The invention relates to a device (100) for activating an emergency function for the deployment of the landing gear of an aircraft, wherein the device comprises: an electric motor; a screw (120) configured to be translated by the electric motor between an extended position and a retracted position, and configured to disengage a holding element that keeps the landing gear in the closed position when it is in the extended position, and to secure the holding element that keeps the landing gear in the closed position when it is in the retracted position; two magnetic field sensors (151, 152); and a finger (160) that comprises a permanent magnet (165) at one of its ends, and which is capable of moving between the two magnetic field sensors, driven by the screw in such a way that the permanent magnet aligns with the magnetic field sensors.
o/fvv) which activates the progressive operating mode, at least one direction of the first movement between a return position of the control member (4) and a supply position being different from a direction of the second movement between the return position and the supply position.
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/00 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage
3.
BRAKING SYSTEM FOR AN AIRCRAFT COMPRISING AN ELECTRICALLY ACTUATED DEVICE CONTROLLED BY A FIRST AND A SECOND CONTROL MEMBER
o/fvv) that activates the progressive operating mode, and wherein the at least one first control member (4) is independent of the at least one second control member (5).
An electromagnet includes a cylindrical core and a bobbin. The bobbin has a first barrel portion delimited by a first flange and a second flange. The bobbin further includes a second barrel portion delimited by the second flange and a third flange. A diameter of the first flange is greater than a diameter of the third flange. The bobbin also includes an aperture extending through the first and second barrel portions, wherein the core is disposed within the aperture. A wire is wrapped around the first barrel portion to define a first portion of a coil and around the second barrel portion to define a second portion of the coil. A power source provides current through the wire.
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
F16D 63/00 - Freins non prévus ailleursFreins combinant plusieurs des types mentionnés dans les groupes
H02K 49/04 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
5.
METHOD FOR DETECTING DAMAGE TO A PART MADE OF CONDUCTIVE MATERIAL
The invention relates to a method (300) for detecting damage (201) to a part (200) made of conductive material, the damage (201) being a burn or a crack, the part (200) being heated (310) by induction by injecting an energy pulse. The method comprises receiving (330) a temporal sequence of thermal images of the part after heating the part (200), and the temporal signal of the intensity of each pixel of the thermal image is used to construct (370) a phase image of the part by means of a discrete Fourier transformation of the temporal signal.
An electromagnet (200) includes a cylindrical core (204) and a bobbin (210). The bobbin (210) has a first barrel portion (212) delimited by a first flange (216) and a second flange (218), and a second barrel portion (214) delimited by the second flange (218) and a third flange (220). A diameter of the first flange (216) is greater than a diameter of the third flange (220). The bobbin (210) also includes an aperture (228) extending through the first and second barrel portions (212, 214), wherein the core (204) is disposed within the aperture (228). A wire (230) is wrapped around the first barrel portion (212) to define a first portion (234) of a coil (232) and around the second barrel portion (214) to define a second portion (236) of the coil (232). A power source provides current through the wire (230).
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
F16D 63/00 - Freins non prévus ailleursFreins combinant plusieurs des types mentionnés dans les groupes
H02K 49/04 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
7.
METHOD FOR CONTROLLING THE VALVE OF A PARKING BRAKE SYSTEM
The invention relates to a method for diagnosing a state of health of an actuator of an electro-hydraulic valve (110A; 110B) of a first hydraulic control circuit (100A; 100B) of a parking brake system of an aircraft, which comprises: - determining a delay (Δt, Δt'), referred to as "actuation delay", between a determined instant following an activation or a deactivation of the valve (110A; 110B) and another instant of exceeding a given pressure threshold measured on a given pressure sensor (121A; 121B) downstream of the valve; - comparing the actuation delay (Δt, Δt') with a predetermined threshold value (Anomaly_threshold_A; Anomaly_threshold_B) referred to as "anomaly detection threshold".
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freinsDispositifs de signalisation
B60T 8/00 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage
8.
HEAT SINK CONFIGURATIONS FOR EDDY CURRENT BRAKE APPLICATIONS
A heat sink configuration for an eddy current brake having a rotor (120) configured to be operably coupled to a wheel (102) of an aircraft is provided. The rotor (120) can include an annular central disc portion (126) and a plurality of heat sinks (122) arranged circumferentially around an outer radial edge. The plurality of heat sinks (122) can each have first and second detachable flanges on opposite axial sides of the heat sinks (122). The rotor (120) may further include grooves (124) arranged between two circumferentially adjacent heat sinks to receive a clamp (140) for operably coupling the brake rotor assembly (110) to the wheel (102) of the aircraft. An axial thickness of the annular central disc portion (126) can be less than an axial thickness of the plurality of heat sinks (122) to promote heat transfer from the annular central disc portion (126) into the plurality of heat sinks (122) during use.
A heat sink configuration for an eddy current brake having a rotor (120) configured to be operably coupled to a wheel (102) of an aircraft is provided. The rotor (120) can include an annular central disc portion (126) and a plurality of heat sinks (122) arranged circumferentially around an outer radial edge. The plurality of heat sinks (122) can each have first and second detachable flanges on opposite axial sides of the heat sinks (122). The rotor (120) may further include grooves (124) arranged between two circumferentially adjacent heat sinks to receive a clamp (140) for operably coupling the brake rotor assembly (110) to the wheel (102) of the aircraft. An axial thickness of the annular central disc portion (126) can be less than an axial thickness of the plurality of heat sinks (122) to promote heat transfer from the annular central disc portion (126) into the plurality of heat sinks (122) during use.
A rolling device for a vehicle includes a wheel having a hub to be mounted to pivot on a shaft and a rim including first annular portion delimiting a recess receiving an eddy current magnetic braking device including a stator constrained to rotate with the shaft, a rotor constrained to rotate with the wheel and provided with a first surface facing a first surface of the stator to form a first pair of surfaces, and first magnets for generating a first magnetic flux which passes through the first pair of surfaces. The rotor includes a second surface facing a second surface of the stator to form a second pair of surfaces and the magnetic braking device includes second magnets for generating a second magnetic flux which passes through the second pair of surfaces. The first magnetic flux is axial and the second magnetic flux is radial.
A vehicle wheel (1), rotatably mounted on an axle (E), comprising a wheel-braking device and a wheel-driving device, the braking device comprising a brake disk (11) constrained to rotate with the wheel and a brake caliper (14) straddling the disk in order to exert friction forces on the disk by means of a brake actuator mounted on the caliper, and the drive device comprising a gear motor (23) driving in rotation a pinion which is arranged to mesh with a ring gear (21) constrained to rotate with the disk.
B60T 1/06 - Aménagements des éléments de freinage, c.-à-d. des parties de ceux-ci dans lesquelles se produit l'effet de freinage en agissant par retardement des roues par action autre que sur la bande de roulement, p. ex. par action sur une jante, un tambour, un disque ou sur la transmission
F16D 55/224 - Freins à surfaces de freinage substantiellement radiales pressées l'une contre l'autre dans une direction axiale, p. ex. freins à disques avec disques ou patins déplaçables selon l'axe pressés contre des organes en rotation situés dans l'axe par serrage entre des organes mobiles de freinage, p. ex. des disques ou des patins de freins mobiles avec un organe d'actionnement commun pour les organes de freinage
F16D 65/12 - DisquesTambours pour freins à disques
F16D 65/18 - Mécanismes d'actionnement pour freinsMoyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
A device (10) for driving at least one wheel (12) of an aircraft landing gear (14), this device (10) comprising: - at least one landing-gear wheel (12), this wheel (12) comprising a rim (16) having an axis of rotation (X), - an electric motor (20) comprising a shaft (30), - a system (22) for mechanical transmission between the shaft of the motor (20) and the rim (16), this mechanical transmission system (22) comprising a mechanical reduction gear (28) which has: - a movable ring gear (38) which rotates conjointly with the shaft of the motor (20), - a movable sun gear (32) which rotates conjointly with the rim (16), - a stationary sun gear (56) attached to a stator of the device (10), and - planet gears (34) which mesh with the ring gear and the sun gears.
B60K 7/00 - Disposition du moteur dans ou jouxtant une roue motrice
B60K 17/04 - Agencement ou montage des transmissions sur les véhicules caractérisées par la disposition, l'emplacement ou le type de mécanisme de transmission
F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
The invention relates to a mechanical part (100) comprising a core (110) having a fibrous reinforcement densified by a matrix, comprising at least one opening adjacent to the core (110) through which a shaft is intended to pass in order to establish a connection with another part, and comprising a belt (120) having a fibrous reinforcement densified by the matrix surrounding the core (110) and the at least one opening. According to the invention, the part (100) is characterized in that at least one insert (140) extending from the opening is positioned between the core (110) and the belt (120).
B29C 70/20 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans une seule direction, p. ex. mèches ou autres fibres parallèles
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29C 70/86 - Incorporation dans des couches de renforcement imprégnées cohérentes
14.
ROLLING DEVICE WITH MIXED FRICTION/MAGNETIC BRAKING, AND AIRCRAFT THUS EQUIPPED
A rolling device for a vehicle, having a wheel rim pivoting about a shaft and delimiting two recesses, one receiving a friction braking device and the other a magnetic braking device having a stator constrained to rotate with the shaft, a rotor constrained to rotate with the wheel, and a control member of the magnetic braking de-vice extending at least partially into the shaft. An aircraft having such a rolling device.
