A locking washer includes an annular main component with a ring equipped, on its inner periphery, with flexible tabs which are curved such that their free ends deviate, on the same side, from a plane formed by the ring and substantially define arcs of the same circle, which is referred to as the locking circle, to produce efficient locking and to obtain a robust locking washer, the locking washer also including an annular auxiliary component to interact with the main component to quickly unlock the locking washer.
F16B 39/24 - Blocage des vis, boulons ou écrous dans lequel le verrouillage se fait en même temps que le vissage ou le serrage par rondelles, rondelles à ressort ou plaques élastiques qui bloquent contre l'objet
2.
SYSTEM FOR FIXING AN ELEMENT AND AIRCRAFT COMPRISING AT LEAST ONE SUCH SYSTEM
A support for a system for fixing an element comprising a hose clamp having a flexible link and a cage, the support comprising: a base comprising a recess in which the cage is housed and a first channel into which the link is fitted; an inclined upright extending from the base by moving away from the recess such that a free end of the upright is disposed at a distance from and facing an aperture which emerges in the recess. The link is able to penetrate into the first channel, surround the element, then penetrate in succession into the aperture of the recess and into the cage.
F16L 3/233 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace pour un faisceau de tuyaux ou un ensemble de tuyaux disposés les uns à coté des autres en contact mutuel au moyen d'une bande flexible
B65D 63/10 - MANUTENTION; EMBALLAGE; EMMAGASINAGE; MANIPULATION DES MATÉRIAUX DE FORME PLATE OU FILIFORME ÉLÉMENTS D'EMBALLAGE; PAQUETS Éléments d'emballage flexibles allongés, p.ex. courroies pour lier ou pour soutenir des objets Éléments filamenteux, p.ex. cordons, fils ou fils métalliques; Jonctions de leurs extrémités
3.
ASSEMBLY OF AN ATTACHMENT PYLON WITH AN AIRCRAFT ENGINE
An assembly of an attachment pylon with an aircraft engine comprising a front engine mount comprising a front tang and a front clevis, a lower tang and a lower clevis connecting the attachment pylon and the engine via a front pin mounted in the front tang and clevis and a lower pin mounted in the lower tang and clevis, and port/starboard links mounted between the attachment pylon and the engine via mounting pins, wherein the front and lower pins are orthogonal to a mid-plane, and wherein the mounting pins of the links are parallel to the mid-plane.
A method for detecting and localizing a failure of an input sensor of a flight control computer of an aircraft including comparing a first piece of information representative of a probability of occurrence of the failure, delivered by a neural network, with a second piece of information representative of a probability of occurrence of the failure, delivered by a classifier trained to carry out a detection and a localization of the failure. It is thus possible to optimize a failure diagnosis and a localization of a failure of an input sensor used in the determination of flight controls.
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
5.
PROPULSION UNIT COMPRISING A SUSPENSION SYSTEM OF THE REAR PART OF THE ENGINE, AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION UNIT
A propulsion unit comprising an engine, a pylon, an engine mount system which connects a front part of the engine and the pylon, in addition to a suspension system which connects the pylon and a rear part of the engine which is offset toward the rear end of the engine relative to the engine mount system.
An aircraft propulsion system comprising a turbojet having a fan casing with a rear face, a pylon with a front part and a lower spar with a rear fitting fixed to it, and a front engine attachment fixed between an upper part of the fan casing and the front part, a front arch having two arms, each having a first end fixed to the lower spar and a second end fastened in an articulated manner to the rear face, and two lateral rods, each having a first end fastened in an articulated manner to the rear fitting and a second end fastened in an articulated manner to the rear face.
A device for sealing a joint between a wall of a wing box and a wall of a central fuselage of an aircraft, the device comprising at least one deformable element clamped between a first and a second rigid end element. The device moreover comprises clamp for moving the first and second rigid end elements closer to one another so as to deform the at least one deformable element by crushing until it is pressed against the walls of the joint.
A support device includes a profiled element having at least one passage hole passing transversely through the profiled element, a fastening support, integral with the profiled element, to fasten the support device to a primary structure, at least one clamping element having a clamp to receive at least one cable and at least one fastening element to fasten the clamping element or elements to the profiled element. The device facilitates the fastening of cables to a primary structure.
F16L 3/127 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers entourant pratiquement le tuyau, le câble ou le conduit de protection comportant un élément entourant pratiquement le tuyau, le câble ou le conduit de protection et faisant un angle avec la surface de fixation
F16L 3/123 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers entourant pratiquement le tuyau, le câble ou le conduit de protection comportant un élément entourant pratiquement le tuyau, le câble ou le conduit de protection et s'étendant le long de la surface de fixation
9.
SYSTEM FOR COMMANDING AND BRAKING AN ARTICULATED MOBILE ELEMENT OF AN AIRCRAFT
A command system of an aircraft mobile element actuated by a motor is provided. The command system is electrically connected to a power supply, to the motor and to a current consuming device used to effect de-icing. The system establishes a connection between the motor and the current consuming device and inhibits a first connection between the power supply and the motor and a second connection between the power supply and the current consuming device when a braking command is received. The system enables the first connection and the second connection to be established and inhibits the third connection as long as no braking command has been received or when a command to stop braking is received. Thus the mobile element can be easily braked and the overall size of the system is limited.
H02P 3/06 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques pour arrêter ou ralentir individuellement un moteur dynamo-électrique ou un convertisseur dynamo-électrique
B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
A wing defines a chord which runs from a leading edge to a trailing edge. The wing has a main portion and a flap which is movable relative to the main portion to change the aerodynamics of the wing, for instance to maximize lift, or to reduce drag at the expense of some loss of lift. The wing has a guide mechanism which guides movement of the flap. The guide mechanism uses a pair of runners which run along respective tracks. The tracks are positioned at different locations along the direction of the chord, but overlap one another in the direction of the chord.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.
A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with first and second sleeves, a pair of flanges and a fasteners to the engine pylon. The fasteners comprise two adjacent fastening screws extending parallel to each other.
A tank comprising a shell having an edge face connecting first and second inner lateral surfaces of first and second portions, at least one end wall, positioned at the first portion of the shell, which has a central part in the shape of a dome, a peripheral sleeve positioned around the central part and a junction zone connecting the central part and the peripheral sleeve and having an edge face, a weld connecting the first portion and the peripheral sleeve, the edge faces of the end wall and of the shell having shapes configured to immobilize the junction zone with respect to the shell in a radial direction. Also a cryogenic reservoir with such a tank.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar, and a complementary front engine attachment fixed between an upper area of the central casing and a lower end of the front wall.
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine, an attachment pylon having a rigid structure, and an extinguishing system. The extinguishing system is located in a front position relative to the rigid structure, the extinguishing system being positioned between the rigid structure and the jet engine.
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
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 35/68 - Réseaux de conduites - Détails, p.ex. de conduites ou de systèmes de soupapes
17.
AIRCRAFT PROPULSION ASSEMBLY HAVING A JET ENGINE, A PYLON AND MEANS FOR ATTACHING THE JET ENGINE TO THE PYLON
A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.
A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising first and second parts of the baseplate placed against each other so as to form a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with a sleeve, a pair of flanges and fasteners to the engine pylon.
