The invention provides an aircraft wing with a wing tip device movable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A hinge arrangement connects the fixed wing and the wing tip device. The hinge arrangement comprises a plurality of fixed wing interface rings, a plurality of wing tip device interface rings, and a geared rotary actuator (GRA) partially located within the fixed wing interface rings and wing tip device interface rings. The GRA is arranged to drive the wing tip device interface rings to move the wing tip device between the flight configuration and ground configuration.
A vortex generator for an aircraft. The generator includes a base configured to be connected to an external surface of an aircraft, a baffle being connected to the base and moveable in rotation around a rotation axis relative to the base, and an actuator configured to move the baffle in rotation around the rotation axis relative to the base. The actuator is controllable into at least one active configuration in which the actuator is moving the baffle to a predetermined active position relative to the base and a passive configuration, in which the actuator is allowing rotation of the baffle relative to the base. The baffle is in a feathered position relative to the base when the actuator is in its passive configuration.
A vortex generating system with a vortex generator formed by a base, a baffle, moveable in rotation around a rotation axis relative to the base, and an actuator, configured to move the baffle in rotation around the rotation axis relative to the base. A control unit is connected to the vortex generator. The control unit has an acquisition module configured for acquiring a target active position of the baffle, a control module configured for controlling the actuator into an active configuration, in which the actuator is applying a controlling torque to the baffle depending on the acquired target active position, and an evaluation module, configured for generating an inconsistency evaluation signal as a function of the controlling torque and of the target active position.
A test coupon for the mechanical testing of a laminar material. The coupon has three regions: an outer region with a first portion which is formed by two first ends which are opposite each other along the longitudinal axis; an inclined region contiguous with the outer region and having at least two first ramps, in which each of the first ramps extends along the longitudinal axis from each of the first ends towards a central region; and the central region which is arranged in the longitudinal axis between the two first ramps and comprises a second portion, in which the thickness of the second portion is less than the thickness of the first portion.
G01N 3/08 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression
A partition wall for dividing an aircraft cabin into individual sections, having at least one opaque air passage for enabling a pressure reduction between the sections through the partition wall. The wall also includes a frame and at least one stress-free planar element which is inserted into the frame. The at least one air passage is formed by a structure, a suspension in the frame, or both.
A data transmission unit for a vehicle interior, in particular for an aircraft interior, with at least one LiFi unit, at least one ToF unit, and a control unit coupled thereto, with a control program for controlling the respective functionalities of the components. The components are designed to transmit respective light signals for their respective functionalities via a common light source module. In addition, a system for transmitting data in a vehicle interior, and an aircraft.
A propulsion system, including a fuel tank, a turbojet including an engine and a fan blowing an airflow, a pipe circuit including a single-skin conduit extending from the tank and a second pipe portion including two double-skin conduits and fluidically connecting the single-skin conduit and a connection interface with the engine. The second portion also includes a second connector arranged between the two double-skin conduits and an air supply conduit fluidically connecting the fan and the double-skin conduits to cause a part of the airflow from the fan to enter the double-skin conduits and to cool the double-skin conduits.
B64D 37/34 - Conditionnement du carburant, p. ex. réchauffage
B64D 27/16 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
8.
AIRCRAFT PROPULSION ASSEMBLY COMPRISING A SUPPORTING STRUCTURE CONNECTING AN ENGINE ASSEMBLY AND A PRIMARY STRUCTURE OF A PYLON AND SUPPORTING AT LEAST ONE ACCESSORY
An aircraft propulsion assembly including: an engine assembly that has front and rear parts offset along a longitudinal axis, a primary structure of the pylon, at least one supporting structure that extends along an axis parallel to the longitudinal axis, connected to the front part of the engine assembly, supporting at least one accessory, an engine-attachment system that includes: at least one front attachment directly connecting the engine assembly and the primary structure, at least one rear attachment offset toward the rear relative to the front attachment connecting the primary structure 42 and the supporting structure.
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
14 - Métaux précieux et leurs alliages; bijouterie; horlogerie
25 - Vêtements; chaussures; chapellerie
28 - Jeux, jouets, articles de sport
36 - Services financiers, assurances et affaires immobilières
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Air vehicles; aircraft; unmanned aircraft; helicopters and
rotorcraft; drones; space vehicles; parts, components and
component parts for aircraft. Key rings; lanyards for keys; pins (jewelry); watches. Clothing; shoes; headwear. Scale model vehicles and parts thereof; model vehicles
(toys); toys; games; video game apparatus; video game
apparatus; video game consoles; video game consoles;
educational games; electronic games. Financial, monetary and banking services; financial
investments; financial crypto asset exchanges; electronic
transfer of crypto-assets; digital currency exchange
services. Custom manufacturing of air vehicles for third parties;
custom manufacturing of aeronautical and space vehicles for
third parties; custom manufacturing of graphics and wraps
for vehicles; recycling and waste treatment of aircraft,
spacecraft and air and space vehicles, and parts and
components therefor; information, advice and assistance with
respect to waste recycling of aircraft, spacecraft and air
and space vehicles, and parts and components therefor. Scientific and industrial research; engineering; engineering
research; engineering design and consulting; conducting
industrial tests and experiments; technological research;
industrial research and analysis services; scientific and
technological services as well as research and design
services relating thereto; technological project studies;
technological analysis services; design and development
services in the field of aviation; design of prototypes;
design of vehicles; graphic arts design services; styling
(industrial design); certification and re-certification
regarding the quality and industry standards of vehicles;
Blockchain as a Service [BaaS]; temporary provision of
non-downloadable software enabling members of an online
community to receive and access digital files authenticated
by non-fungible tokens (NFTs); computer programming of
online, non-downloadable virtual goods intended for use in
virtual environments.
10.
METHOD FOR AUTOMATED INSPECTION OF THE SURFACE OF A SOLID OBJECT AND SYSTEM CONFIGURED TO EXECUTE THE METHOD
A method for automatically inspecting a surface of a solid object such as, for example, a surface of an aircraft; the method using a step of blurring said surface represented in the form of a depth map image, followed by three successive derivation operations applied to said image. The invention also relates to a system configured to perform the method. Advantageously, it is thus possible to automatically detect planarity defects in a surface of an aircraft with a level of accuracy not yet achieved.
A hinge to open or to close a door, for example a door of an electrical cabinet of an aircraft, including at least one first wall and one second wall defining an angular opening of the hinge and a hollow internal space of the hinge sized to receive a cable. The first wall and the second wall are positioned relative to one another in order to open the hinge in a cable insertion or extraction position to allow the cable to pass through the angular opening of the hinge inside or outside the internal space, and to close the hinge in working positions of the hinge between a maximum open position of the door and a closed position of the door to block the angular opening of the hinge so as to be able to enclose the cable in the hollow space.
A thermal protection device for a lower longitudinal member of an aircraft box structure. The device incudes a shield which includes a first panel extending parallel and at a first distance from the lower longitudinal member, a second panel arranged between the first panel and the lower longitudinal member and which extends parallel and at a second distance from the lower longitudinal member. The panels delimit, relative to one another, a channel extending parallel to and at a distance from the lower longitudinal member. A front end of the channel forms an inlet orifice of an airflow originating from the fan of the aircraft and flowing from the front to the rear of the aircraft through the channel. A rigid thermal protection of the lower longitudinal member is provided by causing an airflow originating from the fan to flow inside the shield.
An aircraft propulsion assembly including an engine unit, a primary structure of the pylon, a nacelle surrounding a rear part of the engine unit, an engine mount system which includes a load-bearing structure positioned between the engine unit and the nacelle, a first connecting system of the rigid type, connecting the front end of the load-bearing structure and the front part of the engine unit, a second connecting system of the rigid type connecting the load-bearing structure and the primary structure, at least one rear damping engine mount interposed between the rear part of the engine unit and the nacelle.
