL DRIVE CHAIN OF AN AIRCRAFT FUEL PUMP POWERED BY A HIGH-VOLTAGE NETWORK AND ASSOCIATED ELECTRICAL DRIVE CHAIN
The invention relates to a method for controlling an electrical drive chain (1) of an aircraft fuel pump, the method comprising receiving (202) a pair of speed and mechanical torque setpoints for the electric motor (2), receiving (204) a maximum voltage setpoint delivered by a DC high-voltage source (3), calculating (206) the minimum voltage required at the input of the electrical inverter (5) for the setpoint torque, calculating (208) the losses in the electrical drive chain (1) for a range of voltages between the minimum voltage and a maximum voltage corresponding to, at most, the maximum voltage setpoint, selecting (210) an optimal voltage to be applied at the input of the electrical inverter (5), the optimal voltage corresponding to the voltage for which the losses in the electrical drive chain (1) are the lowest, and calculating (212) the duty cycle to be applied to the step-down converter (6) on the basis of the selected optimal voltage.
H02P 27/08 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p. ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs avec modulation de largeur d'impulsions
H02M 1/00 - Détails d'appareils pour transformation
H02M 7/501 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande les tensions de sortie sinusoïdales étant obtenues par la combinaison de plusieurs impulsions de tension d'amplitude et de largeur différentes
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
8.
METHOD FOR SURFACE CONTRAST LASER MARKING OF ANODIZED ALUMINUM OR ALUMINUM ALLOY PARTS
A method for marking the surface of an aluminum or aluminum alloy part includes an anodizing step, a sealing step, and a marking step that uses a fiber laser beam. The marking method may be used for the manufacture or marking of aluminum or aluminum alloy parts intended for the aeronautical, aerospace, automotive, railway, watchmaking, medical, nuclear and oil industries.
The invention relates to a fuel boost system (1) for a fuel circuit, the system comprising: - a hydraulic subassembly (2) comprising a rotary part capable of circulating the fuel (C), which part is mounted in a first chamber (E1); - an electric motor (3) capable of driving the hydraulic subassembly (2); - a driven rotor (4) mechanically coupled to the rotary part of the hydraulic subassembly (2) and mounted in the first chamber (E1) and; - a driving rotor (6) mechanically coupled to a rotor of the electric motor (3) and mounted in a second chamber (E2), the driving rotor (6a) and the driven rotor (4a) being magnetically coupled.
A device deices an aerodynamic profile that has a lower surface, a plurality of unitary cavities delimited by a lattice of partitions on the lower surface, and a barrier arranged on the lattice of partitions. The surface includes a first plurality of holes which connect the unitary cavities to a device for generating a negative pressure in the cavities simultaneously so as to press the barrier onto the lattice of partitions. A second plurality of holes connect the unitary cavities to a device for generating one or more pressure pulses in at least some of the selected unitary cavities. The barrier is equipped with one or more resistive networks positioned below the barrier in line with some of the cells in order to create localized electrothermal deicing zones in the device.
The invention relates to a de-icing system (101) capable of de-icing a surface (103) of an aircraft (105), the system comprising a fluid circuit (119) that comprises at least: ‐ a pressurised tank (113); ‐ at least one pneumatic de-icing device (109), ‐ at least one first switching means (115); ‐ at least one second switching means (117); and ‐ a pressurised fluid distribution device (111) configured to bring about: o the delivery of a pressurised fluid to the pneumatic de-icing device (109) via the pressurised tank (113) and the switching means (115); and/or o the removal of the pressurised fluid from the pneumatic de-icing device (109) via the first switching means (115) and the second switching means (117).
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
The invention relates to an operability indicator device (200) configured to be fitted to a packaging box inside which there is a bag (50) containing a vacuum-packed item of safety equipment, in particular a protective hood, this operability indicator device comprising: - a viewing port (201); - a flag member (202) comprising a visual operability indicator (203) and a visual inoperability indicator (204), this flag member being movable between a nominal position in which the visual operability indicator is visible through the viewing port and a warning position in which the visual inoperability indicator (204) becomes visible through the viewing port and replaces the visual operability indicator, the flag member (202) further comprising a bearing face (210) against which, upon the inflation of this bag inside the packaging box, the bag presses and causes the flag member to move from the nominal position to the warning position.
The invention relates to a cartridge (25) for capturing CO2, the cartridge being configured to adsorb the CO2 from a user's breath, this cartridge comprising: a storage space (60) for an adsorbent product (P) capable of adsorbing CO2, this product being in the form of grains, in particular soda lime, the storage space (60) comprising a bottom (63) and an opening (61) opposite this bottom, a compression member (62) arranged on the side of the opening (61) in the storage space (60), which compression member is movable in the storage space (60) towards the bottom and configured to tamp down the adsorbent product in the form of grains against the bottom of the storage space (60), a spring (65) configured to exert a force on the compression member (62) tending to push the compression member (62) towards the bottom of the storage space (60).
The invention relates to a protective hood (1) in a bag, in particular a vacuum bag, the hood comprising: - a flexible shell (2) configured to be stored in a folded state and to be pulled, in an unfolded state, through an open base (3) of the flexible shell and over the head of the user; - a visor (7); - an articulated device rigidly attached to the open base and configured to be placed around the neck of the user when the flexible shell is pulled over the head of the user, the articulated device comprising at least two rigid portions connected by a joint that allows these two rigid portions to transition from a folded position, which prevents the head of the user from entering the hood (1), to an unfolded position, which allows the head of the user to enter the hood; - a handle (10) rigidly attached to the flexible shell, this handle being placed on top of the flexible shell (2) in such a way as to be accessible to the user when the flexible shell is in the folded state.
The invention relates to an ejector (1) comprising an ejector body (2) and a nozzle (3) with a tubular body (11) housed inside the ejector body (2) and having a fluid inlet (12) in an upstream portion (11a) and a fluid outlet (13) in a downstream portion (11b) spaced apart from the ejector body (2), the nozzle (3) comprising an inner duct (14) housed inside the tubular body (11) and spaced apart from the tubular body (11), a downstream end of the inner duct (14) opening at the fluid outlet (13) of the nozzle (3).
F04F 5/00 - Pompes à jet, p. ex. dispositifs dans lesquels le flux est produit par la chute de pression causée par la vitesse d'un autre fluide
F04F 5/24 - Pompes à jet, p. ex. dispositifs dans lesquels le flux est produit par la chute de pression causée par la vitesse d'un autre fluide le fluide inducteur étant un fluide compressible déplaçant des liquides, p. ex. contenant des solides ou bien déplaçant des liquides et des fluides compressibles
The invention relates to an in-flight refueling device (100), in particular for a refueling aircraft (118), comprising a pipe (102) intended for transferring a fluid, comprising - a first end (102a) able to be connected to a fluid source (106), and - a second end (102b) equipped with an in-flight refueling connection (108), characterized in that it further comprises a light system (114) arranged along at least part of the pipe (102) and comprising at least one series of radiation sources (120) distributed along that part of the pipe (102).
The invention relates to a guillotine system (114), in particular for an in-flight refueling device (100), comprising - a passage (124) through which a pipe (102) is able to pass, - a blade (126) movable between a first position in which the pipe (102) is able to slide freely through the passage (124), and a second position in which the blade (126) is able to cut the pipe (102), the guillotine system (114) further comprising an actuator (128) of the non-pyrotechnic type configured to contain and/or generate a pressurized fluid released to move the blade (126) from the first position to the second position.
The invention relates to a buoyancy system (2) intended to be connected to a structure (4) of an aircraft (1), comprising roll (R) stabilization means (7), having at least one floating mat (10) intended to be deployed on a water surface (9) in order to reduce a roll movement (R) of the aircraft (1).
