AIRCRAFT PROPULSION ASSEMBLY EQUIPPED WITH A THRUST-REVERSING DEVICE COMPRISING AT LEAST ONE INFLATABLE BARRIER, AND AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION ASSEMBLY
An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.
F02K 1/32 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyère; Tubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour inverser la poussée
A system for managing flight parameters of aircraft is parametrized with overarching flight cost objectives. For a first flight, parameters of a cost function for the first flight are determined relative, respectively, to different cost factors. Flight parameters are optimized so as to minimize the cost function. Avionics of an aircraft carrying out the first flight are programmed with the flight parameters. On detecting an event in flight requiring the flight parameters to be revised, the parameters of the cost function are recalculated, as well as the flight parameters, and the avionics are reprogrammed accordingly. The method is repeated for at least a second flight, taking into account the effective contribution of the first flight to the overarching objectives, and so on. Thus, an airline can carry out overarching multi-objective optimization on its flights.
An apparatus contains a dihydrogen tank and/or a dihydrogen circuit, and a device for regulating a concentration of dihydrogen located outside the tank and/or the circuit. The device includes at least one pair of electrical conductors including a first electrical conductor supplied with a first voltage and a second electrical conductor supplied with a second voltage which is different from the first voltage. At least one controller repeatedly commands the application of a predetermined voltage difference between the first electrical conductor and the second electrical conductor so that an electric arc of controlled power is formed in order to burn dihydrogen possibly coming from the tank and/or from the circuit. Thus, dihydrogen does not accumulate in undesired places in the apparatus.
A nacelle includes a thrust reverser having a cowl movable in translation and an ejection structure also movable in translation and forming with the cowl a moving assembly, the moving assembly configured to moved, alternately, into a closed position in which the ejection structure is inserted into a housing formed in the nacelle and the cowl closes an ejection opening in the nacelle, and an open position in which the cowl releases the ejection opening in the nacelle and the ejection structure is located in this ejection opening, the positioning of the ejection structure in the housing in the closed position making it possible, in particular, to make space in the ejection opening and to reduce the size of the thrust reverser.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
F02K 1/76 - Commande ou régulation des inverseurs de poussée
5.
METHOD FOR MOUNTING A VORTEX GENERATOR ON A CURVED AERODYNAMIC PANEL OF AN AIRCRAFT AND AIRCRAFT COMPRISING AT LEAST ONE VORTEX GENERATOR MOUNTED IN THIS WAY
A method for mounting a vortex generator on an aerodynamic panel of an aircraft, including, before the step of assembling the vortex generator and the aerodynamic panel, a step of installing at least one shim interposed between the base of the vortex generator and the aerodynamic panel, the shim including a first face, oriented towards the aerodynamic panel during operation, that is shaped like the inner surface of the aerodynamic panel, and a second face, oriented towards the base during operation, that is shaped like the upper face of the arm of the base. This solution makes it possible to manufacture the vortex generator without taking into account the curvature of the aerodynamic panel. An aircraft is provided including at least one vortex generator mounted in this way.
An aircraft comprising a structure, a tank housed in the fuselage, and fastening means which comprise a front fastening system, a rear fastening system and a lateral fastening system. The front system comprises a front plate, two lateral connecting rods and a central connecting rod that are fastened between the front plate and the tank. The rear system comprises a rear plate and a rear connecting rod fastened between the rear plate and the tank. The lateral system comprises a lateral connecting rod fastened between the structure and the tank, wherein one of the connection points is behind the other connection point.
An aircraft sound diagnostic method includes a step of measurement of acoustic signals by a plurality of microphones mounted at different positions inside the aircraft, a step of recording of the measured acoustic signals, a computation step which generates a sound mapping on the basis of the measured acoustic signals, a step of comparison of the sound mapping and a reference mapping and a step of transmission of the comparison to a user device. The method makes it possible to track the trending of an abnormal noise or of an abnormal noise level and assist in determining the context thereof. An aircraft sound diagnostic device for implementing the method is also described.
G01H 17/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores non prévue dans les autres groupes de la présente sous-classe
A fuel tank for an aircraft, including a fuel pumping system which includes a set of hoses, first ends of which are distributed over a lower part of the tank, a manifold to which second ends of the different hoses of the set of hoses are connected as input, an output of the manifold being connected to a fuel pump, a fuel level sensor associated with each hose of the set of hoses and placed in the vicinity of the first end of said hose, and a valve associated with each hose and controlled by a control system which is configured such that when the fuel level sensor associated with this hose detects a low fuel level, the valve is controlled into a closed position, and otherwise the valve is controlled into an open position.
A propulsion assembly for an aircraft, which has a propulsion system with a combustion chamber surrounded by a casing, a supply pipe that conveys dihydrogen to the combustion chamber through the casing via injectors, and a housing fastened to the casing in a sealed manner around the latter, wherein the supply pipe has a downstream part housed inside the housing and wherein the injectors are also housed inside the housing.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
F02C 7/22 - Systèmes d'alimentation en combustible
A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
F02C 7/22 - Systèmes d'alimentation en combustible
11.
Cellular Sandwich Panel Containing Boron Nitride Powder and Manufacturing Method for Said Panel
A cellular sandwich panel containing boron nitride powder and a manufacturing method. The sandwich panel has a first skin and a second skin between which is positioned a cellular core with cells opening out on both sides respectively in the first skin and the second skin, the cells being separated from one another by side walls. The side walls of the core comprise an aramid-, carbon- or glass-fibre-based reinforcement, a polymeric reinforcing resin and boron nitride powder.
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de 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
B32B 3/26 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche comportant des cavités ou des vides internes
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 5/16 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par le fait qu'une des couches est formée de particules, p.ex. de copeaux, de fibres hachées, de poudre
12.
METHOD FOR ASSEMBLING A FUSELAGE PORTION USING WELDING, WITH IMPROVED FLEXIBILITY, AND FUSELAGE PORTION AND AIRCRAFT THUS OBTAINED
A method for assembling aircraft panels by welding improves the flexibility thereof. Panels are butted together along longitudinal joining lines and fixed to one another via their longitudinal edges by welding without the longitudinal ends of their welded edges being connected to one another. Longitudinal hoops are fixed to partially cover the concave surface of the panels at least partially at the ends. The absence of welding at the ends introduces the desired flexibility. The disclosure also covers the fuselage portions formed by assembling panels according to this method and the aircraft including such portions.
A method for estimating a residual stress field in a workpiece. The method includes measuring geometric parameters of the workpiece during machining at which a residual stress field is to be known to determine a geometric profile of said workpiece, estimating, from the geometric profile and an estimation model, subsequent deformations that the workpiece is liable to undergo during further machining, said estimation model being trained by machine learning on training workpieces to use the geometric profile of the workpiece and prerecorded data on the training workpieces to estimate said subsequent deformations of the workpiece, and estimating from the subsequent deformations and a simulation model, the residual stress field in the workpiece, said simulation model being a generic physical model based on simulations defining a variability of the residual stress field in the workpiece as a function of manufacturing parameters of the raw workpiece.
A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.
F02K 3/04 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux
B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes
B64D 29/06 - Fixation des nacelles, carénages ou capotages
15.
AIRCRAFT PROPULSION ASSEMBLY HAVING A DEVICE FOR REACTING THRUST FORCES
A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R2), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R2), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.
A tank including interior and exterior skins separated by an intercalated zone and at least one inspection device. The inspection device includes a first orifice configured to establish communication between the interior zone of the tank and the intercalated zone via the interior skin, configured to be blocked by a first plug, a second orifice configured to establish communication between the intercalated zone and the exterior zone of the tank via the exterior skin, configured to be blocked by a second plug, the first and second orifices being aligned in a radial direction, an intercalated pipe connecting the interior and exterior skins, communicating with the first and second orifices and including a bellows configured to be deformed in the radial direction.
