Einhakenvorrichtung, mit Befestigung der Fahrwerkeinfahrverriegelung eines Flugzeuges.

ECHTZEITKONTROLLVERFAHREN ZUR ANWENDUNG BEIM VERNADELN VON FASERGEBILDEN UND ENTSPRECHENDE VERNADELVORRICHTUNG

Architektur eines hydraulischen Flugzeugbremssystems

Verfahren zum Schutz eines Bremssystems eines Fahrzeuges mit elektrischen Bremsen

Hydraulische Ventilanordnung in Form einer Patrone

PROCESS FOR MANAGING THE ATTITUDE CONTROL OF AIRCRAFT LANDING GEAR

L'invention concerne un procédé de gestion d'une commande d'orientation d'une partie orientable d'un atterrisseur d'aéronef, comportant la mise en uvre d'un asservissement pour asservir un actionneur électromécanique d'orientation à une consigne de position angulaire, dans lequel, selon l'invention, l'asservissement met en uvre une loi de commande de type H.infin., les informations de position et de vitesse étant remontées vers un calculateur mettant en uvre l'asservissement au moyen d'un bus de terrain de type déterministe.

PROCESS FOR SUPPLYING POWER TO ACTUATORS ASSOCIATED WITH AIRCRAFT LANDING GEAR

Dans le domaine, il est connu qu'un aéronef soit muni d'actionneurs associés aux trains d'atterrissage, l'aéronef comportant : - une génération d'énergie principale qui fonctionne indépendamment d'une rotation des roues; et - une génération d'énergie locale comprenant au moins un générateur local entraîné par la rotation d'une roue. La génération d'énergie locale est utilisée en cas de secours, lorsque la génération d'énergie principale vient à défaillir. Cette configuration a le désavantage d'utiliser des câbles de haute tension pour acheminer l'énergie principale vers les atterrisseurs. Le procédé selon l'invention inverse l'ordre d'approvisionnement en énergie de sorte que: - on alimente les actionneurs par la génération d'énergie locale; et - lorsque la fourniture d'énergie par la génération d'énergie locale est insuffisante, on assure en complément ou totalement la fourniture d'énergie audits actionneurs au moyen de la génération d'énergie principale. On peut ainsi utiliser des câbles ...

DEVICE FOR CONNECTING AN AIRCRAFT WHEEL PNEUMATIC TIRE TO THE AIRCRAFT'S CENTRAL PNEUMATIC SYSTEM

L'invention concerne un dispositif pour connecter sélectivement à une centrale pneumatique d'un aéronef un pneumatique d'une roue montée tournante sur un essieu creux de l'aéronef, le dispositif comprenant un stator et un rotor qui est monté tournant sur le stator et qui comporte des moyens de son entraînement en rotation par la roue. Selon l'invention, le stator est en forme de cloche qui est prévue pour être reçue à ajustement dans l'essieu et qui comporte une paroi de fond qui porte un premier port pneumatique pour sa connexion à la centrale pneumatique par un tuyau cheminant dans l'essieu, le rotor s'étendant substantiellement à l'intérieur du stator.

ACTUATOR HAVING MAIN ROD AND AUXILIARY ROD

L'invention concerne un Actionneur télescopique comportant un corps dans lequel une tige principale est montée pour coulisser télescopiquement selon un axe de coulissement entre une position rentrée et une position sortie, l'actionneur télescopique comportant une tige auxiliaire montée pour coulisser télescopiquement dans la tige principale selon le dit axe de coulissement entre une position rentrée et une position sortie, l'actionneur comportant des moyens commandés de retenue de la tige auxiliaire en position rentrée dans la tige principale, l'actionneur comportant en outre des moyens de freinage d'un coulissement de la tige auxiliaire dans la tige principale dans le sens d'une extension. Selon l'invention, la tige auxiliaire comporte un filetage sur une surface externe, la tige principale portant à son extrémité un palier tournant qui centre la tige auxiliaire dans la tige principale et qui coopère par une liaison hélicoïdale réversible avec le filetage de la tige auxiliaire de sorte ...