The invention relates to a computer-implemented method for verifying the swell stability of a buoyancy system (2) comprising at least one float (3) intended to ensure the buoyancy of an associated means of transport (1), comprising steps of: - two-dimensional digital finite-element simulation of a two-dimensional fluid domain comprising at least one two-dimensional liquid domain representative of an irregular swell of given spectrum, - selection of critical swell times, - verification of swell stability via three-dimensional digital finite-element simulation of a three-dimensional model representative of the float (3) and of the associated means (1) in a three-dimensional fluid domain comprising at least one three-dimensional liquid domain representative of a selected critical swell time.
B64C 35/00 - Hydravions à coqueHydravions à flotteurs
G06F 30/23 - Optimisation, vérification ou simulation de l’objet conçu utilisant les méthodes des éléments finis [MEF] ou les méthodes à différences finies [MDF]
A method for controlling an anti-icing device protecting at least one outer surface of an aircraft, the device being provided with at least one anti-icing means (5, 6) and with a means (4) for measuring the ice accretion rate, comprising steps of determining at least one parameter for the activation of the at least one anti-icing means (5, 6) as a function of the ice accretion rate determined by the measurement means (4), in order to prevent the accretion of ice on the at least one outer surface to be protected or in order to reduce the thickness of ice accreted on the at least one outer surface to be protected.
B64D 15/22 - Mise en action automatique par détecteur de givrage
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
21.
COMMUNICATION METHOD FOR A SENSOR COMPRISING A MEMORY
The invention relates to a communication method for a control system having a sensor comprising an analogue component and a digital component. The communication method comprises: - a step of transmitting an analog signal, during a first time interval (T1); - a step of receiving a response; - a step of transmitting a digital interrogation signal of the digital component, during a third time interval (T3); and - a step of receiving a digital response signal from the digital component, during a fourth time interval (T4). The analog signal varies within a range of voltages extending between a lower bound and an upper bound, the digital interrogation signal has a high interrogation voltage, the digital response signal has a high response voltage, and the high interrogation voltage and the high response voltage are greater than the upper bound of the analog signal.
The invention relates to a sensor (24) for measuring at least an amount and/or density of a fuel (18) in an aircraft tank (10), comprising: - at least one probe (26), which is configured to measure at least the amount and/or density of the fuel, and intended to be placed in an internal space (16) of the tank (10); - a memory (38), placed in the internal space (16) and configured to store at least values of calibration parameters of the probe (26); and - a single communication bus, intended to connect the probe (26) and the memory (38) to remote measurement electronics (20), via a harness (22) passing through a wall (14) of the tank (10).
G01F 23/263 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme en mesurant des variables physiques autres que les dimensions linéaires, la pression ou le poids, selon le niveau à mesurer, p. ex. par la différence de transfert de chaleur de vapeur ou d'eau en mesurant les variations de capacité ou l'inductance de condensateurs ou de bobines produites par la présence d'un liquide ou d'un matériau solide fluent dans des champs électriques ou électromagnétiques en mesurant les variations de capacité de condensateurs
G01N 27/22 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant l'impédance en recherchant la capacité
G06F 13/42 - Protocole de transfert pour bus, p. ex. liaisonSynchronisation
23.
METHOD FOR DISCRIMINATING ICING CONDITIONS BY MACHINE LEARNING
One aspect of the invention relates to a computer-implemented method (10) for discriminating icing conditions in an environment of an aircraft, the aircraft having an on-board ice accumulation sensor (20), the method (10) comprising, in each current measurement cycle of a plurality of measurement cycles: - acquiring (13) data from the ice accumulation sensor (20) for the current measurement cycle; - classifying (14) the data acquired for the current measurement cycle, by a machine learning algorithm, into one of a plurality of classes comprising at least: - a first class representative of a first icing condition in the environment of the aircraft and - a second class representative of a second icing condition in the environment of the aircraft.
The invention relates to a system (1) for de-icing a part (4), in particular a blade (4), comprising - a main surface (2) intended to cover a first face (5) of the part (4), capable of de-icing the first face (5), and - a protective surface (3), in particular folded with respect to the main surface (2), intended to cover a second face of the part (4), in particular opposite the first face (5), the main surface (2) and the protective surface (3) being formed by the same part and being in material continuity with one another.
The invention relates to an electrically insulating composite material (40), characterized in that said material is a composite material comprising a matrix (42) made of an elastomer or polymer, and inclusions (41) providing the material with a thermal conductivity greater than 0.6 W/m.K at room temperature, in particular greater than 1.5 W/m.K at room temperature.
H01B 3/12 - Isolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances inorganiques céramiques
H01B 3/30 - Isolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques matières plastiquesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques résinesIsolateurs ou corps isolants caractérisés par le matériau isolantEmploi de matériaux spécifiés pour leurs propriétés isolantes ou diélectriques composés principalement de substances organiques cires
26.
ICE PROTECTION MAT, IN PARTICULAR FOR AN AIRCRAFT PART AND METHOD FOR INSTALLING SAME
The invention relates to an ice protection mat (1) for a part (BA), in particular an aircraft part (BA), which mat comprises a multilayer structure with at least one heating layer (3) capable of generating a heat flux, a contact layer (2) forming at least one thermal barrier between the heating layer (3) and the part (BA), and at least one intermediate layer (4) and/or reinforcing layer (5) and/or outer layer (6) which is/are thermally conductive and arranged between the heating layer (3) and an external environment.
The invention relates to an ice protection mat (1) for at least one part (BA), in particular an aircraft part (BA), which mat comprises at least one heating layer (3), in particular incorporating at least one heating resistor, and at least one reinforcing layer (5) positioned between the heating layer (3) and an external environment, characterised in that the reinforcing layer (5) has a thermal conductivity perpendicular to a general plane of extension of the reinforcement (5) greater than 0.6 W/m.K. at ambient temperature.
The invention relates to a fuel system for an aircraft (1) comprising at least one wing tank (5a) having at least one manifold (7), a transfer system, able to supply the manifold (7) with fuel, and a filling system, able to introduce fuel into the fuel system from an external source of fuel, comprising a filling connector (22) connected to the wing tank (5a) by at least one main filling line (23), and a mixing device (28), able to mix fuel present in the manifold (7) and fuel introduced at the filling connector (22).
A configuration server generates configuration information of a multi-system platform including hardware and software resources shared by different functional systems of an aircraft or spacecraft. The configuration server includes a connection module, adapted to establish a remote connection with a plurality of configuration clients, a storage unit (110) adapted to store configuration information relating to the hardware and/or software resources allocated to each functional system, and a system configuration module (112) accessible by means of different system configuration profiles associated respectively with the different functional systems, adapted to generate configuration information for a functional system associated with the system configuration profile used for connection between the connection module and a configuration client, according to the hardware and/or software resources allocated to said functional system.
A control valve, in particular for an aircraft turbine engine, includes a movable seal which is carried by a rod that passes through ports of a body of the valve. Sealing means are mounted in each of these ports. The sealing means include a tubular bellows mounted around the rod, a ring mounted around the rod and the tubular bellows and at least partially housed in one of the ports, and a washer mounted around the rod. The washer is inserted between the tubular bellows and one end of the ring which bears against the bottom of said port.