F17C 13/00 - RÉCIPIENTS POUR CONTENIR OU EMMAGASINER DES GAZ COMPRIMÉS, LIQUÉFIÉS OU SOLIDIFIÉS; GAZOMÈTRES À CAPACITÉ FIXE; REMPLISSAGE OU VIDAGE DE RÉCIPIENTS DE GAZ COMPRIMÉS, LIQUÉFIÉS OU SOLIDIFIÉS - Détails des récipients ou bien du remplissage ou du vidage des récipients
In an aircraft, a fuel return valve (FRV) controls a flow of fuel, used to cool an oil feeding a propulsion engine and an oil of an integrated drive generator (IDG). A first sensor supplies measurements of the oil temperature at an output port of the IDG and a second sensor supplies measurements of oil temperature of the propulsion engine. An FRV operation monitoring system: determines, for each flight of the aircraft, an oil temperature maximum at an output port of the IDG and/or a maximum oil temperature of the propulsion engine; assesses a trend of one and/or the other of the oil temperature maxima over several flights; and generates an alarm when the trend of one and/or the other of the oil temperature maxima shows that a predetermined threshold has been exceeded.
F02C 9/36 - Commande de l'alimentation en combustible caractérisée par un retour du combustible au réservoir
G01K 1/02 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres
G01K 3/00 - Thermomètres donnant une indication autre que la valeur instantanée de la température
G01K 13/02 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler
18.
METHOD OF CONTROLLING A DEVICE FOR SUPPLYING A PROPULSION SYSTEM OF AN AIRCRAFT AND SUPPLY DEVICE ENABLING EXECUTION OF THAT METHOD
A method of controlling a fuel supply device of at least one aircraft propulsion system. The method includes a step of determining the state of the fuel flowrate control system following a change of state that has moved it away from an initial state, a step of modifying the pressure of the fuel as a function of the state of the fuel flowrate control system that has been determined, and a step of changing the state of the fuel flowrate control system to return it to or toward the initial state.
F02C 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
F02C 9/26 - Commande de l'alimentation en combustible
19.
METHOD FOR DETECTING A MALFUNCTION SUFFERED BY AN INTEGRATED DRIVE GENERATOR, IN AN AIRCRAFT
A data analysis system comprises an artificial intelligence of the machine learning type. The data analysis system collects reference data relating to measurements made and recorded during previous flights of aircraft. A training of the artificial intelligence of the machine learning type is implemented by virtue of reference data, with a first classification run for training to detect potential malfunctions suffered by integrated drive generators and a second classification run for training to determine causes of the malfunctions, where relevant. After using in production, the data analysis system collects data to be analyzed relating to measurements made and recorded during flights of the aircraft comprising an integrated drive generator to be monitored, and uses the artificial intelligence of the machine learning type to predict a potential malfunction and, where relevant, predict its cause using data to be analyzed.
G01R 31/00 - Dispositions pour tester les propriétés électriques; Dispositions pour la localisation des pannes électriques; Dispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
H02K 11/20 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection pour la mesure, la surveillance, les tests, la protection ou la coupure
20.
AIRCRAFT FUSELAGE DOOR COMPRISING AN INTERNAL PANEL AND AN EXTERNAL PANEL, AND AIRCRAFT FUSELAGE PART COMPRISING SUCH A DOOR
An aircraft fuselage door with an internal and external panel, and an aircraft fuselage part with the door. The door includes a movable internal panel to be subjected to pressurization and an aerodynamic external panel, the external panel being on an external face of the internal panel by covering the surface of the external face and elastically linked to the internal panel to form an internal free space between them, the internal panel being movable relative to the external panel. The external panel includes a centering piece to ensure a self-centering function of the door allowing the internal panel to move independently with regard to the external panel when the door is in a closed position so a clearance between the periphery of the outer panel and the fuselage can be reduced, thereby reducing drag at the outer surface of the door and improving the aerodynamic performance of the aircraft.
An aircraft electrical structure comprises equipment items that are interconnected by cables. A processing system constructs (400) a digital representation of the electrical structure in the form of nested graphs. A first graph represents the electrical structure by first arcs representing the cables and first nodes representing the equipment items. A second graph represents an internal interconnection structure between at least one input and at least one output of each equipment item which has such an internal interconnection structure, second arcs representing interconnections between inputs and outputs, second nodes representing the inputs and the outputs concerned. The first graph is obtained from contextual data (411) describing the electrical structure and each second graph is obtained from a generic model (412) for each type of equipment item concerned. An analysis is carried out by performing a search (404) for equipotentials by browsing through the nested graphs. Thus, the analysis is facilitated.
An aircraft pylon comprising a box-section primary structure and at least one tank positioned inside the primary structure. To facilitate mounting or demounting the tank, the pylon is equipped with a guide system configured to move the tank from its mounted position toward a through-hole, including a guide rail fastened to the primary structure and positioned above the tank and a guide pin fastened to the tank cooperating with the guide rail so that the tank is supported by the guide rail and is able to slide along the latter. This guide system contributes to simplifying manipulation of the tank when mounting or demounting the tank by at least partly compensating its weight and guiding the tank.
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
A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice
A system for controlling aircraft flight control surfaces implements a method including: obtaining a control law for the flight control surfaces as a function of flight controls of the aircraft; obtaining measurements of ground speed, true speed, roll angle, pitch angle, angle of attack, sideslip angle and slope angle; performing an estimation of the wind in three dimensions using the measurements obtained; performing an adjustment of the control law for the flight control surfaces, to counter the estimated wind effect and to obtain an adjusted control law for the flight control surfaces, by adding, to the control law, a term for wind compensation comprising a term proportional to the derivative of the wind estimation; and controlling the aircraft by applying the adjusted control law. Thus, the impact of the wind on the aircraft is reduced by digital processing and automatic adjustment of the control of the flight control surfaces.
An avionics rack module, with two shelves and a column, the column linking the two shelves. The module has a first airstream and a second airstream each circulating in the column and in the shelves, to cool at least one avionics element. Each of the two shelves comprises (i) a plate extending on a transverse plane and intended to support an avionics element and comprises (ii) a half-shell extending on a longitudinal plane secant to the transverse plane and being intended to be joined to another half-shell of the other shelf of said module, to form the column. Also an avionics rack made from multiple modules and an aircraft with such an avionics rack.
A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
26.
NACELLE OF AN AIRCRAFT ENGINE, COMPRISING AN IMPROVED HEAT EXCHANGER
An aircraft engine nacelle in which the inner fixed structure has a heat exchanger which is filled with a two-phase heat transfer fluid and which comprises a tube forming a loop with front, rear, lower and upper strands, and also a first complementary strand between the central zones of the front strand and of the upper strand, a second complementary strand between the central zones of the front strand and of the lower strand, a third complementary strand between the central zones of the rear strand and of the upper strand, and a fourth complementary strand between the central zones of the rear strand and of the lower strand.
A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective cylinder fastened to the frame or to the casing by fastening means and positioned around the casing and between the supply pipe and the turbine. With such an arrangement, if a blade of the turbine became detached it would meet the protective cylinder blocking its path to the dihydrogen pipe and would thus be diverted or stopped.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
28.