An aircraft propulsion assembly including an engine assembly that includes front and rear parts offset along a longitudinal axis, a primary structure of a pylon, at least one supporting structure that extends along the longitudinal axis, separate from the rear part and connected to the front part of the engine assembly, an engine-attachment system that includes at least one front attachment directly connecting the engine assembly and the primary structure, and at least one rear attachment offset toward the rear relative to the front attachment connecting the primary structure and the supporting structure.
An assembly forming a sound-absorbing material and having a sheet having at least two first zones pierced with holes and, for each first zone, a solid second zone, wherein the first and second zones are disposed alternating along a direction of alignment, and, for each first zone and associated second zone, a conduit having a first end which bears against the sheet around the first zone and a second end which bears against the sheet around the second zone.
A sealing system with a guide that guides a pair of layers and heating rollers that apply heat and pressure to an edge of the layers for sealing the layers to each other, the heating rollers movable along the edge. Also a method which includes aligning a pair of layers so that a portion of one of the layers is placed in front of a portion of the other layer, defining an edge, applying heat and pressure to the edge of the layers by heating rollers, and moving the heating rollers along the edge of the layers, sealing both layers to each other at the edge, forming a vacuum bag.
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
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
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
An aircraft has a landing gear with a main leg, a support leg, and a wheel arm which has a wheel support and is pivotably connected to the main leg and support leg. The main leg and support leg are pivotably connected to the airframe of the aircraft, and can be pivoted aft to move the wheel arm aft and upward and move the landing gear from a deployed configuration to a stowed configuration. With the landing gear in the deployed configuration, the support leg is positioned forward of the main leg. The main leg, support leg and wheel arm form a triple-rocker four bar linkage such that pivoting the main leg and support leg aft pivots the wheel arm and retracts the wheel support.
Controller of an Electrical Power Supply Circuit for Electrical Power Supply of a Superconducting Motor, Superconducting Electrical Power Supply System of a Motor, and Aircraft Comprising Such a System
A control method executed by a circuit for controlling a power supply circuit of an electric motor, the power supply circuit comprising an inverter supplying the motor via a power supply link, the control method comprising a detection of an increase in the voltage on the terminals of the power supply link by monitoring the sum of the voltages of a balanced three-phase power supply system together with an inhibition of an output configured for controlling the inverter if the sum of the voltages exceeds a predetermined value for a predetermined duration. Also a circuit for controlling a power supply circuit configured for executing the method.
H02P 21/22 - Commande du courant, p. ex. en utilisant une boucle de commande
B64D 31/16 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques
A superconducting coil system having a coil of superconducting strips, stacked one against the other and wound so as to form rectilinear sections passing through a first orifice and a second orifice and a winding of at least one turn comprising rectilinear sub-sections passing through each of the two orifices and a heat-exchanger system having, for each orifice, a thermal unit arranged in the orifice and positioned against an edge face of each strip arranged in the same orifice, at least one duct embedded in the thermal unit and having a heat-transfer fluid passing through it, and two radiator plates arranged in the respective orifice and arranged one on each side of the thermal unit and of the strips arranged in the same orifice where each radiator plate is fixed against the thermal unit.
H02K 55/02 - Machines dynamo-électriques comportant des enroulements qui fonctionnent à des températures cryogéniques du type synchrone
20.
METHOD, CONTROL PROGRAM, COMPUTER-READABLE DATA CARRIER, CONTROL UNIT, COMMUNICATION DEVICE, AND SYSTEM FOR PROVIDING A NETWORK STRUCTURE, AS WELL AS APPARATUS CONFIGURED TO PARTICIPATE AS A NETWORK NODE
Providing a data connection to transfer a data object between a sender and a receiver via a routing path provided by network nodes of the network structure by: assigning a global number of network nodes to a global domain controlled by a global controller; providing a global model of the global domain based on routing parameters representing routing capabilities associated to the network nodes assigned to the global domain; assigning a local number of nodes assigned to the global domain as subsets of the global number to at least two local domains each controlled by a controller; and providing respective local models of the local domains to the network nodes assigned to each of the local domains. The global controller interacts with the local controllers to identify a network node which provides routing capabilities with the network node as a local proxy for the data object along the routing path.
H04L 67/56 - Approvisionnement des services mandataires
H04L 67/04 - Protocoles spécialement adaptés aux terminaux ou aux réseaux à capacités limitéesProtocoles spécialement adaptés à la portabilité du terminal
21.
PROPELLER PROPULSION SYSTEM FOR AIRCRAFT INCLUDING MEANS FOR ADJUSTING THE BLADE ANGLE OF THE BLADES OF THE PROPELLER AND AIRCRAFT INCLUDING SUCH A PROPULSION SYSTEM
A propulsion system for aircraft having a longitudinal axis and including: a propeller mobile in rotation around the longitudinal axis and including a plurality of blades distributed angularly relative to the longitudinal axis. A blade angle of the blades may be adjusted to modify the blade angle of each blade as a function of the angular position of each blade around the longitudinal axis.
An aircraft wing tip that is movable by an actuator between a flight configuration, and a ground configuration which has a shorter wingspan for use in ground-based operations. Lugs that connect to arms of the actuator are integrally formed as part of the primary structure of either the fixed wing or outboard wing section, such as a folding tip section.
A structure for refuelling an aircraft with cryogenic fuel includes a walkway to allow personnel to access the aircraft and a pipework arrangement attached to the walkway. The pipework arrangement includes a feed line, a return line and a bypass valve between the feed line and the return line and fluidically connecting the inlet line to the return line. A first end of the feed line is configured to connect to a source of cryogenic fuel, and a second, opposite end of the feed line is configured to connect to the aircraft. The bypass valve is switchable between a refuelling configuration in which the bypass valve prevents fluid flow between the feed line and return line through the bypass valve, and a chill down configuration in which the bypass valve allows fluid flow between the feed line and the return line through the bypass valve.
A compliant mount for an aircraft, for attaching equipment (such as a latching unit, for example) to a structural member of the aircraft, the compliant mount comprising: a mounting member for attachment to the structural member of the aircraft; a receptacle for supporting the equipment, the receptacle being coupled to the mounting member along a longitudinal axis; and one or more spring elements arranged to resiliently bias the receptacle into alignment with the longitudinal axis and to allow angular movement of the receptacle away from the longitudinal axis. Also provided is an aircraft equipment assembly comprising such a compliant mount, and aircraft equipment supported by the receptacle, and an aircraft having one or more such equipment assemblies. The aircraft may be a folding wingtip aircraft and the equipment assembly may be part of a folding wingtip actuation mechanism.
A fuel tank for an aircraft, and an aircraft with such fuel tank. The fuel tank is configured to contain liquid hydrogen, and it has at least one adjustable anti-sloshing baffle. The fuel tank may have an adjustment mechanism adapted to adjust the at least one anti-sloshing baffle. Also a fuel tank arrangement with such a fuel tank and a control unit for control of the at least one adjustable anti-sloshing baffle.
A method, control program, computer-readable data-carrier, controller, and milling device for milling a cover layer of metal sheets for removing a cladding layer from cladded sheets. The method includes providing a milling tool to rotate around a rotational axis, having at least one milling face extending essentially perpendicularly to the rotational axis and adapted to face the metal sheet to mill the cover layer. A fixture assembly is configured for fixing the metal sheet and defining a working plane with which at least flat sections of the metal sheet are supposed to be aligned, such that a surface normal of the flat section extends essentially perpendicularly to the working plane. The rotational axis is being tilted under at least one work angle with respect to the surface normal of the flat section during the milling process.
B23C 3/13 - Fraisage en surface de plaques, de feuilles ou de bandes
B23Q 15/007 - Commande automatique ou régulation du mouvement d'avance, de la vitesse de coupe ou de la position tant de l'outil que de la pièce pendant l'action de l'outil sur la pièce
27.
CEILING PANEL HAVING A LIGHT MODULE FOR AN AIRCRAFT AND AIRCRAFT EQUIPPED WITH A CEILING PANEL
A ceiling panel for an aircraft with a base panel and a light module. The base panel has a base plate and two side plates extending from a bottom surface of the base plate. The two side plates form a personal service channel on a respective interior side, the personal service channel configured to support at least one personal service unit. The light module is connected to the base plate on an exterior side of one of the two side plates.