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
A method diagnoses a state of deterioration of an uplock having an unlocking actuator provided with a hydraulic cylinder. The method includes the step of supplying the cylinder with pressurized fluid with an evolution law according to which the pressure of the fluid is, for a predetermined period, equal to a predetermined pressure lower than a full pressure, then equal to the full pressure. The method further includes the steps of determining a time of deactivation of the uplock and comparing it with the time when the predetermined time period ends; and deducing therefrom a state of deterioration of the uplock.
B64C 25/28 - Systèmes de commande ou de verrouillage à cet effet avec dispositifs indicateurs ou avertisseurs
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
F15B 20/00 - Dispositions propres à la sécurité pour systèmes de manœuvre utilisant les fluidesUtilisation des dispositifs de sécurité dans les systèmes de manœuvre utilisant des fluidesMesures d'urgence pour les systèmes de manœuvre utilisant des fluides
A gantry crane and associated method of erection, the gantry including a frame having at least three first members; a longitudinal rail supported by the frame; and at least three second members extending between a first end portion and an opposite second end portion. Each second member can be connected to the frame by means for rigid connection and continuous rotational movement of the second member relative to the frame between a first position in which the second member forms an angle of less than 90° with the first plane and a second position in which the second member is substantially perpendicular to the first plane.
B66C 17/00 - Ponts roulants à chariot transbordeur comportant une ou plusieurs poutres principales sensiblement horizontales dont les extrémités reposent directement sur des roues ou des rouleaux se déplaçant sur une voie soutenue par des supports espacés
B66C 23/78 - Appuis, p. ex. des longerons, pour grues mobiles
17.
METHOD FOR SEALING ALUMINIUM ALLOYS USING A TUNGSTEN SALT AND ALUMINIUM-BASED OR ALUMINIUM ALLOY-BASED PART OBTAINED BY THIS METHOD
The present invention relates to a part (1) based on aluminium or an aluminium alloy, comprising a body (10) made of aluminium or of an aluminium alloy, an inner layer (12) comprising aluminium oxide placed on the body (10), an intermediate layer (14) comprising chromium and zirconium, and an outer layer (16) comprising tungsten oxide, the intermediate layer (14) being placed between the inner layer (12) and the outer layer (16). It also relates to a method for post-anodizing sealing of a body (10) made of aluminium or of an aluminium alloy.
The invention relates to a method for measuring the wear of the discs of an aircraft brake provided with a wear indicator (6) movably mounted on a fixed part of the aircraft brake and moving as the discs wear, the method comprising the steps of: - acquiring an image of a portion of the discs of the aircraft brake, - identifying the wear indicator (6) in the acquired image, - identifying at least three reference points (A1, B1, C2) on the wear indicator (6), and - determining at least one measurement of the wear of the discs of the aircraft brake by determining at least one dimension (L, W) associated with the wear indicator (6) from the three identified reference points (A1, B1, C2).
B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freinsDispositifs de signalisation
B60T 17/00 - Éléments, parties constitutives ou accessoires des systèmes de freins non couverts par les groupes , ou , ou présentant d'autres caractéristiques intéressantes
19.
STRUT FOR AIRCRAFT LANDING GEAR EQUIPPED WITH AN ACCUMULATOR, LANDING GEAR COMPRISING SUCH A STRUT, AND AIRCRAFT COMPRISING AT LEAST ONE SUCH LANDING GEAR
A strut for an aircraft landing gear is provided. The strut includes a casing configured to absorb landing forces applied to the aircraft landing gear. The casing includes a cavity in which an energy accumulator is housed. The energy accumulator can be a removable cartridge which can be inserted in the cavity. An aircraft landing gear comprising such a strut is also provided. An aircraft comprising at least one such landing gear having such a strut is also provided. A method for emergency deployment of such a landing gear, using energy stored in the energy accumulator integrated in the strut of the landing gear to deploy the landing gear is also provided.
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
PARKING ELECTROVALVE FOR AN AIRCRAFT BRAKING SYSTEM, ELECTRIC CIRCUIT FOR CONTROLLING A PARKING BRAKE AND BRAKING SYSTEM COMPRISING SUCH AN ELECTOVALVE
L1L1'L2L3L4.1L4.2L4.2) connected to the electromagnet, the logic switch being arranged to adopt a closed state or an open state according to a logic operation taking account of at least a signal representative of a critical state of progress of the aircraft that requires the slide-valve to be in the first stable position or the second stable position.
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/00 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage
21.
METHOD FOR LIMITING THE VIBRATIONS INDUCED BY BRAKES PROVIDED ON AIRCRAFT LANDING GEAR WHEELS
1.11.22.12.21.11.42.12.41.11.62.12.61212121.11.22.12.21.11.42.12.41.11.62.12.62.6'') of the brake discs of each of the two wheels; − determining, from the acquired temperatures, the wheel whose brake is the least likely to induce vibrations; − activating the brake that is the least likely to induce vibrations.
1.11.22.12.2 1.11.42.12.41.11.62.12.61212121.11.22.12.21.11.42.12.41.11.62.12.62.6'') of the brake discs of each of the two wheels; − determining the wheel whose brake has the lowest or highest temperature; − activating the brake having the lowest or highest temperature depending on the material from which the brake discs are made.
A landing gear system (5) for an aircraft (1), the landing gear system comprising a front landing gear (2) and at least one rear landing gear, the rear landing gear being of the bogie beam type and comprising at least two wheels, the landing gear system furthermore being equipped with a hybrid braking system comprising at least one friction brake and at least one auxiliary brake providing energy dissipation by means other than friction, at least one of the wheels of the rear landing gear being equipped solely with one or more auxiliary brakes and at least one of the wheels of the rear landing gear being equipped solely with one or more friction brakes, all the wheels of the rear landing gear being equipped with at least one auxiliary brake or with a friction brake. An aircraft equipped with such a landing gear system.
The invention relates to a method for controlling the braking of an aircraft comprising at least one control member (11) providing a value of at least one braking control parameter, and an eddy current magnetic braking device (1), the method comprising the steps of: acquiring the value of the braking control parameter and values of state parameters of the magnetic braking device (1), and determining a braking torque command and an air gap setpoint and/or a supply current setpoint from a model which is stored in the electronic processing unit (7) and which correlates values of the braking control parameter, values of the braking torque, values of the air gap and values of the supply current according to the state parameters of the magnetic braking device (1). The invention also relates to a magnetic braking device implementing this method.
A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tubes of a second individual module and the gas inlet openings of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.
C04B 35/52 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbone, p. ex. graphite
C04B 38/00 - Mortiers, béton, pierre artificielle ou articles de céramiques poreuxLeur préparation
Disclosed is a vehicle wheel (1) rotatably mounted on an axle (E) and comprising: - an annular rim (2), a web (3) and a hub (4) delimiting a closed-off annular space, - an electric motor (10) comprising a first stator (11) and a first rotor (12) which are arranged coaxially to the wheel, and - a magnetic brake (20). The motor and the brake extend one inside the other within the annular space. Either the first rotor serves as a rotor for the brake (22), or the first stator (11) serves as a stator for the brake (21) in order to produce a second magnetic flux capable of inducing eddy currents that generate a braking torque. Either the first stator or the first rotor has a Halbach array formed at least in part by electromagnets.
H02K 7/104 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des freins à courants de Foucault
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
H02K 21/14 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant à l'intérieur des induits
27.
Chemical vapor infiltration densification method using single-pile plates for a semi-forced flow
A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tube of a second individual module and the gas inlet opening of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.
C23C 16/455 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour introduire des gaz dans la chambre de réaction ou pour modifier les écoulements de gaz dans la chambre de réaction
C23C 16/04 - Revêtement de parties déterminées de la surface, p. ex. au moyen de masques
C23C 16/44 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement
C23C 16/458 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c.-à-d. procédés de dépôt chimique en phase vapeur [CVD] caractérisé par le procédé de revêtement caractérisé par le procédé utilisé pour supporter les substrats dans la chambre de réaction
28.
WHEEL WITH MAGNETIC BRAKING DEVICE; AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to a wheel comprising an eddy current magnetic braking device, the device comprising at least one stator and at least one rotor, and magnets secured to one of these in order to produce a magnetic flux therebetween that is capable of inducing eddy currents in the other when the wheel rotates. According to the invention, the rotor is rotatably connected to the wheel via a transmission mechanism of the wheel. The invention also relates to a landing gear and an aircraft comprising such a wheel.
B60T 8/32 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p. ex. accélération ou décélération
H02K 7/102 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des freins à friction
H02K 49/04 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
30.
METHOD FOR MANUFACTURING A FIBROUS PREFORM FOR A COMPOSITE PART INTENDED TO BE ARTICULATED TO OTHER PARTS
The present invention relates to a method for manufacturing a fibrous preform (40, 240) of a core for a composite part intended to be articulated to other parts, comprising the formation of a strip (10, 110) in a single piece by three-dimensional weaving and the shaping thereof to give it a generally H-shaped cross-section.