F16K 1/226 - Forme ou disposition du joint d'étanchéité
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gazCommande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
F16K 1/22 - Soupapes ou clapets, c.-à-d. dispositifs obturateurs dont l'élément de fermeture possède au moins une composante du mouvement d'ouverture ou de fermeture perpendiculaire à la surface d'obturation à éléments de fermeture articulés à pivot comportant disque ou volet pivotant dont l'axe de rotation traverse le corps de soupape, p. ex. régulateurs à papillon
The invention relates to a drain (10) comprising: − a body (11) having at least one fluid intake opening (12, 15) and at least one fluid discharge opening (13), − a valve (30) provided with at least one lug (37), and − a disengagement device (43) comprising: o - a fixed guide (44), able to be mounted so as to be fixed with respect to a body (11), o - a movable guide (45), comprising at least one housing (38) for receiving the lug (37), o the fixed guide (44) and/or the movable guide (45) comprising at least one projection (48) and/or at least one recess (49), in particular having a shape complementary to the projection (48), and o a pressure spring (50), able to bias the movable guide (45) against the fixed guide (44) so that the projection (48) cooperates with the recess (49).
The invention relates to a ball joint (12) for the piping (6) of an engine intended to connect a first and a second fluid flow pipe (8, 10) to one another, which ball joint is provided with an annular casing (14) comprising an internal element (30) and an external element (34) that are intended to be mounted on the first and second flow pipes (10), an annular bearing (18) arranged transversely between the internal element (30) and the external element (34) in contact with the internal element (30) and the external element (34), and a metal bellows (16) provided with a first end (22) that is rigidly attached to the internal element (30) and with a second end (26) opposite the first end (22) that is rigidly attached to the external element (34), the bellows (16) comprising a stack of five metal layers (20).
F16L 27/073 - Raccords universels, c.-à-d. avec une liaison mécanique permettant un mouvement angulaire ou un réglage des axes des parties raccordées dans une direction quelconque avec surfaces de contact partiellement sphériques et joints particuliers entre les surfaces de contact l'une des surfaces de contact formant en même temps moyen d'étanchéité
The invention relates to a gas separation system (1), comprising: - a gas separation unit (2) comprising a body (3) having - at least one gas inlet (4), - at least one gas outlet (5, 6), and - at least one gas separation membrane (7), capable of being arranged in the body (3) between the gas inlet (4) and the gas outlet (5, 6); and - a filtering member (8), capable of being arranged upstream of the gas separation membrane (7), in particular upstream of the gas separation unit (2). Furthermore, the gas separation unit (2) and/or the filtering member (8) comprises at least one sensor (20, 21, 22) of a parameter of the gas passing through the gas separation membrane (7).
B01D 53/22 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par diffusion
One aspect of the invention relates to a method (100) for selecting an activation logic of an inerting system (3122) of at least one fuel tank of an aircraft (31) for at least one mission of the aircraft (31), the method (100) comprising the following steps: - transmitting (101) data relating to the preparation of the mission to a computer (32); - estimating (102), by the computer (32), a plurality of N risks of flammability of the fuel contained in the fuel tank, N being a non-zero natural number, each risk of flammability being estimated from: - a single activation logic of the inerting system selected from among a plurality of N activation logics of the inerting system (3122); and - data relating to the preparation of the mission; - selecting (103) an activation logic, from among the plurality of N activation logics, on the basis of the plurality of N estimated flammability risks and on the basis of a condition relating to the inerting system (3122).
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
36.
POWER CONVERTER, IN PARTICULAR FOR AN AIRCRAFT, AND ASSOCIATED METHODS
The invention relates to an electrical power converter (2) for supplying power to an electric load (3), in particular of an aircraft (1), comprising - a supply module (5); - at least one main switching arm (18, 19, 20) comprising a first main switch (21) and a second main switch (22); - at least one intermediate connection (29, 30, 31) arranged between the first main switch (21) and the second main switch (22) and intended to be connected to one phase (35, 36, 37) of the electric load (3); - an auxiliary circuit (7) comprising at least one control line (41, 42, 43) comprising at least one switching cell (44, 45, 46). The switching cell (44, 45, 46) comprises at least one auxiliary switch (62), particularly an auxiliary switch (62) made of silicon carbide or of gallium nitride.
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
The invention relates to a respiratory system (1), in particular for an aircraft, comprising a distribution member (20, 30), suitable for delivering a gas mixture to at least one occupant, a gas mixture inlet (11) connected to a source (12) of breathable gas, comprising a gas mixture intake valve (13), intended to regulate a proportion of breathable gas in the gas mixture, a diluent gas inlet (31), able to be connected to a source of diluent gas, comprising a diluent gas inlet valve (32), intended to regulate a proportion of diluent gas in the gas mixture, at least one sensor (15, 35), suitable for measuring information representative of a proportion of breathable gas in the gas mixture delivered by the distribution member (20, 30), and a control system (40), configured to regulate the proportion of breathable gas delivered as a function of the measured information and to control the gas mixture intake valve (13) and the diluent gas inlet valve (32) as a function of the proportion of breathable gas delivered and of a desired proportion of breathable gas.
A respiratory system, in particular for an aircraft, comprising: - a remote controller (1) comprising: o a chamber (102), o a gas mixture inlet (100), opening into the chamber (102) via an intake valve (101), and o a gas mixture outlet (103) opening into the chamber (102), and o a means (104) for regulating a pressure in the chamber (102), - a breathing mask (3) comprising a pressure sensor (304), suitable for measuring a pressure in an internal space (305), - a pipe (2) connecting the gas mixture outlet (103) to the mask (3), - an inlet valve (303), suitable for delivering a diluent gas into the internal space (305), and - a control system (4) connected to the pressure sensor (304) and to the regulating means (104) and configured to control the intake valve (101) and/or the diluent gas inlet valve (303).
F16K 17/04 - Soupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage ouvrant sur excès de pression d'un côtéSoupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
F16K 31/528 - Moyens mécaniques d'actionnement à manivelle, excentrique ou came à ergot et encoche
40.
PRESSURE VALVE PROVIDED WITH A ROTARY VALVE MEMBER
The present invention relates to a pressure valve (10) comprising: - a body (11) having • a fluid inlet opening (12) and • a fluid discharge opening (13), - a valve member (18) provided with a stem (19) mounted movably in an axial direction with respect to the body (11) between • a closed position, in which the valve member (18) bears against a valve seat (15), and • an open position, in which the valve member (18) is moved away from the valve seat (15). More specifically, the pressure valve (10) further comprises at least one fin (41) arranged upstream of the valve member (18) and intended to generate rotation of the valve member (18) when a fluid passes from upstream to downstream through the body (11) from the fluid inlet opening (12) towards the fluid discharge opening (13).
F16K 17/04 - Soupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage ouvrant sur excès de pression d'un côtéSoupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
F16K 31/528 - Moyens mécaniques d'actionnement à manivelle, excentrique ou came à ergot et encoche
This device for guiding piping comprises a bearing (3) made of a material with a low coefficient of friction and configured to encircle a pipe of the piping, an insert (5) radially encapsulating the bearing (3), at least one elastic means (15) radially surrounding the insert (5), and a shell (19) positioned around said bearing (3), elastic means (15) and insert (5).
F16L 3/18 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger permettant un mouvement selon l'axe
F16L 3/21 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger permettant un mouvement latéral avec des ressorts supportant les tuyaux la force de support des ressorts étant constante
01 - Produits chimiques destinés à l'industrie, aux sciences ainsi qu'à l'agriculture
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
Produits et services
Chemical products for use in industry; chemical compositions
for surface coatings other than paints; water resistant
protective coatings for surfaces [chemicals, except paints];
chemical preparations intended for use in the manufacture of
surface coatings; chemicals intended for treating metals. Treating common metals and their alloys; treatment of metals
and all mechanical, thermo-mechanical or chemical processing
of the properties and characteristics of metals; treating
materials, namely, treating anode surfaces on aluminum;
treatment of materials using chemicals; treatment and
coating of metal surfaces; providing information with
respect to treatment of materials.
43.