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
19.
AIRCRAFT NACELLE EQUIPPED WITH AT LEAST ONE THRUST REVERSAL DEVICE COMPRISING AT LEAST ONE LONGITUDINAL DEFLECTOR CONFIGURED TO HOUSE A LONGITUDINAL ACTUATOR
An aircraft nacelle equipped with a thrust reversal device, which comprises: at least one longitudinal actuator for activating or deactivating the thrust reversal device, at least one deflection system configured to deflect an air stream channeled in the nacelle towards a lateral opening in the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system towards the upstream end of the nacelle, for each longitudinal actuator, a hollow longitudinal deflector, which is configured to house the longitudinal actuator and has an aerodynamic profile that has a leading edge oriented towards the deflection system.
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
A cooling system for aircraft comprises a first loop intended to cool fuel cells and on which there is a ram air heat exchanger, and a second loop intended to cool power electronic equipment items and to supply heat to an evaporator to gasify dihydrogen in order to supply the fuel cells. The first loop and the second loop are interconnected by a flow line starting at the output of the ram air heat exchanger and by a return line. A controller regulates the coolant temperature in the first loop, and in the second loop by controlling the opening of the flow line. Also an aircraft with such a cooling system.
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 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
H01M 8/04007 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration
A method for assisting landing of an aircraft on a landing runway of a destination airport facility includes two successive determinations of the position of the aircraft with respect to the landing runway and based on a photographic image taken from the aircraft, respectively according to two different algorithms for determining the position of the aircraft, together with the supply of at least one piece of information representative of a difference between the two determined positions. It is thus possible to verify whether the destination landing runway observed from the photographic image taken from the aircraft is indeed the target destination runway on which a landing of the aircraft is planned, or whether there exists an error in positioning of the aircraft with respect to the destination landing runway.
B64D 45/08 - Aides à l'atterrissage; Dispositifs de sécurité pour éviter la prise de sol brutale optiques
22.
AIRCRAFT PROPULSION ASSEMBLY COMPRISING AT LEAST ONE AERODYNAMIC PANEL WHICH IS SUPPORTED BY AT LEAST ONE INTERMEDIATE RADIAL SUPPORT, AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION ASSEMBLY
A propulsion assembly comprising a fan casing and a nacelle which comprises an air inlet which is connected to the front end of the fan casing, an intermediate portion which is positioned around the fan casing and a rear portion which cooperates with the rear end of the fan casing. The intermediate portion comprises at least one aerodynamic panel which extends from a front edge which is attached to the air inlet as far as a rear edge which is attached to the rear portion and at least one intermediate radial support comprising an internal edge which is connected to the fan casing and an external edge which is connected to the aerodynamic panel, this panel comprising a front edge which is connected to the air inlet by a first connection system. Also an aircraft with such a propulsion assembly.
An enhanced interface for checking an aircraft electrical power supply line, the interface being configured to easily and rapidly check an absence of electrical potential at at least one determined point of an aircraft electrical installation comprising an equipment item of high-voltage type. Also to an aircraft comprising such an enhanced interface and a method for checking and neutralizing an electrical power supply line of an aircraft.
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
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01R 1/04 - Boîtiers; Organes de support; Agencements des bornes
24.
METHOD FOR ASSISTING WITH LANDING AN AIRCRAFT AND SYSTEM CONFIGURED TO EXECUTE THE METHOD
A method for assisting with landing an aircraft is disclosed and configured to determine a number of probable theoretical positions (POS1, POS2, POS3) of the aircraft equal to the facing plurality of runways of a destination airport facility to reproject the runways into an image (F) obtained by a camera of the aircraft by means of a theoretical camera model (e.g. pinhole camera model), each reprojection being with reference to one of the determined theoretical positions (POS1, POS2, POS3); and to establish, for each of the reprojections, a consistency score making it possible to then deliver an estimated position (POSA) of the aircraft.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
G06F 18/2413 - Techniques de classification relatives au modèle de classification, p.ex. approches paramétriques ou non paramétriques basées sur les distances des motifs d'entraînement ou de référence
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06V 20/17 - Scènes terrestres transmises par des avions ou des drones
25.
Tank, In Particular For A Liquid Hydrogen Reservoir, Provided With At Least One Dome Fixed By Way Of An Outer Welded Joint
A tank, in particular for a liquid hydrogen reservoir, provided with at least one dome fixed by way of an outer welded joint and having a central portion provided with at least one free end including a first connecting element and at least one dome provided with an open end including a second connecting element, the dome and the central portion being able to be joined together, the first connecting element and the second connecting element being configured to form, when the central portion and the dome are joined together, a protruding tab extending toward the outside of the tank and able to be welded to a protruding end, such a protruding tab making it possible in particular to join together the tank, this being done entirely from the outside of said tank, and to easily mount and dismount the dome, in particular without accessibility issues.
F17C 1/14 - Récipients sous pression, p.ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en acier amagnétique
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage la chaleur étant produite par friction; Soudage par friction
A simulation of efforts applied to positioners to support the fuselage and the airfoil of an aircraft during operations of assembly is performed. The efforts are defined in a digital model of a load plan of the aircraft in assembly phase. The simulation is performed using the load plan digital model of the aircraft in assembly phase and a digital model of each positioner in the form of a set of three equivalent springs defined by three respective eigenvectors associated with three respective eigenvalues, in which the eigenvalues provide rigidity values and the eigenvectors provide directions on which the respective eigenvalues are applied. Thus, the simulation times are reduced.
G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
27.
METHOD FOR ASSEMBLING AN AIRCRAFT CENTRAL WING BOX INVOLVING A STEP OF FASTENING THE EQUIPMENT TO AT LEAST ONE ASSEMBLY SUPPORT SITUATED OUTSIDE THE CENTRAL WING BOX
A method for assembling a central wing box for an aircraft by assembling the upper and lower panels and the front and rear spars in order to obtain a main structure, fastening equipment to at least one assembly support positioned outside the main structure, inserting at least one mounting support inside the main structure, and securing the assembly support to the main structure. Also a central wing box and an aircraft having such a central wing box.
A method for estimating the need to replace a cutting tool includes the following steps: collecting data representative of efforts undergone by the cutting tool during cutting tool usage operations, each datum associating a cutting tool usage operation number and at least one measurement of effort during the cutting tool usage operation; comparing the collected data, or data which are derived therefrom, with a reference curve representative of a nominal wear of the cutting tool during the cutting tool usage operations; checking whether or not the collected data, or the data which are derived therefrom, cause an overshoot of a predefined tolerance with respect to the reference curve; and in the event of such an overshoot, deducing an appropriate moment to perform a replacement of the cutting tool, as a function of the overshoot. The cutting tool may then be replaced at or near the deduced appropriate moment.
B23Q 17/09 - Agencements sur les machines-outils pour indiquer ou mesurer pour indiquer ou mesurer la pression de coupe ou l'état de l'outil de coupe, p.ex. aptitude à la coupe, charge sur l'outil
29.