The invention relates to an eddy current magnetic braking device (1) comprising two outer stators (2.1) surrounding a central stator (2.2) and two rotors (3) made of an electrically conductive material. Each outer stator has a surface facing a surface of one of the rotors and is provided with a plurality of permanent magnets (11, 13) having a magnetisation vector normal to the surface so as to emit, via the surface, a first magnetic flux capable of inducing eddy currents in the rotors. The central stator comprises electromagnets (21) that have a magnetisation vector parallel to those of the permanent magnets and that are connected to a controlled power source (22) to produce a second magnetic flux that either opposes the first magnetic flux or reinforces the first magnetic flux. The invention also relates to a vehicle wheel, an aircraft landing gear and an aircraft comprising such a device.
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
H02K 49/04 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
H02K 1/17 - Noyaux statoriques à aimants permanents
H02K 21/04 - Bobinages disposés sur les aimants pour une excitation additionnelle
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
32.
INDUSTRIAL PROCESS FOR THE HEAT TREATMENT OF PREFORMS MADE OF A CARBON PRECURSOR MATERIAL FOR THE MANUFACTURE OF C/C PARTS
The invention relates to an industrial process for the heat treatment of preforms made of a carbon precursor material, the process comprising the following sequential steps: - introducing (S10) a load of preforms made of a carbon precursor material into a first sealed airlock that selectively communicates with a first furnace; - replacing (S20) the air present in the first sealed airlock with a neutral gas; - transferring (S30) the load into the first furnace; - performing a first carbonisation treatment (S40) in the first furnace; - transferring (S50) the load into a second sealed airlock that selectively communicates with the first and second furnaces; - evacuating (S60) the second sealed airlock; - transferring (S70) the load into the second furnace; - performing a second carbonisation treatment (S80) in the second furnace; - transferring (S80) the load into a third sealed airlock that selectively communicates with the second furnace and with an open air outlet.
C04B 35/83 - Fibres de carbone dans une matrice carbonée
C04B 35/626 - Préparation ou traitement des poudres individuellement ou par fournées
D01F 9/14 - Filaments de carboneAppareils spécialement adaptés à leur fabrication par décomposition de filaments organiques
D01F 9/20 - Filaments de carboneAppareils spécialement adaptés à leur fabrication par décomposition de filaments organiques à partir de produits de polyaddition, de polycondensation ou de polymérisation
F27B 9/02 - Fours dans lesquels la charge est déplacée mécaniquement, p. ex. du type tunnel Fours similaires dans lesquels la charge se déplace par gravité à trajets multiplesFours dans lesquels la charge est déplacée mécaniquement, p. ex. du type tunnel Fours similaires dans lesquels la charge se déplace par gravité à plusieurs chambresCombinaisons de fours
F27B 9/04 - Fours dans lesquels la charge est déplacée mécaniquement, p. ex. du type tunnel Fours similaires dans lesquels la charge se déplace par gravité adaptés pour le traitement de la charge sous vide ou sous atmosphère contrôlée
F27B 19/02 - Combinaisons de différents genres de fours qui ne sont pas tous couverts par un seul des groupes principaux combinés en une seule structure
A hydraulic assembly for an aircraft engine includes a pump with a housing and a rotor arranged inside the housing. The housing has at least one hydraulic line configured for the passage of a fluid; and a hydraulic transfer unit comprising: a hydraulic transfer block attached to the housing and comprising an internal fluid passage channel which communicates with the hydraulic line, and a casing which covers the transfer block and which is guided in rotation about an axis of revolution (Y) and about the transfer block, the casing having a fluid outlet port that communicates with the internal channel.
F15B 15/18 - Ensembles combinés comportant moteur et pompe
F15B 15/14 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autreTransmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit
34.
METHOD FOR POWERING AIRCRAFT ACTUATORS HAVING A SINGLE GENERATOR
The invention relates to a method for powering actuators of an aircraft comprising at least one generator (500), the actuators being associated with landing gear of the aircraft and comprising at least one actuator for providing at least one of the following functions: A/ extending/retracting the landing gear, B/ steering the steerable wheels of the landing gear, C/ normal braking of the aircraft; and one actuator for providing at least one of the following functions: D/ applying the parking brake of the aircraft, E/ extending the landing gear in emergency mode, F/ braking in emergency mode. The method of the invention comprises the steps of: • - powering the actuator providing at least one of the functions A/, B/, C/ directly with the generator; • - powering the actuator providing at least one of the functions D/, E/, F/ by means of an accumulator (501) connected to the generator by a power line (502) comprising a normally closed switching member (503) for isolating the accumulator from the generator so as to have two independent and segregated power sources, each powering actuators that perform separate functions, the switching member (503) being controllable to open and allow the accumulator to be charged by the generator.
A method for filling a hydraulic circuit of an electro-hydrostatic system includes connecting first and third shut-off valves to a discharge valve, and connecting a second shut-off valve to a filling valve, while the second and third shut-off valves are closed, opening the filling valve, the discharge valve and the first shut-off valve and operating a vacuum generator, once a vacuum has been established in the hydraulic circuit, opening the second shut-off valve in order to fill the hydraulic circuit with pressurized hydraulic fluid while the vacuum generator is still in operation, once the hydraulic circuit has been filled with fluid, closing the first shut-off valve and then opening the third shut-off valve in order to bypass the vacuum generator and circulate the fluid through the electro-hydrostatic system until the fluid contained in the hydraulic circuit reaches a predetermined pressure, and closing the discharge valve and the filling valve.
F15B 21/00 - Caractéristiques communes des systèmes de manœuvre utilisant des fluidesSystèmes de manœuvre à pression ou parties constitutives de ces systèmes, non couverts par l'un quelconque des autres groupes de la présente sous-classe
F15B 1/26 - Réservoirs d'alimentation ou de pompage
The invention relates to a device for measuring the oxidation of an element comprising a carbon-carbon composite, including a means for measuring the diamagnetism of the element and a means for converting the diamagnetism measurement into an oxidation measurement.
G01N 27/82 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques pour rechercher la présence des criques
B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freinsDispositifs de signalisation
F16D 66/00 - Dispositions pour la surveillance des conditions de fonctionnement des freins, p. ex. de l'usure ou de la température
37.
EDDY CURRENT MAGNETIC BRAKING DEVICE, BRAKED VEHICLE WHEEL AND AIRCRAFT LANDING GEAR, AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to an eddy current magnetic braking device (1) for a vehicle wheel, the device comprising a first element (3) and a second element (2) that has a main surface (2.1) facing a main surface (3.1) of the first element, the first element being made of an electrically conductive material and the second element being provided with magnets (7) for producing, between the main surfaces of the elements, a magnetic flux capable of generating eddy currents in the first element. The first element comprises a core that is made of a first metal for transmitting a braking torque and is at least partially coated with an outer layer made of a second metal in order to form the main face of the first element. The invention also relates to a vehicle wheel, a landing gear and an aircraft comprising such a device, and to a method for manufacturing the first element of such a device.
A system and method for a hybrid braking architecture for an aircraft is provided. The system can include a friction brake operably coupled to a main landing gear assembly, an eddy current brake operably coupled to a nose or main landing gear assembly and configured to impart up to a maximum resistive force, and a brake controller in communication with the friction brake and the eddy current brake. The brake controller can actuate one or both of the friction and eddy current brakes in response to receiving a braking signal with a required braking force based on an input amplitude of a braking input device. When the required braking force of the braking signal is less than or equal to the maximum resistive force, the eddy current brake can be actuated in the absence of actuating the friction brake to reduce wear on the friction brake, e.g., during taxiing maneuvers.
A system and method for a hybrid braking architecture for an aircraft is provided. The system can include a friction brake operably coupled to a main landing gear assembly, an eddy current brake operably coupled to a nose or main landing gear assembly and configured to impart up to a maximum resistive force, and a brake controller in communication with the friction brake and the eddy current brake. The brake controller can actuate one or both of the friction and eddy current brakes in response to receiving a braking signal with a required braking force based on an input amplitude of a braking input device. When the required braking force of the braking signal is less than or equal to the maximum resistive force, the eddy current brake can be actuated in the absence of actuating the friction brake to reduce wear on the friction brake, e.g., during taxiing maneuvers.
A diffuser for diffusing a gas flow within a stack of blanks that are impregnated with a sol-gel solution, the gas flow evaporating a solvent, each blank having a central through-opening, the openings forming a central well, includes diffusion fins extending from a central cavity toward the periphery of the diffuser, each fin having a central through-opening, the openings forming the open central cavity of the diffuser so as to form an upwardly open gas inlet, the cross section of the central cavity decreasing from the gas inlet, the fins extending into the central well, the fins diffusing and homogenizing the gas flow flowing from the central well through the stack.
F26B 21/00 - Dispositions pour l'alimentation ou le réglage de l'air ou des gaz pour le séchage d'un matériau solide ou d'objets
F26B 3/04 - Procédés de séchage d'un matériau solide ou d'objets impliquant l'utilisation de chaleur par convection, c.-à-d. la chaleur étant transférée d'une source de chaleur au matériau ou aux objets à sécher par un gaz ou par une vapeur, p. ex. l'air le gaz ou la vapeur circulant sur ou autour du matériau ou des objets à sécher
41.