DISPOSITIF DE GUIDAGE AMORTISSANT D'UNE TUYAUTERIE
F16L 3/18 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger permettant un mouvement selon l'axe
F16L 3/21 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger permettant un mouvement latéral avec des ressorts supportant les tuyaux la force de support des ressorts étant constante
44.
COMMUNICATION ASSEMBLY, AIRCRAFT PROVIDED WITH THE COMMUNICATION ASSEMBLY AND METHOD FOR PREVENTING INTERFERENCE IN COMMUNICATIONS
A communication assembly for avoiding interferences due to oxygen flow noise, including a) a breathing mask having a body having a face shell having a breathing cavity and a regulator delivering a breathing gas, b) a microphone configured to capture a sound signal in the breathing cavity, c) a test button for supplying the breathing cavity with breathing gas, d) an attenuation device, e) a sound monitoring system, f) a controller configured to the attenuation device operate in an active mode when a flow noise though the breathing cavity during inhalation by the user is detected, and an inactive mode when a vocal sound or a flow noise in the breathing cavity in a stowed configuration is detected, and g) a transmitter for transmitting an output signal.
F16K 15/06 - Soupapes, clapets ou valves de retenue à corps de soupapes rigides guidés par tige-guide
F16K 17/04 - Soupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage ouvrant sur excès de pression d'un côtéSoupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
46.
NON-RETURN VALVE FOR AN AIRCRAFT GAS DISTRIBUTION SYSTEM, AND CORRESPONDING SYSTEM
The invention relates to a non-return valve for a gas distribution system of an aircraft, the valve comprising a valve component (9) provided with a control rod (10) for the valve component, the valve component being intended to slide along a first axis (X) between a closed position in which the valve component engages in use with a seat (11) of the distribution system and an open position in which the valve component is moved away from the seat, the valve comprising a first spring (12) arranged outside the control rod and tending in use to hold the valve component against the seat, the valve comprising an assembly comprising at least one weight (18) and a second spring (19) which are arranged at least partially inside the control rod, the spring being connected at a first of its two ends to the control rod and at a second of its two ends to the weight. The invention also relates to a corresponding system.
F16K 15/06 - Soupapes, clapets ou valves de retenue à corps de soupapes rigides guidés par tige-guide
F16K 17/04 - Soupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage ouvrant sur excès de pression d'un côtéSoupapes ou clapets de sûretéSoupapes ou clapets d'équilibrage fermant sur insuffisance de pression d'un côté actionnés par ressort
47.
METHOD FOR BONDING A LAYER OF ELASTOMERIC MATERIAL TO AN ALUMINIUM SUBSTRATE
B05D 3/14 - Traitement préalable des surfaces sur lesquelles des liquides ou d'autres matériaux fluides doivent être appliquésTraitement ultérieur des revêtements appliqués, p. ex. traitement intermédiaire d'un revêtement déjà appliqué, pour préparer les applications ultérieures de liquides ou d'autres matériaux fluides par des moyens électriques
B29C 65/64 - Assemblage d'un élément en matière autre que plastique avec un élément en matière plastique, p. ex. à force
48.
METHOD FOR BONDING A LAYER OF ELASTOMERIC MATERIAL TO AN ALUMINIUM SUBSTRATE
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
UNIVERSITE DU MANS (France)
Inventeur(s)
Soto Puente, Jorge Arturo
Poncin-Epaillard, Fabienne
Benyahia, Lazhar
Ji, Marisol
Briand, Valerie
Abrégé
The invention relates to a method for bonding a layer of elastomeric material (CE) to an aluminium substrate (SM), characterised in that it comprises carrying out the following steps: a) treating the surface (S) of the aluminium substrate (SM) so as to roughen it; b) treating the surface (S) by means of an argon plasma; c) exposing the surface (S) to a plasma, in the presence of a gaseous chemical precursor, the precursor being chosen from the epoxides, acrylics, alkenes, alkynes and imides, until a deposit of chemical species with a thickness of between 5 and 110 nanometres is obtained; d) placing the layer of elastomeric material (CE) in contact with the surface (S) of the aluminium substrate (SM); and e) vulcanising the layer of elastomeric material; said step c) being carried out at low pressure, i.e. under a pressure of between 10-2 and 10-5 mbar.
B29C 65/64 - Assemblage d'un élément en matière autre que plastique avec un élément en matière plastique, p. ex. à force
B05D 1/00 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces
B05D 3/14 - Traitement préalable des surfaces sur lesquelles des liquides ou d'autres matériaux fluides doivent être appliquésTraitement ultérieur des revêtements appliqués, p. ex. traitement intermédiaire d'un revêtement déjà appliqué, pour préparer les applications ultérieures de liquides ou d'autres matériaux fluides par des moyens électriques
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
01 - Produits chimiques destinés à l'industrie, aux sciences ainsi qu'à l'agriculture
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
Produits et services
(1) Produits chimiques destinés à l'industrie; compositions chimiques pour enduits de surface autres que peintures; revêtements de protection résistants à l'eau pour les surfaces [produits chimiques, à l'exception des peintures]; préparations chimiques destinées à la fabrication de revêtements de surface; produits chimiques destinés au traitement des métaux. (1) Traitement de métaux communs et de leurs alliages; traitement des métaux et toutes transformations mécaniques, thermomécaniques ou chimiques des propriétés et caractéristiques de métaux; traitement de matériaux, à savoir traitement de surfaces anodique sur aluminium; traitement de matériaux à l'aide de produits chimiques; traitement et revêtement de surfaces métalliques; mise à disposition d'informations en matière de traitement de matériaux.
01 - Produits chimiques destinés à l'industrie, aux sciences ainsi qu'à l'agriculture
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
Produits et services
Industrial chemicals, namely, chemical compositions for use as surface coatings other than paints; water-resistant chemical compositions used as protective coatings for surfaces, except paints; chemical preparations intended for use in the manufacture of surface coatings; chemicals intended for treating metals Treating common metals and their alloys; treatment of metals and all mechanical, thermo-mechanical or chemical processing of the properties and characteristics of metals; treating materials, namely, treating anode surfaces on aluminum; treatment of materials using chemicals; treatment and coating of metal surfaces; providing information with respect to treatment of materials
51.
DEVICE FOR DETECTING FROSTING INTENSITY FOR AN AIRCRAFT IN FLIGHT
A device for detecting a frosting intensity for an aircraft in flight includes a surface for collecting the frost and measuring means capable of measuring the thickness of the frost deposited on the frost collection surface. The device further includes calculation means configured to determine, at predetermined time intervals (Tsamp), the change in the thickness of the frost, and control means configured to generate an alarm signal when the difference in the thickness of the frost measured between two time intervals (Tsamp) is greater than a threshold value.
G01B 21/08 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la longueur, la largeur ou l'épaisseur pour mesurer l'épaisseur
B64D 15/20 - Dispositifs pour détecter le givrage ou amorcer la mise en action du dégivrage
A regulator assembly for an aircrew breathing mask is provided The regulator assembly includes a support, a mode selection knob movable between a first position, a second position and a third position, the mode selection knob comprising a base pivotably mounted on the support with respect to an axis of rotation, and a cover supported by the base. The cover can be movable relative to the base between a locked position of the mode selection knob and an unlocked position of the mode selection knob, the locked position locking the rotation of the mode selection knob from the second position to the third position, the unlocked position permitting rotation of the mode selection knob from the second position to the third position.
An aircraft includes an engine, a fuel tank, a chamber, a system, and an introduction line. The chamber is located in the tank, occupies only a part of the tank, and includes a sensor for measuring a property of the fuel. The system injects fuel into the line. The introduction line introduces fuel from the injection system into the chamber. The introduction line includes a valve capable of preventing an introduction of fuel from the injection system into the chamber via the line.
