A composite spar (100) for horizontal structures external to the fuselage of an aircraft, the composite spar (100) including a web (110) configured as a longitudinal element, upper and lower flanges (110a) and two distal ends, wherein for each end, the composite spar (100) includes an end portion (105) established in the longitudinal direction of the web (110), and a curved-edged end portion (120) with curved flanges (120a) and a truncated section (125) established in the transverse direction of the web (110), wherein the truncated section (125) is connectable to a frame of the fuselage of the aircraft and configured as a load transfer element between the web (110) and the frame, and wherein one or more of the lower flanges (110a) are connected to the curved flanges (120a).
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
An assembly with a continuous structural element for aircraft and a fitting. The continuous structural element has an outer flange, an inner flange and a web between the flanges. The inner flange has at least one portion with a wavy shape such that the height of the web increases or decreases in that portion. The fitting has at least one through hole and is configured to fit the web at the portion of the inner flange with a wavy shape so that in an assembled state the fitting is joined to the web in such a way that the at least one through hole of the fitting is not covered by the web.
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
37 - Services de construction; extraction minière; installation et réparation
39 - Services de transport, emballage et entreposage; organisation de voyages
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus for locomotion by air, water and rail;
aeronautical apparatus, machines and devices; airplanes;
structural accessories, parts and components for airplanes;
structural accessories, parts and components for aircraft;
Unmanned aerial vehicles [UAV]; structural accessories,
parts and components for unmanned aerial vehicles; drones;
structural accessories, parts and components for drones. Repair, maintenance and overhaul in the field of aviation,
in particular for airplanes, aircrafts, unmanned aerial
vehicles and drones; dismantling in the field of aviation,
in particular for airplanes, aircrafts, unmanned aerial
vehicles and drones; repair, maintenance and overhaul of
machines in the field of aviation, in particular for
airplanes, aircrafts, unmanned aerial vehicles and drones;
dismantling machines in the field of aviation, in particular
for airplanes, aircrafts, unmanned aerial vehicles and
drones; installation services for machines, in the field of
aviation, in particular for airplanes, aircrafts, unmanned
aerial vehicles and drones; providing information in
relation to repair, maintenance and overhaul in the field of
aviation, in particular for airplanes, aircrafts, unmanned
aerial vehicles and drones; technical support and technical
assistance in the field of aviation, namely concerning the
repair, maintenance, overhaul, servicing, reconditioning of
airplanes, aircrafts, unmanned aerial vehicles and drones. Air transport; warehousing and storage of parts, components,
accessories and connectors for airplanes, aircrafts,
unmanned aerial vehicles and drones; freighting; airplane
rental; aircraft rental; rental of unmanned aerial vehicles;
rental of drones; rental of aircraft and aerial vehicles;
transport by airplane, aircraft, unmanned aerial vehicle and
drone. Scientific services, research services and technological
services in relation to the following fields: aviation;
industrial analysis in relation to the following fields:
aviation; design and development services in relation to the
following fields: aviation; conducting technical project
studies, in relation to the following fields: aviation;
technological advice in relation to the following fields:
aviation; industrial design, in relation to the following
fields: aviation; interior furnishing design services in the
field of aviation; interior design, in the following fields:
aviation; graphic design, in the following fields: aviation;
certification and re-certification with respect to industry
standards and aircraft quality; technical flight testing;
providing scientific, technical and technological support
center services, in relation to the following fields:
aviation; testing services for airplanes, aircrafts,
unmanned aerial vehicles and drones, in particular safety
testing; technical support in the field of avionics for
airplanes, aircrafts, unmanned aerial vehicles and drones;
engineering solutions for the modification of airplanes,
aircrafts, unmanned aerial vehicles and drones.
4.
CIRCUIT BREAKER WITH A PASSIVE CLAMPING CIRCUIT INCLUDING CAPACITORS, OPERATION METHOD, DC NETWORK AND AIRCRAFT
A circuit breaker having a main switching unit configured to be switched off in the event of a fault, and a passive clamping circuit for absorbing energy and protecting against overvoltage wherein the clamping circuit is connected in parallel to the main switching unit. The clamping circuit includes a plurality of passive transient suppression components and delaying components arranged and configured to shift the action of the passive transient compression components so that the passive transient suppression components respond sequentially rather than simultaneously.
H02H 3/20 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à un excès de tension
In order to allow functional integration in a single structure for fluid transport in vehicles, a pipe arrangement is provided that includes at least one multi-walled pipe section that includes a multi-walled pipe for separately transporting each fluid medium or for separately accommodating each solid medium. In one solution, the multi-walled pipe section includes at least two nested pipe layers and the multi-walled pipe section is formed in a location of the pipe arrangement that is disposed in a confined space of the vehicle. In another solution, the multi-walled pipe section includes at least three nested pipe layers, wherein each pipe layer is chosen to transport a fluid medium or to accommodate a solid medium.
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Recherches scientifiques et industrielles; Recherches technologiques; Recherche aéronautique; Services scientifiques et technologiques ainsi que services de recherches et de conception y relatifs; Services d'essais et de recherche dans le domaine de l'électricité; Recherche dans le domaine de la technologie relative à l'électricité à très haute tension; Recherche liée à la sécurité électrique; Ingénierie; Recherche en ingénierie; Conception et conseil en ingénierie; Conduite de tests et d’expériences industrielles; Services de tests dans le domaine de l’aviation; Services d'essais dans le domaine de l'électricité; Etudes de faisabilité scientifiques; Etudes de faisabilité technique; Analyse et recherches industrielles dans le domaine de l'aviation; Développement de systèmes de gestion d'énergie et d'électricité; Études de projet technologiques; Services d’analyses technologiques; Services de conception et de développement; Conception de prototypes; Conception de véhicules.
7.
HIGH-PRESSURE HYDROGEN DISTRIBUTION SYSTEM FOR AN AIRCRAFT WITH A TANK STORING SUPERCRITICAL HYDROGEN
A system for supplying hydrogen to hydrogen consumer on an aircraft with a tank storing supercritical hydrogen. Energy is added to the tank to ensure tank pressure maintains supercritical. The system includes a supply pipe fluidly connected between the tank and the hydrogen consumer; a primary heat exchanger arranged on the supply pipe and configured to heat the hydrogen flowing in the supply pipe from the tank to the hydrogen consumer; and a tank heater arranged in the tank and configured to heat the hydrogen in the tank.
F17C 7/00 - Procédés ou appareils pour vider les gaz liquéfiés, solidifiés ou comprimés contenus dans des récipients sous pression, non couverts par une autre sous-classe
A welding device (70) includes a probe assembly (90) including at least a first and second probe device (100a, 100b). A first and second part (31a, 31b) to be joined along the weld line (40) are provided, wherein the parts are each formed as a laminate (1; 1′) including at least a first layer (2a, 2b) formed with a first material and a second layer (5a, 5b) formed with a second material. The first and second materials have different material properties. The method friction stir welds of the parts using the welding device, wherein simultaneously the first probe device acts on the first layers and the second probe device acts on the second layers.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B23K 11/00 - Soudage par résistanceSectionnement par chauffage par résistance
B23K 101/00 - Objets fabriqués par brasage, soudage ou découpage
9.
METHOD FOR INFORMING ABOUT SPEECH INTELLIGIBILITY QUALITIES, HEADSET DEVICE, HAND MICROPHONE DEVICE, HANDSET FOR AIRPLANES, SYSTEM FOR COMMUNICATION ROUTINES IN AND AROUND AIRPLANES, AIRPLANE
A method for informing about speech intelligibility qualities comprising: receiving of speech information data exchanged between a first technical device and a second technical device that is currently used by a user; analyzing a speech intelligibility of the speech information data using a control unit with a control program; providing at least one alarm routine for the user depending on the analysis result of the speech intelligibility of the speech information data. Also a headset device, a hand microphone device, a handset for airplanes, a system for communication routines in and around airplanes, and an airplane.