VENTILATION DEVICE COMPRISING AT LEAST ONE AUTOMATICALLY CLOSING FLAP, AIRCRAFT COMPRISING AT LEAST ONE SUCH VENTILATION DEVICE
A ventilation device comprising a ventilation grille comprising a frame delimiting at least one opening, at least one flap designed to be in an open state in which the flap at least partially opens the opening and a closed state in which the flap blocks the opening, at least one articulation connecting the flap and the frame, a closed position holding system that is elastically deformable and designed to push and hold the flap in the closed state, an open position holding system that is fusible and designed to hold the flap in the open state against the closed position holding system, enabling the flap to be closed automatically. Also an aircraft having at least one such ventilation device.
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
A solvent composition for solvent-based paints or other similar coatings which comprises a combination of dimethyl glutarate and of at least one other compound chosen from a group which includes isobutyl acetate, ethyl lactate, dimethyl 2-methylglutarate, 2-methyltetrahydrofuran, ethyl acetate, cyclopentyl methyl ether, diethoxymethane, dimethyl carbonate, dimethyl succinate, benzyl alcohol, dimethyl adipate or glycerol triacetate. Also a method of cleaning with such a solvent composition.
A display on a screen of human-machine interface of a cockpit of an aircraft includes a text entry region, a navigation chart region, and at least one other region. A specific pointing mode, active when text entry is in progress, and a normal pointing mode, active at all other times, are implemented. In normal pointing mode, a pointing action triggers the command if any associated with the location where the pointing action is carried out. In specific pointing mode, only a pointing action in the text entry region or in the navigation chart region triggers a command if any associated with the location where the pointing action is carried out, while a pointing action in the at least one other region triggers an abandonment of text entry. Thus, tasks requiring a pilot of the aircraft to enter text are simplified.
An assembly comprising a wing with a lower surface panel and an upper surface panel and an engine pylon comprising a primary structure fixed to the wing with a fixing base. The fixing base comprises fourth fixing yokes while the primary structure bears fourth fittings, the fourth fixing yokes being secured to the fourth fittings with fourth rods.
An aircraft fairing having at least one structure, at least one fairing panel, at least one fastening element connecting the fairing panel and the structure, and at least one compressible seal interposed between first and second bearing zones that are as one, respectively, with the fairing panel and with the structure. The fairing panel comprises at least one rigid stop positioned in the first bearing zone, the stop and the compressible seal being configured such that the compression ratio of the compressible seal is less than or equal to 90%.
An aircraft with at least one engine system, at least one zone for ejection of debris originating from the engine system and at least one fluid supply circuit. The latter comprises a shutter configured to occupy open and closed states, at least one return element configured to push the shutter to the closed state and at least one control positioned at least partially in the ejection zone and configured to hold the shutter in the open state against the return element. When the control is broken in the case of an accident, it no longer holds the shutter, which switches automatically to the closed state.
A system for recovering gaseous dihydrogen produced in a distribution duct arranged between a main tank and a dihydrogen consumer device, the distribution duct comprising a pump. The system comprises: an auxiliary tank; a bypass duct, arranged between the distribution duct and the auxiliary tank, downstream of the pump; a valve arranged on the bypass duct; a module for obtaining a temperature of the dihydrogen in the distribution duct, upstream of the pump. A control module of the valve opens the valve when the temperature is greater than a predetermined value and closes the valve when the temperature is less than or equal to the predetermined value.
F02C 7/22 - Systèmes d'alimentation en combustible
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
B64D 37/30 - Circuits de carburant pour carburants particuliers
F02C 9/26 - Commande de l'alimentation en combustible
36.
AIRCRAFT NACELLE EQUIPPED WITH AT LEAST ONE THRUST REVERSAL DEVICE COMPRISING AT LEAST ONE LONGITUDINAL DEFLECTOR, AIRCRAFT COMPRISING AT LEAST ONE PROPULSION UNIT HAVING SUCH A NACELLE
An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system in radial directions and toward the upstream end of the nacelle, at least one longitudinal deflector configured to orient the air stream deflected by the deflection system in at least one direction that forms an angle with a radial direction.
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
37.
AIRCRAFT NACELLE EQUIPPED WITH AT LEAST ONE THRUST REVERSAL DEVICE COMPRISING A DOWNSTREAM DEFLECTOR, AIRCRAFT COMPRISING AT LEAST ONE PROPULSION UNIT HAVING SUCH A NACELLE
An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.
B64D 29/06 - Fixation des nacelles, carénages ou capotages
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
38.
TANK COMPRISING INNER AND OUTER ENCLOSURES AND AT LEAST ONE TUBULAR INTERFACE IN TWO PARTS PASSING THROUGH THE INNER AND OUTER ENCLOSURES
CETIM (Centre Technique des Industries Mécaniques) (France)
Inventeur(s)
Toureille, Nicolas
Mesic, Chloé
Moretti, Laure
Espinassou, Denis
Abrégé
A tank comprising an outer enclosure, an inner enclosure positioned in the outer enclosure and at least one tubular interface passing through the outer and inner enclosures and linked to the outer enclosure by a first link and to the inner enclosure by a second link, the tubular interface comprising at least two sections placed end-to-end and at least one joining system linking the sections pairwise, a first section being linked to the outer enclosure by the first link, a second section being linked to the inner enclosure by the second link.
An aircraft comprising a dihydrogen transport pipe, a pipe shroud around the transport pipe, a dihydrogen tank, a chamber delimiting a fluidtight volume containing a system fluidically connected to the transport pipe which joins the pipe shroud through a chimney, an extraction chamber into which the chimney and the pipe shroud open, and a device for extracting to the outside the gases present in the extraction chamber.
An aircraft comprising at least one secondary structure which separates an inner zone from an outer zone and at least one hydrogen supplying device connecting a hydrogen tank and a motor, and having at least one portion fitted with shut-off valves for isolating it in the event of a leak. The portion has at least one outer enclosure, at least one inner element that is located in the outer enclosure and carries the hydrogen, and at least one interior zone located between the inner element and the outer enclosure, the hydrogen supplying device comprising at least one ventilation system configured to vent gases present in the interior zone toward the outer zone of the secondary structure.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
F17C 7/00 - Procédés ou appareils pour vider les gaz liquéfiés, solidifiés ou comprimés contenus dans des récipients sous pression, non couverts par une autre sous-classe
41.
TANK COMPRISING INNER AND OUTER ENCLOSURES AND AT LEAST ONE DUCT PASSING THROUGH AT LEAST ONE DEFORMABLE CLOSURE PLATE
A tank comprising an outer enclosure, an inner enclosure positioned in the outer enclosure, and at least one duct passing through first and second walls connected respectively to the outer and inner enclosures. The first and/or second walls comprises at least one deformable zone interposed between, on the one hand, an attachment zone which connects the wall and the outer or inner enclosure and, on the other hand, a connection zone which comprises a connection connecting the wall and the duct. Also an aircraft with such a tank.
TANK COMPRISING INNER AND OUTER ENCLOSURES AND AT LEAST ONE DUCT PASSING THROUGH SAID ENCLOSURES AND FOLLOWING A CURVED TRAJECTORY BETWEEN SAID ENCLOSURES
A tank comprising an outer enclosure, an inner enclosure positioned in the outer enclosure, and at least one duct passing through first and second walls respectively fastened to the outer and inner enclosures, the tank comprising, for each duct, first and second rigid connections connecting the duct and respectively the first and second walls. Each duct comprises an intermediate segment, situated between the first and second walls, which has a curved axis such that the intermediate segment has an excess length between the first and second walls.