An aircraft galley having a smart countertop and a controller. The countertop comprises a base plate and a component layer arranged thereon which has at least one electrical and/or electronic component, in particular at least one display. The controller is set up to show on the display a work-supporting message describing at least part of an activity currently to be carried out on the countertop. Alos an aircraft with such a galley.
A conduit for a heat exchanger with an outer tube having an outer inlet and an outer outlet and defining an outer passage configured for guiding a working fluid from the outer inlet to the outer outlet, and an inner tube having an inner inlet and an inner outlet and defining an inner passage configured for guiding the working fluid from the inner inlet to the inner outlet. The inner tube is arranged in the outer passage and defines with the outer tube an annular space the inner outlet opening in the outer passage. Also a tubesheet, heat exchanger and aircraft with such conduits.
F28D 7/10 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation les canalisations étant disposées l'une dans l'autre, p. ex. concentriquement
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
Siempelkamp Maschinen- und Anlagenbau GmbH (Allemagne)
Inventeur(s)
Joern, Paul
Koehler, Filipp
Finger, Lennart
Schwickert, Joerg
Koeffers, Fabian
Schoeler, Michael
Abrégé
An in-situ thermoforming and (co-)consolidation process for joining two components together. An adaption of one of the components to the contour of the other component is done directly before a joining step with the other component in the same tooling by adapting process parameters such as heat and pressure. Also a stiffened component manufactured by such a method.
A propulsion assembly having an engine and an engine attachment which connects the engine and a primary structure of a pylon and which comprises a removable connection connecting a transverse beam and the primary structure. This removable connection has a first contact surface integral with the transverse beam, a second contact surface integral with the primary structure, at least one connection element keeping the first and second contact surfaces pressed against one another, at least one system for transmission of transverse forces between the engine and the primary structure and at least one waiting fail-safe connection distinct from each connection element and configured to generate an additional path for forces only in the event of malfunction of an element of the first removable connection.
A landing gear assembly for an aircraft having a main body on which one or more wheels of the aircraft are mounted, the main body aftwardly pivotable, about a pintle line, into a landing gear bay of the aircraft; and a bracing structure coupled to the main body, the bracing structure movable between an extended configuration to support the main body in a deployed configuration, and into a folded configuration in which the main body is held in a retracted configuration. The bracing structure includes at least a first component of preferential weakness configured to fail when subjected to a critical load when the main body is in the deployed configuration, to thereby decouple the main body from at least part of the bracing structure and enable the main body to pivot aftwards, into the landing gear bay. Also an aircraft having such a landing gear assembly.
A free-space optical communications (FSO) terminal including a first arm having a combined transmit-receive system configured to produce a data beam, encoding data, for transmission to a target and receive a received data beam from the target, a second arm having a component configured to transmit a further transmitted beam or utilise a further received beam, a pointing unit configured to steer the data beam to the target or the received data beam received from the target, and an optical fibre including a single-mode portion configured to carry the transmitted data beam and received data beam and couple the first arm to the pointing unit, and a multi-mode portion configured to carry the further transmitted beam or the further received beam and couple the second arm to the pointing unit.
A spacer for covering a gap between a sidewall arranged in a longitudinal direction and a monument wall arranged in a transverse direction in an aircraft. The spacer includes an upper mount, and a lower mount. The lower mount restricts a relative movement between the monument and the spacer in the longitudinal direction, and allows a relative movement in the transverse direction.
B64C 1/40 - Insonorisation ou isolation calorifique
F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles
35.
FASTENING DEVICE FOR CONNECTING TO A HOLDING DEVICE BY INTERLOCKING AND FRICTIONAL ENGAGEMENT, FASTENING SYSTEM FOR A SUPPORTING STRUCTURE OF A MEANS OF TRANSPORT, IN PARTICULAR FOR A STIFFENING PROFILE OF AN AIRCRAFT, AND AIRCRAFT
A fastening device for connecting to a holding device by interlocking and frictional engagement, including a base body, which has along an axis of rotation a head portion and a handling portion, a plurality of elastically deformable segments arranged around the axis of rotation on the head portion and together form a thread which can be brought into engagement with a complementary thread of a holding device. The elastically deformable segments are configured such that, when the fastening device is pushed onto the complementary thread along the axis of rotation in a mounting direction, they will snap axially over the thread tips of the two threads, and a peripheral predetermined breaking point, which connects the head portion to the handling portion and is configured to break when there is a predetermined torque around the axis of rotation, so that the handling portion is separable from the head portion.
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
36.
SOLID OXIDE OXIDATION UNIT AND PRESSURE-RESISTANT FUEL CELL
An oxide oxidation unit for converting a reductant to thermal energy by producing exhausts and further exhausts from an oxidant supply flow and a reductant supply flow. The solid oxide oxidation unit has a duct wall separating the supply flows and which includes an electrolyte layer for a transfer of ions from the oxidant to the reductant. The duct wall has an electrically conducting material allowing for a transfer of electrons from the reductant to the oxidant. Also a fuel cell arrangement, at least one fuel cell setup, and a vehicle with such an oxide oxidation unit.
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyteHumidification ou déshumidification
H01M 8/0612 - Combinaison d’éléments à combustible avec des moyens de production de réactifs ou pour le traitement de résidus avec des moyens de production des réactifs gazeux à partir de matériaux contenant du carbone
H01M 8/12 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé
H01M 8/1213 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé caractérisés par la combinaison électrode/électrolyte ou par le matériau de support
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
37.
PROPULSION ASSEMBLY COMPRISING A DAMPING REAR ENGINE ATTACHMENT, AIRCRAFT HAVING AT LEAST ONE SUCH PROPULSION ASSEMBLY
A propulsion assembly with a damping rear engine attachment, aircraft having at least one such propulsion assembly. The propulsion assembly has an engine attachment system, connecting a primary structure of a pylon and a motor, which has a plurality of attachments each having at least one engine anchor point on the motor, all the engine anchor points being approximately positioned in the same transverse plane, a damping rear engine attachment connecting the primary structure and the rear part of the jet engine core, the damping rear engine attachment forming a force path that has at least one elastically deformable element.
F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet
B64D 27/16 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
38.
AUTOMATIC COMMUNICATION METHOD AND SYSTEM FOR AN AIRCRAFT
A communication method for an aircraft with an air traffic control center includes receiving information relating to the activation of guidance of the aircraft along a contingency trajectory, sending a first message on a first communication frequency, to inform air traffic control of the activation of guidance of the aircraft along the contingency trajectory, and of the sending of further messages on a second communication frequency used for emergency communications, sending a second message on the second communication frequency, to inform air traffic control of the activation of guidance of the aircraft along the contingency trajectory, and sending a set of messages on the second communication frequency, to inform air traffic control of maneuvers that the aircraft is going to implement.
A propulsion system includes an engine, a pylon box, and a structural attachment. The engine includes an engine casing and an engine core. The pylon box has a front part and a rear part. The rear part is configured to attach the engine to an aircraft structure. The structural attachment has a front end configured to attach to the engine casing and a rear end configured to attach to the pylon which allows load transfer to the aircraft structure through the pylon box.
An aircraft wing including a skin and a framework for supporting the skin. The framework includes a spar extending along a length of the wing, the length extending between a root end and a tip end of the wing, a plurality of ribs extending chordwise between a leading edge of the wing and a trailing edge of the wing; and a plurality of stringers attached to the skin. The plurality of stringers includes a first stringer extending along the length of the wing, wherein a proximal end of the first stringer is arranged nearer the root end and a distal end of the stringer is arranged nearer the tip end; and an auxiliary stringer extending non-parallel with the first stringer and arranged such that a portion of the auxiliary stringer is proximal to the distal end of the first stringer.