AIRCRAFT FLOOR COMPRISING A SEALING TARPAULIN, AND AIRCRAFT COMPRISING SAID FLOOR
An aircraft floor including a structure, a deck attached to the structure, and first and second sealing barriers superposed at least in line with a protection zone, the deck being configured to form the first sealing barrier at least in line with the protection zone. The second sealing barrier includes a sealing tarpaulin interposed between the deck and the structure and having several reinforcing strips fixed against a face of the sealing tarpaulin oriented toward the structure, at least some of the reinforcing strips being interposed between the sealing tarpaulin and longitudinal reinforcements of the structure of the floor.
An electrical supply system (10) with first and second electrical sourced (S1, S2), coupled together to electrically supply electrical loads (Z1, Z2, Z3 . . . Zn) of an aircraft. The first electrical source (S1) is mechanically coupled to a primary energy source (12), to which at least one other energy consumer (16) is coupled. A controller (30) controls the first and second electrical sources (S1, S2) so that the power drawn by the first electrical source from the primary energy source (12) corresponds to a difference between an instantaneous nominal power capable of being delivered by the primary energy source and an instantaneous power drawn by the energy consumer (16), and an electrical power delivered by the second electrical source is a sum of an electrical power delivered by the first and second electrical sources which corresponds to an instantaneous electrical consumption of the electrical loads.
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.
A supply system for an aircraft arranged between two dihydrogen tanks and an engine. The supply system includes a supply module that assures the flow of dihydrogen between the tanks and an outlet pipe and two heaters mounted in series on a main pipe connected to the engine. The supply system also includes a network of pipes and solenoid valves that, in the event of a problem in one of the components of the supply system, enable dihydrogen to be redirected so as to reach the engine. Also an aircraft with such a supply system.
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
F02C 7/232 - Soupapes pour combustible; Systèmes ou soupapes de drainage
32.
AIRCRAFT FLOOR GRID TRANSPORT SYSTEM FOR ASSEMBLING AN AIRCRAFT FUSELAGE BARREL AND METHOD OF CALIBRATING SAID TRANSPORT SYSTEM
An aircraft floor grid transport system for assembling an aircraft fuselage barrel and method of calibrating the transport system are disclosed. The transport system includes a rectangular beam, a stabilizer device to be associated with referential positioning devices of an assembly platform and a plurality of fixing devices to be fixed to the floor grid, each of the fixing devices having a vertically adjustable length. The transport system makes it possible to handle the floor grid without deforming it in order to assemble a fuselage barrel.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
33.
SYSTEM FOR HANDLING A SIDE SHELL OF AN AIRCRAFT WITH A VIEW TO ASSEMBLING A FUSELAGE BARREL OF THE AIRCRAFT AND METHOD FOR ASSEMBLING A FUSELAGE BARREL OF AN AIRCRAFT
A system for handling a side shell of an aircraft with a view to assembling a fuselage barrel of the aircraft and method for assembling a fuselage barrel of an aircraft are disclosed. The handling system includes at least two fixing devices per side shell. Each of the fixing devices is configured to be fixed to a longitudinal end of the side shell. Each of the fixing devices has a fixing part configured to be fixed on the side shell, a fixing support is configured to mount the fixing device movably on a holding device of an assembly platform, and an elastic element connecting the fixing part to the fixing support.
An assembly platform configured to manipulate at least one aircraft lower shell without deforming it with a view to assembly of an aircraft fuselage barrel is disclosed including at least one rectangular chassis, at least two frames having an adjustable trim with respect to the rectangular chassis, at least two setting systems intended to adjust the trim of the frame and at least two cradles fixed onto the frames and intended to receive the lower shell and to hold the lower shell in a desired form. The cradles of the assembly platform make it possible to prevent a deformation of the lower shell during the assembly of the fuselage barrel.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
35.
REFERENTIAL POSITIONING DEVICE INTENDED TO POSITION RELATIVE TO EACH OTHER AT LEAST ONE CABIN FLOOR GRID AND ONE SIDE SHELL OF AN AIRCRAFT IN ORDER TO ASSEMBLE A FUSELAGE BARREL OF THE AIRCRAFT
A referential positioning device configured to position relative to each other at least one cabin floor grid and one side shell of an aircraft in order to assemble a fuselage barrel of the aircraft is disclosed having at least one fixing support for fixing the referential positioning device to the top of an alignment post of an assembly platform, and a partially spherical support having a spherical surface (S) intended to receive the V-shaped surface of an end of an arm of a transport system for a cabin floor grid of an aircraft. The referential positioning device makes it possible to arrange the cabin floor grid precisely on the assembly platform with respect to the other elements of the fuselage barrel.
A test apparatus and method for testing a trained classifier configured to control an aircraft system. Scenario data includes operating inputs representing an operational state of an aircraft and classifier outputs for controlling the aircraft system, is obtained. Model data representing a model of the at aircraft system is obtained. Error categorisation data for each aircraft operating scenario is generated based on respective classifier outputs applied to the model.
A pipe comprising at least one flexible duct, wherein the pipe comprises at least one stiffening band, which is pressed against the duct over at least some of its length, extends along a longitudinal direction substantially parallel to the axis of the duct and has, at least in one state, considerable rigidity along the longitudinal direction, the stiffening band being configured to deform elastically between a rolled-up state, when the cross sections of the stiffening band are rectilinear, and an elongate and rigid state, when the cross sections of the stiffening band are curved. An aircraft comprising at least one such pipe.
F16L 3/26 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour le support des tuyaux sur toute leur longueur, p.ex. chenal ou conduite de tuyaux
F16L 3/14 - Potences en forme de bandes ou de chaînes
ELECTRIC PROPULSION ASSEMBLY COMPRISING AT LEAST ONE ELECTRIC MOTOR POSITIONED IN FRONT OF A TRANSMISSION SYSTEM, AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION ASSEMBLY
An aircraft propulsion system comprising a propeller, a plurality of electric motors, a transmission system configured to couple the electric motors to the propeller, and a propeller pitch adjustment system positioned at the rear of the transmission system. At least one of the electric motors is positioned in front of the transmission system. A connection structure is interposed between the propeller and the transmission system, the connection structure and the output shaft of the transmission system connected to the propeller being configured so that no electric motor positioned in front of the transmission system interferes with the propeller. Also an aircraft with such a system.
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
39.
ASSEMBLY FOR AIRCRAFT INCLUDING A CHASSIS AND A VISION MODULE OF AN ENHANCED FLIGHT VISION SYSTEM
An assembly for an aircraft including a vision module including a base and a chassis including a first beam fixed to the base by four fixing means, a second beam fixed to the first beam by four fixing means, and two third beams fixed to the structure of the aircraft and between which the second beam is fixed by two third fixing means, where each fixing means takes the form of a system with two eccentric rings where the two rings are mobile in rotation relative to one another about parallel rotation axes. Also an aircraft with such an assembly fixed to a structure thereof.
AIRCRAFT AIR CONDITIONING DEVICE COMPRISING A LARGE-CAPACITY MIXER, METHOD FOR INSTALLING SUCH A DEVICE AND AIRCRAFT EQUIPPED WITH SUCH AN AIR CONDITIONING DEVICE
An air conditioning device includes a mixer configured to mix the air withdrawn from a conditioned-air zone with the regulated air. This mixer includes a body, at least one withdrawn-air inlet connected to a withdrawing circuit and positioned in the vicinity of the lower end of the body, and at least one air outlet connected to a distribution circuit and positioned in the vicinity of the upper end of the body, at least one orifice from among the withdrawn-air inlet and the air outlet being positioned between the lower and upper ends, in the vicinity of one of the lower and upper ends that is closed off by a transverse wall.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
41.