G10L 25/60 - Techniques d'analyse de la parole ou de la voix qui ne se limitent pas à un seul des groupes spécialement adaptées pour un usage particulier pour comparaison ou différentiation pour mesurer la qualité des signaux de voix
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
G08B 6/00 - Systèmes de signalisation tactile, p. ex. systèmes d'appel de personnes
A lavatory arrangement for an aircraft cabin includes a first lavatory compartment accessible from an aisle area via a first door, and a second lavatory compartment accessible from the aisle area via a second door. A movable bi-functional partition wall is arranged between the first and second lavatory compartments. The bi-functional partition wall is movable between primary and secondary positions. In the primary position, the bi-functional partition wall separates the first lavatory compartment from the second lavatory compartment, and in the secondary position, the bi-functional partition wall is brought into a position outside the first and second lavatory compartments, in which secondary position the first lavatory compartment and the second lavatory compartment provide an enlarged common lavatory. In the secondary position, the bi-functional partition wall is arranged at least partly outside the lavatory arrangement and within the aisle area outside the first lavatory compartment and the second lavatory compartment.
a method for mounting, in a nacelle for a hydrogen-powered aircraft, a box containing at least part of the equipment necessary for transporting dihydrogen to an engine of the aircraft, called H2 box, the mounting method comprising a step of positioning the H2 box in the nacelle by virtue of at least one rail secured to a chassis of the nacelle, or to the H2 box, or both.
A method of controlling a pressure in a hydrogen fuel tank of an aircraft hydrogen fuel system. The hydrogen fuel tank stores hydrogen fuel. The method comprises receiving leak information indicative of a leak of hydrogen fuel from the hydrogen fuel system. The method also comprises, based on the leak information received, causing control of the pressure in the hydrogen fuel tank.
An aircraft system is disclosed including a hydraulic actuator, an inlet line for supplying hydraulic fluid to the hydraulic actuator, an outlet line for removing hydraulic fluid from the hydraulic actuator, a first one-way valve configured to allow fluid flow along the inlet line in a direction toward the hydraulic actuator, and a second one-way valve configured to allow fluid flow along the outlet line in a direction away from the hydraulic actuator.
An aircraft with an energy management system for an electrical energy source in a hybrid electric propulsion architecture with at least one heat engine, an avionics system and components conveying parameters of the aircraft. An energy management module stores functions available for a given mission of the aircraft that are likely to be used by the engine and allowing assistance from the source, as well as the necessary associated charge required for the execution thereof. A controller is provided for authorizing their execution and ensuring the execution of the safety functions, the controller being linked to the components, to the electrical energy source and to an engine activation module in order to send it the authorized functions according to the control that has been completed.
B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
A method for providing cooling to cargo in the hold of an aircraft includes providing a temperature-reactive cargo item in the hold of an aircraft, providing an alert condition associated with the temperature-reactive cargo item corresponding to a need to cool the temperature-reactive cargo item in the aircraft hold, identifying via a sensor arrangement the alert condition within the aircraft hold, and cooling the aircraft hold after identification of the alert condition.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
A62C 3/06 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers pour des matériaux très inflammables, p. ex. les métaux légers, les produits du pétrole
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 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
16.
INDIVIDUAL AIR SUPPLY SYSTEM WITH ADJUSTABLE HOSE FOR AN AIRCRAFT
An individual air supply system having a flexible hose connecting an air nozzle unit with an air manifold. The hose has a layout includes a substantially straight part and a bent part irrespective of a position of the air nozzle unit relative to a connector of the manifold and along the manifold. Also an aircraft having such individual air supply system.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
An aircraft cabin lavatory with increased available space has a lavatory door including a door panel and an extension arrangement with at least one vertical extension segment. The door panel includes a hinge arrangement on one lateral side such that the door panel is movable around a main vertical axis between closed and opened positions. The vertical extension segment is movably mounted relative to the door panel around a subordinate vertical axis to be movable between stored and extended positions. The vertical extension segment is configured to be temporarily fixed in the stored position for a first use of the door panel. For a second use, the vertical extension segment is movable to the extended position when the door panel is in a partly opened position such that a vertically running gap between the door panel and a door frame is covered by the vertical extension segment.
An aircraft section having a monument and a buffer region. The buffer region includes at least one buffer tank storing a water supply for at least one water consumer of the monument. The buffer region does not intersect with a dedicated three-dimensional space encased by the monument and including the water consumer.
E03B 7/07 - Disposition des appareils, p. ex. filtres, commandes du débit, dispositifs de mesure, siphons ou valves, dans les réseaux de canalisations
E03B 11/02 - Aménagements ou adaptations de réservoirs pour l'alimentation en eau pour l'alimentation en eau à usage domestique ou alimentation locale analogue
19.
FASTENING SYSTEM FOR FASTENING AN OBJECT TO A SUPPORT AND AIRCRAFT COMPRISING AT LEAST ONE SUCH SYSTEM
A fastening system for fastening an object to a support, comprising a first fastening element and a second fastening element placed on either side of the support, and fasteners for fastening the object, the fasteners fastened to one of the fastening elements. The fastening system comprises an element, such as an elastic element, which is integrally fixed to the fastening elements and/or a lock integrally fixed to the fastening elements. Also an aircraft with such a fastening system.
F16L 3/10 - 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 fractionnés, c.-à-d. à deux éléments en prise avec le tuyau, le câble ou le conduit de protection
20.
METHOD AND DEVICE FOR DETECTING A DISCONNECTION STATE OF A PIPE FORMING PART OF A PUMPING SYSTEM OF A FUEL COLLECTOR OF AN AIRCRAFT
A method includes a receiving step for receiving a value of the quantity of fuel present in the collector, a processing step including a sub-step for classifying the value received in the receiving step as a normal value, or as an abnormal value, a sub-step for computing the value of a health indicator, based on the received value, as well as on a predetermined number of values received beforehand, and a sub-step for comparing the value of the health indicator with a threshold to be able to detect a disconnection state, as well as a warning step for transmitting a warning in the event of the detection of a disconnection state, the method allowing, by taking into account the quantity of fuel present in the collector, reliable detection of a disconnection state and allowing operators, notably maintenance operators, to be warned.
A hydraulic actuator for a hydraulic actuation system of an aircraft includes a housing defining a cavity, a piston dividing the cavity into extension and retraction chambers and movable relative to the housing to increase volume of one chamber and decrease volume of another of the chambers. A bypass includes first and second bypass ports and a connecting bypass line, and first and second chamber ports opening into the extension and retraction chambers at all positions of the piston relative to the housing for passage of hydraulic fluid. The first and second bypass ports open into one of the extension chamber and retraction chamber when the piston is at a first position relative to the housing so the first bypass port and the second bypass port open into respective ones of the extension chamber and the retraction chamber when the piston is at a second position relative to the housing.
F15B 11/024 - Systèmes comportant essentiellement des moyens particuliers pour commander la vitesse ou la puissance d'un organe de sortie au moyen d'une liaison différentielle des circuits du servomoteur, p. ex. circuits à récupération de fluide
A method of actuating a wing tip device on an aircraft, from a flight configuration to a ground configuration in which the span is reduced. The method includes receiving data indicative of a condition, such as the location or speed of the aircraft, and determining an actuation profile in dependence on the condition. The actuation profile may include determining a time period, and/or speed profile of the wing tip actuation over that time period. In this manner the actuation of the wing tip device can be tailored to minimize loads and wear on the actuator assembly.