FABRICATING THREE-DIMENSIONAL ANNULAR FIBER STRUCTURES

A first fiber sheet made up of substantially unidirectional elements, is brought (by device 300) and laid (by shuttle 322) in alternation in one direction and in the opposite direction between coaxial outer (100) and inner (200) circular rings with the sheets being held by pegs (102, 202) at said rings; and a second fiber sheet made up of substantially unidirectional elements is deposited (by device 400) in a circumferential direction between said outer and inner rings, the transverse and circumferential annular sheets are bonded together by a bonding device (500) and are driven in rotation about the axis of the outer and inner rings so as to perform a plurality of complete revolutions in order to obtain a thick annular fiber structure having layers made up by the transverse sheet alternating with and bonded to layers made up by the circumferential sheet.

PROCESS FOR SURFACE TREATMENT OF A HIGH-STRENGTH STEEL MECHANICAL PART

L'invention concerne un procédé de traitement de surface d'une pièce mécanique en acier à haute résistance, visant à conférer à ladite pièce des propriétés en frottement et en lubrification nécessaires à son utilisation. Conformément à l'invention, le procédé comporte les étapes successives suivantes : a) on soumet la pièce (P) à une étape de finition primaire organisée pour abaisser sa rugosité en surface (Ra) à un premier seuil prédéterminé (S1) ; b) on soumet ensuite la pièce (P) à un nettoyage de surface au moyen d'une solution de dégraissage ; c) on soumet la pièce (P) ainsi nettoyée à une étape de tribofinition organisée pour d'une part abaisser encore sa rugosité en surface (Ra) à un deuxième seuil prédéterminé (S2) qui est inférieur au premier seuil prédéterminé (S1), et d'autre part augmenter sa mouillabilité aux fluides hydrauliques ; et d) on soumet la pièce (P) à une projection, à haute vitesse et à température ambiante, de poudre de bisulfure de tungstène (WS2)se présentant ...

TELESCOPIC ACTUATOR WITH MAIN ROD AND AUXILIARY ROD

La présente invention a trait à actionneur télescopique comportant un corps 1 dans lequel coulisse une tige principale selon un axe de coulissement entre une position de rentrée et une position de sortie, l'actionneur comportant en outre une tige auxiliaire coulissant dans la tige principale entre une position de rentrée et une position de sortie, et un palier tournant porté par la tige principale ou la tige auxiliaire et coopérant respectivement avec la tige auxiliaire ou principale selon une liaison hélicoïdale réversible. Selon l'invention l'actionneur comprend des moyens de retenue du coulissement de la tige auxiliaire comportant un organe de blocage agencé pour agir directement sur le palier tournant de sorte à commander un blocage ou une libération de la rotation du palier tournant, le blocage en rotation du palier tournant entraînant une immobilisation de la tige auxiliaire dans la tige principale.

MAKING DIMENSIONAL FIBROUS ANNULAR STRUCTURES

MANUFACTORING PROCESS OF HELICOID TWO-DIMENSIONAL FIBROUS TABLECLOTH

STRUCTURE OF HYDRAULIC BRAKING FOR AIRCRAFT WITH BRAKES HAS DEMI-CAVITES

Architecture de freinage hydraulique pour aéronef comportant une pluralité de roues équipées de freins (102; 202) comportant chacun deux demi-cavités (102a, 102b; 202a, 202b), l'architecture comportant : - un premier circuit de freinage (N1) comportant des servovalves (103;203) alimentant une ou plusieurs demi-cavités sur des freins distincts ; - un deuxième circuit de freinage (N2) comportant des servovalves (104; 204) alimentant une ou plusieurs demi-cavités sur des freins distincts ; les deux circuits hydrauliques fonctionnant simultanément de sorte que sur chaque frein, l'une des demi-cavités est alimentée par une servovalve du premier circuit de freinage, et l'autre demi-cavité est alimentée par une servovalve du deuxième circuit de freinage, une au moins des demi-cavités étant alimentée par une servovalve qui n'alimente que cette demi-cavité.