SELF-CLEANING EXTERNAL LAYER COMPRISING A SELF-CLEANING AERODYNAMIC SURFACE, AND VEHICLE COMPRISING SAID EXTERNAL LAYER
A self-cleaning external with a self-cleaning aerodynamic surface configured to extract at least some of the oxygen present in the atmosphere in contact with the aerodynamic surface so as to at least partially deprive a haemolymph of the insect residue, present on the aerodynamic surface after being hit by insects, of oxygen. Also, a vehicle with at least one such self-cleaning aerodynamic surface.
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
42.
METHOD FOR MANUFACTURING AN AIRCRAFT RADOME BY ASSEMBLING SMALL-SIZED PIECES OF SKIN, AIRCRAFT RADOME AND AIRCRAFT
A method of assembling an aircraft radome and a radome comprising at least a first skin and a second skin arranged on two opposite faces of the same shell, the first skin and the second skin being formed from a first assembly of skin pieces and from a second assembly of skin pieces, respectively, the assemblies being such that all or some of the skin pieces of the first and second assemblies partially overlap one or more neighboring skin pieces of the assembly that includes them, and such that the ratio between the surface area of a piece of skin overlapping one or more neighboring pieces of skin and the total surface area of that piece of skin does not exceed a predetermined threshold value.
A structure for an aircraft is disclosed including comprising at least one node which having first and second plates which are pressed against two opposite faces of a first reinforcement, and to which upstream and downstream reinforcements positioned on either side of the first reinforcement are connected. A connection system connecting the first and second plates is disclosed including at least one boss projecting from a surface of one of the plates pressed against the first reinforcement, for each boss, a housing recessed relative to a surface of the other plate pressed against the first reinforcement, configured to house the boss, and at least one fastening element, passing through the first reinforcement, connecting the first and second plates and spaced apart from the boss.
An aircraft propulsion assembly including at least one first support that supports an electric propulsion system, at least one first attachment configured to connect the first support and a support structure of an aircraft, at least one second support distinct from and dissociated from the first support supporting a source of electrical energy configured to supply the electric propulsion system with electrical energy, as well as at least one second attachment configured to connect the second support and the support structure. An aircraft may include at least one such propulsion assembly. Given that the second support is distinct from and dissociated from the first support system, vibrations generated by the electric propulsion system are not transmitted to the source of electrical energy.
A tank system comprising a tank, a drainage line fixed in the bottom part of the tank and having a drainage port at each end and, for each drainage port, a funnel having a wall through which at least one window passes, a body that can move in translation, for each funnel, a plug that is secured to the body and arranged to be able to move inside said funnel between an open position and a closed position, and an arm, a first end of which is mounted in an articulated manner to the top part of the tank and a second end of which is mounted in an articulated manner on the body.
An aircraft including at least one pressure-relief device having: at least one fixed part, at least one deformable mobile wall configured to occupy a closed position in which it blocks an opening, at least one retaining system configured to retain the mobile wall in the closed position as long as the wall is not in a given deformed state, the retaining system including: at least one first slot through the mobile wall opening at the level of one of its edges, for each slot, a first retaining element fastened to the fixed part and configured to cooperate with the slot as long as the mobile part is not in the given deformed state.
An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.
A casing system mounted between an upstream solenoid valve of an upstream pipe and a downstream solenoid valve of a downstream pipe and which has a casing divided by a separation wall into a first volume which is placed under reduced pressure and a second volume, a heat exchanger which is fixed inside the casing with a first inlet which is arranged in the first volume and which is connected to the upstream pipe and a first outlet which is arranged in the second volume and which is connected to the downstream pipe, and a control unit which closes the solenoid valves if the deviation between two successive values of the pressure in the first volume or in the second volume is greater than a threshold.
The electrical supply system (10) of an electrical propulsion system (4) of an aircraft (1) includes: two first sets of fuel cells (FC11, FC12), configured to supply electrically an electric motor driving a propulsion propeller; a first compressor (C1) configured to supply compressed air to at least part of the at least two first sets of fuel cells (FC11, FC12); and a first electric motor (M1) designed to drive the first compressor. The first electric motor (M1) includes electrical windings (W1a, W1b), each electrical winding supplied electrically by a set of distinct fuel cells from amongst the at least two first sets of fuel cells (FC11, FC12).
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B60L 50/70 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des piles à combustible
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 35/02 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le type de groupe moteur
B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
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 8/04014 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur Échange de chaleur par combustion des réactifs
H02P 25/22 - Enroulements multiples; Enroulements pour plus de trois phases
H02P 29/028 - Détection d’un défaut, p.ex. court circuit, rotor bloqué, circuit ouvert ou perte de charge le moteur continuant de fonctionner malgré le défaut, p.ex. élimination, compensation ou résolution du défaut
50.
DEVICE FOR DEPOSITING MATERIAL IN THE FORM OF WIRE COMPRISING AT LEAST ONE WIRE SPOOL AND AT LEAST ONE SYSTEM INDICATING THE FILLING LEVEL OF THE SPOOL
A device for depositing material in the form of wire including a coil of wire configured to pivot around an axis of rotation as well as at least one indication system including a support, at least one rod oriented in a direction secant to the axis of rotation, a pad connected to the first end of the rod and configured to bear against a wire wound on the coil of wire, a sliding link configured to allow the rod to translate in the secant direction, as well as a return element configured to translate the rod in the direction of the axis of rotation, the rod occupying a position according to a level of filling the coil. This solution makes it possible to obtain a passive type indication system.
B23K 9/133 - Moyens pour l'alimentation en électrodes, p.ex. tambours, rouleaux, moteurs
B65H 63/08 - Dispositifs d'alarme ou de sécurité utilisés pour le déroulage, le dévidage, le défilement, l'enroulage, le bobinage ou l'emmagasinage d'un matériau filiforme, p.ex. détecteurs automatiques de défectuosités ou mécanismes d'arrêt réagissant à la livraison d'une longueur donnée du matériau, à l'achèvement de l'enroulage d'un paquet ou au remplissage d'un récipient
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
An aircraft having at least one dihydrogen transport pipe, an embedding channel with a lower gutter, an aeration aperture with an air inlet collecting external air and at least one supply pipe opening at the air inlet, a control unit, and, for one or more lower gutters, a bypass box having, for each lower gutter, an inlet connected to the supply pipe and an outlet connected to the lower gutter, between each associated inlet and outlet, a door able to move alternately between an open position and a closed position, and, for each door, a maneuvering system controlled by the control unit and moving the door.
A fastening system for an aircraft configured to fasten at least one tank intended to contain liquid hydrogen includes a longitudinal box, an upper structure fastened to an upper side of the longitudinal box, a lower structure fastened to a lower side of the longitudinal box and at least two fastening frames including, on either side of the vertical plane of symmetry (P1), a fastening device for connecting a tank to the upper structure. The fastening system further includes at least two fastening devices for connecting a fastening point of the tank to the longitudinal box and at least two fastening devices for connecting a fastening point of the tank to the lower structure. The fastening system makes it possible to securely fasten at least one hydrogen tank on board an aircraft (AC).
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
53.
TOOL FOR LAYING A SEALING STRIP AROUND A PROTRUDING PART OF A CONNECTING ELEMENT, METHOD FOR LAYING A SEALING STRIP USING SAID TOOL, AND AIRCRAFT COMPRISING AT LEAST ONE SEALING STRIP OBTAINED USING SAID LAYING METHOD
A tool for laying a sealing strip around a protruding part of a connecting element protruding from a bearing surface, the laying tool including an annular duct having an outer surface configured to delimit, with the bearing surface and the protruding part, a cavity when the annular duct is positioned around the protruding part and in contact with the bearing surface, the annular duct including at least one orifice for supplying pasty composition and outlet orifices for injecting the pasty composition into the cavity to form the sealing strip. A method for laying a sealing strip using the tool is disclosed and an aircraft with at least one sealing strip obtained using the method.