A tape structure for use in automated fiber placement method to manufacture a composite structure includes a first layer and a second layer connected to the first layer with the first layer being configured as a support layer and the second layer being configured as a pre-impregnated layer, wherein the first layer is removable from the second layer during or after placement of the second layer on the composite structure to be manufactured, an automated fiber placement device an automated fiber placement method and a composite structure manufactured in the method.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
A fuselage portion of or for an aircraft. The fuselage portion comprises an aircraft component which is installed in a shell of the fuselage portion by a plurality of connector elements. Therein, a respective first end of each connector element is held in an associated bore b running through the shell, and a respective second end of each connector element is joined to the aircraft component by a joint providing the respective connector element with a margin of swiveling relative to the aircraft component. Also an aircraft comprising such a fuselage portion, and a method for assembling such a fuselage portion.
A connection system for connection between a front element and a rear element, comprising a threaded bolt with a rear portion and a front portion, a sleeve concentrically around the threaded bolt which is tapered towards the rear portion of the threaded bolt, a housing for the sleeve, and a fastening element configured to be threaded with the threaded bolt. The sleeve has a generally elliptical rear cross-section.
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
26.
SYSTEM AND METHOD OF COMPOSITE MATERIALS INSPECTION FOR AERONAUTICS
A NDI system and method for non-destructive inspecting aeronautical composite material parts include ultrasonics inspection equipment or device for generating raw inspection data of the composite material parts by using phased array, total focusing methodology, and phased coherence imaging, a computed tomography module for obtaining information of volumes of the composite material parts, data processor of cloud-shared resources configured to receive and process the raw inspection data from the ultrasonics inspection equipment and the information from the computed tomography module and to apply AI models created to identify defects within the composite part, the AI models trained using an inspection dataset obtained from the ultrasonics and the computed tomography inspection, and configured to classify the defects of the composite part according to a list of defect types and provide a classification output to make decisions.
A method and system to detect air leaks in inerting systems by comparing the nitrogen outlet with the nitrogen inlet in the inerting system. The inerting system monitors in real time the nitrogen mass flow in the outlet compared to the nitrogen mass flow in the inlet and react if air leakage is detected. The inerting systems is for use on aircraft. The inerting system includes a casing housing a hydrogen system and having an inlet and an outlet for nitrogen. An air leak is detected if the difference between the nitrogen mass flow leaving the casing and entering the casing exceeds a first threshold.
A method for reducing thermal runaways in a battery pack includes detecting a temperature inside the battery pack, if the temperature detected is higher than a predetermined temperature, injecting air with nitrogen and oxygen, the oxygen being less than 10% in volume, inside the battery pack and removing oxygen from the inside of the battery pack. The system includes a temperature sensor, an inerting system for injecting air with nitrogen and oxygen, the oxygen being less than 10% in volume, inside the battery pack if a temperature detected by the temperature sensor is higher than a predetermined temperature, and an exit duct, through which oxygen is removed from the battery pack if the temperature detected by the temperature sensor is higher than a predetermined temperature.
A62C 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
A62C 3/16 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les installations électriques, p. ex. chemins de câbles
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p. ex. le niveau ou la densité de l'électrolyte
H01M 10/613 - Refroidissement ou maintien du froid
H01M 50/249 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports spécialement adaptés aux aéronefs ou aux véhicules, p. ex. aux automobiles ou aux trains
H01M 50/383 - Moyens pare-flammes ou moyens de prévention de l’allumage
29.
COOLING SYSTEM AND METHOD FOR AN ELECTRICAL AIRCRAFT PROPULSION SYSTEM
A method for cooling an electrical aircraft propulsion system includes decreasing a temperature of a portion of a coolant below an operating temperature, acting this portion of the coolant as a thermal buffer, and maintaining a rest of the coolant at the operating temperature.
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B60L 58/33 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des piles à combustible pour la commande de la température des piles à combustible, p. ex. en commandant la charge électrique par refroidissement
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
30.
COMPUTER-IMPLEMENTED METHOD FOR NETWORK-ASSISTED DATA TRANSPORT
A computer-implemented method for transporting data between an end-user device and a server device for providing a network service via a time-varying network, the time-varying network including a plurality of nodes that are interconnected intermittently in time. Also, a network arrangement, a gateway device, a computer program, and a computer-readable data carrier for carrying out the method.
A computer-implemented method for transmitting data in an information-centric network, the information-centric network being connectable to a plurality of server devices for providing network service data, respectively, the information-centric network being configured for receiving a request for network service data from a client device, wherein the information-centric network includes a plurality of interconnected nodes including, respectively, a cache for caching network service data, each of the nodes being configured for routing any request to another of the nodes along a corresponding routing path from the client device to the corresponding server device, the corresponding routing path having one or more nodes successively visitable by the request via one hop.
A navigation system for navigating an autonomous mobile robot in an environment is provided. The navigation system includes at least one optical sensor attached to the autonomous mobile robot, a controller in communication with the at least one optical sensor, and a plurality of optical identifiers distributed within the environment at fixed locations and detectable by the at least one optical sensor. Each of the plurality of optical identifiers encodes a location within the environment. The controller is configured to obtain pictures of the environment via the at least one optical sensor, detect visible optical identifiers of the plurality of optical identifiers, which are within a field of view of the at least one optical sensor, decode the visible optical identifiers, and navigate the autonomous mobile robot based on real-time localizations of the autonomous mobile robot within the environment using the decoded visible optical identifiers.
G05D 1/244 - Dispositions pour déterminer la position ou l’orientation utilisant des aides à la navigation passive extérieures au véhicule, p. ex. marqueurs, réflecteurs ou moyens magnétiques
G05D 1/246 - Dispositions pour déterminer la position ou l’orientation utilisant des cartes d’environnement, p. ex. localisation et cartographie simultanées [SLAM]
G05D 1/644 - Optimisation des paramètres de parcours, p. ex. consommation d’énergie, réduction du temps de parcours ou de la distance
G05D 101/10 - Détails des architectures logicielles ou matérielles utilisées pour la commande de la position utilisant des techniques d’intelligence artificielle [IA]
A multi-use platform for a mobile robot is provided. The multi-use platform includes a first platform element, and a second platform element. The first platform element is fixedly attachable to a robot body of the mobile robot. The second platform element is movable relative to the first platform element between at least a first position and a second position. In the first position, the second platform element and the first platform element together build a flat surface, and in the second position, the first platform element and the second platform element together build a functional arrangement. Further, an autonomous mobile robot is provided that includes a corresponding multi-use platform.
A water supply system including a main tank, a water network and buffer tanks, each being associated with a respective water consumer unit. A controller is configured to operate in a first mode, where water from the main tank is filled into the buffer tanks, and a second mode, where water from one more first buffer tanks is conducted to the main tank and/or to one more second buffer tanks being different from the one or more first buffer tanks.
A pipe connector includes a sleeve which can be arranged concentrically to pipe sections with a first diameter and has a first sleeve section and a second sleeve section which can be welded to the first sleeve section to form the sleeve with the sleeve having a second diameter which is larger than that of the pipe sections of a pipe system and a method for connecting pipe ends in a pipe system using the pipe connector.
An aircraft structural element configured to be assemblable into an aircraft structure is disclosed having a sensor disposed on or within the aircraft structural element. The sensor is configured to sense a parameter during assembly of the aircraft structural element into the aircraft structure, and to output a signal indicative of the parameter during assembly of the aircraft structural element into the aircraft structure. An aircraft assembly system, and method of assembly based on the same are also disclosed.