The present invention relates to an assembly for a tank comprising: an inner wall (1) delimiting a cavity (2) intended to receive a liquid, the inner wall (1) having a first surface (101) facing the cavity (2), and a second surface (102) opposite the first surface (101) with respect to the cavity (2); a sealing device (5) comprising a sealing layer (50) and a guide (51), the sealing layer (50) comprising a material, the sealing device (5) being fastened to the second surface (102) of the inner wall (1), the material being expansible when an opening (4) is formed in the inner wall (1), the guide (51) being configured to be fastened to the sealing layer (50) so as to exert a stress on the sealing layer (50) to control a direction of expansion of the sealing layer (50).
On board an aircraft, a method is perform in which the following steps are implemented in the following order: measuring a first density value, a first dielectric constant value and a first temperature value of the fuel at a first time, measuring a second density value, a second dielectric constant value and a second temperature value of the fuel, determining parameters of a function for calculating a density from a temperature or a dielectric constant, measuring a volume flow rate value and at least one of a third temperature value and a third dielectric constant value of the fuel in a fuel injection duct in the engine, and determining a density value of the fuel and a mass flow rate of the fuel in the injection line.
G01F 1/86 - Débitmètres massiques indirects, p. ex. mesurant le débit volumétrique et la densité, la température ou la pression
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor
01 - Produits chimiques destinés à l'industrie, aux sciences ainsi qu'à l'agriculture
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
Produits et services
Industrial chemicals; Surface coating compositions [chemicals], other than paints; Water resistant protective surface coatings [chemical, other than paints]; Chemical preparations for use in the manufacture of surface coatings; Chemicals for use in metal treatment. Processing of common metals and their alloys; Metal treating and Mechanical, thermo-mechanical or chemical changes of all kinds to the properties and characteristics of metals; Treatment of materials, namely Surface anodising of aluminium; Treatment of materials using chemicals; Treatment and coating of metal surfaces; Providing material treatment information.
57.
METHOD FOR SURFACE CONTRAST LASER MARKING OF ANODISED ALUMINIUM OR ALUMINIUM ALLOY PARTS
The invention relates to a method for marking the surface of an aluminium or aluminium alloy part, comprising at least the following steps: A) an anodising step; B) a sealing step; and D) a step of marking by means of a fibre laser beam. The invention also relates to the use of a marking method according to the invention for the manufacture or marking of aluminium or aluminium alloy parts intended for the aeronautical, aerospace, automotive, railway, watchmaking, medical, nuclear and oil industries.
A servovalve having a pilot stage includes two hydraulic elements that are movable relative to each other so as to move a power-directing member, the pilot stage including a linear actuator having a main pusher arranged to modify the relative position of the hydraulic elements. The pilot stage has a position feedback lever.
F15B 13/043 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique actionnés par la pression du fluide avec clapets-pilotes commandés électriquement
59.
SYSTEM FOR DETECTING LEAKS, IN PARTICULAR FOR A FUEL SYSTEM OF AN AIRCRAFT, AND METHOD FOR DETECTING A FUEL LEAK
The invention relates to a system (2) for detecting leaks from an aircraft engine, comprising: - a tank (10) having an outlet opening (18); - a piping system (12) comprising a main pipe (20) having a first portion (22) of pipe connected to the outlet opening of the tank and a second portion (26) of pipe connected to the fuel injection system of the combustion chamber; - a first sensor (28) capable of estimating an instantaneous flow rate of fuel leaving the tank; - a second sensor (30) capable of estimating an instantaneous flow rate of fuel entering the combustion chamber; - a controller (32) configured to calculate a difference between the instantaneous flow rate estimated by the first sensor and the instantaneous flow rate estimated by the second sensor for the presence of a leak in the main pipe.
Device for de-icing an aerodynamic profile (100), comprising a surface referred to as a lower surface, a plurality of unitary cavities (2a, 2b) delimited by a lattice of partitions (3a, 3b) on the surface, and a barrier arranged on the lattice of partitions, for which the surface comprises a first plurality of holes (5), which connect the unitary cavities to a device for generating a negative pressure in the cavities simultaneously so as to press the barrier onto the lattice of partitions, and a second plurality of holes (6), which connect the unitary cavities to a device for generating one or more pressure pulses in at least some of the selected unitary cavities, for which the barrier is equipped with one more resistive heating networks (8) positioned below the barrier in line with some of the cells (2b, 2c) in order to produce localized electrothermal de-icing zones in the device.
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
Device for de-icing an aerodynamic profile (100), comprising a surface referred to as a lower surface, a plurality of unitary cavities (2a, 2b) delimited by a lattice of partitions (3a, 3b) on the surface, and a barrier arranged on the lattice of partitions, for which the surface comprises a first plurality of holes (5), which connect the unitary cavities to a device for generating a negative pressure in the cavities simultaneously so as to press the barrier onto the lattice of partitions, and a second plurality of holes (6), which connect the unitary cavities to a device for generating one or more pressure pulses in at least some of the selected unitary cavities, for which the barrier is equipped with one more resistive heating networks (8) positioned below the barrier in line with some of the cells (2b, 2c) in order to produce localized electrothermal de-icing zones in the device.
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p. ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
A method for the surface treatment of a part made of aluminum or aluminum alloy, comprising an anodization step and a step of sealing with a silicate salt. Additionally, a surface treatment method according to the invention for manufacturing an aluminium or aluminium alloy part intended, in particular for use in the aviation sector.
C25D 11/08 - Anodisation de l'aluminium ou de ses alliages caractérisée par les électrolytes utilisés contenant des acides inorganiques
B05D 7/14 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers à du métal, p. ex. à des carrosseries de voiture
B05D 7/00 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers
63.
CONTROL ASSEMBLY FOR A BREATHING MASK OF AN AIRCRAFT CREW MEMBER
A control unit for an aircraft crew member's breathing mask, includes a support, a mode-selection knob pivotally mounted on a holder between at least a first position, a second position and a third position. A controller supplies a breathing cavity in three modes of operation depending on the position of the mode-selection knob. A locking/unlocking system includes an operating member moveable between a locking position and an unlocking position. The locking position blocks the rotation of the mode-selection knob from the second position to the third position, and the unlocking position allows rotation of the mode-selection knob from the second position to the third position.
Apparatus for supplying oxygen to a vehicle user, comprising a source of pressurized respiratory gas containing oxygen-enriched air, a flow-regulating and/or pressure-regulating unit, and at least one mask provided for supplying gas to the respiratory tract of said user, the regulating unit comprising at least one inlet connected to the source and at least one outlet connected to the mask, the regulating unit being configured to regulate the flow and/or the pressure of the respiratory gas supplied to the mask according to the respiratory demand of the user, the apparatus comprising at least one sensor measuring the pressure and/or the flow of respiratory gas delivered by the regulating unit to the mask, and an electronic data storage and processing unit configured to receive the measurements from the at least one sensor and to calculate, from these measurements, the frequency of the gas flows supplied to the mask and corresponding to the respiratory frequency of the user, to compare this calculated frequency against a threshold frequency and, when this calculated frequency is greater than the threshold frequency, to generate an audible and/or visual and/or vibratory warning signal.
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant pressurisé
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
A regulator assembly for an aircrew breathing mask includes a support and a mode selection knob mounted with the ability to pivot on the support. The selection knob is able to pivot between at least a first position, a second position and a third position. The mask further includes regulator designed to supply a breathing cavity at least in three modes of operation according to the position of the mode selection knob. At least one locking/unlocking device locks and unlocks the rotation of the mode selection knob towards the third position. The locking/unlocking device comprising has an operating member that pivots between a position in which the rotation of the mode selection knob is locked, and a position in which the rotation of the mode selection knob is unlocked.