B29C 39/10 - Moulage par coulée, c. à d. en introduisant la matière à mouler dans un moule ou entre des surfaces enveloppantes sans pression significative de moulage; Appareils à cet effet pour la fabrication d'objets de longueur définie, c. à d. d'objets séparés en incorporant des parties ou des couches préformées, p.ex. coulée autour d'inserts ou sur des objets à recouvrir
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
A tow-bar fitting for connecting a tow-bar to an aircraft landing gear is disclosed including a tow-bar attachment to which, in use, the tow-bar is coupled. The tow-bar fitting also includes a first fuse member via which linear loads but not torque loads are transmitted from the tow-bar attachment to the rest of the landing gear. The first fuse member is configured to fail at a predetermined linear load threshold. The tow-bar fitting includes a second fuse member via which torque loads are transmitted from the tow-bar attachment to the rest of the landing gear. The second fuse member is configured to fail at a predetermined torque load threshold. A method of towing an aircraft is also disclosed.
A fuel cell system comprises a fuel cell unit in a housing and comprising an anode part and a cathode part, a hydrogen source for supplying hydrogen to the fuel cell unit, an air supply unit for supplying air to the fuel cell unit, and a catalytic converter for catalytically converting oxygen and hydrogen to generate an inert gas mixture and supplying it to the interior of the housing. The catalytic converter comprises a cathode exhaust gas intake for receiving a cathode exhaust gas from the cathode part of the fuel cell unit. In a method for generating inert gas for a fuel cell system, a purge gas is supplied from the anode part of the fuel cell unit, and/or fresh hydrogen is supplied from a hydrogen supply unit of the fuel cell unit to the catalytic converter, to generate the inert gas mixture.
H01M 8/0662 - Traitement des réactifs gazeux ou des résidus gazeux, p.ex. nettoyage
H01M 8/04223 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides pendant le démarrage ou l’arrêt; Dépolarisation ou activation, p.ex. purge; Moyens pour court-circuiter les éléments à combustible défectueux
H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux
ADDITIVE MANUFACTURING METHOD BY DEPOSITION OF MATERIAL UNDER FOCUSED ENERGY ENABLING PRODUCTION OF INTERSECTING RIBS AND RIBBED PART OBTAINED USING SAID METHOD
A method for additive manufacturing at least one intersection of first and second ribs by stacking layers of material, at least one layer of material of a first section of the first rib being obtained by depositing at least one bead of material that extends on respective opposite sides of the intersection. Wherein in that at least one layer of material of a second section of the second rib comprises a first part obtained by depositing at least one bead of material at a distance from the first section that extends in the direction of the second section and a second part obtained by depositing at least one bead of material adjacent to the first section that extends in the first direction. Also a method of manufacturing a ribbed panel and a ribbed panel.
Institut National des Sciences Appliquées de Toulouse (INSAT) (France)
Centre National de la Recherche Scientifique (CNRS) (France)
Université Toulouse III - Paul Sabatier (UT3) (France)
Institut Supérieur de l'Aéronautique et de l'Espace (ISAE) (France)
École nationale supérieure des Mines d'Albi - Carmaux (IMT Mines ALBI) (France)
Inventeur(s)
Bourhis, Arnaud
Rafik, Younes
Palanque, Valerian
Pommier Budinger, Valérie
Budinger, Marc
Saudel, Brice
Clergent, Yves
Olivier, Philippe
Abrégé
A de-icing element having a skin with a surface to be de-iced, at least one excitation actuator attached to the skin, the excitation actuator configured to excite the skin according to at least one predetermined vibration mode generating a deformation of the skin, the deformation of the skin comprising at least one antinode and one node. The skin having a characteristic thickness generally constant with, locally, at least one thickness variation that is localized according to the predetermined vibration mode or modes.
B64D 15/16 - Dégivrage ou antigivre des surfaces externes des aéronefs par dispositifs mécaniques, p.ex. des gaines ou des bourrelets fixés ou incorporés à la surface et soumis à des pulsations
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
58.
METHOD OF MONITORING A STATE OF A MACHINE LEARNING CLASSIFIER
Techniques for monitoring a state of a machine learning classifier to determine an operational mode of an aircraft system are provided. The techniques include applying to each input node of the machine learning classifier an operational mode status of a respective component an aircraft system and a node priority determined by the order of priority of the respective series component path of the aircraft system. Varying, for an operational mode status combination, an input node state of an input node having a relatively low node priority. Indicating a normal state of the machine learning classifier where output node states do not vary in response to the varying, and indicating an altered state of the machine learning classifier where a hidden layer node state and an output node state vary in response to the varying of the input node state.
G06N 3/063 - Réalisation physique, c. à d. mise en œuvre matérielle de réseaux neuronaux, de neurones ou de parties de neurone utilisant des moyens électroniques
59.
ACOUSTIC PANEL FOR AN AIRCRAFT PROVIDING NOISE ATTENUATION OVER A WIDE FREQUENCY BAND BY COMBINING TWO RESONATORS, AND ACOUSTIC PANEL MANUFACTURING METHOD
An acoustic panel for an aircraft providing noise attenuation over a wide frequency band by combining two resonators, and acoustic panel manufacturing method. The acoustic panel includes a rear skin, a cellular structure, an intermediate layer including perforations, a cellular structure, a cellular structure and a resistive skin including perforations. The acoustic panel combines quarter-wave resonators with Helmholtz resonators to provide noise attenuation over a wide frequency range.
B64C 1/40 - Insonorisation ou isolation calorifique
F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyère; Tubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
B32B 37/02 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la séquence des opérations de stratification, p.ex. par addition de nouvelles couches à des postes successifs de stratification
B32B 37/12 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par l'usage d'adhésifs
B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de 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
60.
SET OF DOORS FOR AN AIRCRAFT FRONT LANDING GEAR BAY COMPRISING FRONT DOORS FITTED WITH DEFLECTORS
A set of doors includes two front doors and two rear doors to open or close the front landing gear bay of the aircraft to enable lowering or retraction of a landing gear, each of the front doors including at least one deflector arranged on an internal face of the front door near a rear leading edge thereof, the deflector extending along the rear leading edge, the set therefore enabling action on an aerodynamic flow between the front doors to disturb it in such a manner as significantly to attenuate undesirable transitory vibratory phenomena that can arise in a particular configuration in which the front doors are open and the rear doors are closed.
A tank configured to store a liquid and that includes at least one capture device which includes at least a first portion of a line situated at the bottom of the tank, close to its first end, and at least a second portion of the line situated at the bottom of the tank, close to its second end, each of the first and second portions including at least one orifice situated on the upper face thereof, a floating shut-off device for each orifice, the floating shut-off device being movable between an open position in which the floating shut-off device is spaced apart from the orifice and a closed position in which the floating shut-off device shuts off the orifice, the floating shut-off device having a density lower than that of the liquid stored in the tank.
A windshield architecture with window including at least one ply of material that is transparent and of mineral origin and having a peripheral edge. At least one of the mineral material plies of the window is coated with a coating layer of viscoelastic transparent organic material over an entire surface of the play, including the peripheral edge.
An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.
A deflector for an ejection structure of a thrust reverser is disclosed including a deflector plate configured to act on an aerodynamic flow, the deflector plate having a concave upstream face, a convex downstream face, an inlet end, and an outlet end. The upstream face and the downstream face of the deflector plate have different curved profiles, the deflector has a particular profile giving it properties allowing it to act effectively on the aerodynamic flow so as to enhance the performance of the thrust reverser in which it is mounted.
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
65.