A hydrogen distribution system for supplying hydrogen to a hydrogen consumer comprising: a tank storing a liquid hydrogen fuel; a conditioning system configured to provide a gaseous hydrogen stream downstream from the tank towards the hydrogen consumer; a compressor downstream of the conditioning system and configured to receive the gaseous hydrogen stream and provide a high-pressure gaseous hydrogen stream; a heater downstream of the compressor and configured to receive the high-pressure gaseous hydrogen stream and provide a high-temperature, high-pressure gaseous hydrogen stream; and, a valve downstream of the heater and configured to adjust a flow of the high-temperature, high-pressure gaseous hydrogen stream; wherein the hydrogen consumer is downstream of the valve and configured to receive the high-temperature, high-pressure gaseous hydrogen stream and provide energy by consuming hydrogen from the high-temperature, high-pressure gaseous hydrogen stream. Also, an aircraft with such a system.
A system for supplying hydrogen to hydrogen consumer on an aircraft with a helium heat transfer circuit. The hydrogen consumer may be a combustion engine or a fuel cell. A supply pipe is fluidly connected between the tank and a hydrogen consumer. A first pump is arranged on the supply pipe and configured to circulate the liquid hydrogen from the tank to the hydrogen consumer.
An aircraft wing (3) comprising an aerofoil structure (5) is disclosed. The aerofoil structure (5) comprises a load-carrying member (10) having stiffness properties selected such that the load-carrying member (10) twists in a predefined manner in response to bending of the load-carrying member (10). The aerofoil structure (5) further comprises an actuator (15A, 15B) which is fixedly mounted to the load-carrying member (10) and which is operable to bend the load-carrying member (10) to thereby cause the load-carrying member (10) to twist. An aircraft comprising the aircraft wing and a method of adjusting the twist in an aircraft wing are also disclosed.
An aircraft structural element configured to be assemblable into an aircraft structure, the aircraft structural element including an external surface having an integrally formed photogrammetry target. The aircraft structural element, the integrally formed photogrammetry target and the external surface are formed of a common material composition and are a single piece structure. A photogrammetry system, aircraft assembly system and method of assembly of the aircraft structural element into the aircraft structure.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
G01C 11/02 - Dispositions de prises de vues spécialement adaptées pour la photogrammétrie ou les levers photographiques, p. ex. pour commander le recouvrement des photos
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Engineering services; Technological research; Scientific technological services, in relation to software; Research and consultancy relating to computer software; industrial analisys; industry research; Industrial design; Development (design) of software, Installation of computer software, Maintenance of computer software, Updating of computer software and Rental of computer software; Computer specification design; Integration of computer software; Providing temporary use of on-line non-downloadable software development tools; Development of computer platforms; Software as a service [SaaS]; Platform as a service [PaaS]; Data security services; AI as a Service (AIaaS); Platforms for artificial intelligence being software as a service [SaaS]; Testing, authentication and quality control; Product certification services.
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Appareils et instruments électriques et électroniques pour véhicules aériens, à savoir composants électriques et électroniques pour véhicules aériens; Appareils et instruments électriques et électroniques de sécurité pour véhicules aériens; Appareils et instruments électriques et électroniques de communication pour véhicules aériens; Appareils et instruments électriques et électroniques de contrôle pour véhicules aériens; Appareils et instruments de navigation pour véhicules aériens; Appareils et instruments de mesure pour véhicules aériens; Appareils et instruments utilisés pour la commande et la surveillance de véhicules aériens; Simulateurs de vol; Matériel informatique et de périphériques pour ordinateurs pour formation et jeux; Logiciel dans le domaine de l'aviation; Logiciel pour la conception, le développement, le contrôle, la navigation, la maintenance dans le domaine de l'aviation; Appareils et instruments pour l'enseignement; Logiciel de simulation de vol; Logiciel de formation; Logiciel pour jeux vidéo; Logiciel de jeux d'ordinateurs. Véhicules; Appareils de transport et de locomotion par terre, air, eau et rail; Véhicules aériens; Aéronefs; Aéronefs sans pilote; Véhicules spatiaux; Hélicoptères; Drones; Pièces, composants et parties constitutives pour aéronefs. Ingénierie; Recherche en ingénierie; Conception et conseil en ingénierie; Services de tests dans le domaine de l’aviation; Conduite de tests et d’expériences industrielles; Recherches scientifiques et industrielles dans le domaine de l'aviation; Etudes de faisabilité scientifiques; Etudes de faisabilité technique; Recherches technologiques dans le domaine de l'aviation; Recherche aéronautique; Analyse et recherches industrielles dans le domaine de l'aviation; Services d'essais et de recherche dans le domaine de l'électricité; Services de conception et de développement dans le domaine de l’aviation; Conception de prototype; Conception de véhicules.
43.
MONITORING A COOLANT FLOW OF A POWER ELECTRONIC SEMICONDUCTOR DEVICE
A method for monitoring a cooling system for power electronics, especially on aircraft. For improving monitoring of a cooling system of a power electronic semiconductor device, wherein the cooling system can generate a coolant flow along a coolant flow path over at least one semiconductor power module of the power electronic semiconductor device, the method includes providing several temperature sensors arranged along the coolant flow path, measuring temperatures at different locations of the coolant flow path by the temperature sensors, comparing an actual temperature difference between the temperatures measured with an expected temperature difference calculated on basis of losses of the at least one semiconductor power module and on basis of nominal coolant flow conditions, and determining the status of the coolant flow on basis of the comparison.
G01M 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
G01K 3/14 - Thermomètres donnant une indication autre que la valeur instantanée de la température fournissant des différences de valeursThermomètres donnant une indication autre que la valeur instantanée de la température fournissant des valeurs différenciées par rapport à l'espace
H01L 23/34 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température
A fuel cell system capable of defreezing a dedicated component by guiding a coolant via a coolant branch line from a fuel cell stack to the dedicated component which may be a water separator, an exhaust water pipe, a valve, a water tank, or a combination thereof. Also a vehicle comprising such fuel cell system.
H01M 8/04223 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides pendant le démarrage ou l’arrêtDépolarisation ou activation, p. ex. purgeMoyens pour court-circuiter les éléments à combustible défectueux
H01M 8/04007 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 8/04029 - Échange de chaleur par des liquides
H01M 8/04225 - Dispositions auxiliaires, p. ex. pour la commande de la pression ou pour la circulation des fluides pendant le démarrage ou l’arrêtDépolarisation ou activation, p. ex. purgeMoyens pour court-circuiter les éléments à combustible défectueux pendant le démarrage
H01M 8/04302 - Procédés de commande des éléments à combustible ou des systèmes d’éléments à combustible appliqués pendant des périodes spécifiques appliqués pendant le démarrage
A fairing for an aircraft, comprises a wall element comprising an inner surface and an outer surface, wherein the outer surface is exposed to a free air flow outside the fairing, and at least one stiffener element attached to the inner surface of the wall element, to keep the fairing in shape under dynamic pressure loads. The fairing comprises at least one air inlet device comprising an inlet opening for a part of the free air flow outside the fairing to pass through the wall element and to enter the interior of the fairing. The air inlet device is at least partially integrated into the stiffener element, and the inlet opening of the air inlet device is formed in the stiffener element and extends into or through the stiffener element. The air inlet device and the stiffener element may be integrally formed as a single part, by 3D printing.