09 - Appareils et instruments scientifiques et électriques
Produits et services
Optical fibers; fiber-optic couplings; fiber-optic
connections; light conducting filaments [optical fibers];
data processing apparatus; signal transmission apparatus;
photovoltaic apparatus for converting light into electrical
energy; apparatus and instruments for conducting, switching,
transforming, accumulating, regulating or controlling
electricity; interconnected system of sensors and data
concentrators using optical fiber for transporting energy
needed between sensors.
67.
Magnetic head for a magnetic detector for detecting metal particles, and magnetic detector provided with such a head
A magnetic head for a magnetic detector for detecting metal particles in a hydraulic circuit includes an axial body internally including at least one magnet, at least a first electrode defining an air gap zone located in the magnetic field created by the magnet, such that the circuit creates a particle alignment zone in the air gap, and an electrical connector for electrically connecting the electrodes. The magnet can be a diametrically magnetized magnet.
F01M 11/10 - Dispositifs indicateursAutres dispositifs de sécurité
F01M 1/10 - Systèmes de lubrification caractérisés par des dispositifs de ventilation ou d'épuration du lubrifiant, p. ex. des filtres
F16N 29/00 - Dispositifs particuliers dans les installations ou les systèmes de lubrification indiquant ou détectant des conditions indésirablesUtilisation des dispositifs sensibles à ces conditions dans les installations ou les systèmes de lubrification
A system for delivering breathing gas to passengers includes:
a face mask including a face part having a breathing cavity,
a tube configured to be supplied by pressurized breathing gas, and
a reservoir bag disposed between the tube and the face part. A passage connects the reservoir bag to the breathing cavity so that the system is configured to supply the breathing cavity through the reservoir bag. The reservoir bag includes a front portion and a back portion. The front portion is connected to the face mask, and the system has a stowed configuration and a deployed configuration. In the stowed configuration, the reservoir bag is maintained folded between a backing and the face part.
The present invention relates to a configuration server (11) for generating configuration information for a multi-system platform comprising hardware and software resources which are shared by different functional systems of an aircraft or space craft. Said server comprises: a connection module (111) suitable for establishing a remote connection to a plurality of configuration clients (12); a storage unit (110) suitable for storing configuration information relating to the hardware and/or software resources allocated to each functional system; a system configuration module (112) which is accessible by means of different system configuration profiles respectively associated with the different functional systems and which is suitable for generating configuration information for a functional system associated with the system configuration profile used for the connection between the connection module and a configuration client, on the basis of the hardware and/or software resources allocated to said functional system.
The present invention relates to a configuration server (11) for generating configuration information for a multi-system platform comprising hardware and software resources which are shared by different functional systems of an aircraft or space craft. Said server comprises: a connection module (111) suitable for establishing a remote connection to a plurality of configuration clients (12); a storage unit (110) suitable for storing configuration information relating to the hardware and/or software resources allocated to each functional system; a system configuration module (112) which is accessible by means of different system configuration profiles respectively associated with the different functional systems and which is suitable for generating configuration information for a functional system associated with the system configuration profile used for the connection between the connection module and a configuration client, on the basis of the hardware and/or software resources allocated to said functional system.
A head armature for a respiratory system includes a cradle and a retention mechanism. The cradle is configured to receive a respiratory mask assembly in a stand-by position. The retention mechanism is configured to detachably connect the respiratory mask assembly with the head armature such that the respiratory mask assembly is movable from the stand-by position to a use position while connected to the head armature and such that the respiratory mask assembly is selectively detachable from the head armature in a stand-alone configuration whereby the respiratory mask assembly is disconnected from the head armature. In the use position, the respiratory mask assembly is configured to provide oxygen to a user. The head armature is configured to be worn on a head of the user such that the cradle is between the respiratory mask assembly and the user's head when the respiratory mask assembly is in the stand-by position.
The invention relates to a stop barrier (BA) for an aircraft, comprising a set of elementary nets (1) arranged parallel to each other, each elementary net comprising a generally vertical stop structure (10) which extends between a first upper strap (2) and at least a second lower strap (3), said first and second straps each comprising two end portions (20) for connection to a braking device, the end portions (20) of either the upper and/or lower strap(s) comprising a slack intermediate section (21), i.e a section which is not tensioned and which forms an "excess length", and the barrier comprising an additional strap (6) the opposite ends (60, 61) of which are attached by connecting means to the corresponding ends of the slack intermediate section (21), the additional strap (6) comprising a region (62) in which it consists of two separate and contiguous strands (62A, 62B), the binding yarn, i.e. the weft or warp yarn of said additional strap (6) being common to the two strands (62A, 62B), the tear resistance of the binding yarn being lower than that of the connecting means.
Breathing apparatus (100) for aircraft including:
Breathing apparatus (100) for aircraft including:
a breathing mask (10) comprising an oronasal face cover (14) and a support (17), the oronasal face cover (14) having a cavity (13, 15) and the support (17) supporting a transparent lens (18) and comprising an upper edge portion (19a),
Breathing apparatus (100) for aircraft including:
a breathing mask (10) comprising an oronasal face cover (14) and a support (17), the oronasal face cover (14) having a cavity (13, 15) and the support (17) supporting a transparent lens (18) and comprising an upper edge portion (19a),
an inflatable harness (20) configured for extending around the user's head opposite the shell, the harness (20) comprising at least one rear portion,
Breathing apparatus (100) for aircraft including:
a breathing mask (10) comprising an oronasal face cover (14) and a support (17), the oronasal face cover (14) having a cavity (13, 15) and the support (17) supporting a transparent lens (18) and comprising an upper edge portion (19a),
an inflatable harness (20) configured for extending around the user's head opposite the shell, the harness (20) comprising at least one rear portion,
a guiding link (110) having an upper end (110a) and a lower end (110b), the upper end (110a) being linked to the upper edge portion (19a), the lower end (110b) being linked to the rear portion of the harness (20), and
Breathing apparatus (100) for aircraft including:
a breathing mask (10) comprising an oronasal face cover (14) and a support (17), the oronasal face cover (14) having a cavity (13, 15) and the support (17) supporting a transparent lens (18) and comprising an upper edge portion (19a),
an inflatable harness (20) configured for extending around the user's head opposite the shell, the harness (20) comprising at least one rear portion,
a guiding link (110) having an upper end (110a) and a lower end (110b), the upper end (110a) being linked to the upper edge portion (19a), the lower end (110b) being linked to the rear portion of the harness (20), and
a plate (120) linked to the lower end (110b) of the guiding link (110) and having an abutment face configured for contacting the oronasal face cover (14), facing the cavity (13).
A cell storage box for storing a battery cell includes a first end provided with a safety valve and a second end. The cell storage box includes a metal case having a bottom wall and side walls, and a thermally insulating support arranged in the metal case. The thermally insulating support includes a shoulder raised relative to the bottom wall of the metal case, a side bearing wall configured such that the cell rests against the at least one side bearing wall so as to keep the cell at a first distance from the at least one side wall of the metal case, and an opening arranged below the shoulder in order to allow smoke and gas to escape during a runaway of the cell.
H01M 50/289 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par des éléments d’espacement ou des moyens de positionnement dans les racks, les cadres ou les blocs
H01M 50/264 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports avec des moyens de fixation, p. ex. des serrures pour des cellules ou des batteries, p. ex. cadres périphériques, courroies ou tiges
Said device for detecting a frosting intensity (2) for an aircraft (1) in flight comprises a surface for collecting the frost and measuring means (4) capable of measuring the thickness of the frost deposited on the frost collection surface. The device comprises calculation means (6) capable of determining, at predetermined time intervals (Tsamp), the change in the thickness of the frost, and control means (7) capable of generating an alarm signal when the difference in the thickness of the frost measured between two time intervals (Tsamp) is greater than a threshold value.