An adjustable connecting rod is disclosed including an adjustment device for adjusting the length of the adjustable connecting rod and a connecting rod body, the adjustment device includes at least one yoke for fixing the adjustable connecting rod to an element and an intermediate part linking the yoke to the connecting rod body between a pivot link and a helical link. The combination of the pivot link and of the helical link implemented by the intermediate part allows the length of the adjustable connecting rod to be adjusted continuously.
An assembly including a support plate through which passes an opening with two faces parallel to a bearing plane, a first fixing fixed against the first face, first sleeves receiving beams, and a stud with a hole having an axis, a second fixing against the second face, second sleeves receiving beams, a housing for the stud and a clamping screw screwed into the hole, with the axis at an angle (α) to the bearing plane between 10° and 80° inclusive. The assembly forms a chassis which may be fixed to a propulsion assembly and a wing of an aircraft.
An internal fixed structure for a nacelle, comprising end panels, an intermediate panel in the form of a half-cylinder between the end panels, splice plates between the intermediate panel and each end panel, wherein each splice plate is made up of a skin with an inner face fastened to the panels and at least one indentation protruding with respect to an outer face, and a pad fastened to each fastening surface of an indentation, wherein each pad of the upper splice plate bears against a surface of an engine pylon, and wherein each pad of the lower splice plate bears against a pad of a lower splice plate of another internal fixed structure.
An assembly having a pylon with two side walls provided with apertures, a reservoir for extinguishing agent, a support which has two support elements, wherein each support element has an upwardly facing first bearing face to which the reservoir is fastened, a distal end, and a proximal end fastened by a first removable fastener, wherein the distal end is rotatable about a horizontal axis, and wherein each support element is movable between a use position, in which the first bearing face is horizontal, and a fitted position, in which the first bearing face is tilted downwards.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
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
47.
SYSTEM FOR MEASURING AT LEAST ONE THERMAL MAGNITUDE DESIGNED TO LIMIT THE IMPACT OF CONVECTIVE HEAT TRANSFERS, AIRCRAFT PROPULSION ASSEMBLY INCLUDING AT LEAST ONE SUCH SYSTEM
A measurement system for measuring at least one thermal magnitude at a point of a propulsion assembly of an aircraft. The measurement system is connected to a structure integral with the propulsion assembly and comprises at least one thermal sensor as well as at least one barrier transparent to infrared radiation in at least one zone of the barrier. The barrier at least partially delimits a cavity in which the thermal sensor is positioned. Also an aircraft propulsion system with at least one such measurement system.
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p.ex. à la pression
48.
AIRCRAFT PART THAT COMPRISES AN ACCESS DOOR AND A FUSELAGE PART FORMING A CAVITY AND IS CONFIGURED TO REDUCE NOISE GENERATED BY THE CAVITY
An aircraft part with a door for accessing inside an aircraft and a fuselage part includes a cavity between an upstream edge of the door in the closed position and a downstream edge of the fuselage part, the cavity opening to the outside of the aircraft part and having a bottom connected to the upstream edge of the door and to the downstream edge of the fuselage part. The aircraft part includes a chamfer on the outer face of an outer plate of the door at the upstream edge of the door, as well as possibly other technical features such as a sharp ridge and/or an add-on component, allowing for reducing noise generated by the cavity.
An aircraft having a wing, a dihydrogen-powered engine, a supply pipe for the dihydrogen, in which each wing has a front spar, a first rear spar extending behind the front spar and a second rear spar extending behind the first rear spar, in which the two rear spars together define a corridor, and in which each supply pipe extends backwards from the related engine then into the corridor of the wing carrying the related engine.
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
An engine pylon has a structure for fastening an aircraft engine beneath a wing and has two lateral faces. The structure has a tunnel laterally passing through it, between and through the lateral faces, and the engine pylon has a spreader housed in the tunnel and fastened in an articulated manner to each lateral face. A first end of the spreader has a first bore. A second end of the spreader has two second bores each forming a connection point with the engine. A rod is fastened in an articulated manner to the first bore and has two third bores each forming a connection point with the engine. Such an engine pylon has the ability to attach the engine, with reduced vertical bulk and with less drag.
A propulsive assembly comprising a nacelle delimiting an internal volume, a T-shaped frame comprising a first wall fixed to the wing and a second wall that is vertical and that divides the internal volume into two sub-volumes, a dihydrogen consumer device, for each sub-volume, a dihydrogen processing system, a supply line connected between the processing system and the consumer device, and an input line connected between the processing system and a dihydrogen tank. Also an aircraft with a wing and such a propulsive assembly.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes
F02K 1/36 - 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 comportant un éjecteur
52.
DEVICE AND SYSTEM FOR ESTIMATING THE POSITION AND SPEED OF AN AIRCRAFT DURING AN APPROACH PHASE ALLOWING AUTOMATIC LANDING
An estimation device for estimating, during an aircraft approach procedure for landing on a runway following a predefined runway approach, a deviation relative to a reference guidance axis corresponding to the predefined runway approach, and a speed of an aircraft relative to the runway, the approach procedure being carried out with a landing aid device including at least one transmitter station configured to transmit the reference guidance signal defining the reference guidance axis. The estimation device includes an acquisition unit for a current aircraft position of a geo-positioning system, an acquisition unit for a current acceleration of an inertial unit, an acquisition unit for a current lateral and vertical deviation of a landing aid device, a filtering unit for estimating an unbiased aircraft speed, a filtering unit for estimating a current lateral deviation, a current vertical deviation as well as current lateral and vertical speeds of the aircraft.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
G01S 5/02 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de position; Localisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques
An aircraft propulsion assembly with at least one ventilation device to cool at least one zone of the propulsion assembly. The ventilation device is regulated and includes at least one ventilation hole emerging in the zone to be cooled, at least one valve movable between a closed position where the valve shuts the ventilation hole and an open position where the valve at least partially frees the ventilation hole, at least one thermoelectric generator to generate an electric current and at least one automatic control to control the position of the valve by using the electrical current generated by the thermoelectric generator. The bleed air flow rate can be adjusted as a function of the cooling needs. An aircraft including at least one such propulsion assembly is disclosed.
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
H10N 10/80 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c. à d. dispositifs présentant l'effet Seebeck ou l'effet Peltier - Détails de structure
54.
METHOD AND SYSTEM FOR GENERATING AND PROVIDING DESCRIPTORS OF METEOROLOGICAL OBSTACLES
A weather data system in an aircraft which: processes georeferenced meteorological-obstacle data in order to categorize a weather severity of the meteorological obstacles and to obtain two-dimensional meteorological-obstacle images that are separated by weather-severity level; polygonizes through outline simplification the meteorological obstacles of the two-dimensional images, for each weather-severity level, in order to obtain polygons representative of the meteorological obstacles; and provides descriptors of meteorological obstacles to a flight management system of the aircraft, the descriptors describing georeferenced polygons; receives at least one requirement parameter representative of a requirement of the flight management system; and configures the polygonization and/or the data processing depending on the requirement.