VEHICLE WHEEL COMPRISING A DRIVE DEVICE AND A BRAKING DEVICE
A wheel (1) rotatably mounted on an axle and comprising: - a rim (2) connected by a web (3) to a hub (4) pivotably received on the axle, and delimiting with the hub an annular space; - a radial flux electric motor (10) comprising a first stator (11) and a first rotor (12) which are arranged to generate a torque for the rotational driving of the wheel; - a magnetic brake (20) comprising a second stator (21) and a second rotor (22) which are arranged to generate a torque for the braking of the wheel, the electric motor and the magnetic brake extending one inside the other inside the annular space, of the first rotor and the second rotor one being adjacent to the rim and of the the first rotor and the second rotor the other being adjacent to the hub, the first stator and the second stator extending between the first rotor and the second rotor.
A method for drying a blank of a part made of a carbon/carbon composite material impregnated with a sol-gel solution, the solution including a solvent and one or more compounds, in a system forming an oven includes gelling the solution so as to form a gel within the blank disposed in the chamber by heating a chamber, where a gas circulator and a desaturation component are deactivated, so as to restrict circulation and desaturation of the gas in a solvent, and drying the gel within the blank by heating, where the gas circulator and the desaturation component are activated, so as to enable circulation and desaturation of the gas in a solvent.
F26B 3/04 - Procédés de séchage d'un matériau solide ou d'objets impliquant l'utilisation de chaleur par convection, c.-à-d. la chaleur étant transférée d'une source de chaleur au matériau ou aux objets à sécher par un gaz ou par une vapeur, p. ex. l'air le gaz ou la vapeur circulant sur ou autour du matériau ou des objets à sécher
F26B 9/06 - Machines ou appareils pour le séchage d'un matériau solide ou d'objets au repos animés uniquement d'une agitation localeAération des placards ou armoires d'appartements dans des tambours ou chambres fixes
F26B 21/08 - Commande, p. ex. régulation des paramètres de l'alimentation en gaz de l'humidité
43.
ELECTROMAGNETICALLY CONTROLLED PARKING BRAKE DEVICE, AND AIRCRAFT WHEEL AND AIRCRAFT PROVIDED WITH SUCH A DEVICE
The invention relates to a device for preventing the rotation of a wheel (1) rotatably mounted on an axle (2) so as to rotate about an axis of rotation (X), the device comprising a receiving member (4) that is rigidly attached to the wheel and provided with an internal face that has regularly distributed axial cavities (4e); a rotationally stationary cage (6) that extends around the axle facing the receiving member, the cage comprising axial recesses (6a) that accommodate segments (7) that are movable in the cage in respective radial directions between an engagement position in which the segments are engaged in the receptacles in the receiving member and a release position in which the segments are disengaged from the receptacles in the receiving member; a push member (5) made of a material capable of channelling a magnetic flux, the push member extending around the axle in order to co-operate with the segments via oblique bearing surfaces and mounted so as to move axially between a locking position in which the push member forces the segments into the engagement position and an unlocking position in which the push member forces the segments into the release position; a return member (12) for returning the push member to its locking position and maintaining it therein; a permanent magnet (14) exerting an electromagnetic force on the push member designed to maintain the push member in the unlocking position against the force of the return member; an electromagnet (15) that can be selectively powered so as to counteract the force of the permanent magnet in order to allow the push member to move from the unlocking position to the locking position under the effect of the return member or to enhance the force of the permanent magnet in order to move the push member from the locking position to the unlocking position against the force of the return member. The invention also relates to a wheel and an aircraft provided with such a device.
An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.
A method and system for mounting an axle in a bore of a bogie mounted on a landing gear of an aircraft, the landing gear being in a gear-down position, the bore extending in a substantially horizontal direction referred to as the axle installation direction, between a first open end and a second open end are disclosed. The method includes a) supplying a mobile bearing structure (30) comprising means for moving the axle (12) which are able to move along a direction substantially parallel to the axle installation direction, b) installing the axle (12) on the means for moving the axle, c) aligning the axis (C) of the axle (12) with the axis (B) of the bore (14), and d) inserting the axle (12) into said bore (14) of the bogie (16) by moving the means for moving the axle (12) along the direction substantially parallel to the axle installation direction.
The invention relates to a braked wheel (1) mounted on an axle (E) so as to be rotatable about an axis (X), comprising: − a first, magnetic braking device (10) comprising a stator (11) and a rotor (12) capable of producing a first braking torque, one of the stator and the rotor being arranged to move along the axis (X) between a position of free rotation and a braking position and to be returned to the position of free rotation by elastic return means; − a second, friction braking device (20) comprising a stack of discs (21.1, 21.2, 21.3, 22.1, 22.2) capable of producing a second braking torque on the wheel, the stack of discs comprising a rear face axially facing the stator or the rotor arranged to move along the axis; and - at least one actuator (41) designed to exert a pressing force on a front face of the stack of discs.
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/32 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p. ex. accélération ou décélération
F16D 55/36 - Freins à plusieurs disques tournants disposés tous côte à côte
F16D 63/00 - Freins non prévus ailleursFreins combinant plusieurs des types mentionnés dans les groupes
47.
METHOD FOR SECURING A PARKING FUNCTION IN AN AIRCRAFT BRAKING SYSTEM
The invention relates to a method for securing a parking function of a hydraulic braking circuit (1) supplying brakes (12a, 12b) of braked wheels (11a, 11b) carried by landing gear of an aircraft, the hydraulic circuit comprising a parking solenoid valve (13) having a service port connected to the brakes (12a, 12b) and a supply port connected, in the rest position, to a hydraulic return (102) of the aircraft, the parking solenoid valve (13) being controllable in order to connect the supply port to a pressure source (101, 2) so as to selectively transmit, to the brakes of the aircraft, a pressure that is sufficient to cause the brakes to operate, thus immobilising the aircraft, which method comprises a step of arranging, in series with the parking solenoid valve (13), a protective solenoid valve (20) allowing, when at rest, pressure to be supplied to the brakes via the parking solenoid valve, and which protective solenoid valve can be controlled to prevent pressure from being supplied to the brakes via the parking solenoid valve; and a step of controlling the protective solenoid valve (20) at least in a situation where a failure of the parking solenoid valve can induce undesired braking.
A measuring device has a magnetic circuit with a first and second armature elements that are positioned one on either side of an axis X and are manufactured with at least one ferromagnetic material. A magnet is situated between the armature elements such that a first pole of the magnet is positioned next to the first armature element and such that a second pole of the magnet is positioned next to the second armature element. A rod is arranged to be secured to a target and inserted between the armature elements to slide along the axis X. The rod has a variable section along its length such that a magnetic flux in the magnetic circuit depends on a linear position of the rod along the axis X. At least one sensor is arranged to measure the magnetic flux, which corresponds to the linear position of the target.
G01D 5/14 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens 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 déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension
B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freinsDispositifs de signalisation
F16D 55/36 - Freins à plusieurs disques tournants disposés tous côte à côte
F16D 65/18 - Mécanismes d'actionnement pour freinsMoyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
F16D 66/00 - Dispositions pour la surveillance des conditions de fonctionnement des freins, p. ex. de l'usure ou de la température
49.
MAGNETIC BRAKING DEVICE FOR A BRAKED WHEEL OF AN AIRCRAFT LANDING GEAR
The invention relates to a magnetic braking device (1) for a braked wheel of an aircraft landing gear, which braking device comprises a stator (2) and a rotor (3). The stator and the rotor comprise a first series of magnets (10.1) defining a radial main surface facing the air gap between the rotor and the stator, and a second series of magnets (10.2) defining a second axial main surface facing the air gap. The magnets are magnetised perpendicularly to the air gap. The first series of magnets and the second series of magnets are magnetised such that they are angularly offset from each other and such that a north pole in the first series is adjacent to a south pole in the second series.
H02K 49/10 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à aimant permanent
H02K 7/102 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des freins à friction
50.
ASSEMBLY CONSISTING OF A WHEEL AND OF A SHAFT CARRYING THE WHEEL, AND VEHICLE EQUIPPED WITH SUCH AN ASSEMBLY
The invention relates to an assembly consisting of a wheel and of a shaft carrying the wheel, comprising an eddy current magnetic braking device (1), the device comprising at least one stator (2) and at least one rotor (3) and at least one rotary actuator (7) connected to the rotor or to the stator, the device comprising a connection mechanism (10) connecting said actuator to the rotor or to the stator, the connection mechanism comprising: - a guide (11) mounted so as to be rotatable relative to the shaft about a first axis, - at least one connecting arm (17) connected at a first end to the guide and at a second end to the stator or to the rotor such that a rotation of the guide, via the actuator, in at least one direction of rotation, causes a translational movement of the stator or of the rotor relative to the shaft along the first axis. The invention also relates to a vehicle equipped with such an assembly.
A method for unlocking a door of an aircraft landing gear movably mounted between an open position and a closed position includes, during a first sequence of opening the door that is locked in the closed position by a first attachment housing and a second attachment housing, controlling a first unlocking actuator to deactivate the first attachment housing, waiting a first waiting time greater than a time necessary for the door to initiate a passage from the closed position to the open position, so as to enable a detector to detect the door starting to open, detecting the door starting to open by the detector and whether there is a failure of the second attachment housing, and controlling a second unlocking actuator to deactivate the second attachment housing.