On board the aircraft (2), the following steps are implemented in the following order: - measuring a first density value, a first dielectric constant value and a first temperature value of the fuel at a first time, - measuring a second density value, a second dielectric constant value and a second temperature value of the fuel - determining parameters of at least one function for calculating a density from a temperature or a dielectric constant, - measuring a volume flow rate value and at least one of a third temperature value and a third dielectric constant value of the fuel in a fuel injection duct in the engine (4), - determining a density value of the fuel and a mass flow rate (MD) of the fuel in the injection line.
The aircraft comprises: - at least one engine (4), - at least one fuel tank (6), - a chamber (22) which is located in the tank and which comprises at least one sensor (24, 26, 28) for measuring a characteristic of the fuel, - a system (8) for injecting the fuel into the engine, and - a pipe (32) for introducing fuel from the injection system into the chamber. The pipe comprises a valve (36) which can prevent the introduction of fuel from the injection system into the chamber via the pipe.
The aircraft comprises: - at least one engine (4), - at least one fuel tank (6), - a chamber (22) which is located in the tank and which comprises at least one sensor (24, 26, 28) for measuring a characteristic of the fuel, - a system (8) for injecting the fuel into the engine, and - a pipe (32) for introducing fuel from the injection system into the chamber. The pipe comprises a valve (36) which can prevent the introduction of fuel from the injection system into the chamber via the pipe.
On board the aircraft (2), the following steps are implemented in the following order: - measuring a first density value, a first dielectric constant value and a first temperature value of the fuel at a first time, - measuring a second density value, a second dielectric constant value and a second temperature value of the fuel - determining parameters of at least one function for calculating a density from a temperature or a dielectric constant, - measuring a volume flow rate value and at least one of a third temperature value and a third dielectric constant value of the fuel in a fuel injection duct in the engine (4), - determining a density value of the fuel and a mass flow rate (MD) of the fuel in the injection line.
A device for disconnection by a mechanical action includes at least one mechanical connection part, in particular a buckle held closed by spring action, linked to at least one trigger via at least one connecting member, and a release lever configured to be triggered by application of a force according to a predefined opening direction. The disconnect device also includes at least one guide for the connecting member configured to redirect an effort applied on the trigger, when opening is required, towards the mechanical connection part linked to the connecting member, according to the predefined opening direction.
The invention relates to a method for the surface treatment of a part made of aluminum or aluminum alloy, comprising an anodisation step and a step of sealing with a silicate salt. The invention also relates to the use of a surface treatment method according to the invention for manufacturing an aluminium or aluminium alloy part intended, in particular, for use in the aviation sector.
The invention relates to a method for the surface treatment of a part made of aluminum or aluminum alloy, comprising an anodisation step and a step of sealing with a silicate salt. The invention also relates to the use of a surface treatment method according to the invention for manufacturing an aluminium or aluminium alloy part intended, in particular, for use in the aviation sector.
A device for regulating breathing gas delivered to a user, comprising a gas circuit comprising a main line having at least an upstream end intended to be connected to at least one gas source and a downstream end intended to be connected to at least one user station such as a mask, the main line comprising at least one electromechanical control valve configured to regulate the gas pressure between the upstream and the downstream, the circuit comprising a secondary line comprising an upstream end intended to be connected to at least one gas source and a downstream end intended to be connected to the same user station(s), the secondary line comprising at least one auxiliary member for regulating the gas flow, the device comprising a switching system configured to control the flow of gas between the upstream and the downstream of the circuit via the main line or via the secondary line, characterized in that the auxiliary member for regulating the secondary line is a pneumatic pressure regulator.
The invention relates to a regulator assembly (1) for an aircrew breathing mask, said assembly comprising a support, a mode selection knob (20) mounted with the ability to pivot on the support, said selection knob (20) being able to pivot between at least a first position, a second position and a third position, a regulator designed to supply a breathing cavity at least in three modes of operation according to the position of the mode selection knob, and at least one locking/unlocking device able to lock and unlock the rotation of the mode selection knob towards the third position, the locking/unlocking device comprising an operating member (31) able to be pivoted between a position in which the rotation of the mode selection knob is locked, and a position in which the rotation of the mode selection knob is unlocked.
The invention relates to a regulator assembly for an aircrew breathing mask, said assembly comprising a support, a mode selection knob mounted with the ability to pivot on the support, said selection knob being able to pivot between at least a first position (EMER), a second position (100%) and a third position (N), a regulator designed to supply a breathing cavity in three modes of operation according to the position of the mode selection knob, and a locking/unlocking device comprising an operating member able to be moved between a locking position and an unlocking position, the locking position locking the rotation of the mode selection knob from the second position (100%) toward the third position (N); the unlocking position allowing the rotation of the mode selection knob from the second position (100%) toward the third position (N).
A data transmission system including an emitting device, a receiving device and a communication link, wherein the emitting device includes: a radio frequency emitter connected to the communication link; a power line connected to the communication link at a connection point, wherein the power line is brought to a supply voltage; and a capacitive coupling component connected between the radio frequency emitter and the connection point, wherein the receiving device includes: a radio frequency receiver connected to the communication link for receiving the radio frequency signal; a power line connected to the communication link at a connection point; and a capacitive coupling component connected between the connection point and the radio frequency receiver, wherein the capacitive coupling components transmit the radio frequency signal and block the supply voltage.
H04B 1/38 - Émetteurs-récepteurs, c.-à-d. dispositifs dans lesquels l'émetteur et le récepteur forment un ensemble structural et dans lesquels au moins une partie est utilisée pour des fonctions d'émission et de réception
H04B 3/54 - Systèmes de transmission par lignes de réseau de distribution d'énergie
H04B 3/56 - Circuits de couplage, blocage ou dérivation des signaux
H04M 11/04 - Systèmes de communication téléphonique spécialement adaptés pour être combinés avec d'autres systèmes électriques avec systèmes d’alarme, p. ex. systèmes d’alarme d'incendie, de police ou systèmes antivol
Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.
An emitting device includes: an oscillator configured for generating at least one carrier wave; an emitter including: at least one input connected to the oscillator; an activation input configured for receiving a signal representative of data to be transmitted; at least one output configured to generate a carrier wave modulated by the signal representative of the data to be transmitted; a communication link connected to the output of the emitter; a power line connected to the communication link at a connection point; a capacitive coupling component connected between the output of the emitter and the connection point. A receiving device and a system for transmission are also described.
A device for unlocking a system for closing a container by means of a tie, such as a rope or strap, in particular a tie tensioned between closing eyelets, includes a cutting tool (O) capable of cutting the tie in order to unlock the closing system. It also includes an actuation member linked to the cutting tool, the actuation member being capable of being manipulated manually by a user in order to cause the cutting tool (O) to move into a position for severing the tie.
The invention relates to a fluid nonreturn device (1) comprising a body (2) defining a chamber (5) intended to receive a fluid and having at least one opening (3), the chamber (5) has an internal wall (6) extended by an elastic return member (8) which forms an integral part of said internal wall (6), said elastic return member (8) is extended by a valve shutter (9) forming an integral part of said elastic return member (8), the elastic return member (8) pushes the valve shutter (9) into a position in which it closes off the opening (3) so as to prevent the fluid in the chamber (5) from leaving via the opening (3).