B32B 5/10 - 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 caractérisés par une couche fibreuse renforcée par des filaments
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
A landing gear for an aircraft, having a leg and a wheel support, and two wheels secured to the leg by the wheel support, the wheels being spaced apart from each other such that a space, called an internal volume, is delimited between the two wheels, the landing gear also has an electrical energy receiving device, the electrical energy receiving device comprising a receiver, configured to receive electrical energy emitted by a transmitter, the electrical energy receiving device mounted movably between a retracted position and a deployed position, in which the receiver is arranged outside the internal volume, the electrical energy receiving device comprising an end secured to the wheel support.
B64F 1/35 - Installations au sol ou installations pour ponts d'envol des porte-avions pour l'alimentation en énergie électrique des aéronefs en stationnement
B64C 25/10 - Atterrisseurs non fixes, p. ex. largables escamotables, repliables ou ayant un mouvement apparenté
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
42.
ELECTRICAL ENERGY RECEPTION SYSTEM FOR MOVING AN AIRCRAFT DURING TAXIING
An electrical energy reception system for an aircraft, having an electrical energy reception device, the electrical energy reception device has an electrical energy reception element, called a receiver, configured to receive electrical energy emitted by an electrical energy transmitter, the electrical energy reception device being mounted with the ability to move between a retracted position and a deployed position, the electrical energy reception system also has a compartment for housing the electrical energy reception device in the retracted position.
B64F 1/35 - Installations au sol ou installations pour ponts d'envol des porte-avions pour l'alimentation en énergie électrique des aéronefs en stationnement
H02J 50/10 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant un couplage inductif
43.
WATER CONVEYING SYSTEM, WATER SUPPLY AND DRAINAGE SYSTEM AND AN AIRCRAFT HAVING A WATER SUPPLY AND DRAINAGE SYSTEM
A water conveying system includes a conveying device and two valves, which can be changed in state to convey water in one of two opposite directions at a time. A water supply and drainage system includes the water conveying system and an aircraft including the water supply and drainage system.
An aircraft fuselage portion including at least four frames arranged uniformly one behind the other in an aircraft longitudinal direction, a fuselage outer skin on an outer side of the frames and at least three window openings. Internal air ducting tube portions are arranged in intermediate regions extending between window openings and frames, and along the frames. All window openings are offset counter to the aircraft longitudinal direction, in each case by a linear amount defined between longitudinal central points of the window openings and central planes which are arranged in parallel between two adjacent frames. The intermediate regions are enlarged by the linear amount on common first longitudinal sides of each window opening, and the intermediate regions are smaller by the linear amount on the other, second, sides of each window opening. The tube portions are arranged in the enlarged intermediate regions.
An aircraft including an aircraft wing wherein the aircraft wing includes a fixed wing, a wing tip device at an end of the fixed wing, and a wing tip device actuator configured to move the wing tip device between a flight configuration and a ground configuration. The wing tip device actuator includes a shaft which is rotatable about a shaft axis to selectively displace respective first and second elbows of the wing tip device actuator towards or away from the shaft. The first elbow is connected to the wing tip device and the second elbow is connected to the fixed wing such that movement of the respective elbows away from the shaft causes the wing tip device to move away from the flight configuration and such that movement of the respective elbows towards the shaft causes the wing tip device to move towards the flight configuration.
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Scientific and industrial research; Technological research; Technical research in the field of aeronautics; Scientific and technological services and research and design relating thereto; Technological research Relating to telecommunications; Research in the field of information technology; IT services; Engineering services; Engineering research; Engineering design and consultancy; Development, design, installation, maintenance, updating or renting out of software in the field of aviation; software as a service for use in the field of aviation; Development of computer platforms in the field of aviation; Platform as a service [PaaS] in the field of aviation; Cloud computing; Computer system analysis; Analysis of technical data in the field of aviation; Conducting industrial tests, Conducting industrial experiments; Scientific testing services; scientific feasibility studies; Technical feasibility studies; Industrial analysis and research services in the field of aviation; Technological project studies; Technological analysis services; Design and development services; Design of prototypes; Design of vehicles.
47.
AIRCRAFT COMPRISING AT LEAST ONE DEFLECTOR CONFIGURED TO DIVERT A GAS EXHAUST CONE EXITING A PROPULSION ASSEMBLY AWAY FROM A TRAILING EDGE OF A WING
An aircraft comprising: a wing, a propulsion unit which comprises a nozzle having a trailing edge, a pylon connecting the propulsion assembly and the wing, which comprises at least one secondary rear fairing having a lower face, offset rearward with respect to the trailing edge, which forms an angle of between 2 and 20°with the inner face of the nozzle. The secondary rear fairing forms a deflector which interferes with the gas exhaust cone exiting the propulsion assembly.
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
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes
A coil system for a motor including a coil formed from strips and including straight sections passing through apertures of the motor, and, for each straight element of the coil passing through the same aperture, a shielding system with at least one first band and at least one second band arranged on either side of the elements, in which the strips are electrically connected to an electrical power source, in which two successive strips in the stack are electrically insulated from each other, and in which each band that is placed next to a strip of the coil is electrically insulated from the strip. With such an arrangement, the losses are reduced.
H02K 3/34 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement entre conducteurs ou entre conducteur et noyau, p. ex. isolement d'encoches
H02K 15/043 - Enroulement de fils ou de feuilles conducteurs plats
H02K 15/122 - Imprégnation, chauffage ou séchage des bobinages, des stators, des rotors ou des machines des enroulements
H02K 55/00 - Machines dynamo-électriques comportant des enroulements qui fonctionnent à des températures cryogéniques
49.
SENSOR ARRANGEMENT AND SYSTEM FOR MEASURING AN AVERAGE TEMPERATURE
A sensor arrangement has a structure extending along a length, an optical fibre carrier, and an optical fibre sensor carried by the optical fibre carrier. The optical fibre carrier is fixed to the structure proximal to each end of the structure and is formed of a first carrier portion and a second carrier portion that are movable relative to each other and is formed substantially of a material having a first coefficient of thermal expansion. The optical fibre sensor has a single measurement point and is fixed to the optical fibre carrier either side of the single measurement point; and the structure is formed of a material having a second coefficient of thermal expansion which is different to the first coefficient of thermal expansion
G01K 11/3206 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant des changements dans la transmittance, la diffusion ou la luminescence dans les fibres optiques en des endroits distincts de la fibre, p. ex. utilisant la diffusion de Bragg
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
G01K 1/08 - Dispositifs de protection, p. ex. étuis
G01K 1/14 - SupportsDispositifs de fixationDispositions pour le montage de thermomètres en des endroits particuliers
G01K 3/06 - Thermomètres donnant une indication autre que la valeur instantanée de la température fournissant des valeurs moyennesThermomètres donnant une indication autre que la valeur instantanée de la température fournissant des valeurs intégrées par rapport à l'espace
G01K 13/00 - Thermomètres spécialement adaptés à des fins spécifiques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
25 - Vêtements; chaussures; chapellerie
28 - Jeux, jouets, articles de sport
Produits et services
Aircraft; Parts, components and elements of aircraft. Clothing; Shoes; Headgear. Scale model vehicles and their parts; Carpets for vehicles (playthings); Toys; Games; Video game apparatus; Computer game apparatus; Video game consoles; Computer game consoles; Educational games; Electronic games.
51.
OPTICAL RECEIVER, COMMUNICATION TERMINAL AND SYSTEM AS WELL AS APPARATUS COMPRISING SAME
An optical receiver, a communication terminal with an optical receiver, an optical communication system with a communication terminal, and an apparatus, such as a vehicle, in particular an aircraft, with a communication system are described, the optical receiver including at least one sensor array having sensor elements configured to detect a light beam carrying data, a capturing unit configured to read out light values from the sensor elements based on the detected light beam, and a processor configured to obtain the light values and to extract at least a part of the data carried by the detected light beam.