AIRCRAFT COMPRISING A WING ATTACHMENT FOR HIGH WINGS HAVING OBLIQUE CONNECTIONS
An aircraft with a wing attachment connecting the wings and the fuselage of the aircraft and having first and second parts positioned on either side of the median longitudinal plane of the aircraft. Each first or second part comprises at least one vertical connection configured to transmit substantially vertical forces between one of the wings and the fuselage, and first and second oblique connections each having at least one first or second oblique rod that has a first end connected to the fuselage structure and a second end connected to the wing structure, the second ends of the first and second oblique rods being further apart than their first ends.
A deflector provided with a spoiler for a thrust reverser of an aircraft engine nacelle. The deflector, a lateral deflector or an orbital deflector, may be in an exhaust structure of a thrust reverser and comprises a deflector plate configured to act on an aerodynamic flow. The deflector plate has a concave upstream face and a convex downstream face, as well as an intake end and an exhaust end. The deflector is fitted with a spoiler rigidly connected to the exhaust end of the deflector plate and arranged transversely in relation to the deflector plate. The spoiler endowing the deflector with specific properties to act on the aerodynamic flow.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
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
67.
MONITORING FRICTION ASSOCIATED WITH A PLURALITY OF AIRCRAFT WHEELS
A method of monitoring friction associated with a plurality of aircraft wheels of an aircraft, the method including, for each of the plurality of aircraft wheels, obtaining wheel speed data associated with the aircraft wheel. The method includes determining, based at least in part on the wheel speed data, deceleration of the aircraft wheel during a time interval, and determining, based at least in part on the determined deceleration, a value indicative of friction associated with the aircraft wheel. The method includes providing, based at least in part on the determined value, a signal indicative of a level of friction associated with the aircraft wheel.
A method for monitoring the integrity of a set of air bleed lines from propulsion engines of an aircraft by: at the start of a use of the aircraft, sending air from an auxiliary power unit into the various lines; over a predetermined period of time, acquiring temperature measurements from temperature sensors associated with the lines; for each line, determining a gradient for rate of change in temperature with respect to time during this period of time; determining a discrepancy between the gradient for rate of change in temperature with respect to time corresponding to a line and a gradient for rate of change in temperature with respect to time corresponding to at least one other line; determining a condition indicator for the condition of the line as a function of the discrepancy determined for said line.
A method of performing a configuration procedure for first and second tire pressure monitoring devices. The method includes loading the first tire pressure monitoring device with first configuration data, and subsequently transmitting, from the first tire pressure monitoring device, a first configuration data signal which encodes the first configuration data. The method includes subsequently loading the second tire pressure monitoring device with second configuration data, and subsequently ending the configuration procedure without transmitting a second configuration data signal which encodes the second configuration data.
A method of configuring a network of tire monitoring devices using an untrusted device is provided. An untrusted device transmits first configuration data to a first tire monitoring device, and then receives a first input verifying that the first configuration data has been loaded to the first tire monitoring device and matches expected first configuration data. The untrusted device transmits second configuration data to a second tire monitoring device, and receives a second input verifying that the second configuration data has been loaded to the second tire monitoring device and matches expected second configuration data. The untrusted device transmits a command initializing generation of a cryptographic parameter by the first tire monitoring device, and causes the cryptographic parameter to be exchanged with the second tire monitoring device such that secure future communication is established between the first and second tire monitoring devices.
B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
H04L 67/12 - Protocoles spécialement adaptés aux environnements propriétaires ou de mise en réseau pour un usage spécial, p.ex. les réseaux médicaux, les réseaux de capteurs, les réseaux dans les véhicules ou les réseaux de mesure à distance
An acoustic panel including first and second cellular structures, the first cellular structure including a set-back portion to form a recess dimensioned to accommodate the second cellular structure such that first faces of the first and second cellular structures, in contact with a first, acoustically resistive layer, are coplanar and that first edge faces of the first and second cellular structures are coplanar when the second edge face of the second cellular structure is in contact with the set-back portion. By virtue of the set-back portion, the first and second cellular structures are positioned correctly with respect to one another, thus contributing to an optimization of the acoustic treatment.
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
F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyère; Tubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
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
72.
AIRCRAFT AIR DUCT PIPE COMPRISING AT LEAST ONE PIPE COUPLING AND METHOD OF MANUFACTURING SAID PIPE
A pipe of an air duct comprising, from the interior toward the exterior, an internal layer, at least one insulating intermediate layer, an external layer and at least at one of its ends a pipe coupling distinct from the internal layer including a first end section that cooperates with the internal layer in sealed manner and a second end section not covered by any of the layers that is configured to cooperate with a connection system. Thus, no clamp of a connection system exerts compression forces on the internal layer of the pipe, which consequently is not necessarily reinforced by means of fibers.
F16L 9/12 - Tuyaux rigides en plastique avec ou sans armature
F16L 59/07 - Dispositions utilisant une couche d'air ou le vide la couche d'air étant enveloppée par une ou plusieurs couches d'isolation
73.
AIRCRAFT COMPRISING AT LEAST ONE SYSTEMS CABINET CONNECTED TO A LANDING GEAR COMPARTMENT BY AT LEAST ONE SLIDING CONNECTION SLIDING IN A LONGITUDINAL DIRECTION
An aircraft having a systems cabinet positioned in an avionics bay to the rear of a landing gear compartment and connected to the fuselage by at least one lower connecting system. The systems cabinet and/or the lower connecting system comprises at least one longitudinal beam, which has a front end connected by a front connection to a wall separating the avionics bay and the landing gear compartment, the front connection comprising a sliding connection sliding in a direction substantially parallel to the longitudinal axis.
A propulsion system for an aircraft comprises a closed cooling circuit which has at least one main segment and at least two secondary segments, in which a heat-transfer fluid circulates. Each secondary segment has: a leak detection device, a shut-off valve, and a non-return valve. The cooling circuit also has electronic circuitry configured to close the shut-off valve of a secondary segment when a leak is detected by the leak detection device of said secondary segment.
A propulsion assembly is disclosed including a pylon, a turbomachine comprising an engine and a fan surrounded by a fan casing, a nacelle surrounding the engine and the fan casing, and including a load bearer positioned at the upper part of the nacelle, a forward fan mount between a frontal zone of the fan casing and a frontal zone of the load bearer, a rear pylon mount between the pylon and the load bearer, and a positioning assembly providing positioning between the fan casing and the load bearer. The propulsion assembly is configured to control the separations between the cowls mounted in a moveable manner on the load bearer and a nose cowl.
A propulsion assembly is disclosed including a pylon, a turbomachine including an engine and a fan surrounded by a fan casing, a nacelle surrounding the engine and the fan casing, and including a load bearer positioned at the upper part of the nacelle and split into two bearers, a forward fan mount between a frontal zone of the fan casing and a frontal zone of the upstream bearer, a rear pylon mount between the pylon and the downstream bearer, and a positioning assembly providing positioning between the fan casing and each bearer. The propulsion assembly is configured to improve the control over the separation between the articulated lateral cowls and the nose cowl.
A honeycomb structure having a core made up of a plurality of corrugated sheets which are superposed and adhesively bonded together is described. The corrugated sheets are made from a thermally insulating material. Bear filaments are made up of thermally conductive filaments. The honeycomb structure can be used when the ambient temperature exceeds, for example, 120° C.
B29D 24/00 - Fabrication d'objets avec parois creuses
B29C 70/08 - 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 comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 70/88 - 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 caractérisées principalement par des propriétés spécifiques, p.ex. électriquement conductrices ou renforcées localement
B29C 65/00 - Assemblage d'éléments préformés; Appareils à cet effet
78.