The invention relates to a method for predicting an item of information on the friction of an aircraft landing runway, the method comprising, for a given time: obtaining (S100) items of runway context data, obtaining (S101) items of friction information history data for the runway comprising items of data that are all older than the given time, a prediction (S102) by a prediction model configured to receive, as input, at least the items of context data for the given time and the items of friction information history data, and to deliver an item of predicted friction information (p) for the runway for the given time.
G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
B60T 8/1764 - Régulation pendant le déplacement sur une surface comportant plusieurs coefficients de frottement, p. ex. mu différent entre les côtés gauche et droit
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/172 - Détermination des paramètres de commande utilisés pour la régulation, p. ex. par des calculs impliquant des paramètres mesurés ou détectés
53.
METHOD FOR PROTECTING A CARBON/CARBON COMPOSITE MATERIAL PART FROM OXIDATION
A method for protecting a carbon-carbon composite material part from oxidation, the method including applying an impregnation composition comprising at least one metal phosphate to at least one portion of the outer surface of the part; depositing, by a dry deposition process, a solid composition of an oxidation-resistant glass on at least one portion of the outer surface of the part, once the impregnation composition has been applied; and conducting an impregnation heat treatment in order to soften or melt the solid composition deposited by a dry deposition process, to allow the internal porosity of the part to be impregnated with the thus-softened or thus-melted composition, and to form an oxidation-resistant glass in the internal porosity of the part.
An eddy current magnetic braking device includes two outer elements surrounding a central element in relative movement with respect to the two outer elements, the central element being made of an electrically conductive material, the two outer elements having first faces facing opposite second faces of the central element and each of the two outer elements including plural magnets for emitting, via the first faces, a magnetic flow that generates in the central element eddy currents when the two outer elements are in relative movement. The plural magnets are arranged in such a way that the two outer elements attract each other. The central element has a thickness such that a skin effect is generated from each face of the central element over more than half the thickness of the central element over at least a range of possible relative speeds of the central element relative to the two outer elements.
A braking device includes one or more stationary elements and one movable element that is movable with respect to the one or more stationary elements, the moveable element being made of an electrically conductive material, one or the one or more stationary elements including magnets capable of generating eddy currents in the movable element, when the one or more stationary elements and the movable element are in relative movement. The magnets include first magnets and second magnets disposed alternating, the first magnets having a first magnetization vector and each of the second magnets having a second magnetization vector, and the magnets have widths such that the first magnets are spaced apart in pairs by a first distance that is less than a second distance separating the second magnets in pairs, and the length of the second magnets being around 70% of the length of the first magnets.
The invention relates to a braked wheel (1) of a vehicle, which wheel is rotatably mounted on an axle (E) so as to rotate about an axis (X) and comprises a magnetic braking device (10, 10') comprising a rotor (20, 20'), a stator (30, 30') and an actuator (40, 40') arranged to move the rotor and the stator relative to one another along the axis of rotation of the wheel between a free rotation position and a braking position, wherein one of the rotor and the stator comprises a first magnetic ring (31, 31' 32', 33') inside which a second magnetic ring (32, 32', 33', 34') extends so as to form an annular groove (36, 36.1', 36.2', 36.3') and the other of the rotor and the stator comprises a sleeve (22, 21', 22', 23') that is arranged so as to fit into the annular groove in order to produce, between the rotor and the stator, a radial magnetic flux capable of generating eddy currents when the wheel rotates.
F16D 63/00 - Freins non prévus ailleursFreins combinant plusieurs des types mentionnés dans les groupes
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/32 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p. ex. accélération ou décélération
57.
EDDY CURRENT MAGNETIC BRAKING DEVICE, BRAKED VEHICLE WHEEL AND AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to a magnetic braking device for a vehicle wheel, the device comprising at least one stator element (2) arranged so as to be rotatably connected to a portion of the vehicle supporting the wheel, a rotor element (3) arranged so as to be rotationally connected to the wheel, magnets for producing, between these elements, a magnetic flux capable of generating eddy currents in one of the elements when the wheel rotates and a braking control unit (11) that receives, as input, a braking command to apply a braking force according to the braking command. The magnets comprise at least one electromagnet (9) and the device comprises at least one anti-locking control unit (16) that receives, as input, a vehicle speed signal and a wheel rotational speed signal and provides, as output, a control signal of the electromagnet according to a comparison of speeds from the signals received as input. The invention also relates to an aircraft wheel and a landing gear comprising such a device.
The invention relates to a method for recycling an effluent gas (50) resulting from chemical vapour deposition or infiltration of pyrocarbon and comprising dihydrogen, C1 to C4 light unsaturated hydrocarbons and C5+ heavy hydrocarbons, the method comprising the following steps: a) removing (60) the heavy hydrocarbons (501) from the effluent gas; b) catalytically hydrogenating (80) the light unsaturated hydrocarbons so as to remove them by transforming them into C1 to C4 light saturated hydrocarbons, this catalytic hydrogenation step being carried out on the effluent gas obtained after carrying out step a) and consuming some of the dihydrogen present in the effluent gas; and c) adding the effluent gas (402) obtained after carrying out step b) to a reaction chamber (30) and forming pyrocarbon by chemical vapour deposition or infiltration using the C1 to C4 light saturated hydrocarbons present in the effluent gas thus added.
Landing gear (101) comprising at least: - a shaft (102), - at least one wheel (103) rotatably mounted on the shaft, - at least one braking device (1) for braking the wheel, - at least one measurement device (10) arranged to measure a rotational speed of the wheel, the landing gear being configured in that the measurement device is arranged between the friction member and the shaft, the measurement device comprising at least one target (11) coupled in rotation to the wheel and at least one support (12) coupled to the shaft, the support bearing at least one sensing component (13) arranged facing a rotary trajectory of the target and able to cooperate with the target to generate at least one signal representative of the rotational speed of the wheel. Corresponding aircraft.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/171 - Détection des paramètres utilisés pour la régulationMesure des valeurs utilisées pour la régulation
B60T 8/32 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p. ex. accélération ou décélération
The invention relates to a hydraulic actuation system (100) comprising at least one tank (104) connected, via a flow restriction, to a pump (103) driven by a motor (101), a hydraulic actuator (112) associated with a control valve (113), a temperature sensor (108) for the hydraulic fluid in the tank (104) and an electronic control unit (102) arranged to implement a heating phase when the temperature of the hydraulic fluid in the tank (104) reaches a first predetermined minimum temperature threshold by activating the motor (101) driving the pump (103) when the control valve (113) is in a state of not supplying the actuator in order to circulate the hydraulic fluid through the restriction. The invention also relates to an aircraft comprising such a system.
The invention relates to a braked vehicle wheel (1) rotatably mounted on an axle (E) about an axis (X), comprising: a first eddy current braking device (10), comprising a first actuator (31) having a first piston (31.1) received in a first cavity (30.1) in order to define therein a first chamber (41.1) and a second chamber (41.2); and a second friction braking device (20), comprising a second actuator (32) having a second piston (32.1) received in a second cavity (30.2) in order to define therein a third chamber (42.1) and a fourth chamber (42.2), characterised in that the first actuator comprises a first main port (51.1) opening into the first chamber, a first connection port (51.2) positioned to open into the first chamber or into the second chamber according to the position of the first piston, and a second connection port (51.3) positioned to open into the second chamber; and in that the second actuator comprises a second main port (52.1) opening into the third chamber, the second main port being connected to the first connection port and to the second connection port of the first actuator by a bypass duct (63).
B60T 1/10 - Aménagements des éléments de freinage, c.-à-d. des parties de ceux-ci dans lesquelles se produit l'effet de freinage en agissant par retardement des roues par utilisation du mouvement des roues pour accumuler l'énergie, p. ex. en entraînant des compresseurs d'air
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/32 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p. ex. accélération ou décélération
F16D 61/00 - Freins permettant de restituer pour usage l'énergie absorbée
62.
WHEEL WITH COMBINED MAGNETIC/FRICTION BRAKING FOR A VEHICLE, AND AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to a braked vehicle wheel (103) comprising at least one hub portion (104.1) and one rim portion (105.1) that is coaxial with the hub portion (104.1), thereby defining an annular space (108), which rim portion is connected to the hub portion (104.1) by a disc portion (106.1), the wheel comprising: - a first friction braking device (50) comprising at least one rotor disc and one stator disc housed in the annular space and at least one first actuator (56) rigidly attached to an actuator-bearing ring (54) that is fixed with respect to a shaft (102) for rotating the wheel; - a second magnetic braking device (1) comprising a rotor (3), a stator (2), at least one second actuator (7) for axially moving the stator (2) and the rotor (3) relative to one another between a braking position and a freely rotatable position, and a plurality of magnets (11, 12, 13, 14) arranged to emit, between the rotor (3) and the stator (2), a magnetic flux capable of producing a braking force when the stator (2) is in the braking position; characterised in that the second actuator (7) is mounted on the actuator-bearing ring (54) in opposition to the first actuator (56). The invention also relates to a landing gear and to an aircraft comprising such a wheel.