A method and system for generating a new technical solution by acquiring PLM data of an industrial product having at least two 3D objects, extracting attributes and rules for each 3D object from the PLM data, generating a knowledge graph of tree relationships between the 3D objects, generating topology attributes for each 3D object, consolidating, for each 3D object, its attributes and rules, its tree relationships and its topology attributes into at least one relational database, in voxel form, receiving a request from a user relating to a technical solution, the request having at least one 3D volume, evaluating whether the technical solution is present in the PLM, and when it is not present: generating a new technical solution in the 3D volume, implementing at least one new 3D object, generating a new voxel associated with the new 3D object, and re-introducing the new voxel into the relational database.
A water supply and drainage system with: a supply tank configured to store water; a Venturi manifold having an inlet, an outlet and a low-pressure coupling. The Venturi manifold is configured to generate a low-pressure when fluid streams from the inlet to the outlet. A conveying device is fluidly coupled to the supply tank and configured to convey water from the supply tank to the inlet of the pump. A water supply pipe is connected to the low-pressure coupling and configured to conduct water to at least one water consumer. A drainage pipe is connected to the outlet of the Venturi manifold and a shutoff valve is in the drainage pipe.
A differential mode filter with a variable inductance, the variable inductance having a primary winding coupled to a secondary winding, the secondary winding having a switch connected in series and configured so that when the switch is in the closed position, the variable inductance has a first inductance value, and when the switch is in the open position, the variable inductance has a second inductance value. The first inductance value is lower than the second inductance value.
H02M 1/12 - Dispositions de réduction des harmoniques d'une entrée ou d'une sortie en courant alternatif
H02M 1/00 - Détails d'appareils pour transformation
55.
METHOD, CONTROL PROGRAM, COMPUTER-READABLE DATA CARRIER, CONTROL UNIT, QUANTUM DEVICE, QUANTUM NETWORK, APPARATUS, AND QUANTUM COMPUTING ARRANGEMENT FOR ESTABLISHING A QUANTUM COMMUNICATION CHANNEL
A method, control program, computer-readable data carrier, control unit quantum device, quantum network, apparatus, such as a satellite, an aircraft and/or a communication station, and/or quantum computing arrangement for establishing a quantum communication channel to transmit quantum data units between a source quantum device and a destination quantum device. The method includes requesting a quantum path between a first quantum device and a second quantum device; establishing at least two quantum bounded channels between respective two quantum devices each designated for enabling the quantum path; providing at least two quantum links by entangling at least one qubit of each of the respective two quantum devices connected by the at least two quantum bounded channels; and synchronizing the quantum devices providing the at least two quantum bounded channels in time to provide the quantum path via the at least two quantum links simultaneously for establishing the quantum communication channel.
An installation for an aircraft having a tank delimiting a volume with a high point, through a wall of the tank, an evacuation channel arranged near the high point, a container in which dihydrogen is present and which is arranged in the volume, and a catalyzer configured to catalyze an oxidation reaction of the dihydrogen with the air in the tank, wherein the catalyzer is fastened at the evacuation channel.
An installation for an aircraft having a structural assembly of the aircraft delimiting a volume with a high point, a container in which dihydrogen is present and which is arranged in the volume, and a catalyzer to catalyze an oxidation reaction of the dihydrogen with ambient air. The catalyzer is fastened in the volume at the high point.
A fuselage structure of an aircraft includes a first fuselage section and a second fuselage section connected to the first fuselage section, the second fuselage section including at least one first fuselage vessel extending the first fuselage section in a longitudinal direction, with the first fuselage section and the first fuselage vessels comprising circumferential flanges arranged at longitudinal ends of the first fuselage section and the first fuselage vessels extending radially in the first fuselage vessels and the first fuselage section wherein fasteners extend through abutting flanges of the first fuselage section and the fuselage vessel to establish a force-fit connection between the first fuselage section and the first fuselage vessels, when assembled, and wherein the first fuselage vessel provides a storage space for at least one tank structure. Also disclosed are a method for assembling the fuselage structure and an aircraft including the fuselage structure.
A method intended for manufacturing a composite structure for an aircraft. The method includes training a set of artificial neural networks (3.1, 3.2, 3.3) to obtain a composite structure which fulfills certain specification requirements (material properties, shear loads, compression loads, buckling constraints). The neural networks are trained with data obtained from analytical equations and from a finite element model.
A joint assembly has an eccentric bush for rotatably mounting to the first aircraft component. The eccentric bush has a rotational axis. A projection is mounted on the eccentric bush such that rotation of the eccentric bush about its rotational axis causes movement of the projection in both a first and a second orthogonal direction relative to the first aircraft component. The first and second orthogonal directions are substantially perpendicular to the rotational axis of the eccentric bush. A rail rotatably mounts to the second aircraft component. The rail has a longitudinal axis which extends in a direction substantially parallel to the second orthogonal direction. The projection has an aperture for receiving the rail. The rail has a threaded surface which is configured to engage with a correspondingly threaded surface of the aperture.
A joint assembly for joining a first aircraft structural component to a second aircraft structural component. The joint assembly has a double eccentric bush for mounting to one of the first and second aircraft structural components, and a spigot mounted on the double eccentric bush. Rotating elements of the double eccentric bush enable adjustment of the spigot relative to the respective aircraft structural component in two orthogonal directions normal to a longitudinal axis of the spigot prior to joining the first aircraft structural component to the second aircraft structural component. A spigot receptacle is provided for mounting to, or is integrally formed with, the other of the first and second aircraft structural components. The spigot receptacle is arranged to receive the spigot. At least one fastener joins the first and second aircraft structural components together when the spigot is received in the spigot receptacle.
An electrical connector with a male part including a pin and a female part including a socket, in a connected position the pin is inserted into the socket. The connector also has a securing part on the socket. The securing made of a metamaterial and configured and arranged on the socket so that, in the connected position, when the electrical connector is subjected to a solicitation that tends to loosen the contact between the pin and the socket, it leads to an expansion of the securing part in a way that avoids loosening of the contact between the pin and the socket.
A hydrogen-powered aircraft with a fuselage with an unpressurised aft portion containing or configured to contain at least one hydrogen tank. A roof portion of the fuselage at least partially covers the unpressurised aft portion and integrates an antenna for satellite internet access from within the aircraft. The antenna may be counter sunk and/or covered by a skin.
B64C 1/36 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
B64D 37/30 - Circuits de carburant pour carburants particuliers
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
64.
FUSELAGE OF AN AIRCRAFT, METHOD FOR CLOSING AN OPENING OF THE FUSELAGE AND AIRCRAFT HAVING SUCH FUSELAGE
A fuselage of an aircraft includes a front portion and a rear portion, with at least one opening in the rear portion, with the opening being closeable by a structural panel fully removeable from the opening, wherein a locking structure for the structural panel is in the opening and configured to transfer loads between a primary structure of the fuselage and the structural panel. A method is disclosed for closing an opening of a fuselage, and an aircraft is disclosed having such a fuselage.
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
Software; data processing apparatus; data processing
equipment and computers; databases; navigation apparatus for
vehicles; navigational instruments; simulators for the
steering or control of vehicles. Air vehicles; aircraft; unmanned aircraft; helicopters;
civil and military drones; parts, components and component
parts for aircraft. Scientific and industrial research; engineering; engineering
research; engineering design and consulting; conducting
industrial tests and experiments; technological research;
industrial analysis and research; scientific and
technological services as well as research and design
services relating thereto; technological project studies;
technological analysis services; design and development
services in the field of aviation; design of prototypes;
design of vehicles.
66.
JOINING FLANGE FOR AIRCRAFT NACELLE WITH ZONE OF FLEXIBILITY
A flange for joining an engine compartment to an air intake compartment of an aircraft, having a first leg, referred to as base, shaped to be placed on an outer surface of one of the engine compartment and the air intake compartment, referred to as mounting surface, and a second leg, referred to as joining leg, including at least one orifice for the passage of an element for connecting the joining flange to another flange, which is inclined relative to the base, the joining flange including at least one groove cut into the joining leg to create a local narrowing of the section.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
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
67.