HONEYCOMB STRUCTURE HAVING IMPROVED THERMAL CONDUCTIVITY
A honeycomb structure has a core made up of a plurality of corrugated sheets which are superposed and fixed together. The corrugated sheets are made from a thermally insulating material. The corrugated sheets are impregnated with a resin filled with thermally conductive powder along their entire length. The honeycomb structure can be used when the ambient temperature exceeds, for example, 120° C.
B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de 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
B32B 3/28 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche comportant des cavités ou des vides internes caractérisés par une couche comportant une feuille mince déformée, p.ex. ondulée, froissée
B32B 27/34 - Produits stratifiés composés essentiellement de résine synthétique comprenant des polyamides
B32B 37/18 - 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 feuilles ou de panneaux individualisés
B32B 37/12 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par l'usage d'adhésifs
B32B 27/08 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique d'une résine synthétique d'une sorte différente
79.
COMPACT ELECTRIC PROPULSION UNIT COMPRISING A STATICALLY DETERMINATE ENGINE MOUNT, AND AIRCRAFT COMPRISING AT LEAST ONE SUCH ELECTRIC PROPULSION UNIT
An aircraft propulsion unit with an engine mount connecting a rigid casing, supporting a propeller, and a structure. First and second transverse link rods connect the casing and the structure with first and second joints each having an axis of pivoting substantially parallel to an axis of rotation of the propeller. First and second thrust rods connect the casing and the structure by first and second thrust rod connections. The first and second thrust rod connections separated from one another in the longitudinal direction. A longitudinal end stop is configured to limit the movement of the casing with respect to the structure in at least the longitudinal direction. An aircraft with at least one such propulsion unit.
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
80.
CONNECTING ROD ADJUSTABLE IN LENGTH COMPRISING AN ANTI-ROTATION SYSTEM COOPERATING WITH A CONNECTING ROD SYSTEM, AIRCRAFT COMPRISING AT LEAST ONE SUCH CONNECTING ROD
A connecting rod with a body, first and second fastening heads provided at each end of the body and connected by first and second connection systems to first and second elements, the first fastening head comprising an extension which is screwed into a housing of the body to adjust the length of the connecting rod. The connecting rod includes an anti-rotation system with a key, positioned astride the first fastening head and the body, which has a first part cooperating with the body so as to be rotationally immobilized with respect to the body and also a second part cooperating with the first fastening head and the first connection system so as to be immobilized with respect to the first fastening head.
A double-walled tank including at least one link system linking the outer and inner chambers of the tank and including a central part linked to the inner chamber and at least three blades distributed around the central part, each blade extending between a first end linked to the central part and a second end which has a head linked to the outer chamber, each blade being sufficiently flexible to be deformed elastically between its first and second ends in a direction of displacement.
F17C 1/12 - Récipients sous pression, p.ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables avec des moyens pour assurer une isolation thermique
82.
METHOD FOR MANUFACTURING AT LEAST ONE PORTION OF A BOX STRUCTURE OF AN AIRCRAFT COMPRISING A FORMING STEP, AND A CENTRAL WINGBOX THUS OBTAINED
A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.
B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices
B29C 70/30 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
83.
TANK WITH AN INTEGRAL EQUIPMENT SUPPORT TO WHICH VARIOUS EQUIPMENT UNITS ARE CONNECTED AND METHOD OF MANUFACTURING SAID TANK
A tank including an enclosure including a tubular body and first and second end walls at the ends of the tubular body, a plurality of equipment units positioned in the enclosure, at least one equipment support to which the equipment units are connected positioned in the enclosure and connected to the enclosure and a method of manufacturing this tank. The equipment units are fixed to the equipment support outside the enclosure, which simplifies putting them into place and limits the risks of damage. Moreover, they are all introduced into the enclosure at the same time, which makes it possible to reduce the time to manufacture the tank.
F17C 1/02 - Récipients sous pression, p.ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables comportant des renforcements
84.
LOCKING MECHANISM FOR AT LEAST ONE MOVABLE ELEMENT SITUATED IN A FIRST ZONE AND COMPRISING A COMPONENT THAT CAN BE ADJUSTED FROM A SECOND ZONE, AND AIRCRAFT COMPRISING AT LEAST ONE SUCH LOCKING MECHANISM
A locking mechanism situated in an inner zone and comprising at least one component that is adjustable in a longitudinal direction and that is linked to a support by a link having a rod secured to the adjustable component. The link includes a guideway link, linking the rod and the support, and an adjustment system. The adjustment system comprises a pivoting control pivoting on itself and having a first end accessible from an outer zone, an intermediate piece configured to pivot on itself, an angle transmission converting a pivoting movement of the pivoting control into a pivoting movement of the intermediate piece, and a helical link converting a pivoting movement of the intermediate piece into a translational movement of the rod. The locking mechanism allows for adjustment from the outer zone. An aircraft comprising at least one such locking mechanism is also provided.
Processes and systems for operating an aircraft having a first engine and a second engine, a non-transitory computer readable media comprising computer executable instructions that when executed cause a processor to execute the steps of the present processes. A plurality of taxiways are determined and zones for changing to or from single engine taxing operations are also determined and displayed. Additionally, countdown timers for takeoff or engine shutdown may be displayed.
A skidding phase shock absorber and protection device to protect a part on an aircraft for example at the level of a fuel tank of the aircraft includes a support and a convex plate to assume a first position and a second position and to in the first position, because of the action of compression forces, undergo resisted plastic deformation via an elastic element and in a second position to withstand friction, the device assuring, during a crash landing of the aircraft with an impact phase followed by a skidding phase, both protection against the compression forces generated during the impact phase, via the plastic deformation and the elastic shock absorption, and mechanical protection and protection against heating during the skidding phase.
An extrusion system including a press with a chassis, a slider mounted to be mobile vertically on the chassis and an actuating arrangement that moves the slider, a hollow container receiving a billet and having at one end an extrusion die and at the other end a piston mobile in translation horizontally in the container, and a movement transformation system arranged between the slider and the piston to transform the vertical movement in translation of the slider into horizontal movement in translation of the piston. With an arrangement of this kind, it is possible to use a press of higher power.
B21C 23/08 - Fabrication de fils, de barres, de tubes
B21C 23/00 - Extrusion des métaux; Extrusion par percussion
88.
CONNECTING DEVICE COMPRISING TWO OFF-CENTER RINGS WITH A FRUSTOCONICAL AND/OR SPHERICAL BEARING SURFACE, AIRCRAFT OR AIRCRAFT FLOOR COMPRISING AT LEAST TWO PORTIONS CONNECTED BY AT LEAST ONE SUCH CONNECTING DEVICE
A connecting device including first and second off-center rings, the second ring being positioned in the first ring. The peripheral outer surface of the first ring is frustoconical and has a smaller cross section oriented in a first direction, and the inner surface of the first ring and the outer surface of the second ring, which surfaces interact with one another, have cross sections which increase between a first cross section and a second cross section that is offset in relation to the first cross section in an opposite direction to the first direction. This arrangement makes it possible to be able to prevent the rotation of the first and second rings once their angular positioning has been adjusted.
A device for connection of double-wall pipes including an interior connection system connecting the first and second interior pipes and an exterior connection system including a first part that cooperates with an end section of the first exterior pipe and a second part that cooperates with an end section of the second exterior pipe. The exterior connection system is configured so that at a first temperature at least one of the first and second parts exerts a contact force on the end section of the corresponding first or second exterior pipe greater than at a second temperature higher than the first temperature in order to reinforce the seal, especially in the event of a hydrogen leak when hydrogen is present in the first and second interior pipes.