A flight control system for an aircraft including a first set of primary flight control computers and a second set of secondary flight control computers, where each primary flight control computer implements a first autopilot functionality. The secondary flight control computers jointly take control of control surface actuators when the primary flight control computers fail. The flight control system further includes another computer, to which the secondary flight control computers are connected, which implements a simplified second autopilot functionality, the second autopilot functionality being able to be activated only when the second set of flight control computers has control of the control surface actuators. Thus, an autopilot functionality is widely available, while at the same time ensuring the robustness sought by the installation of the secondary flight control computers.
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) rotatably about a folding axis (13) between an extended position (15) and a folded position (17), and a drive unit (24) for driving the foldable wing tip portion (9) for movement between the extended position (15) and the folded position (17), wherein the drive unit (24) includes a rotary actuator (25) mounted to the fixed wing (5) and having a drive arm (27) rotatably driven about a rotation axis (29) and drivingly engaging the foldable wing tip portion (9).
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
48.
AIRCRAFT COMPRISING AT LEAST ONE PROPULSION ASSEMBLY COMPRISING AT LEAST ONE MOTORIZATION AND A TRANSMISSION SYSTEM CONNECTED BY AN EXTERNAL COUPLING SYSTEM
An aircraft comprising at least one propulsion assembly comprising: at least one electric motor, a transmission system, at least one coupling module comprising a freewheel inserted between inner and outer shafts coupled by first and second coupling mechanisms to the output and input shafts of the electric motor and of the transmission system, at least one of the first and second coupling mechanisms comprising an angle gearset, at least one hollow intermediate element in which the output shaft of the electric motor, the input shaft of the transmission system and the inner and outer tubes of the coupling module are at least partially positioned.
B64D 35/021 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques
An aircraft control system and method for controlling electrical power distribution in an aircraft are disclosed. The aircraft control system and method obtain state signals from electrical systems in the aircraft, control characteristics of a power source, and control characteristics of the electrical systems. The control characteristics of the electrical systems are dependent on a flight phase status of the aircraft. Output control data is generated, based on the control characteristics and state signals, and used to control electrical power distribution in the aircraft.
37 - Services de construction; extraction minière; installation et réparation
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
Produits et services
Peintures; Vernis; Laques; Apprêts [peintures]; Enduits [peintures]; Peintures pour véhicules; Teintures, colorants, pigments et encres; Encres d'imprimerie; Pigments pour impression; Laques pour encre d'imprimerie; Revêtements [peintures] anticorrosion; Enduits (peintures) pour surfaces extérieures de véhicules à moteur; Produits pour le traitement de surfaces métalliques afin de les rendre résistantes à la ternissure; Produits utilisés comme revêtements imperméabilisants pour surfaces de structures [peintures]; Revêtements de protection à pulvériser sur les métaux [peintures]. Services de peinture; Services de peinture décorative; Peinture d'aéronefs; Peinture de véhicules; Services de vaporisation de peinture; Services de conseillers en rapport avec la peinture de véhicules; Services de nettoyage par sablage; Services de ponçage et polissage; Réparation, entretien, révision, démontage, remise à neuf, nettoyage et vernissage de véhicules et leurs parties; Services de pose de couche de fond sur véhicules; Inspection d’aéronefs et de leurs parties avant entretien et réparation; Réparation et finition de carrosseries de véhicules aérien pour le compte de tiers. Services d'impression par jet d'encre; Services d'impression; Impression numérique; Services d'impression on numérique; Services d'impression directe sur forme.
51.
TRAINING MACHINE LEARNING MODEL WITH PERIPHERAL IGNORE MASK
A method of training a machine learning model to identify image features including providing training image data including pixels, assigning a groundtruth annotation to each pixel relating to a respective pixel and each groundtruth annotation indicating whether or not that the pixel corresponds with an image feature, providing an ignore mask including a set of ignore flags relating to a respective pixel and each ignore flag providing an indication that the pixel should be ignored, for each pixel, receiving a prediction value from the machine learning model indicating a probability of the pixel corresponding with an image feature, for each pixel which has no ignore flag, determining a loss value based on the prediction value and groundtruth annotation for that pixel, and training the machine learning model based on the loss value, and for each pixel having an ignore flag, ignoring the prediction value for that pixel.
A cargo lining assembly for an aircraft, and an aircraft section and aircraft having the same. The cargo lining assembly has a ventilation inlet and outlet arranged at different sidewalls of the cargo lining assembly, and independent therefrom an air recirculation system. Also, an aircraft section and an aircraft with such a cargo lining assembly.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
53.
MANUFACTURING OF FIBER-MATRIX COMPOSITES COMPONENTS
A manufacturing tool with an adaptable form for winding applications of fiber-matrix composites to generate duct components from fiber-matrix composites includes a support structure, outer deposit surface and adjustable manipulators. The support structure has at least two support connectors and is configured to be mounted to bearings of a winding manufacturing system by the support connectors. The outer deposit surface is configured for material deposit support and to provide a variable circumferential contour for laying down fiber material in a winding process. The adjustable manipulators are between the outer deposit surface and the support structure to adjustably support the outer deposit surface on the support structure. The adjustable manipulators are configured to adjust a distance between the outer deposit surface and the support structure to provide different adjustable outer shapes of the manufacturing tool.
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
An interface for a wing folding mechanism of an aircraft. The interface has a central region comprising an internal surface, the internal surface being suitable for engaging a driven gear of a rotary actuator, and an attachment pad extending away from the central region in a first direction for attaching a surface to the interface. The interface can be used as part of the casing of a Geared Rotary Actuator. Also described are related wing assemblies, and aircraft and related methods.
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
An aircraft structure configured to be exposed to an ambient airflow which flows over the structure in an airflow direction. The aircraft structure includes: a first exhaust vent configured to exhaust a first stream of gas into the ambient airflow; and a second exhaust vent configured to exhaust a second stream of gas into the ambient airflow. The first exhaust vent is positioned downstream of the second exhaust vent in the airflow direction, the first exhaust vent is positioned in line with the second exhaust vent relative to the airflow direction, and the first exhaust vent has a larger area than the second exhaust vent.
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
F02C 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail
56.
CABIN SEARCH SUPPORT SYSTEM FOR AIRCRAFT COMPARTMENTS
A cabin search support system for aircraft compartments. The system comprises at least one camera and a system control with a screen for displaying image data from the at least one camera. The at least one camera and the system control with screen are connected to each other and spaced apart by a connecting element. The system control comprises a system program which is designed to compare in real time image data from the at least one camera with user-defined reference data stored in the system program, so that the image data can be displayed on the screen in a form processed by the system program depending on the result of the comparison.
G06V 10/764 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant la classification, p. ex. des objets vidéo
G06V 20/59 - Contexte ou environnement de l’image à l’intérieur d’un véhicule, p. ex. concernant l’occupation des sièges, l’état du conducteur ou les conditions de l’éclairage intérieur
57.
AIRCRAFT ENGINE ATTACHMENT SYSTEM COMPRISING A TWO-POINT SHACKLE EQUIPPED WITH AT LEAST ONE STOP, AIRCRAFT COMPRISING AT LEAST ONE SUCH ENGINE ATTACHMENT SYSTEM
An engine attachment system connecting an aircraft motive-power unit and a primary structure of an aircraft pylon, and comprising: at least one clevis block secured to the primary structure or to the motive-power unit, at least one two-point shackle which comprises a body, an extension forming just one single component with the body, at least a first stop connected to the extension and facing a first flange of the clevis block and/or at least a second stop connected to the extension and facing a second flange of the clevis block, a connection pin housed in an orifice passing through the body, and a ball-joint connection positioned in the orifice and interposed between the body and the connection pin.
An air intake lip of an aircraft engine nacelle provided with a passive shut-off device for exhaust devices. The passive shut-off device is capable of adopting a shut-off position in which it shuts off the exhaust devices and an open position in which it clears the exhaust devices as a function of the temperature perceived by the passive shut-off device.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
59.