METHOD AND SYSTEM FOR DETECTING INAPPROPRIATE PILOTING RELATED TO THE SPATIAL DISORIENTATION OF AT LEAST ONE PILOT AND FOR PROTECTING AN AIRCRAFT AGAINST SAID INAPPROPRIATE PILOTING
A system and a method for detecting and protecting an aircraft against inappropriate piloting by a pilot potentially experiencing spatial disorientation related to a somatogravic illusion. The method includes: obtaining flight information and status information; estimating a current value of a perceived longitudinal attitude based on the flight information; computing a difference between the current value of the perceived longitudinal attitude and a current value of an actual longitudinal attitude; and then determining, when this deviation is greater than or equal to a predetermined longitudinal attitude deviation threshold, whether a piloting action performed by the pilot is inappropriate based on the status information of the aircraft; and then activating, when the performed piloting action is inappropriate, a protective measure.
G05D 1/81 - Transfert de la commande entre la commande automatique embarquée et la commande manuelle embarquée
68.
MANUFACTURING METHOD FOR MANUFACTURING A PROFILE RAIL, PROFILE RAIL OBTAINABLE THEREBY, MOUNTING SYSTEM AND VEHICLE EQUIPPED THEREWITH AND USE OF THE PROFILE RAIL
A profile rail for a floor of a vehicle has a base made of a first material and a top portion exposed during use of the profile rail in the floor of the vehicle. The top portion has a cold sprayed coating of a second material that is at least one of harder, more wear-resistant, or less corrosive as the first material. The top portion has a seat rail crown having a first hook element produced entirely from the second material.
A lavatory with a divider wall for a lavatory arrangement in an aircraft cabin. The divider wall has a primary wall section and a secondary wall section. Both wall sections are movably mounted such to be arranged in a closed state and in an opened state, wherein in the closed state, a separation of two adjacent lavatory spaces is provided, and in the opened state, the separation is cancelled, and the two adjacent lavatory spaces form a common enlarged lavatory space. The primary wall section has a primary wall panel movable between a separating position and a non-obstructing stored position. The secondary wall section has a secondary wall panel that with a first secondary panel segment movable between a vertical separating position and a horizontal position, in which it can be temporarily fixed to act as a seating transfer portion for a user of the common lavatory space.
A monitoring system for an aircraft involved in a formation flight as a trailing aircraft or as a leading aircraft comprises electronic circuitry configured to repeatedly implement the steps of receiving barometric altitude information from the leading aircraft, receiving barometric altitude information from the trailing aircraft, computing a difference between the barometric altitude of the leading aircraft and the barometric altitude of the trailing aircraft, determining an inconsistency between the barometric altitude of the trailing aircraft and the barometric altitude of the leading aircraft, within the context of the formation flight, if the computed difference is greater than a height value of the vortex at a current position of the trailing aircraft, increased by a height margin, and commanding, if such an inconsistency is determined, a transmission of a warning in the cockpit of the aircraft.
A method for controlling an electrical system of a hybrid aircraft, the electrical system includes at least two busbars configured to transfer electrical energy between a plurality of subsystems of said aircraft and comprising at least one centralised regulation control device, the method includes the regulation of a voltage level performed by the controller from one or more variable regulation points determined from among a plurality of predefined regulation points and each located in either one of the busbars, as a function of the nature of the transfers of electrical power that are to be performed.
An acoustic absorption structure including at least one cellular structure between an acoustically resistive layer and a reflective layer. The cellular structure includes a first face in contact with the acoustically resistive layer, a second face in contact with the reflective layer, and a multitude of cells each discharging at the level of the first and second faces, each cell being delimited by at least one partition, wherein the cellular structure comprises at least one partitioning enclosure positioned in one of the cells of the cellular structure and connected to at least one partition delimiting the cell. The partitioning enclosure separates an interior zone inside the partitioning enclosure and an exterior zone situated in the cell and outside the partitioning enclosure. The partitioning enclosure includes at least one through-orifice configured so that the interior and exterior zones communicate.
B64C 1/40 - Insonorisation ou isolation calorifique
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
73.
ACOUSTIC ABSORPTION STRUCTURE COMPRISING COMPARTMENTALIZED CELLS COMBINING A PLURALITY OF TYPES OF RESONATORS
An acoustic absorption structure having a cellular structure, interposed between an acoustically resistive layer and a reflective layer, which has walls delimiting cells and, for at least one cell: at least one, and at most three, L-shaped partitions which are impermeable and spaced apart from one another and which delimit a straight compartment and at least one L-shaped compartment, in each L-shaped compartment an inclined acoustically resistive porous partition which has a perforation rate of less than or equal to 15% and divides the L-shaped compartment into first and second zones forming two types of resonators. Also an aircraft with at least one such acoustic absorption structure.
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
G10K 11/168 - Sélection de matériaux de plusieurs couches de matériaux différents, p. ex. sandwiches
A vacuum-insulated pipe assembly having an outer pipe and an inner pipe within the outer pipe, the inner pipe distanced from the outer pipe to provide a space, the space evacuated to define a vacuum. The vacuum-insulated pipe assembly has an annular wall extending inwardly from the outer pipe and defining an aperture about a central axis, the annular wall defining a closed end of the space. The vacuum-insulated pipe assembly has a first connector connected to the inner pipe, and a second connector extending through the aperture and connected to the first connector. The first connector and the second connector are each hollow and connected such that the inner pipe is in fluid communication with the second connector through the aperture. Also a system and a method for making a vacuum-insulated pipe assembly.
A latch for locking an aircraft folding wing is disclosed having a lug including an aperture, and a latch pin moveable within the aperture. The latch further includes a seal configured to inhibit fluid transfer between the aperture and the latch pin as the latch pin moves within the aperture.
A vacuum-insulated pipe assembly including an outer pipe and an inner pipe within the outer pipe, the inner and outer pipes concentric along a common central axis, the outer pipe spaced from the inner pipe to define a space, the space evacuated to define a vacuum. The outer pipe includes first and second outer pipe sections, the first outer pipe section includes a first outer connector, and the second outer pipe section includes a second outer connector, the first outer connector removably connected to the second outer connector at an outer connection interface. The inner pipe includes first and second inner pipe sections, the first inner pipe section includes a first inner connector, and the second inner pipe section includes a second inner connector, the first inner connector removably connected to the second inner connector at an inner connection interface.
A method for determining a deformation field of at least one layer of paint applied to a support during crosslinking of the layer or the layers of paint is disclosed. The method includes a step (E1) of provision of a sample, a step (E2) of 3D tomographic measurement of the sample and a set of successive steps(S) repeated iteratively comprising a step (E3) of dynamic mechanical analysis of the sample subjected to at least one temperature cycle (C), a step (E4) of 3D tomographic measurement of the sample, a step (E5) of determining a deformation field of each layer of paint of the sample.
G01N 23/046 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p. ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et formant des images des matériaux en utilisant la tomographie, p. ex. la tomographie informatisée
78.
METHOD FOR MANUFACTURING A PROFILED ELEMENT MADE OF COMPOSITE MATERIAL INCLUDING A PIGMENTED COATING, PROFILED ELEMENT OBTAINED FROM SAID METHOD
A method for manufacturing a profiled element made of composite material including a step of obtaining a preform and a step of placing at least one pigmented layer on the preform, the pigmented layer including at least one pigmented film and at least one support structure having a knitted structure. Because the knitted structure is flexible, it is possible to obtain profiled elements with complex geometries. A profiled element obtained from such a method and a stiffened panel comprising at least one such profiled element are also provided.
B32B 27/12 - Produits stratifiés composés essentiellement de résine synthétique adjacente à une couche fibreuse ou filamenteuse
B32B 1/00 - Produits stratifiés ayant une forme non plane
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 37/20 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de bandes continues
A vacuum insulated pipe assembly including a first pipe section and a second pipe section. The first pipe section has a first outer wall and a first inner wall within the first outer wall. The first outer and inner walls are concentric along a common central axis, and the first outer wall is spaced from the first inner wall to define a first space. The second pipe section has a second outer wall and a second inner wall within the second outer wall. The second outer and inner walls are concentric along the common central axis, and the second outer wall is spaced from the second inner wall to define a second space. The first inner wall includes a first inner connector and the second inner wall includes a second inner connector connected to the first inner connector.