CIRCULAR MACHINE Of TAGGING HAS FIBROUS TABLECLOTH SUPPLY BY a CONVEYOR AND a VERTICAL CHUTE

L'invention concerne une machine d'aiguilletage (10) circulaire d'une structure textile formée à partir d'une nappe fibreuse hélicoïdale, comprenant une table d'aiguilletage (200) disposée sous une table (100) d'alimentation en nappe fibreuse hélicoïdale à aiguilleter. La table d'alimentation comprend un convoyeur circulaire (102) centré sur un axe vertical (104) et sur lequel est destiné à être disposée une nappe fibreuse hélicoïdale (106) à aiguilleter, le convoyeur ayant une fente radiale (120) débouchant sous le convoyeur circulaire pour dérouler en continu la nappe fibreuse disposée sur le convoyeur, la fente débouchant sous le convoyeur vers une goulotte (400) droite qui s'étend verticalement entre le convoyeur et un plateau support de la table d'aiguilletage de façon à reprendre la nappe déroulée du convoyeur et l'amener sur la table d'aiguilletage, le plateau support ayant des moyens d'entraînement en rotation de la nappe fibreuse autour de l'axe vertical.

Hydraulic system architecture for controlling steering

The invention relates to an architecture for a hydraulic steering control system including at least one actuator; the hydraulic system comprises a directional-control valve connected to a pressure-generator device and to an associated main supply, the hydraulic system further comprising a reversible electrically-driven pump unit having two ports and being fitted with a general selector arranged, in a normal mode of operation, to put the chambers of the actuator into communication with the directional-control valve, and in an alternate mode of operation to put the chambers of the actuator into communication with the ports of the pump unit. A compensation device makes it possible in the alternate mode to compensate for any flow differential between the flow drawn in by the pump unit from one of the chambers of the actuator and the flow delivered by the pump unit into the other chamber of the actuator.

PROCESS FOR MANAGING THE ATTITUDE CONTROL OF AN AIRCRAFT

L'invention concerne un procédé de gestion de la commande d'orientation d'un atterrisseur d'aéronef pourvu d'au moins une roue orientable par la commande d'orientation, comprenant les étapes de: - surveiller un ou plusieurs paramètres de roulage de l'aéronef pour déterminer si l'aéronef entre dans une situation de remorquage, - placer la commande d'orientation dans un mode de libre orientation de la roue orientable si l'aéronef entre dans une situation de remorquage ; - activer la commande d'orientation de sorte que la roue orientable ait une orientation angulaire contrôlée par la commande d'orientation si l'aéronef sort de la situation de remorquage. Figure 3.

THE INVENTION CONCERNS A HYDRAULIC BRAKING ARCHITECTURE FOR AN AIRCRAFT WITH HALF-CAVITY BRAKES

Architecture de freinage hydraulique pour aéronef comportant une pluralité de roues équipées de freins comportant chacun deux demi-cavités, l'architecture comportant : - un premier circuit de freinage comportant des servovalves alimentant une ou plusieurs demi-cavités sur des freins distincts ; - un deuxième circuit de freinage comportant des servovalves alimentant une ou plusieurs demi-cavités sur des freins distincts ; les deux circuits hydrauliques fonctionnant simultanément de sorte que sur chaque frein, l'une des demi- cavités est alimentée par une servovalve du premier circuit de freinage, et l'autre demi-cavité est alimentée par une servovalve du deuxième circuit de freinage, une au moins des demi-cavités étant alimentée par une servovalve qui n'alimente que cette demi-cavité.

PARKING BRAKE MANAGEMENT PROCESS IN THE BRAKING SYSTEM OF A VEHICLE EQUIPPED WITH ELECTRIC BRAKES

L'invention a trait à un procédé de gestion d'un freinage de parc dans un système de freinage pour véhicule équipé d'au moins un frein électrique comportant au moins un actionneur électromécanique qui comprend un poussoir actionné par un moteur électrique pour appliquer sélectivement un effort sur des éléments de friction du frein, le procédé comportant les étapes suivantes : - établir une série de tables d'ajustement direct du freinage de parc correspondant à des situations de freinage à différents niveaux d'énergie, - effectuer durant un freinage de parc une sélection d'une table d'ajustement direct en relation avec une situation de freinage précédant la mise en freinage de parc, - ajuster de façon directe un effort de frein de pare selon la table d'ajustement direct sélectionnée.