METHOD FOR REPAIRING A DENT PRESENT ON A WALL, AND REPAIR DEVICE FOR THE IMPLEMENTATION THEREOF
A method for repairing a dent situated on a wall includes hammering the dent using at least one ferromagnetic striker, positioned in line with the dent to be repaired, and at least one electromagnetic emitter that generates at least one electromagnetic field configured to animate the ferromagnetic striker according to alternating movements such that it hammers the wall. A repair device makes it possible to implement the method.
A vapor cycle refrigeration system comprising a closed loop refrigerant piping for circulating a refrigerant, and a hermetically sealed housing with an internal space. The entire piping is accommodated within the housing such that leakage from the piping leads into the internal space instead of an atmosphere surrounding the housing. Also an aircraft galley unit, aircraft galley, and aircraft with such a vapor cycle refrigeration system.
A radio altimetry system to be housed on board an aircraft and provide an altitude of the aircraft above ground level, including a first subsystem based on FMCW technology and providing a first altitude value, a second subsystem based on UWB technology and providing a second altitude value, and consolidation electronic circuitry to compare the second value with a predetermined threshold, if the second value is less than or equal to the threshold, determine a consolidated value based on the first and second values, and if the second value is greater than the threshold, determine a consolidated value based on the first value and without taking into account the second value. In this way, the radio altimetry system offers resilience to various interference.
An aircraft section comprising a primary structure forming at least a portion of an aircraft fuselage, a cabin floor coupled to the primary structure, a sidewall covering at least a portion of the primary structure, and a rapid decompression unit arranged between the sidewall and the primary structure. The sidewall has a certain distance to the cabin floor and the rapid decompression unit has a certain distance to the sidewall.
A method for selecting a communication channel, called utilization channel, includes a step of determining, for each channel, one or more items of information representing a transmission quality of a message, with the message being either a “useful” message received by the on-board system, or a probe message, called “ping” message, a step of classifying the communication channels according to indices respectively representing transmission qualities, based on the information, a step of selecting the utilization channel as being the channel exhibiting the best transmission quality based on the indices, a step of determining a buffering time for each received useful message, and, if this time is non-zero, a step of transmitting the useful message, called eligible useful message, instead of a ping message.
A computer-implemented method of estimating characteristics of a hydraulic accumulator of an aircraft. The computer-implemented method includes obtaining pressure information representative of a pressure of hydraulic fluid in the hydraulic accumulator at a plurality of times during a mission of the aircraft, and estimating the characteristics based on the pressure information and a model including relationships between pressure and time for respective variants of the characteristics.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
A tire monitoring system including a tire monitoring device and a remote device. The tire monitoring device includes a first processor, and a first wireless communication interface. The remote device includes a second processor, a display device, and a second wireless communication interface. The first processor monitors the tire monitoring device to determine an altered operational mode of the tire monitoring device and causes transmission of a signal encoding an indication of the altered operational mode of the tire monitoring device to the remote device via the first and second wireless communication interfaces. The second processor determines, based on the signal encoding the indication of the altered operational mode of the tire monitoring device, a maintenance message corresponding to the altered operational mode of the tire monitoring device and causes the maintenance message to be displayed on the display device.
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01K 3/00 - Thermomètres donnant une indication autre que la valeur instantanée de la température
G01L 17/00 - Dispositifs ou appareils pour mesurer la pression des pneumatiques ou la pression dans d'autres corps gonflés
G01L 19/00 - Détails ou accessoires des appareils pour la mesure de la pression permanente ou quasi permanente d'un milieu fluent dans la mesure où ces détails ou accessoires ne sont pas particuliers à des types particuliers de manomètres
METHOD FOR COMPUTING AT LEAST ONE OUTPUT VALUE FOR A NUMBER OF INPUT VALUES BY A COMPUTING DEVICE, AS WELL AS CORRESPONDING COMPUTING DEVICE, COMPUTER PROGRAM, COMPUTER-READABLE DATA CARRIER, AND APPARATUS
A method for computing an output value from a number of input values, a computer program, apparatus, and a vehicle, an aircraft. The method includes an input number representing a vector size of an input vector containing the input values; defining a projection number of projections as a multiple of the input number based on a multiplying number; precomputing a transformed projection tensor as a transformation of a projection tensor having a projection size of the input number multiplied by the multiplying number and containing weight values in the frequency domain; obtaining a transformed embedded input tensor by computing a transformed input vector as a transformation of the input vector into the frequency domain; embedding the transformed input vector into the transformed embedded input vector; and using the transformed projection tensor and the transformed embedded input vector for computing the output value.
A method for obtaining a cascade of vanes of an aircraft thrust reversal device by: manufacturing tubular preforms each having transverse and longitudinal facets that form a single piece, delimit a cell of the cascade of vanes and constitute at least one layer of the vanes, and longitudinal walls of the cascade of vanes situated around the cell; assembling the tubular preforms by connecting the transverse facets of the two tubular preforms so as to form a common vane, and/or the longitudinal facets of two tubular preforms so as to form a segment of a common longitudinal wall. Also a cascade of vanes obtained using such a method.
A tire monitoring system that includes a tire monitoring device and a remote device. The tire monitoring device includes a processor, a memory, and a first wireless communication interface. The remote device includes a second wireless communication interface. The processor monitors the tire monitoring device to determine unauthorized interactions with the tire monitoring device, stores a log of determined unauthorized interactions in the memory, and transmits a signal encoding the log to the remote device via the first and second wireless communication interfaces.
A fuel line terminating in a refuel connector is used to fuel or defuel an aircraft, for example with liquid hydrogen. A supply of nitrogen housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line to supply nitrogen into the fuel line, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line. The aircraft supply of nitrogen is also used to supply inert gas, via a gas line, to the Ground Support Equipment refuelling or defuelling the aircraft. This can provide redundancy for the Ground Support Equipment's systems, and may allow the aircraft to operate at less well-equipped airports.
A pipe support assembly (114), suitable for supporting pipework handling cryogenic fluids, where the pipework passes through a fuel tank support. The pipe support assembly includes first and second pipe supports (116) each having male (119) and female (152) portions that interlock with male (119) and female (152) portions of the other pipe support (116). The pipe supports (116) have an internal surface (121) that contacts a section of the pipe outer surface (112). Each pipe support (116) has a split (140) which allows for a change in dimension of the internal surface (121) of the pipe support (116) contacting the pipe (110). This allows the pipe support assembly (114) to provide a consistent clamping force to the pipe (110) during thermal contraction or expansion. Longitudinal movement of the pipe (110) is permitted if the pipe (110) overcomes the frictional force between itself and the pipe support assembly (114).
09 - Appareils et instruments scientifiques et électriques
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Computer software for use in real-time collaborative engagement by a group of vehicles across multiple domains and environments, especially air, land, sea, space and submarine; Computer software for single vehicle autonomy and real-time collaborative engagement with other vehicles, especially for planning, enhancement and execution of missions for vehicles, especially crewed or uncrewed aircraft; Computer software for enabling communication and data exchange among vehicles, especially crewed or uncrewed aircraft; Computer software for enabling communication and data exchange among vehicles, especially for planning, enhancement and execution of missions for vehicles, especially crewed and uncrewed aircraft; Computer software for use in facilitating real-time collaboration and information sharing among vehicles, especially crewed and uncrewed aircraft; Computer software for use in facilitating real-time collaboration and information sharing among vehicles, especially for planning, enhancement and execution of missions for vehicles, especially crewed and uncrewed aircraft; Computer software for planning, enhancement and execution of missions for vehicles, especially crewed and uncrewed aircraft. Providing online non-downloadable computer software for use in real-time collaborative engagement by a group of vehicles across multiple domains and environments especially air, land, sea, space and submarine; Software as a service (SaaS) featuring software for enabling communication and data exchange among diverse vehicles for collaborative purposes; Providing computer software for use in facilitating single vehicle autonomy and real-time collaboration and information sharing among vehicles; Updating and maintenance of computer software, all related to the computer software as set forth in class 9, above; Technical support services, namely, providing troubleshooting in the nature of diagnosing problems with computer software, all related to the computer software as set forth in class 9, above; Licensing of computer software, all related to the computer software as set forth in class 9, above.