F16L 59/075 - Dispositions utilisant une couche d'air ou le vide la couche d'air ou le vide étant délimités par des canaux longitudinaux répartis sur la périphérie d'un tube
B64D 37/30 - Circuits de carburant pour carburants particuliers
A bush is provided including a sleeve for receiving a pin; a shoulder extending from the sleeve, the shoulder for delimiting insertion of the sleeve into an aperture; and a sensor mount for mounting a sensor such that the sensor may detect the presence of a pin within the sleeve. Installing such a bush within an aperture of a component may negate the requirement for lugs and/or brackets on the component. This may enable reduction of the weight, size and/or complexity of the component.
A system for synchronized data playback in an aircraft comprising at least one offset calculation device; and a plurality of clients; wherein the plurality of clients are each synchronized to a shared reference timeframe, each of the plurality of clients is configured to receive a common set of timestamped data frames, the offset calculation device is configured to determine a synchronized playback time for each of the common set of timestamped data frames with respect to the shared reference timeframe; and each of the plurality of clients is configured to playback each of the common set of timestamped data frames at the respective determined playback time.
H04N 21/214 - Plate-forme spécialisée de serveur, p. ex. serveur situé dans un avion, un hôtel ou un hôpital
H04N 21/43 - Traitement de contenu ou données additionnelles, p. ex. démultiplexage de données additionnelles d'un flux vidéo numériqueOpérations élémentaires de client, p. ex. surveillance du réseau domestique ou synchronisation de l'horloge du décodeurIntergiciel de client
H04N 21/472 - Interface pour utilisateurs finaux pour la requête de contenu, de données additionnelles ou de servicesInterface pour utilisateurs finaux pour l'interaction avec le contenu, p. ex. pour la réservation de contenu ou la mise en place de rappels, pour la requête de notification d'événement ou pour la transformation de contenus affichés
82.
TAPE STRUCTURE OF A TAPE FOR USE IN MANUFACTURING A COMPOSITE STRUCTURE, AUTOMATED FIBER PLACEMENT (AFP) DEVICE, AUTOMATED FIBER PLACEMENT (AFP) METHOD AND COMPOSITE STRUCTURE
A tape structure of a tape for manufacturing a composite structure includes a layer of unidirectional pre-impregnated dry fibers embedded in a polymer matrix having a composition of 20% and 50%, or between 25% and 40% by weight of the polymer matrix of a first monomer or oligomer, between 30% and 60%, or between 35% and 40% by weight of the polymer matrix of a second monomer or oligomer, between 4% and 25%, or between 4% and 7% by weight of the polymer matrix of a curing agent, between 0.5% and 5%, or 0.8% and 1.5% by weight of the polymer matrix of at least one reactive chain extender, and an additive. The polymer matrix can be solid or semi-solid in a first temperature range and softened in a second temperature range different from the first temperature range. An automated fiber placement device, method and composite structure are disclosed.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/00 - 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
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
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
83.
ACOUSTIC ABSORPTION STRUCTURE COMPRISING A PARTITIONING SYSTEM PROVIDED WITH AT LEAST ONE FOOT
An acoustic absorption structure including a cellular structure which comprises tubular cells, closed at each of their ends by an acoustically resistive layer and a reflective layer, and at least one individual partitioning system, placed in a single cell and including a partition configured to separate the cell into first and second compartments, at least one opening passing through the partition, several feet independent of the conduit, having a first end connected to the partition and a second end in contact against the reflective layer, and at least one conduit which has a first end rigidly secured to the partition surrounding the opening and a second end spaced apart from the reflective layer.
A structural panel for use in aeronautical applications. The structural panel includes a composite skin that comprises composite material and a stiffening framework that is rigidly attached to the composite skin. The composite skin is configured as a load bearing monolithic structure with a structure thickness of less than 1 mm. The composite skin comprises a composite laminate with a plurality of carbon composite plies. Each one of the plurality of carbon composite plies comprises a ply thickness in a range from 0.02 mm to 0.05 mm.
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
B32B 3/08 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p. ex. au voisinage des bords caractérisés par des éléments ajoutés à des endroits déterminés
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 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
85.
METHOD AND SYSTEM FOR DETERMINING AT-RISK AREAS AROUND AN AIRCRAFT
A method for determining at least one at-risk area around an aircraft during an execution of ground operations around and/or on the aircraft. This method includes, upon receipt of a request to determine at least one at-risk area, obtaining first information which is representative of at least one element which is a source of at least one risk, and operational context information which is representative of an operational context of the aircraft during said ground operations, determining said at-risk area and location thereof, then transmitting said location to indicate a presence of at least one at-risk area in said location to personnel operating on and/or around the aircraft during said ground operations. It is possible to identify one or more at-risk areas and to locate them in an area around the aircraft for one or more risks associated with various hazards which can be encountered during ground operations.
In a method for manufacturing an aircraft panel that has a composite skin with integrated components (stringers/frames) having unsupported slots, a male tool with the integrated component is obtained. The composite skin is laid up directly over the unsupported slots of the integrated component with an automated fiber placement, AFP machine that provides tow deposition The integrated components lack auxiliary support tools. A force applied to the tow with the AFP machine is adjusted during deposition over the unsupported slots to compensate the lack of auxiliary support tools.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
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 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
A Coriolis flow sensor for sensing a flow of a cryogenic fluid is disclosed having a flow member for the passage of a flow of cryogenic fluid therethrough, a driver for vibrating the flow member, and one or more detectors configured to generate output signals corresponding to Coriolis deflections of the vibrating flow member with flow of cryogenic fluid therethrough. The flow member includes at least 50 wt % indium.
Disclosed is a wing assembly for an aircraft. The wing assembly comprises a fixed wing, a wing tip device, a wiring harness and a harness guide. The wing tip device is moveably mounted at a joint at an end of the fixed wing. The wing tip device is moveable about the joint between: (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved relative to the fixed wing such that the span of the wing is reduced. The wiring harness extends between the fixed wing and the wing tip device. The wiring harness comprises a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. The harness guide is located between the fixed wing and the wing tip device. The harness guide comprises a helical channel configured to receive the wiring harness and guide the wiring harness between the fixed wing and the wing tip device.
A double-eccentric connecting device for connecting a fixing lug to a clevis and connecting system comprising at least one such connecting device is disclosed. The connecting device includes a main sleeve having a central section inserted into an orifice of the fixing lug and two end sections on either side of the central section, the centers of the external surfaces of the two end sections being offset from the center of the external surface of the central section, as well as two bushings, each of them inserted into an orifice passing through the clevis and mounted on one of the end sections, each of the bushings having an external surface the center of which is offset from the center of its internal surface, the connecting device thus including two eccentric elements, making it possible, through appropriate angular positioning, to compensate for an alignment error between the orifice passing through the fixing lug and the through-orifices of the clevis.
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
90.
TOOL FOR ADJUSTING AND HOLDING A CHAIN ON A SPROCKET
A tool for adjusting and holding a chain with links engaging with a sprocket, the tool has a shoe intended to be mounted in a fixed manner with respect to the sprocket, and a finger secured to the shoe and intended to be inserted into a link. Also, an assembly with such a tool.
B25B 27/22 - Outils à main ou outillage d'établi, spécialement conçus pour assembler ou séparer des pièces ou des objets, que cela entraîne ou non une certaine déformation, non prévus ailleurs pour assembler des objets autrement que par ajustage à la presse, ou pour les détacher pour mettre en place des chaînes articulées, chaînes de chenille, chaînes antidérapantes
91.