F16L 39/00 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux
F16L 59/147 - Dispositions pour l'isolation des tuyaux ou des tuyauteries l'isolation étant placée à l'intérieur par rapport à la surface extérieure du tuyau
F16L 59/18 - Dispositions spécialement adaptées aux nécessités localisées telles qu'à l'endroit des brides, des jonctions, des soupapes ou d'autres éléments similaires adaptées aux raccords
A method for producing a component with a surface that is suitable for plastic welding or adhesive bonding of two parts is provided. As a preparation step prior to joining, a filler sheet comprising a thermoplastic material or adhesive is arranged on a first surface of a first component and a structuring tool is arranged on the filler sheet. Mechanical force is applied to the structuring tool and heat is applied to the filler sheet such that the filler sheet is attached to the first surface of the first component and such that the structuring tool is partially embedded in the filler sheet. The structuring tool is subsequently removed from the filler sheet to produce a plurality of protrusions in the outer surface of the filler sheet. After surface structuring the first and second components are joined using any type of welding technique or joined using of adhesive bonding.
An assembly of at least one extinguishing agent tank in the interior of an aircraft strut. The strut has an elongate chamber form extending in a longitudinal direction and includes a plurality of ribs which are spaced apart and arranged in parallel along the strut, each extending orthogonally to the longitudinal direction. The ribs are covered by lateral walls, at least one of the walls comprising a window opening into a space between two consecutive ribs, and via which a spherical extinguishing agent tank is installed in the interior of the strut. The assembly of the tank on the strut includes a frame arranged in the interior of the strut, facing the window and secured on each of the two consecutive ribs. The frame forms a support area on which the tank is supported. A system locks the extinguishing agent tank on the frame.
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
A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
An aircraft landing gear 100 includes a structural main leg 110, having a substantially circular cross-section and defining a front side for facing upstream in use and a rear side for facing downstream in use. The landing gear includes a shaped element 151 attached to an attachment point located on the rear side of the structural main leg. The shaped element extends rearwards from the structural main leg to provide a combined cross-sectional shape of the structural main leg and shaped element that is elongated in the upstream-downstream direction compared to the structural main leg.
An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.
A system for conditioning fuel for an air-breathing hydrogen engine (M), comprising: • - at least one hydrogen pump (16) configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, • - one or more heat exchangers (24, 26, 28) configured to increase the temperature of the pressurized hydrogen, • - an air supply circuit (10G), • - at least one combustion device (32) configured to provide partial combustion of the hydrogen with the air coming from the air supply circuit in order to produce a fuel comprising a mixture of gas including gaseous hydrogen and not including oxygen.
F02K 9/42 - Moteurs-fusées, c. à d. ensembles fonctionnels portant à la fois le combustible et son oxydant; Leur commande utilisant des propergols liquides ou gazeux
F02K 9/78 - Moteurs-fusées, c. à d. ensembles fonctionnels portant à la fois le combustible et son oxydant; Leur commande combinés avec un autre ensemble fonctionnel à propulsion par réaction avec un ensemble fonctionnel de propulsion par réaction alimenté par de l'air ambiant
95.
AIRCRAFT PART HAVING A FLOOR JOINED TO A FUSELAGE PORTION VIA ELASTIC LINK RODS
An aircraft part has a fuselage portion and a floor, at least a part of which is joined to the fuselage portion via elastic link rods. Each elastic link rod is provided with a first end that is configured to be fixed to the floor and with a second end that is configured to be fixed to the fuselage portion. The elastic link rods are configured to exhibit a stiffness that makes it possible both to transmit loads between the floor and the fuselage portion and to absorb displacements brought about by deformations of the fuselage portion. The aircraft part thus making it possible, at a lower cost and with a lower mass, to obtain a connection between the floor and the fuselage portion that exhibits suitable elasticity to be able to transmit inertial loads while absorbing deformations of the fuselage portion.
An aircraft including at least one system rack positioned under a floor and including a series of vertical first uprights, distributed in a direction parallel to the longitudinal axis of the aircraft. The aircraft includes at least a first upper connecting system connecting at least one of the first uprights and a rail of the floor oriented parallel to the longitudinal axis. In so far as the first uprights of the system rack are not connected to the crossbeams of the floor, they can be positioned irrespective of the position of the crossbeams, and this contributes to simplifying the design of the system racks and allows these to be standardized.
An assembly method includes a succession of assembly steps of assembling fuselage components of the fuselage portion of the aircraft, for example the nose of the aircraft, to form a fuselage body, a mounting step of introducing, into the fuselage body thus formed, a floor module having at least a predetermined width, and which can be provided with items of equipment, and a fastening step of fastening the fuselage body to the floor module such that the floor module shapes the final shape of the fuselage body and the assembled fuselage portion is obtained, the floor module, which has at least a suitable predetermined width, making it possible, when it is incorporated into the fuselage body, to provide the fuselage body, which is slightly flexible, with its desired and definitive shape corresponding to the desired and definitive shape of the assembled fuselage portion.
A flexible corner fitting configured to contribute to a connection between at least three walls of at least one aircraft box structure, and to make them leaktight with respect to liquids. The corner fitting has at least three fixing plates and at least three edge corners made of flexible material. Each of the at least three fixing plates is connected to each of the other at least three fixing plates by one of the edge corners made of flexible material. The edge corners made of flexible material ensure adjustment of the corner fitting without machining or the addition of shims.
DEVICE FOR MANUFACTURING A STIFFENED PANEL MAKING IT POSSIBLE TO CONTROL THE GEOMETRY OF SAID STIFFENED PANEL, AND METHOD FOR MANUFACTURING A STIFFENED PANEL USING SAID DEVICE
A device for manufacturing a stiffened panel with reinforcements which each have a final thickness and a final height. The manufacturing device includes tools configured to each support a preform of fibers having a U-shaped or C-shaped cross section with a base and two wings. Each tool comprises, at at least one of its first and second lateral faces, a set-back portion which, when two tools are juxtaposed, delimits a recess configured to form a reinforcement during a consolidation or polymerization step. The tools are dimensioned such that each recess has a width, at the consolidation or polymerization temperature, that is substantially equal to the thickness of the reinforcements. This solution makes it possible to more effectively control the geometry of the stiffened panel by avoiding the formation of beads. A method for manufacturing a stiffened panel using the device is also disclosed.
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.à d. d'objets distincts utilisant des moules opposables, p.ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29C 70/30 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29C 51/26 - Façonnage par thermoformage, p.ex. façonnage de feuilles dans des moules en deux parties ou par emboutissage profond; Appareils à cet effet - Eléments constitutifs, détails ou accessoires; Opérations auxiliaires
B29C 70/54 - 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 opération de façonnage des matières composites comprenant uniquement des renforcements - Parties constitutives, détails ou accessoires; Opérations 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
100.
METHOD OF MANUFACTURING AN ACOUSTIC TREATMENT PANEL AND ACOUSTIC TREATMENT PANEL OBTAINED BY SAID METHOD
A method of manufacturing an acoustic treatment panel including at least one cellular structure with at least one anchor layer at the level of at least one of its faces. The anchor layer includes at least one adhesive sheet chosen from an adhesive film or a ply of pre-impregnated adhesive fibers in contact with the cellular structure. The method of manufacture includes, before the integration of the cellular structure in an acoustic treatment panel, a step of placing the anchor layer on a support, the adhesive sheet being the last to be placed, a step of placing the cellular structure on the anchor layer in contact against the adhesive sheet, and then a step of polymerization of the anchor layer and of the cellular structure.
B29D 24/00 - Fabrication d'objets avec parois creuses
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B29C 70/08 - 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 comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 70/88 - 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 caractérisées principalement par des propriétés spécifiques, p.ex. électriquement conductrices ou renforcées localement