B60T 1/10 - Aménagements des éléments de freinage, c.-à-d. des parties de ceux-ci dans lesquelles se produit l'effet de freinage en agissant par retardement des roues par utilisation du mouvement des roues pour accumuler l'énergie, p. ex. en entraînant des compresseurs d'air
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
63.
AIRCRAFT LANDING GEAR COMPRISING A WHEEL WITH INTEGRATED MAGNETIC BRAKING DEVICE
The invention relates to a landing gear for an aircraft comprising a leg having an end carrying a shaft on which a wheel (103) is mounted. The wheel comprises a hub (104.1) and a rim (105.1) that is coaxial with the hub and connected to the hub via a disc portion (106.1). The wheel comprises an eddy-current magnetic braking device (1) comprising a rotor (3) that is rotatably connected to the wheel and a stator (2) that is rotatably connected to the leg, that is rotatable with respect to the rim (105.1) and to the rotor (3), and that carries a plurality of magnets (11, 12, 13, 14) capable of emitting a magnetic flux in the rotor. The rotor is made of an electrically conductive material so as to be able to give rise to eddy currents and the rotor is formed of one piece with the rim (105.1).
WHEEL LANDING GEAR PROVIDED WITH AN EDDY-CURRENT MAGNETIC BRAKING DEVICE USING RADIALLY MOVABLE MAGNETS, AND AIRCRAFT PROVIDED WITH SUCH A LANDING GEAR
The invention relates to a landing gear comprising a wheel provided with an eddy-current magnetic braking device (1) that comprises at least one stator (2) and one rotor (3), and magnets (4) rigidly attached to one of the stator or the rotor in order to produce therebetween an axial magnetic flux capable of generating eddy currents in the other of the stator or the rotor as the wheel rotates. One of the rotor (3) and of the stator (2) is a disc and the other of the rotor (3) and of the stator (2) is a ring divided into at least two ring sectors (2A, 2B, 2C, 2D) which are radially movable between a first position in which each ring sector (2A, 2B, 2C, 2D) has at least one face (2.1, 2.2) facing a face (3.1, 3.2) of the disc in order to establish the axial magnetic flux and a second position in which the at least one face (2.1, 2.2) of the ring sector (2A, 2B, 2C, 2D) is radially offset with respect to the face (3.1, 3.2) of the disc in order to interrupt the axial magnetic flux. The invention also relates to an aircraft comprising such a landing gear.
The invention relates to an assembly comprising at least a first part (1) and a second part (11) which are concentric, extending about a common axis (X). At least the first part (1) comprises first radial bores (1.1) having two open ends, and the second part (11) comprises second radial bores (11.1), each second radial bore (11.1) forming an extension of one of the first radial bores (1.1) and having one end opening opposite one of the open ends of the first radial bore (1.1) in order to form a pair of aligned bores. One key (2) extends in each pair of aligned bores in order to connect the concentric parts (1, 11) with one another so as to rotate about and translate along the common axis.
A method for manufacturing a diaphragm holder for a shock absorber of the oleo-pneumatic type, in particular for an aircraft landing gear. The diaphragm holder includes a first end with a dome, and a tubular portion extending from the dome to a second end. The method includes a step of overmolding a first material onto an insert. The insert can be a second material with a value of compression breaking stress divided by density that is higher than the first material or alternatively, of a material identical to the first material. A diaphragm carrier which can be manufactured by this method.
F16F 15/023 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens fluides
67.
BRAKED VEHICLE WHEEL ACTUATED BY MEANS OF DEFORMABLE PARALLELOGRAMS, AIRCRAFT LANDING GEAR AND AIRCRAFT PROVIDED WITH SUCH A WHEEL
The invention relates to an eddy-current-based magnetic braking device comprising two external elements (2) flanking a central element (3) aligned with the same axis as the external elements, which central element rotates about the axis with respect to the external elements (2), the external elements (2) each carrying a plurality of magnets (11, 12, 13, 14) able to emit a magnetic flux which gives rise to eddy currents in the central element (3) when the elements (2, 3) are moving relative to one another. The magnets are arranged so as to cause the external elements to be magnetically attracted to one another. Friction-based braking surfaces are joined so as to rotate as one with the external elements and with the central element, respectively. The external elements are movable with respect to the axis between a position close to the central element, in which position the first braking surfaces are held applied against the second braking surfaces by magnetic attraction and a position spaced apart from the central element, in which position the first braking surfaces are spaced apart from the second braking surfaces. The invention also relates to an aircraft wheel and to a landing gear comprising such a device.
F16D 55/224 - Freins à surfaces de freinage substantiellement radiales pressées l'une contre l'autre dans une direction axiale, p. ex. freins à disques avec disques ou patins déplaçables selon l'axe pressés contre des organes en rotation situés dans l'axe par serrage entre des organes mobiles de freinage, p. ex. des disques ou des patins de freins mobiles avec un organe d'actionnement commun pour les organes de freinage
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
F16D 63/00 - Freins non prévus ailleursFreins combinant plusieurs des types mentionnés dans les groupes
F16D 65/18 - Mécanismes d'actionnement pour freinsMoyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
F16D 121/20 - Électrique ou magnétique utilisant des électroaimants
68.
EDDY CURRENT MAGNETIC BRAKING DEVICE, BRAKED VEHICLE WHEEL AND AIRCRAFT LANDING GEAR AND AIRCRAFT WHICH ARE EQUIPPED WITH SUCH A WHEEL
An eddy current magnetic braking device (1) for a wheel, comprising a stator (2) and a rotor (3), wherein the rotor comprises at least two sub-assemblies (13) and the stator comprises at least two sub-assemblies (10), one proportion of the sub-assemblies each comprising at least one magnet (4) for producing, between the rotor and the stator, a magnetic flux in the other proportion of the sub-assemblies when the wheel rotates, the rotor or the stator being mounted so as to be movable between a first position in which each sub-assembly of the rotor has at least one face facing a face of one of the sub-assemblies of the stator and a second position in which said faces are offset from one another, the device comprising at least one actuator (6) connected to the rotor or to the stator in order to move the rotor or the stator between these two positions. The invention also relates to an aircraft wheel, landing gear and aircraft comprising such a device.
H02K 49/04 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
The invention relates to a wheel including an eddy current magnetic braking device, the device comprising at least one stator and at least one rotor, and magnets secured to one of the latter in order to produce therebetween a magnetic flux capable of generating eddy currents in the other when the wheel rotates. According to the invention, the rotor is rotatably connected to the wheel via a transmission mechanism of the wheel. The invention also relates to a landing gear and an aircraft including such a wheel.
An industrial assembly (80) with a gas turbine (90) comprises a pollutant-gas treatment device (70) capable of treating the gas flow displaced by the gas turbine (90). This treatment device (70) comprises a solid adsorbent (71), and the industrial assembly (80) comprises a heat recuperator (40) able to recover the heat emitted by the turbine (90) and then transfer this heat to a fluid supply device (50) that heats a fluid (51), the treatment device (70) being able to adsorb the pollutant gas from the gas flow into the adsorbent (71), and then to desorb the adsorbent (71) by heating, by the fluid (51), to a heating temperature (Tc) at least equal to the desorption temperature (Td) of said adsorbent (71), and to send the pollutant gas supplied by this desorption into a storage tank (60).
B01D 53/04 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par adsorption, p. ex. chromatographie préparatoire en phase gazeuse avec adsorbants fixes
The invention relates to a gas turbine (90) test bench (80) comprising a building (88) which comprises an air inlet stack (81) at its first end and a gas exhaust stack (83) at its second end, a test hall (82) containing the gas turbine (90) intended to be tested, and at least one pollutant gas treatment device (70) capable of treating the gas flow which is displaced by the gas turbine (90) during operation and which flows to the exhaust stack (83). The pollutant gas treatment device (70) comprises a solid adsorbent (71) which consists of at least one modular block (72) having a plurality of channels (73), the walls of which are adsorbent and in which the displaced gas flow is able to flow.
B01D 53/04 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par adsorption, p. ex. chromatographie préparatoire en phase gazeuse avec adsorbants fixes
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
72.
EDDY-CURRENT-BASED MAGNETIC BRAKING DEVICE, VEHICLE BRAKED WHEEL AND AIRCRAFT LANDING GEAR EQUIPPED WITH SUCH A WHEEL
An eddy-current-based magnetic braking device includes two external elements flanking a central element that is aligned with a same axis as the external elements and that rotates about said axis with respect to the external elements, the external elements each bearing magnets that emit a magnetic flux that engenders in the central element eddy currents. The magnets are placed so as to generate a magnetic attraction between the external elements. Friction-based braking surfaces are joined so as to rotate as one with the external elements and with the central element, respectively. The external elements are moveable with respect to the axis between a proximate position of the central element, in which position the first braking surfaces are held applied against the second braking surfaces via the magnetic attraction, and a separated position of the central element, in which position the first braking surfaces are separated from the second braking surfaces.
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
F16D 55/38 - Freins à plusieurs disques tournants disposés tous côte à côte actionnés mécaniquement
F16D 65/18 - Mécanismes d'actionnement pour freinsMoyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
F16D 121/20 - Électrique ou magnétique utilisant des électroaimants
H02K 49/04 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à induction asynchrone du type à courants de Foucault ou à hystérésis
73.