Dispositif de raccord 1 rapide de transfert de liquide pour aéronef, comprenant un organe femelle 7 configuré pour être relié à un premier réservoir, ledit organe femelle 7 formant un passage et comprenant une partie cylindrique 13 et une partie radiale 14, un organe mâle 2 configuré pour être relié à un deuxième réservoir, ledit organe mâle 2 formant un passage, monté à coulissement de manière étanche aux liquides dans l'organe femelle 7 et comprenant une partie cylindrique 3 et une partie radiale 4, et un organe de verrouillage 40 de l'organe mâle 2 dans l'organe femelle 7, l'organe de verrouillage 40 étant disposé entre la partie radiale 14 de l'organe femelle 7 et la partie radiale 4 l'organe mâle 2, l'organe de verrouillage 40 entourant l'organe mâle 2 et laissant une course limitée de coulissement à l'organe mâle 2 par rapport à l'organe femelle 7, venant en prise avec l'organe femelle 7 en position verrouillée et libérant l'organe femelle 7 en position déverrouillée, l'organe de verrouillage 40 comprenant un verrou de blocage axial actionnable par un mouvement axial puis rotatif et libérable par un mouvement axial puis rotatif, et un frein de rotation, le verrou et le frein étant actifs en position verrouillée.
F16L 37/10 - Accouplements du type à action rapide dans lesquels l'assemblage entre les extrémités s'aboutant ou se chevauchant est maintenu par des organes de blocage utilisant sur une partie un manchon ou segment externe rotatif
F16L 37/24 - Accouplements du type à action rapide dans lesquels l'assemblage est réalisé par insertion selon l'axe d'un organe dans l'autre organe et en le faisant tourner d'une amplitude limitée, p. ex. comme dans un raccord à baïonnette
F16L 37/40 - Accouplements du type à action rapide avec moyens pour couper l'écoulement du fluide avec un obturateur dans une seule des deux extrémités de tuyau avec un clapet dont l'ouverture se fait automatiquement au moment de l'accouplement
F16L 37/60 - Accouplements du type à action rapide avec un connecteur mâle et une prise fixée sur une paroi
Quick coupling device 1 for transferring liquid for an aircraft, comprising a female member 7 configured to be connected to a first reservoir, said female member 7 forming a passage and comprising a cylindrical portion 13 and a radial portion 14, a male member 2 configured to be connected to a second reservoir, said male member 2 forming a passage, slidably mounted in a liquid-tight manner in the female member 7 and comprising a cylindrical portion 3 and a radial portion 4, and a member 40 for locking the male member 2 in the female member 7, the locking member 40 being disposed between the radial portion 14 of the female member 7 and the radial portion 4 of the male member 2, the locking member 40 surrounding the male member 2 and leaving a limited sliding extent for the male member 2 with respect to the female member 7, engaging with the female member 7 in the locked position and releasing the female member 7 in the unlocked position, the locking member 40 comprising an axial blocking lock that can be actuated by an axial then rotating movement and that can be released by an axial then rotating movement, and a rotation brake, the lock and the brake being active in the locked position.
F16L 37/084 - Accouplements du type à action rapide dans lesquels l'assemblage entre les extrémités s'aboutant ou se chevauchant est maintenu par des organes de blocage combinés à un verrouillage automatique
F16L 37/50 - Accouplements du type à action rapide réglablesAccouplements du type à action rapide permettant un déplacement des parties raccordées
A respiratory equipment for an aircraft, a pilot or first officer of the aircraft forming a user of the respiratory equipment, the respiratory equipment comprising a head armature, configured to be worn on the user's head, a respiratory mask configured to be applied, in a use position around the mouth and nose of a user, an inflatable harness configured to be coupled to a pressurized gas source, an inflation of the inflatable harness causing an extension of the inflatable harness such that the respiratory mask can be brought opposite the mouth and nose of a user, and a purge of the inflatable harness causing a constrained application of the inflatable harness against the mouth and nose of a user, wherein the head armature comprises at least an occipital member, and a front cradle for receiving and lodging the respiratory mask in a waiting position, wherein the inflatable harness is fixed to the occipital member and the inflatable harness is coupled to the respiratory mask.
An inflatable device for aircraft buoyancy, configured to be inflated in case of emergency landing on water, the device comprising a first inflatable chamber configured to be inflated from a source of gas, to change from a folded state to an inflated stated, a plurality of second inflatable chambers, each configured to be supplied from gas flowing in the first chamber, via at least one supply passage, each second inflatable chamber configured to be inflated to change from a folded state to an inflated stated, wherein each supply passage comprises a check valve.
The invention relates to a battery storage housing (4) able to store a battery (12) having a first end (14) provided with a safety valve (16) and a second end (18), said housing comprising: - a metal casing (20) comprising a bottom wall (32) and side walls (34); and - a thermally insulating support (22) arranged in the metal casing (20), said support comprising: - a shoulder (52) that is raised with respect to the bottom wall (32) of the casing; - a lateral bearing wall (55), said battery (12) bearing against said lateral bearing wall (55) so as to hold the battery (12) at a first distance from the lateral wall (34) of the casing, - an opening (56) arranged below the shoulder (52) to allow issuing smoke and gas to escape in the event of runaway of the battery.
The invention relates to a system (1) for holding a cable (2), comprising: - a body (3) forming a passage (4), in which the cable (2) can be at least partially housed, said body comprising a male connection, and - a support (5) comprising a female connection (6) capable of cooperating with the male connection so as to mechanically connect the body (3) to the support (5).
F16L 3/137 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers entourant pratiquement le tuyau, le câble ou le conduit de protection comportant un élément entourant pratiquement le tuyau, le câble ou le conduit de protection l'élément consistant en une bande flexible
B60R 16/02 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques
F16L 3/22 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p. ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace
H02G 3/32 - Installations de câbles ou de lignes sur les murs, les sols ou les plafonds utilisant des colliers de fixation
98.
Inert gas generator for an inerting system of an aircraft system of an aircraft fuel tank, and inerting method
A generator of inert gas from an airflow, in an inerting system for at least one aircraft fuel tank is disclosed. The generator includes a system with an air inlet and means for distributing the airflow to a plurality of air separation modules arranged in parallel on the air system to deplete oxygen in the air and generate a nitrogen-enriched inert gas at the outlet. The generator also includes a programed control unit for the distribution means to selectively supply air to a single, a portion or all of the air separation modules, depending on the flight phase of the aircraft.
B01D 53/30 - Commande par appareil d'analyse des gaz
B01D 53/22 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par diffusion
B64D 37/32 - Mesures de sécurité non prévues ailleurs, p. ex. contre les explosions
99.
REPAIRABLE HERMETICALLY SEALED CONNECTOR FOR COUPLING OPTICAL FIBRES
This connector for the sealed coupling of optical fibres (20), able to couple fibres in a sealed manner, comprises a body of which the internal part comprises a cylindrical insert (27) equipped internally with longitudinal ducts, an optical-connection device comprising, for each optical fibre, a cylindrical ferrule (22) which is pierced for the passage of the core of the fibre, a ferrule-holder (28) intended to be connected to the end of the fibre, to be inserted into a longitudinal duct of the body and to provide the mechanical connection between the ferrule and the insert (27), and an assembly of at least one O-ring seal (31) provided between the ferrule-holder (28) and the insert, characterized in that the optical-connection device comprises, for each optical fibre, assembly means (34) for assembling the ferrule-holder on the body, the assembly means acting on each ferrule-holder separately.
This invention relates to a generator (1) of inert gas from an airflow, in an inerting system for at least one aircraft fuel tank, the generator (1) comprising a system with an air inlet and means (5) for distributing the airflow to a plurality of air separation modules (2) arranged in parallel on the air system to deplete oxygen in the air and generate a nitrogen-enriched inert gas at the outlet, characterized in that it comprises a programed control unit (6) for the distribution means (5) to selectively supply air to a single, a portion or all of the air separation modules (2), depending on the flight phase of the aircraft.
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
B64D 37/32 - Mesures de sécurité non prévues ailleurs, p. ex. contre les explosions