AIRCRAFT AUXILIARY POWER UNIT FUEL SUPPLY CIRCUIT EQUIPMENT SURVEILLANCE METHOD AND DEVICE
A method and a system for surveillance of equipment in a fuel supply circuit of an auxiliary power unit of an aircraft. The method includes determining if the fuel supply circuit was during a predetermined period in a configuration such that these conditions were satisfied: (i) the auxiliary power was in an “on” operating state, and ii) the fuel supply circuit was in a “trim tank fueling” operating mode, and (iii) the trim tank had an “empty” fuel filling status, then determining a duration for which the configuration was maintained and, if the duration is above a first predetermined threshold, storing an event, and if a number of events stored is above a second predetermined threshold generating an alert message.
An emergency power generation system within a main duct of an aircraft that includes: a rotating electric machine operable in a generator mode and a motor mode; a control unit; a first switch in communication with the control unit to select the generator or motor mode; an air outlet actuator in communication with the control unit that selectively opens and closes an air outlet of the main duct; an airflow passage controller in communication with the control unit that opens and closes an inlet to a secondary duct wherein the inlet is at the main duct, wherein the control unit commands, during an emergency mode of flight, the first switch to place the rotating electric machine in the generator mode, the airflow passage controller to close the inlet of the secondary duct, and the air outlet actuator to open the air outlet of the main duct.
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
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
93.
DEVICE FOR CLAMPING AND UNCLAMPING TEMPORARY FASTENERS
A device for clamping and unclamping temporary fasteners is stored in an automatic tool changer and is introduced automatically in an end effector. The device clamps and unclamps temporary fasteners without manual intervention. It applies torque to the fastener's screw via an inner drive, typically using a hexagonal head actuated by an electrical screwdriver. The device has a support for the fastener, a holder for the rotating tool that rotates with the support to clamp or unclamp the fastener, and an outer body with an anti-rotation profile between the support and the holder.
A computer implemented method to prevent a non-viable state of loading in an aircraft before the aircraft is loaded. Given a layout of the load space and a set of load units, the method estimates the state of loading and prevents loads that would be non-viable once the aircraft is loaded.
B64D 9/00 - Appareillage pour manutention du fretAppareillage pour faciliter l'embarquement des passagers ou autres
G01G 19/414 - Appareils ou méthodes de pesée adaptés à des fins particulières non prévues dans les groupes avec dispositions pour indiquer, enregistrer ou calculer un prix ou d'autres quantités dépendant du poids utilisant des moyens de calcul électromécaniques ou électroniques utilisant uniquement des moyens de calcul électroniques
A method of applying an ice-removal fluid (113) to a folding wing aircraft (100) is described, the method comprising applying the ice-removal fluid (113) to the folding wing portion (103) and holding the folding wing portion in an over-folded position (111) once the ice-removal fluid (113) has been applied. A method of operating an aircraft (100) during ground based operations is further described using the method of applying an ice-removal fluid (113).
B64F 5/23 - Installations au sol pour le dégivrage d’aéronefs par application de liquideInstallations de pulvérisation à cet effet, p. ex. montées sur des véhicules
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
An aircraft wing having a fixed wing and a moveably mounted wing tip device is disclosed. A first cable harness and a second cable harness which are received in a protective sleeve extend between the fixed wing and the wing tip device. The protective sleeve is in a secured configuration in which at least two opposing parts of the protective sleeve are secured together between the first cable harness and the second cable harness to provide the sleeve with a first channel in which the first cable harness is received a second channel in which the second cable harness is received, and a webbing region extending between the first channel and the second channel such that the first and second cable harnesses are held apart by the webbing region.
An air distribution system for an aircraft includes a fabric air manifold, and a utility line attached to the fabric air manifold. The utility line may be located interior or exterior of the fabric air manifold, such as in a pocket provided in the fabric air manifold, or attached with a fastener.
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
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
14 - Métaux précieux et leurs alliages; bijouterie; horlogerie
25 - Vêtements; chaussures; chapellerie
28 - Jeux, jouets, articles de sport
36 - Services financiers, assurances et affaires immobilières
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Air vehicles; Aircraft; Pilotless aircraft; Helicopters and rotorcraft; Drones; Space vehicles; Parts, components and elements of aircraft. Key rings; Lanyards for keys; Pins [jewellery]; Watches. Clothing; Shoes; Headgear. Scale model vehicles and their parts; Carpets for vehicles (playthings); Toys; Games; Video game apparatus; Computer game apparatus; Video game consoles; Computer game consoles; Educational games; Electronic games. Financial, monetary and banking services; Financial investment; Financial exchange of crypto assets; Electronic transfer of cryptocurrency; Exchange of digital currencies. Custom manufacture of air vehicles for others; Custom manufacture of aeronautical and space vehicles for others; Custom manufacture of graphics and trim for vehicles; Recycling and treatment of waste from aircraft, spacecraft and aeronautical and space vehicles, and parts and elements thereof; Information, consultancy and advisory services Relating to the recycling of waste from aircraft, spacecraft and aeronautical and space vehicles, and parts and elements thereof. Scientific and industrial research; Engineering services; Engineering research; Engineering design and consultancy; Conducting industrial tests and Conducting industrial experiments; Technological research; Industrial analysis and research; Scientific and technological services and research and design relating thereto; Technological project studies; Technological analysis services; Design and development services in the field of aviation; Design of prototypes; Design of vehicles; Graphic arts design; Styling [industrial design]; Certification and re-certification of the quality and industrial standards of vehicles; Blockchain as a service [BaaS]; providing temporary use of non-downloadable software for enabling members of an online community to receive and access digital files authenticated by non-fungible tokens (NFTs); Computer programming of online, non-downloadable virtual goods for use in virtual environments.
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
14 - Métaux précieux et leurs alliages; bijouterie; horlogerie
25 - Vêtements; chaussures; chapellerie
28 - Jeux, jouets, articles de sport
36 - Services financiers, assurances et affaires immobilières
40 - Traitement de matériaux; recyclage, purification de l'air et traitement de l'eau
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Air vehicles; aircraft; unmanned aircraft; helicopters and rotorcraft; drones; space vehicles; parts, components and component parts for aircraft. Key rings; lanyards for keys; pins (jewelry); watches. Clothing; shoes; headwear. Scale model vehicles and parts thereof; model vehicles (toys); toys; games; video game apparatus; video game apparatus; video game consoles; video game consoles; educational games; electronic games. Financial, monetary and banking services; financial investments; financial crypto asset exchanges; electronic transfer of crypto-assets; digital currency exchange services. Custom manufacturing of air vehicles for third parties; custom manufacturing of aeronautical and space vehicles for third parties; custom manufacturing of graphics and wraps for vehicles; recycling and waste treatment of aircraft, spacecraft and air and space vehicles, and parts and components therefor; information, advice and assistance with respect to waste recycling of aircraft, spacecraft and air and space vehicles, and parts and components therefor. Scientific and industrial research; engineering; engineering research; engineering design and consulting; conducting industrial tests and experiments; technological research; industrial research and analysis services; scientific and technological services as well as research and design services relating thereto; technological project studies; technological analysis services; design and development services in the field of aviation; design of prototypes; design of vehicles; graphic arts design services; styling (industrial design); certification and re-certification regarding the quality and industry standards of vehicles; Blockchain as a Service [BaaS]; temporary provision of non-downloadable software enabling members of an online community to receive and access digital files authenticated by non-fungible tokens (NFTs); computer programming of online, non-downloadable virtual goods intended for use in virtual environments.
100.
INTERACTIVE MANAGEMENT DEVICE AND METHOD FOR MANAGING MAINTENANCE DEVICES FOR AN AIRCRAFT
The present invention relates to an interactive management device (1) for managing maintenance devices (15) for an aircraft (100) comprising: a computer unit (2) with computer program (3) and at least one interactive interface (4) configured to connect external technical participants with the computer unit (2) with computer program (3) wherein the external technical participants comprise at least one participant from a group of maintenance devices (15), in particular from a group of ground support equipment, for an aircraft (100). In addition, a method (M) for managing maintenance devices for an aircraft (100) is disclosed.