The invention relates to a propulsion assembly having a jet engine with an intermediate casing with a rear face and a core casing to the rear of the intermediate casing, and an attachment pylon with a frontal wall and two lateral walls, a front engine attachment having a front fitting fastened in an articulated manner via two lateral fastening points to the rear face and in a rigid manner via an upper fastening zone to the frontal wall, and an intermediate engine attachment comprising a front link rod and a rear link rod on each side. Each of the link rods is mounted in an articulated manner between the front fitting and the lateral wall. With such an arrangement, the bulk of the engine attachments is reduced in the bypass flow.
A computational unit of a configurable integrated circuit includes an input receiving data, an output and a core which is configured to execute an operation on the basis of at least one datum in order to obtain a result, and transmit the result to the output. The unit further includes a memory of first in, first out type associated with each input and configured to store each datum received by the input. The unit triggers the storage of a datum when a validity signal of a predefined value is detected, transmits, to the core, a stored datum and triggers an execution of the operation when a datum is stored in each memory and when no execution of the operation is in progress. The unit transmits, to the output, a validity signal of the predefined value at the same time as each transmitted result, and a different one otherwise.
H03K 19/17764 - Circuits logiques, c. à d. ayant au moins deux entrées agissant sur une sortie; Circuits d'inversion utilisant des éléments spécifiés utilisant des circuits logiques élémentaires comme composants disposés sous forme matricielle - Détails structurels des ressources de configuration pour la fiabilité
H03K 19/17756 - Circuits logiques, c. à d. ayant au moins deux entrées agissant sur une sortie; Circuits d'inversion utilisant des éléments spécifiés utilisant des circuits logiques élémentaires comme composants disposés sous forme matricielle - Détails structurels des ressources de configuration pour la configuration partielle ou la reconfiguration partielle
57.
CENTRAL FASTENING SYSTEM FOR AN AIRCRAFT, FASTENING A STRUCTURE OF A WING TO A STRUCTURE OF A PYLON
A central fastening system having a first central fitting as one with a structure of a wing, a second central fitting as one with a structure of a pylon, a first connection system and a second connection system, wherein each connection system is fastened to the first central fitting and to the second central fitting by clevis type connections and wherein the two connection systems cross between the first central fitting and the second central fitting.
AIRCRAFT COMPRISING A DIHYDROGEN TRANSPORT LINE, A CHANNEL FOR EMBEDDING SAID TRANSPORT LINE AND A SYSTEM FOR EVACUATING AIR AND WATER PRESENT IN SAID EMBEDDED CHANNEL
An aircraft comprising a dihydrogen transport line, an embedded channel comprising a gutter in which the transport line is fixed and having a first end by which the transport line enters into the gutter and a second end by which the transport line leaves the gutter, and an evacuation system fluidically connected between the second end of the gutter and the outside of the aircraft for the evacuation of air and of water.
An electrical protection system for protecting an electrical circuit comprising a generator and a plurality of electrical apparatuses, each apparatus comprising a chassis. The protection system comprises a first link associated with each apparatus, connecting the chassis of the apparatus to an earth, and comprising a protection resistor. For at least one electrical apparatus operating under direct current, the associated first electrical link comprises a protection capacitor in parallel with the protection resistor. The protection system comprises a second link connecting a neutral point of the generator to the earth.
H02H 3/16 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à un courant de défaut à la terre ou à la masse
60.
ENHANCED CABLE SUPPORT ELEMENT, CABLE SUPPORT ASSEMBLY, AIRCRAFT ELECTRICAL SYSTEM AND AIRCRAFT
A cable support includes an open annular body and two jaws secured to the open annular body and extending therefrom, arranged with one facing the other to form a clamp, the open annular body having an aperture. The aperture of the annular body is configured to allow insertion of at least one cable into the annular body. The terminal parts of the open annular body bordering the aperture each have a loop configured for passage of a self-locking clamping collar around the open annular body. The clamp-forming jaws each include at least one through aperture configured for the passage of a fixing structure that can be locked in position. A fixing assembly includes a cable support and an intermediate fixing support of the cable support. It is advantageously possible to carry out a fast and reliable installation of cables, notably in cramped spaces such as on board an aircraft.
A module between a dihydrogen tank and an engine in an aircraft. The module comprises outer and inner boxes, a pipeline between the tank and the engine through the boxes, pressure limiters mounted on the pipeline and the inner box, an exhaust pipeline between the pressure limiters and the outside, shut-off valves mounted on the pipeline at the outer box, a detector for detecting a leak of the pipeline or of the outer box and a controller configured to control each shut-off valve as a function of the information delivered by the detector.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 37/32 - Mesures de sécurité non prévues ailleurs, p.ex. contre les explosions
62.
PROPULSION ASSEMBLY COMPRISING A FUEL CONDITIONING SYSTEM POSITIONED BEHIND A DEBRIS EJECTION ZONE, AIRCRAFT COMPRISING AT LEAST ONE SUCH PROPULSION ASSEMBLY
A propulsion assembly comprising a propulsion system including at least one exhaust duct, from which an exhaust gas stream is discharged, and also a debris ejection zone, a supply device, configured to supply the propulsion system with gaseous fuel, including at least one conditioning system for the gaseous fuel, at least one enclosure in which the conditioning system is positioned, the enclosure being located in the propulsion assembly behind the debris ejection zone. Also an aircraft including at least one such propulsion assembly.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
B64D 37/34 - Conditionnement du carburant, p.ex. réchauffage
F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
63.
AIRCRAFT CENTRAL WING BOX COMPRISING BEAMS PRESSED RESPECTIVELY AGAINST OUTER FACES OF THE TOP AND BOTTOM PANELS OF SAID BOX, EACH PROVIDED WITH AT LEAST ONE ATTACHMENT PASSING THROUGH THE TOP OR BOTTOM PANEL
A central wing box comprising at least one first beam positioned against the outer face of a top panel of the central wing box and linked thereto, at least one second beam positioned against the outer face of a bottom panel of the central wing box and linked thereto, at least one first attachment forming a single piece with the first beam, protruding from the inner face (Fint) of the top panel and at least one second attachment forming a single piece with the second beam, protruding from the inner face (Fint) of the bottom panel, the top and bottom panels comprising, for each first or second attachment, a through-hole to allow the first or second attachment to pass through them.
An electric cable configured to be mounted in an aircraft. This electric cable includes at least one spacer at least partially surrounding a part of the electric cable and making it possible to hold it at a distance greater than a minimum segregation distance from any other element. According to one configuration, the electric cable comprises several spacers distributed along the electric cable and separated from one another.
H01B 17/58 - Tuyaux, manchons, perles isolantes ou bobines au travers desquels passe le conducteur
B60R 16/02 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleurs; Agencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques
65.
ENHANCED SUPPORT FOR THE MAINTENANCE OF AN AIRCRAFT RADOME
A support for the maintenance of an aircraft radome comprising an annular element having a flat surface and from which extend at least three feet. The support comprising a plurality of articulated holding elements, for example articulated fittings, applying a lock function and each comprising a bearing surface on a surface portion of an aircraft radome, for example an interface fitting, when said radome is placed on said flat surface of said annular element.