DEVICE FOR AXIALLY LOCKING A FIRST TUBULAR ELEMENT FITTING TIGHTLY INTO A SECOND TUBULAR ELEMENT
The invention relates to a device (100) for axially locking a first tubular element (20) fitting tightly into a second tubular element (E), the locking device comprising a tubular body (101) including an outer annular groove (101.2) in which a ring (102) is slidably mounted along a longitudinal axis (Y101) of the body between a locked position and a released position, the ring comprising a wheel (102.1) having a front face from which elastically deformable outer hooking claws (102.2) extend projecting axially between a state in which they project radially from the body and a state in which they are retracted into the body, and the groove in the body comprising a bottom (101.7) shaped to keep the claws in their projecting state when the ring is in the locked position, and to allow the claws to transition from the projecting state to the retracted state when the ring is in the released position.
B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
F16D 1/033 - Accouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour liaison bout à bout de deux arbres ou de deux pièces analogues par serrage de deux surfaces perpendiculaires à l'axe de rotation, p. ex. avec des brides boulonnées
F16B 21/18 - Dispositifs sans filetage pour empêcher le mouvement relatif selon l'axe d'une broche, d'un ergot, d'un arbre ou d'une pièce analogue par rapport à l'organe qui l'entoureFixations à ergots et douilles largables sans filetage à parties séparées par gorges ou encoches pratiquées dans l'axe ou l'arbre et avec bague annulaire formant ressort insérée dans la gorge (circlip) ou autre dispositif élastique de fixation du même genreDispositifs sans filetage pour empêcher le mouvement relatif selon l'axe d'une broche, d'un ergot, d'un arbre ou d'une pièce analogue par rapport à l'organe qui l'entoureFixations à ergots et douilles largables sans filetage à parties séparées par gorges ou encoches pratiquées dans l'axe ou l'arbre Détails
A shock absorber for a vehicle includes a cylinder and a piston, a portion of which slidably disposed with the cylinder. A magnetic target is fixedly positioned relative to the piston, and a sensor is fixedly positioned relative to the cylinder. The sensor generates a signal according to the position of the magnet target relative to the sensor.
B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
75.
DEVICE AND METHOD FOR MONITORING A DISK BRAKE SYSTEM OF AN AIRCRAFT LANDING GEAR
An assembly of a disk brake system (2) of an aircraft landing gear (I) and a monitoring device (3), the disk brake system (2) comprising at least one stator disk (21) and at least one rotor disk (22) configured to be pressed against said stator disk (21), the monitoring device (3) comprising a tape (30), the tape (30) comprising at least one visual information item associated with a predetermined circumferential range of the stator disk (21), the tape (30) being positioned in contact with the circumference of the stator disk (21), a first gripping member (31) attached to a first end of the tape (30) and a second gripping member (32) attached to a second end of the tape (30) so as to make it possible to stretch the tape around the circumference of the stator disk (21) in order to accurately determine the circumference of the stator disk (21).
A shock absorber for a vehicle includes a cylinder and a piston, a portion of which slidably disposed with the cylinder. A magnetic target is fixedly positioned relative to the piston, and a sensor is fixedly positioned relative to the cylinder. The sensor generates a signal according to the position of the magnet target relative to the sensor.
An aircraft landing gear includes a strut mounted to an aircraft structure and moveable between extended and retracted positions. A bracing member includes a first bracing connecting rod hinged to the aircraft structure and a second bracing connecting rod hinged to the first bracing connecting rod and to the strut. A stabilizing member includes a first stabilizing connecting rod and a second stabilizing connecting rod hinged together. The second connecting stabilizing rod is hinged to the first bracing connecting rod. At least one spring is arranged to be resiliently subjected to a bending force when the hinges of the first and second stabilizing connecting rods move from their aligned position.
An aircraft landing gear includes a stationary element and one or more movable elements which can move relative to the stationary element between a first position and a second position, and one or more shape sensors, connected to an electronic processor arranged to deduce the position of the movable element of the shape of the shape sensor. The shape sensor includes a first section rigidly connected to the stationary element and a second section rigidly connected to the movable element so that the first section and the second section are immobile with respect to the stationary element and the movable element respectively, and are movable relative to one another.
B64C 25/10 - Atterrisseurs non fixes, p. ex. largables escamotables, repliables ou ayant un mouvement apparenté
G01B 11/26 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer des angles ou des cônesDispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour tester l'alignement des axes
79.
SYSTEM OF VARIABLE-HEIGHT WEDGES FOR OLEO-PNEUMATIC SHOCK ABSORBER
The invention relates to a maintenance system (1) of an oleo-pneumatic shock absorber (2), comprising wedges arranged to be assembled so as to form a plurality of wedge devices of different heights and each associated with a separate temperature range, each wedge device being arranged to be installed on the shock absorber by being positioned between one end (8) of the cylinder (4) through which the rod (5) is inserted and one end (9) of the rod located outside the cylinder, such that, when the shock absorber is compressed so that the end of the cylinder or the end of the rod abuts against the wedge device, an oil volume in the chamber (10), when the latter is maximally filled, is equal to an optimised volume for an oil temperature comprised in the temperature range associated with the wedge device.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F16F 9/44 - Dispositifs inhérents à l'amortisseur ou portés par lui pour le réglage manuel ou un réglage non-automatiqueRessorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement Parties constitutives de tels dispositifs combinés avec la correction de température
80.
SYSTEM FOR LOCKING A SLIDING MEMBER COMPRISING AN INTEGRATED MONITORING MEMBER, AND CORRESPONDING DRIVE MECHANISM, WHEEL AND AIRCRAFT
The invention relates to a system for locking a member comprising: - a housing (9) having a chamber (12) which is intended to slidably receive the member; - balls (20) that are arranged to at least partially project out into the chamber; - a lock (22) that is mounted in the housing so as to be movable between a locked position in which, when in operation, the lock presses the balls against the member in order to hold the member in position in the housing and an unlocked position in which, when in operation, the member can slide inside the housing, the lock being arranged in the housing in such a way that, in the locked position, the lock bears against at least one wall (15) of the chamber and that, in the unlocked position, the lock is away from the wall, the system further comprising at least one element (36) for detecting this temporary contact. The invention further relates to a corresponding drive mechanism and an aircraft wheel.
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
E05B 17/20 - Moyens indépendants du mécanisme de verrouillage pour empêcher une ouverture non autorisée, p. ex. pour bloquer le pêne en position de fermeture
E05B 47/00 - Fonctionnement ou commande des serrures ou autres dispositifs d'immobilisation par des moyens électriques ou magnétiques
E05B 47/06 - Commande des pênes à fonctionnement mécanique par des cliquets à déclenchement électro-magnétique
B60R 25/00 - Équipements ou systèmes pour empêcher ou signaler l’usage non autorisé ou le vol de véhicules
81.
SELECTIVE BRAKING ON WHEELS NOT PROVIDED WITH A DRIVE ACTUATOR
The invention relates to a method for braking an aircraft (11) on the ground, which aircraft comprises at least a first wheel (13a) provided with a first brake (14a) and with a drive actuator (15), and at least a second wheel (13b) provided with a second brake (14b) but not provided with a drive actuator, the method comprising the steps of: • - selecting, in order to brake the aircraft on the ground, a first braking mode or a second braking mode having a lower braking capacity; • - braking the aircraft by producing a first braking setpoint (Cl) for the first brake (14a) and a second braking setpoint (C2) for the second brake (14b) such that, if the first mode is chosen, a ratio of the first braking setpoint to the second braking setpoint is equal to a first value and, if the second mode is chosen, the ratio is equal to a second value that is lower than the first value.
The invention relates to an aircraft wheel (1) braking device (10), comprising: - a torque tube (13, 13') extending along a longitudinal axis; - a stack of brake discs (11) including a last stator disc; - at least one actuator (18) comprising a piston translatably mounted between a first end position in which the piston is spaced apart from the stack of discs and a second end position, in order to exert a pressing force on the first stator disc; and - at least one stud (14) arranged between a second end of the torque tube and the last stator disc in order to take up and transfer the pressing force to the torque tube. The last stator disc and the torque tube are shaped so as to define therebetween a minimum clearance which is less than the distance separating the piston from its second end position when the piston exerts the pressing force.
F16D 55/40 - Freins à plusieurs disques tournants disposés tous côte à côte actionnés par un dispositif à pression de fluide disposé dans, ou sur le frein
83.
WHEEL WITH EDDY CURRENT MAGNETIC BRAKING DEVICE AND AIRCRAFT LANDING GEAR PROVIDED WITH SUCH A WHEEL
A wheel including a rim that rotates on a shaft defining a primary rotational axis and a magnetic braking device. The magnetic braking device includes an actuator which includes a first transmission assembly and one second transmission assembly each includes a pinion mounted on the support to pivot about a secondary rotational axis parallel to the primary axis, an operating bar extending about the secondary axis, a first mechanical connecting member connecting the operating bar to the pinion of the transmission assembly and a second mechanical connecting member connecting the operating bar to one of the stators, and the mechanical connecting members are arranged. The rotation of the pinions causes a movement of the stators parallel to the secondary axis in opposite directions, for varying the air gap, one or more of the mechanical connecting members of each transmission assembly being arranged to ensure a screw-nut helical connection.