A fastening device for temporarily mounting equipment to a seat rail support, the fastening device comprises a bearing body, having a through hole in a longitudinal direction and a body contour in a cross-section transverse to the longitudinal direction and a pin, having a longitudinal rod portion with a first and second abutment portions at first and second ends. The rod portion is rotatably held in the through hole. The second abutment portion extends at least over an outer edge of the through hole. The first abutment portion has an outer shape in a cross-section transverse to the longitudinal direction of the rod portion, which cross section is inscribed in the body contour. The first abutment portion is rotatable by the pin from an aligned position, with the outer shape aligned with the body contour, to an extended position, with the first abutment portion laterally extending over the contour.
An aircraft wing includes a main wing and a high lift assembly which includes a high lift body and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body is movable between retracted and extended positions. The connection assembly includes primary and secondary connectors mountable to and engageable with the main wing via primary and secondary mount profiles, respectively. The primary connector is rotatable relative to the primary mount profile and at least one of the connection assembly and the main wing to configure the primary connector and mount profile between a decoupled configuration in which the primary connector may be moved into so as to be engaged with, and removed from so as to be disengaged from, the primary mount profile, and a locked configuration wherein movement between the primary mount profile and the secondary mount profile is restricted.
A wing for an aircraft, a method of connecting a high lift assembly to the wing, and an aircraft including such a wing. The wing includes a main wing, a bracket and a high lift assembly. The high lift assembly includes a high lift body including a connection assembly movably connecting the high lift body to the main wing. The bracket includes a plurality of bracket connection points. The high lift assembly includes a plurality of high lift connection points, each high lift connection point corresponding to a bracket connection point and being connected thereto by a connector. The bracket includes first and second flanges. The bracket connection points are located on the first and second flanges. The first and second flanges each include respective first and second landing surfaces configured to abut a connection assembly surface, the first landing surface being oriented perpendicular to the second landing surface.
A triple-walled conduit comprising a main section that has internal, intermediate and external tubes extended by internal, intermediate and external endpieces, respectively, at least one connector that has a through-hole and first and second joining tubes, which surround the through-hole and face at least one surface of the internal, intermediate and external endpieces, at least one first sealing system interposed between the internal endpiece and one of the joining tubes of the connector, at least one second sealing system interposed between the intermediate endpiece and one of the joining tubes of the connector, at least one third sealing system interposed between the external endpiece and one of the joining tubes of the connector.
A method of obtaining a grid of blades of an aircraft thrust reversing device by producing U-shape elements each including an integral central part corresponding to a blade and first and second branches each corresponding to at least a part of a longitudinal wall of the grid of blades and assembling which includes connecting the first branches of the various U-shape elements to one another in such a manner as to form a first longitudinal wall and connecting the second branches of the various U-shape elements to one another in such a manner as to form a second longitudinal wall.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
An aircraft wing, including a main wing with upper and lower skin panels, a leading-edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing, the high lift body being movable relative to the main wing between stowed and deployed positions. The connection assembly includes a rotation element mounted to both the high lift body and the main wing rotatably about a rotational axis. The upper skin panel has a leading-edge portion. The high lift body includes a rigid portion and a flexible skin portion with the rigid portion mounted to the rotation element. The flexible skin portion connects to the upper skin panel leading-edge portion and to the high lift body rigid portion, while being configured to be deformed between stowed and deployed deformation states, when the high lift body moves between the stowed and deployed positions.
A joint assembly in an aircraft, for example between a wing skin and rib foot. The joint assembly includes fasteners mechanically holding the wing skin and rib foot together. The rib foot includes circular faying surfaces and a layer of material is sandwiched between the faying surfaces and the wing skin. The layer of material has adhesive properties such that the joint is a hybrid joint. The layer of material also has structural properties to function as a solid shim, for example once it has cured after application.
A computer-implemented encoding method for encoding an input data stream for transmission from a transmitter coding point using a plurality of data links to improve communication networks. After segmenting the input data stream into data symbols, a link set of transmission data links is randomly selected from all data links. The data symbols are encoded by network coding. The encoded data symbol is packetized into a data packet together with decoding information and the randomly selected data links. The data packets are sent each along one randomly selected data link.
A method for modelling a composite part, comprising the steps: preparing a model of the composite part having at least one ply with a single or multiple curved in-plane fiber orientation; and modifying the model iteratively, thereby modifying the fiber orientation until a weight reduction of the model is achieved compared to a preceding model maintaining predetermined mechanical properties of the composite part. Also a composite part.
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29C 70/20 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans une seule direction, p. ex. mèches ou autres fibres parallèles
G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations
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]
82.
FLAT BULKHEADS, AN AIRCRAFT, AND A METHOD OF PRODUCING A FLAT BULKHEAD
A bulkhead for an aircraft, that has a substantially flat shape. The bulkhead has an exterior shell and a stiffening structure provided thereon. An interior shell can be formed and connected in an outer region to the exterior shell and in an inner region to the stiffening structure. Further disclosed are an aircraft having such bulkhead and a method of manufacturing such bulkhead.
A fastening system comprises a rail, a fastening device to fasten the rail to an instrument panel of a cockpit of an aircraft without modification of the instrument panel, and at least one movable carriage provided with a support device and configured to move in translation along the rail and to be brought into an operation position, the support device being provided with a support bracket to bear the screen and to be raised into the operation position and lowered on the movable carriage during a translational movement of the movable carriage on the rail.
A machining system includes an automated manipulator configurable between a measuring configuration, in which a position probe is operable, and a machining configuration, in which a tool is operable, a fixture for holding a template or a workpiece, and a controller. The controller is configured cause the automated manipulator, in the measuring configuration, to move the position probe to at least one reference feature of the template held in the fixture, to determine coordinate data associated with the at least one reference feature. Then, the controller provides the determined coordinate data to a machine learning agent which is trained to provide an estimate of machining coordinate deviation based on the determined coordinate data. If the estimated machining coordinate deviation is below a threshold coordinate deviation, the automated manipulator is allowed to proceed to machine a workpiece.
An aircraft with a folding wing tip arrangement having a wing tip device mounted at a joint at the end of a fixed wing. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. A wiring harness includes a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. A length of the harness is received in a protective sleeve, and the sleeve extends over a length of the wiring harness spanning the joint, the sleeve being removable from the wiring harness.
An aircraft with a folding wing tip arrangement and a wiring harness extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. The wiring harness includes a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. The harness is received in a protective sleeve. The sleeve includes a fluorosilicone polymer.
A wireless network infrastructure for an aircraft includes a first communication unit to receive and transmit data signals from and to a control system in a secured domain of the aircraft, the first communication unit configured as a first network node of a wireless communication network, second communication units of corresponding aircraft devices in an unsecured domain of the aircraft and configured as second network nodes of the wireless communication network. The aircraft devices are operable by control signals sent from the control system to the aircraft devices and transmit control signals to the control system over the wireless communication network, each aircraft device having a communication unit further comprising additional control dissimilar from the control signals sent over the wireless communication network for operating the aircraft device independently. Also provided are an aircraft including the wireless network infrastructure and a method for wireless communication onboard an aircraft.