B64C 1/36 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
A structural assembly for an aircraft having pairs of main gantries distributed in the longitudinal direction, two transverse panels fixed to the front and the rear of the pairs of main gantries to together define a compartment for a landing gear of the aircraft, at least one pair of secondary gantries between the main gantries, at least one crossmembers parallel to the transverse panels and that straddles at least one secondary gantry, and, for each secondary gantry and each crossmember straddling the secondary gantry, a connecting rod mounted to be able to freely rotate, via a first end, on a lower part of the crossmember and, via a second end, on an outer lateral part of the secondary gantry. Such an arrangement reduces the vertical bulk of the structural assembly.
An assembly for an aircraft includes a pylon with a frame and two lateral walls pierced with an aperture, a reservoir, a hooking system to suspend the reservoir facing the apertures, a carriage having a cradle for the reservoir, the carriage being movable in translation between an installation position, in which the cradle is facing the apertures and is under the reservoir, and a use position, in which the cradle is not facing the apertures, fastening elements for fastening the reservoir to the cradle, and a locking system arranged to immobilize the carriage in the use position. The assembly allows quick and simple removal and installation of the reservoir from and into the pylon.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
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
68.
TANK COMPRISING INNER AND OUTER ENCLOSURES AND AT LEAST ONE ANNULAR LINEAR CONNECTION SYSTEM CONNECTING SAID ENCLOSURES
A double-walled tank comprising at least one connection system connecting the outer and inner enclosures and enabling them to move in relation to one another in at least a longitudinal direction parallel to an axis of displacement when in operation. The connection system has an annular linear connection between a first contact surface rigidly connected to the outer enclosure and a second contact surface rigidly connected the inner enclosure, the first and second contact surfaces arranged opposite one another and configured to be in contact with one another along a contact circle that has a center positioned on the axis of displacement.
An autonomous air conditioning system for an aircraft includes a compressor compressing ambient air and supplying compressed air, a first portion of the compressed air being injected into a cabin of the aircraft so as to condition the cabin air in terms of pressure and of temperature. The autonomous system further includes an electric motor providing mechanical energy to the compressor. The system includes a fuel cells stack supplied with air by a second portion of the compressed air supplied by the compressor and supplying electrical energy, the electric motor being electrically powered with electrical energy supplied by the fuel cells stack. Thus, the cabin air conditioning is performed autonomously, avoiding the need to modify a pre-existing electrical network of the aircraft.
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
70.
TUBULAR INSERT FOR A SANDWICH PANEL, METHOD FOR PLACING SUCH A TUBULAR INSERT IN A THROUGH-ORIFICE OF A SANDWICH PANEL AND SANDWICH PANEL HAVING AT LEAST ONE SUCH TUBULAR INSERT
A tubular insert designed to be positioned in a through-orifice of a sandwich panel. This tubular insert comprises a tubular body and at least one tab that has a first end connected to the tubular body and a second end at a distance from the first end, the tab being able to move between a deployed position in which the second end is moved away from the tubular body and a retracted position in which the second end is positioned at the tubular body, the latter having, for each tab, a cutout delimiting the tab and an opening when the tab is in the deployed position. Also a sandwich panel having at least one such insert and a method for placing such an insert.
B32B 3/08 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords caractérisés par des éléments ajoutés à des endroits déterminés
B32B 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
71.
ELECTRICAL CONTACTOR SUITABLE FOR HIGH-POWER ELECTRICAL CIRCUITS, AND AIRCRAFT COMPRISING AN ELECTRICAL CIRCUIT INTEGRATING AT LEAST ONE SUCH ELECTRICAL CONTACTOR
An electrical contactor comprising at least one couple of contacts that are spaced apart from one another when the electrical contactor is in the open state and are in contact with one another when the electrical contactor is in the closed state, and at least one system for extinguishing electrical arcs that comprises at least one switch that connects the contacts of a given couple of contacts and is configured to occupy an on state, in which the switch allows an electric current to pass between the contacts of the couple of contacts in at least one direction, and an off state, in which the switch prevents an electric current from passing between the contacts of the couple of contacts, and a control configured to control the state of the switch. Also an aircraft comprising at least one such electrical contactor.
H01H 50/64 - Dispositions d'entraînement entre en élément mobile de circuit magnétique et un contact
H01H 50/04 - Montage complet de relais ou d'éléments de relais sur un support ou à l'intérieur d'une enveloppe
72.
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 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 70/30 - 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 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
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 70/54 - 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
B29K 105/00 - Présentation, forme ou état de la matière moulée
B29K 105/12 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de longueur réduite, p.ex. filaments coupés, fibres coupées ou crins
73.
PRESSURE MEASURING RAKE COMPRISING A PATCHED LEADING EDGE, IN PARTICULAR FOR AN ENGINE OF AN AIRCRAFT, AND MORE PARTICULARLY FOR A BYPASS TURBOJET ENGINE
A measuring rake, configured to be arranged on a link rod, includes a sheath including a front face and two side walls delimiting between them a recess configured to receive the link rod, an electronic circuit arranged on the front face of the sheath and including at least one sensor, a patched leading edge fixed removably to the sheath, and a seal arranged between the patched leading edge and the electronic circuit, the patched leading edge including a plurality of air intakes, each forming a fluidic passage between an outer face and an inner face of the patched leading edge opening out facing at least one sensor of the electronic circuit, the measuring rake making it possible to obtain a measuring tool which can be assembled simply and quickly, with easy access to the electronic circuit, and making it possible to avoid problems of orifice blockages or air leaks.
An aircraft propulsion unit comprising a motor, a system for supplying fuel to the motor, a fairing inside which the motor and at least part of the fuel supplying system are positioned, and at least one pressure relief device configured to establish communication between the inner and outer zones of the fairing when the pressure in the inner zone is greater than or equal to a given threshold or when a leak is detected. Also an aircraft comprising at least one such propulsion unit.
A measurement bar includes a sheath, a leading edge having a plurality of cavities, a steady pressure sensor generating first data and an unsteady pressure sensor generating second data in each of the cavities, an electronic circuit including the steady pressure sensor and the unsteady pressure sensor of each of the cavities, a processing unit configured to merge the first data and the second data, and a second communication module configured to transmit the first data, the second data and the merged first data and second data to a user device. Thus, it is possible to monitor unsteady aerodynamic phenomena.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
G01L 9/00 - Mesure de la pression permanente, ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments électriques ou magnétiques sensibles à la pression; Transmission ou indication par des moyens électriques ou magnétiques du déplacement des éléments mécaniques sensibles à la pression, utilisés pour mesurer la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent
76.
ANTISTATIC PRESSURE MEASURING RAKE, IN PARTICULAR FOR AN ENGINE OF AN AIRCRAFT, AND MORE PARTICULARLY FOR A BYPASS TURBOJET ENGINE
A pressure measuring rake, intended for arrangement on a link rod, includes at least: a sheath including two side walls which between them delimit a recess configured to receive the link rod, and an electronic circuit arranged on the sheath and including at least one sensor, the measuring rake additionally including at least one conductive layer at least partially covering the sheath and a conductive strip, the conductive layer and the conductive strip being configured to be electrically connected to at least one conductive element configured to drain off charges that are liable to build up on the conductive layer, the measuring rake making it possible to avoid the build-up of electrostatic charges liable to disrupt measurements taken by the sensors and/or electrical communications between the sensors and a data processing unit.