A tooling for winding a fibrous fabric on a support, allowing gradual modification of the shape of the support as winding progresses, and includes compaction devices to reduce wrinkling of the fabric obtained after compaction.
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
85.
METHOD FOR MONITORING AN AIRCRAFT LANDING GEAR EMPLOYING AT LEAST ONE ACCELEROMETER SUPPORTED BY A WHEEL OF THE LANDING GEAR, AND AIRCRAFT IMPLEMENTING THIS METHOD
A method for monitoring an aircraft landing gear. The method includes using information from at least one accelerometer firmly secured to a landing gear wheel mounted to rotate on a landing gear axle to estimate an angle of deflection α of the axle at least when the wheel is in contact with the ground.
An inspection tool configured to be fitted to an endoscope includes a body with an attachment portion configured to be attached to one end of the endoscope, and an opening. The tool further includes a transparent element with at least one visual reference mark having a calibrated dimension, wherein the transparent element is mounted at the opening in the body.
A61B 1/00 - Instruments pour procéder à l'examen médical de l'intérieur des cavités ou des conduits du corps par inspection visuelle ou photographique, p. ex. endoscopesDispositions pour l'éclairage dans ces instruments
An uplock for retaining a capture pin of a movable part includes a hook that is movable between a release position and a retaining position, a locking part that interacts with the hook and is movable between a locking position and an unlocking position, and a detector. The detector includes a first sensor for detecting whether the hook is in the retaining position, and a second sensor for detecting a presence of the mobile part in the immediate vicinity of the uplock in the position occupied by the mobile part when the capture pin is in the hook.
B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet
E05B 81/68 - Contrôle ou détection, p. ex. par des interrupteurs ou des détecteurs de la position du pêne, c.-à-d. l’état d´enclenchement par détection de la position du cliquet
E05B 81/70 - Contrôle ou détection, p. ex. par des interrupteurs ou des détecteurs de la position du battant
Device (10, 10') for hooking a moving element (T) with a hook (C), the device comprising a roller (11, 11') mounted on a shaft (12) such that it can move in translation between two end positions along a longitudinal axis of the shaft, and be returned to a rest position between the two end positions by elastic return means (18.1, 18.2).
A method for treating a surface of a rod of a piston, the rod being made of high mechanical strength alloy with a minimum hardness above 45 HRC, includes a grinding procedure, and a polishing procedure performed until a mean roughness Ra≤0.2 μm is obtained. This results in a surface finish allowing the dynamic sealing requirements of the piston to be maintained without requiring chrome plating.
B24B 19/00 - Machines ou dispositifs conçus spécialement pour une opération particulière de meulage non couverte par d'autres groupes principaux
F16D 65/18 - Mécanismes d'actionnement pour freinsMoyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein adaptés pour rapprocher les organes par traction
F16D 121/04 - Pression de fluide agissant sur un actionneur du type piston, p. ex. pour pression de liquide
A method for manufacturing a part includes a metal substrate at least partially covered with a protective layer, includes preparing a surface of the substrate to be covered, forming by spraying, according to an HVOF spraying method, a coating layer on the prepared surface, this coating layer being formed by spraying a powder mixture containing submicronic metal carbide grains, impregnating the coating layer with an organic impregnant together forming an impregnated layer, finishing by polishing at least one surface of the impregnated layer in order to form a protective layer having a polished surface having a roughness Ra of less than 0.2 μm or of less than 0.1 μm depending on the applications.
The invention relates to a landing gear (1) comprising: a leg (2) having a hinge for pivoting between a retracted position and a deployed position; a main brace (5) having a state in which the leg (2) is stabilised in the deployed position, in which position the main brace (5) defines a main force-take-up path; a mechanism for manoeuvring the leg (2) at least from its deployed position to its retracted position; and a mechanism for stabilising the leg (2) in the retracted position. The manoeuvring mechanism comprises a rotary actuator (15) which is positioned outside the main force path when the leg (2) is in the deployed position and which actuates a single crank (16), and a connecting rod (17) having a first end hinged to the leg (2) and a second end hinged to the crank (16) in order to form with the crank the mechanism for stabilising the leg (2) in the retracted position. The invention also relates to an aircraft provided with such a landing gear.
A thrust reverser device for an aircraft turbojet engine nacelle an electro-hydrostatic actuation system that includes a motor pump and a first actuation assembly. The first actuation assembly includes a series of at least two actuators configured to be attached to a movable cover of the thrust reverser and to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle. The first electro-hydraulic actuation system further includes a volumetric flow divider with an inlet connected to the motor pump and at least two outlets, wherein each outlet is connected to an actuator. The volumetric flow divider is configured to receive a fluid and to supply the fluid to the actuators with an equal flow rate.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
F15B 7/00 - Systèmes de manœuvre utilisant la pression d'un fluide dans lesquels le mouvement produit est lié de façon définie au débit d'une pompe volumétriqueTélémoteurs
F15B 20/00 - Dispositions propres à la sécurité pour systèmes de manœuvre utilisant les fluidesUtilisation des dispositifs de sécurité dans les systèmes de manœuvre utilisant des fluidesMesures d'urgence pour les systèmes de manœuvre utilisant des fluides
93.
AIRCRAFT LANDING GEAR PROVIDED WITH AT LEAST ONE MOTORIZED WHEEL
An aircraft has an upper portion and a lower portion provided with a first and second axle. The first axle is provided with a braked wheel and the second axle is provided with a motorized wheel. A landing gear of the aircraft includes a main arm pivoting with respect to the strut on which the first axle is fixed. The second axle is fixed on the strut, and a main actuator moves the first axle between a remote position and a close position with respect to the upper portion. In the close position, the braked and motorized wheels are simultaneously in contact against a running plane, and in the remote position, the braked wheels are in contact against the running plane while the motorized wheel is at a distance from the running plane.
Embodiments of the invention relate to a landing gear wherein it includes at least one static sealing point, the static sealing point comprising a gasket made of elastically deformable material held between a portion of a first part of the landing gear and a portion of a second part of the landing gear, the first and second parts of the landing gear comprising a steel substrate coated with a zinc and nickel alloy coating, including in mass percentage of the alloy between 12% and 18% and nickel, at most 0.5% of elements other than nickel and zinc, the balance being zinc, and the roughness Ra of the surface of the portions of the first and second parts of the landing gear being less than or equal to 1.6 μm.
The invention relates to a method for taxiing an aircraft while anticipating an inability of a drive member equipping at least one wheel (RA) borne by a landing gear (AA) of the aircraft (A) to move said aircraft on the ground, the method comprising the following steps: a) determining at least one of the following values: a minimum traction effort (101) required by the drive member to move the aircraft, a maximum traction effort (201) that is transmissible to the ground via the wheel through grip, and heating (301) of the drive member; b) comparing each value with a predetermined threshold (102, 202, 203); c) from the comparison, deducing a capacity of the drive member to move the aircraft.
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
An uplock for the selective retention of a capture pin of a movable element includes a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position for retaining the capture pin. The locking member moves between a locked position, and an unlocked position. The detector detects whether the hook is in the retaining position and the capture pin is in the hook. The detector includes a sensor movable relative to a target. The target or the sensor is carried by the locking member and the other by an indicator lever which is movable between a first position indicating absence of the capture pin in the hook and a second position indicating presence. The target and the sensor are only in the proximate position if the locking member is in the locked position and the indicator lever is in the second position.
The invention relates to a method for post-anodisation sealing of aluminium or aluminium alloy without using chromium. The invention also relates to a method for treating the surface of a part made of aluminium or aluminium alloy intended for use in the aviation sector, including at least the following steps: i) subjecting the part to an anodisation step; ii) treating the anodised part by a post-anodisation sealing method according to the invention; and optionally iii) applying one or more coat(s) of paint. The invention also relates to a part made of aluminium or aluminium alloy treated by a post-anodisation sealing method according to the invention, optionally including one or more coat(s) of paint.
An uplock for selectively retaining a capture pin of a movable element including a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position. The locking member is movable between a locked position that immobilizes the hook and an unlocked position in which the hook is free. The detector detects whether the hook is in the retaining position and the capture pin is present in the hook. The detector includes a sensor associated with a single target which is movable between two positions The sensor emits a signal which is modified when the target passes from one of the positions to the other. The target is independently in kinematic interaction with the hook and the capture pin.
Said method for determining aircraft landing runway conditions comprises the steps of: acquiring a set of data groups of different types (D1, D2) for evaluating and monitoring runway degradation conditions; deriving weighting coefficients (Ki) from each data group; filtering the data; determining, for each data group, a partial runway condition; modifying the weighting coefficients of each data group; and combining the partial runway conditions to derive a runway condition coefficient (RWYCC) associated with a confidence index (C1) derived from the modified weighting coefficients.
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
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
C21D 9/50 - Traitement thermique, p. ex. recuit, durcissement, trempe ou revenu, adapté à des objets particuliersFours à cet effet pour joints de soudure
C22C 38/02 - Alliages ferreux, p. ex. aciers alliés contenant du silicium
C22C 38/04 - Alliages ferreux, p. ex. aciers alliés contenant du manganèse
C22C 38/44 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du molybdène ou du tungstène
C22C 38/46 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du vanadium