An aircraft enclosure inerting system has an inerting apparatus which receives air from an inlet, separates that air into nitrogen enriched air to be delivered to one or more enclosures of the aircraft, and oxygen enriched air. The inerting apparatus comprises at least first and second air separators. The first and second air separators are configured differently to one another. In some embodiments one of the air separators is a vortex tube and the other is a membrane-based air separation module. In some embodiments the inerting apparatus has at least two vortex tubes which are configured differently to one another.
An aircraft with a folding wing tip arrangement and first and second wiring harnesses extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. The wiring harnesses include a plurality of conductors and are arranged to transmit electrical power and/or data to the wing tip device. The sleeve includes two channels to receive the harnesses, the position of the channels being fixed, relative to one another, such that the harnesses are held apart.
A ring-shaped solid oxide fuel cell assembly, for an aircraft engine, with a ring-shaped inner manifold, a ring-shaped outer manifold arranged coaxially around the inner manifold, wherein one of the manifolds comprises a hydrogen inlet and the other comprise a hydrogen outlet, a plurality of tubular solid oxide fuel cells arranged radially between the manifolds, wherein each fuel cell comprises an anode formed as an inner tube, an inner end fluidly connected to the inner manifold and an outer end fluidly connected to the outer manifold, a cathode formed as an outer porous tube around the anode, and, between, the anode and the cathode, an electrolyte. For each fuel cell, an inner electrical contact electrically connects at the inner end of that fuel cell to the anode or the cathode, and an outer electrical contact electrically connects at the outer end to the other.
H01M 8/243 - Groupement d'éléments élémentaires de forme tubulaire ou cylindrique
H01M 8/00 - Éléments à combustibleLeur fabrication
H01M 8/12 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé
H01M 8/1246 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé caractérisés par le procédé de fabrication ou par le matériau de l’électrolyte l'électrolyte étant constitué d’oxydes
H01M 8/2485 - Dispositions pour le scellement des collecteurs d’admission externesDispositions pour le montage des collecteurs d’admission externes autour de l’empilement
91.
FLOOR ASSEMBLY AND AIRCRAFT WITH MONOLITHIC FLOOR ELEMENT
A floor assembly for an aircraft which includes a monolithic floor element including an integral cross strut. The monolithic floor element has an upper surface, which includes a seat rail surface portion configured to mount a seat rail thereon. The floor assembly further includes at least one support structure arranged underneath the monolithic floor element and configured to support the monolithic floor element at least in an area of the seat rail surface portion.
A fuselage for an aircraft or spacecraft includes a first fuselage section having a support structure with a load bearing outer skin, and a second fuselage section having a non-load bearing outer skin and a space frame structure for supporting the non-load bearing outer skin, wherein the non-load bearing outer skin includes at least one skin area, which is configured to be openable for venting a compartment, which is at least sectionwise enclosed by the at least one skin area. An aircraft or spacecraft is disclosed including the a fuselage.
A floor module includes a forward sub-module and a aft sub-module arranged relative to each other in a longitudinal direction of the floor module, the sub-modules connected together by connecting elements configured to allow relative movement between the sub-modules at least in the longitudinal direction and to allow the transmission of forces between the sub-modules in a vertical direction substantially orthogonal to the floor module without generating relative movement, the sub-modules thus connected by the connecting elements being structurally decoupled, that is, they can be moved slightly relative to each other, which makes it possible to adjust the geometry of the floor module, for example to overcome tolerance defects of the fuselage portion on which it is intended to be installed.
A method of inspecting an aircraft fuel tank fastener assembly. The assembly includes a fuel tank with a fuel chamber; a fastener comprising a head and a tail at opposite ends of the fastener; and a cap inside the fuel chamber, wherein the cap surrounds the tail of the fastener. The method includes: heating the tail of the fastener; obtaining a thermal image of the tail of the fastener; and inspecting the thermal image of the tail of the fastener.
A robot arrangement is disclosed including one or more robots for moving a component into an assembly position adjacent a fixed structure. The robots are configured to operate collectively to move the component from an initial position located in a coarse adjustment zone into a fine rotational adjustment zone within a set distance of the fixed structure. The coarse adjustment zone is at least the set distance from the fixed structure; and in the fine rotational adjustment zone, robots are configured to collectively perform a rotational alignment cycle to rotationally align the component with the assembly position of the component ready for joining the component to the fixed structure and, upon completion of the rotational alignment cycle, collectively perform a translational movement to move the component into the assembly position.
B23P 21/00 - Machines pour l'assemblage de nombreuses pièces différentes destinées à composer des ensembles, avec ou sans usinage de ces pièces avant ou après leur assemblage, p. ex. à commande programmée
A method and a repair kit for repairing a sandwich structure, in particular a floor panel in a vehicle, such as an aircraft, the sandwich structure having a top layer and a bottom layer defining an intermediate space between them which is at least partially filled out with a core material, the method comprising the steps of localizing a damaged section of the sandwich structure, such as a hole in the top layer and the underlying core material; removing the damaged section to create a repair cavity while preserving the bottom layer; filling up the repair cavity with a filling material; covering the filled-up repair cavity with a cover layer; and fixing the cover layer with at least one fixing element extending through the cover layer and the filling material and/or the core material next to the filling material.
B29C 73/02 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant un liquide ou un matériau pâteux
B29C 73/06 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des bouchons insérés dans la perforation et l'obturant
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
B29C 73/26 - Appareils ou accessoires non prévus ailleurs pour le prétraitement mécanique
97.
SYSTEM AND METHOD FOR AUTOMATICALLY CONTROLLING A DIMMABLE WINDOW PANEL, AS WELL AS AIRCRAFT OR SPACECRAFT
A system for automatically controlling a dimmable window panel, in particular a dimmable window panel of an aircraft cabin and/or spacecraft cabin, the system comprising: a dimmable window panel of a cabin, wherein the dimmable window panel has an adjustable light transmissivity; an optical detection unit for detecting an illumination level inside the cabin; and a control unit, which is operatively coupled to the dimmable window panel and to the optical detection unit, wherein the control unit is configured to automatically adjust the light transmissivity based on the illumination level. Also an aircraft comprising such a system as well as a method for automatically controlling a dimmable window panel.
A system for speech-to-text conversion of passenger announcements on board of an aircraft comprises a cabin management control configured to provide a speech signal related to an announcement to passengers on board of the aircraft; a cabin application server comprising a processing unit configured to convert the speech signal into a text message containing text corresponding to spoken words of the speech signal, wherein the processing unit is configured to convert the speech signal locally without accessing online computing resources; and a network interface configured to provide the text message to at least one passenger device on board of the aircraft.
An air inlet of an aircraft propulsion assembly, comprising a lip which includes juxtaposed panels connected by at least one splice plate. This air inlet combines a main de-icing system and at least one secondary de-icing system which includes at least a main layer, which is made of a thermally conductive material and comprises a through-opening for each fixing element passing therethrough, the main layer being interposed at least partially between the splice plate and at least one of the first and second panels.
A robot arrangement for interacting with an object is disclosed including a plurality of robots adjacent an object; the plurality of robots configured to interact with the object sequentially such that: a first robot of the plurality of robots is configured to perform a first portion of a first task on the object and then, whilst the first robot is not interacting with the object, a second robot of the plurality of robots is configured to perform a second portion of the first task on the object, and the plurality of robots are configured to simultaneously interact with the object, before or after completion of the first task, so as to collectively perform a second task on the object.