A method for establishing a flight plan for an aircraft by: determining a correction factor F1 related to a degradation in performance of the aircraft; using, to establish the flight plan, a model of the aircraft that incorporates a lower heating value of a reference fuel; obtaining a correction factor F2 related to a difference in lower heating value between the reference fuel and a fuel intended to be used to follow the flight plan; modifying the correction factor F1 by adding the correction factor F2; and determining the flight plan using the model of the aircraft, to which the modified correction factor F1 is given at input. It is thus possible to use an aircraft model in which the lower heating value is fixed internally.
The electronic device includes an acquisition board including at least one pressure sensor and extending over a length of a sleeve of the measuring rake, a processing unit detachably electrically connected to the acquisition board and detachably fixed to the sleeve, a loading/charging unit configured to be electrically connected to the processing unit and to recharge a power supply module of the processing unit when the processing unit is electrically disconnected from the acquisition board; the processing unit including a storage module configured to store the data; the loading/charging unit allowing data to be loaded into a user device. It is thus possible to remove the processing unit in order to load the data without having to completely dismantle the measuring rack.
A probe for use with a tank having a wall pierced by an orifice and configured to contain a fluid containing paramagnetic particles. The probe comprises a magnet, a displacement system arranged at the orifice to displace the magnet from a capturing position in which the magnet is bathed in the fluid to a checking position in which the magnet is outside of the tank, and a seal ensuring the seal-tightness of the orifice in the transition from the capturing position to the checking position and vice versa.
G01N 27/74 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques des fluides
A propulsion assembly for an aircraft having a chassis in the form of a cage with bars, a turbine, a dihydrogen supply pipe winding inside a nacelle as far as the rear of the turbine, with a radial step towards the outside of the nacelle, a rail with a radial step towards the outside of the nacelle, a bypass pipe connected between the two radial steps outside the nacelle, and a protection plate fastened to the bars, and an absorber between the protection plate and the related bar.
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
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 37/30 - Circuits de carburant pour carburants particuliers
F02C 7/22 - Systèmes d'alimentation en combustible
F02K 3/02 - 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
An aircraft fuselage (4) comprising: fore and aft sections of the aircraft fuselage (4), a barrier wall (20) separating the fore and aft sections, the barrier wall (20) defining an opening; a door (25) moveable in a straight line across the barrier wall (20) that defines a direction of movement between an open position in which the door (25) is offset from the opening and a closed position in which the door (25) covers the opening; a seal assembly (50) comprising a first member (51) attached to the barrier wall (20) and extending around a perimeter of the opening, and a second member (52) attached to the door (25) and configured to engage with the first member (51) at respective seal surfaces to form a seal around the perimeter of the opening.
An access door assembly for a fuselage having a structure delimiting an access hatch, an upper part and a lower part of an access door, hinges fastened between the structure and the upper part in the vicinity of an upper edge, a guiding system between the lower part and the structure and guiding the lower part in translation, upper locks between the upper part and the lower part and/or the structure and lower locks between the lower part and the structure.
B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
83.
AIRCRAFT AIR INLET COMPRISING AT LEAST TWO WALLS CONNECTED END TO END BY WELDING, METHOD FOR THE ASSEMBLY OF SUCH AN AIR INLET, AND AIRCRAFT COMPRISING AT LEAST ONE SUCH AIR INLET
An air inlet of a nacelle of an aircraft including a lip having a leading edge configured to split an air flow into interior and exterior air flows, the interior air flow entering the air inlet, an exterior panel, an intermediate panel, interposed between the lip and the exterior panel, having a first edge connected to the lip by at least a first connection and a second edge connected to the exterior panel by at least a second connection, the first connection connecting the first edge of the intermediate panel and the lip comprising at least one butt weld bead having an outer face in the extension of the outer faces of the lip and of the intermediate panel.
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
84.
FLIGHT MANAGEMENT METHOD AND DEVICE IN THE EVENT OF A CHALLENGING CONTEXT IN THE EVENT OF INCAPACITY OF AT LEAST ONE PILOT FLYING
A device configured to warn a pilot flying an aircraft that erroneous data have been entered into a secondary flight plan, to monitor pressure in a cabin of the aircraft, to monitor operation of at least one engine of the aircraft, to determine a capacity of the pilot flying and to automatically activate an escape route when a depressurization of the cabin is detected or when a failure of at least one engine is detected and when an incapacitation of the pilot flying is detected. Also a method and an aircraft with such a device.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
85.
ELECTRICAL PROPULSION SYSTEM INCLUDING A PLURALITY OF ELECTRIC MOTORS COUPLED TO THE SAME INPUT SHAFT OF A TRANSMISSION SYSTEM, AIRCRAFT INCLUDING AT LEAST ONE SUCH ELECTRICAL PROPULSION ASSEMBLY
An electrical propulsion assembly that includes: a propeller that has a rotation axis, at least two electric motors offset relative to one another in a longitudinal direction parallel to the rotation axis of the propeller, a main drive shaft parallel to the rotation axis of the propeller to which the electric motor are coupled, a transmission system including an output shaft connected to the propeller and an input shaft connected to the main drive shaft. Also an aircraft including at least one such electrical propulsion assembly.
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
F01D 15/02 - Adaptations pour véhicules de traction, p.ex. locomotives
F01D 15/12 - Combinaisons avec des transmissions mécaniques
86.
ALVEOLAR STRUCTURE OF AN ACOUSTIC DAMPING PANEL COMPRISING AT LEAST ONE PARTITION CONFIGURED FOR VIBRATING AT A DESIRED FREQUENCY, METHOD FOR PRODUCING SAID ALVEOLAR STRUCTURE
An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave at a sound frequency, wherein the alveolar structure comprises at least one partition provided with at least one cavity configured such that the partition vibrates at a vibrational frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.
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
87.
ALVEOLAR STRUCTURE OF AN ACOUSTIC DAMPING PANEL COMPRISING AT LEAST ONE ATTACHED ELEMENT CONFIGURED FOR VIBRATING AT A DESIRED FREQUENCY, METHOD FOR PRODUCING SAID ALVEOLAR STRUCTURE
An alveolar structure of an acoustic damping panel which is configured for damping at least one sound wave of a sound frequency, wherein the alveolar structure comprises at least one attached element, separate from partitions, and configured for vibrating at a frequency substantially equal to the sound frequency of the sound wave to be damped. Also a method for producing such an alveolar structure, an acoustic damping panel comprising at least one such alveolar structure, and an aircraft comprising at least one such acoustic damping panel.
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
88.
DEVICE FOR BLOCKING THE SHUT-OFF OF A PROPULSION ENGINE FOR AIRCRAFT
A blocking device for preventing an inappropriate shut-off of an engine of an aircraft. The blocking device enables by default the actuation of the shut-off unit and receives information representative of an activated or inactivated state of a fuel shut-off lever, of a reduced or non-reduced speed state of a throttle lever, and a correct or incorrect operating state of the engine. The blocking device blocks the actuation of the shut-off unit when the throttle lever is in an inactivated state, when the engine is in a correct operating state, and when, in addition, the throttle lever is in a non-reduced speed state or the throttle lever is in a reduced speed state and, in addition, the opposite propulsion engine is in a failed state or in an incorrect operating state.
F02C 9/46 - Commande de secours de l'alimentation en combustible
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
An aircraft comprising a fuel tank in which a lower wall of the tank corresponds to a panel of a structure of the aircraft, the panel being provided with reinforcing profiles, a fuel retention zone being associated with at least one reinforcing profile, the retention zone being delimited by the lower wall of the tank and by the reinforcing profile. The tank has a set of passive fuel transfer systems, each system being installed between a fuel retention zone associated with a reinforcing profile and a lower part of the tank. Each passive fuel transfer system is configured to allow fuel retained in the retention zone to be siphoned in such a manner that this fuel is transferred to a pumping zone in the lower part of the tank.
A method for monitoring an aircraft during takeoff is initiated when a first speed threshold is reached. During successive calculation cycles, the following steps are implemented: obtaining a current ground speed; calculating a time taken by a numerical aircraft model to increase its speed to the current ground speed; multiplying this time by the current ground speed and, by integration, deducing therefrom the distance theoretically travelled by the aircraft. Furthermore, the following steps are implemented when a second speed threshold is reached: estimating an acceleration degradation based on a difference between the distance actually travelled by the aircraft and the distance theoretically travelled by the aircraft; and generating a warning when the estimate of the acceleration degradation is greater than a degradation threshold.
A system includes at least a plane semi-reflecting mirror, a light source which is configured to emit a continuous illumination and an event camera to generate events when the object exhibits at least one movement. The plane semi-reflecting mirror is arranged so that it reflects at least the illumination toward the event camera in order to dazzle the camera. The system makes it possible to limit the memory and energy consumption required for monitoring.
G01H 9/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores en utilisant des moyens sensibles aux radiations, p.ex. des moyens optiques
G01D 5/28 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens optiques, c. à d. utilisant de la lumière infrarouge, visible ou ultraviolette avec déviation des rayons lumineux, p.ex. pour une indication optique directe
92.
AIRCRAFT HAVING A LOCKING DEVICE AND A SYSTEM FOR VISUAL INDICATION OF THE STATE OF SAID LOCKING DEVICE
An aircraft with a visual indication system for indicating the locked or unlocked state of a locking device. The system comprises has an opening passing through a wall, a transparent wall closing off the opening and allowing an inner zone of the aircraft to be seen from an outer zone, an indicator to move between first and second positions depending respectively on the locked or unlocked state. The indicator is positioned in the inner zone of the aircraft and has a zone visible through the transparent wall from the outer zone of the aircraft when the indicator is in the first position, the zone not being visible when the indicator is in the second position.
A propulsion system comprising a chassis, a fan cowl, an articulation system fixed between the chassis and the fan cowl and comprising a shaft with two offset cylinders in which a central cylinder is movably mounted in rotation on the chassis and wherein a lateral cylinder is movably mounted in rotation on the fan cowl, a blocking device limits the rotation of the central cylinder relative to the chassis between a closed position and an intermediate position, and a stopping device allows rotation of the fan cowl between the intermediate position and the open position and preventing rotation of the fan cowl beyond the intermediate position.
An aircraft fuel storage system is disclosed including a fuel tank comprising a chamber for storing fuel, the chamber comprising a first side, a second side, and a base connecting the first side to the second side; a collector; and a first conduit and a second conduit, each of the first and second conduits fluidically coupling the chamber to the collector so that fuel is freely passable from the chamber to the collector via the respective first and second conduits. The first and second conduits open into the chamber at respective first and second conduit openings, the first conduit opening is nearer to the first side than the second conduit opening is to the first side, and the second conduit includes a second conduit lock portion that is nearer to the first side than the second conduit opening is to the first side. Also disclosed is an aircraft including the aircraft fuel storage system.
A method of manufacturing an aircraft assembly is disclosed including forming a first tension hole in a first aircraft component and a second tension hole in a second aircraft component. The first and second aircraft components are positioned relative to each other such that the first tension hole at least partially overlies the second tension hole, to define a pair of tension holes. The first aircraft component is secured relative to the second aircraft component by providing a first fastener between the first tension hole and the second tension hole of the pair of tension holes. A first shear hole is formed in the first aircraft component and a second shear hole is formed in the second aircraft component. The first shear hole is axially aligned with the second shear hole, to define a pair of shear holes.
An electrical protection device of circuit-breaker type including a casing, a severing system, positioned in the casing, configured to assume inactivated and activated states corresponding to the on and off states of the electrical protection device, respectively, and a connection system configured to assume an open state in which it allows the electrical cable to be inserted and a second, closed state in which it surrounds the electrical cable. The connection system and the severing system are configured and arranged such that, when the connection system is in the closed state, the severing system severs the electrical cable when passing from the inactivated state to the activated state.
A turbofan with a nacelle having a fixed structure, a mobile assembly bearing second blocking element and able to move between an advanced position and a withdrawn position, a set of deflectors able to move in translation between an advanced position and a withdrawn position, and an actuation system having a carriage, a blocking lever bearing first attachment element and able to move between a blocking position and a free position, and a transmission system configured to move the blocking lever from the blocking position to the free position when the mobile assembly reaches a tilting position between the advanced position and the withdrawn position.
A resin film configured to hold a conductive metallic track against a panel. The resin film partially covers the conductive metallic track, such that the conductive metallic track has at least one region which does not have the resin film, so as to allow an electrical connection by contact. Thus, in the context of assembly on a panel, the metallic track incorporated between the panel and the resin film is protected, thus rendering this technical solution particularly robust. Furthermore, the resin film electrically insulates the metallic track from surrounding elements, and the regions which do not have resin film allow an electrical connection by contact.
B32B 3/10 - 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
B32B 3/08 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords caractérisés par des éléments ajoutés à des endroits déterminés
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 15/092 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique comprenant des résines époxy
B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
B32B 27/12 - Produits stratifiés composés essentiellement de résine synthétique adjacente à une couche fibreuse ou filamenteuse
B32B 27/38 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines époxy
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 38/00 - Opérations auxiliaires liées aux procédés de stratification
B64C 1/12 - Structure ou fixation de panneaux de revêtement
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
H01B 5/16 - Conducteurs ou corps conducteurs non isolés caractérisés par la forme comprenant un matériau conducteur incorporé à un matériau isolant ou faiblement conducteur, p.ex. du caoutchouc conducteur
99.
Aircraft propulsion system having a nacelle equipped with an improved articulation system
A propulsion system having a chassis, two fan cowls and, for each one, an articulation system fastened between the chassis and the fan cowl, so as to move the fan cowl between a closed position and an open position and a locking device like a clamping screw, wherein each articulation system has, for each fan cowl, two pantograph hinges. With such an arrangement, each fan cowl moves away laterally as soon as its opening starts.
An assembly comprising a nut, in addition to a retaining system which is configured to retain the hole of the nut substantially in the extension of a through-hole of a part. The retaining system comprises at least two resilient tabs which are configured to be housed in the through-hole of the part, the free ends of the resilient tabs being positioned, in the undeformed state, on a circle having a greater diameter than an internal diameter of the through-hole. Also a mounting system comprising such a retaining system for a nut.
F16B 37/04 - Dispositifs pour fixer les écrous à des surfaces, p.ex. à des feuilles, à des plaques
F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