BRAKING SYSTEM ARCHITECTURE FOR AN AIRCRAFT WITH ELECTRO- MECHANICAL BRAKES

L'invention est relative à une architecture de système de freinage pour aéronef équipés de freins électromécaniques comportant au moins un actionneur électromécanique. Conformément à l'invention, l'architecture comporte au moins un boîtier de proximité disposé à proximité des freins en bas d'atterrisseur et comportant des moyens d'entrée/sortie pour collecter et calibrer au moins des signaux en provenance de capteurs associés aux freins, et transmettre les signaux ainsi traités à des organes de contrôle des actionneurs au moyen d'un bus de communication courant le long de l'atterrisseur, le boîtier de proximité comportant en outre des moyens de gestion d'organes de blocage des actionneurs.

Sicherheitsvorrichtung für ein System an Bord eines Fahrzeuges, insbesondere eines Flugzeuges

Axialkolbenpumpe

FAHRZEUGRADANORDNUNG MIT EINEM DRUCKSENSOR

Leistungsverteilungsaufbau zur sequenziellen Betätigung von beweglichen Elementen eines Luftschiffs

STELLGLIED MIT ZWEI MOTOREN, EINEM UNTERSETZUNGSGETRIEBE UND EINEM DREHMOMENTBEGRENZER

METHOD OF CONTROLLING A VEHICLE BRAKE WITH TORQUE CORRECTION

L' invention concerne un procédé de commande d'un frein de véhicule adapté à exercer un effort de freinage en réponse à une consigne d'actionnement, dans lequel : - à partir d'une consigne de freinage incluant des composantes à basse fréquence et des composantes à haute fréquence, on détermine une consigne nominale d'actionnement de l'actionneur du frein tenant compte de toutes les composantes de la consigne de freinage ; - à partir de cette même consigne de freinage, et d'une mesure du couple développé par le frein, on détermine une correction de la consigne nominale d'actionnement, la correction ne tenant compte que des évolutions de basse fréquence de la consigne de freinage, la correction étant adaptée pour tenir compte de conditions de fonctionnement actuelles ou à venir au moins dudit frein ou des freins soumis à la même consigne de freinage ; - on ajoute la correction à la consigne nominale.

PROCESS FOR APPLYING A VEHICLE BRAKE WITH TORQUE CORRECTION

L'invention concerne un procédé de commande d'un frein de véhicule adapté à exercer un effort de freinage en réponse à une consigne d'actionnement, dans lequel : - à partir d'une consigne de freinage incluant des composantes à basse fréquence et des composantes à haute fréquence, on détermine une consigne nominale d'ac- tionnement de l'actionneur du frein tenant compte de tou- tes les composantes de la consigne de freinage ; - à partir de cette même consigne de freinage, et d'une mesure du couple développé par le frein, on déter- mine une correction de la consigne nominale d'actionne- ment, la correction ne tenant compte que des évolutions de basse fréquence de la consigne de freinage; - on ajoute la correction à la consigne nominale.

PROCESS FOR APPLYING A VEHICLE BRAKE WITH SELF-ADJUSTMENT

L'invention concerne un procédé de commande d'un frein électromécanique de roue de véhicule comportant un actionneur muni d'un poussoir actionné par un moteur électrique et adapté à exercer sélectivement un effort de freinage sur des éléments de friction en réponse à une consigne d'actionnement, dans lequel : - à partir d'une consigne de freinage (~), on détermine une consigne nominale de position (~) de l'ac-tionneur du frein ; - à partir de cette même consigne de freinage (~), on estime un courant de référence (i*) qui devrait normalement circuler dans le moteur de l'actionneur pour appliquer un effort égal à la consigne de freinage ; - on compare le courant de référence (i*) à un courant (i) circulant dans le moteur de l'actionneur, et on en déduit une correction de position (x corr) ; et on ajoute la correction de position à la consigne nominale de position.

SAFETY DEVICE FOR A SYSTEM TRANSPORTED IN A VEHICLE, ESPECIALLY AN AIRCRAFT

L'invention concerne un dispositif de sécurité pour un système transporté à bord d'un véhicule, notamment d'un aéronef, qui est relié à la structure du véhicule par au moins un elément à corps cylindrique et à tige télescopique. Conformément à l'invention, le corps et la tige de l'élément télescopique délimitent deux chambres de fluide qui sont normalement isolées l'une de l'autre, un passage de communication étant prévu et normalement fermé par une valve de laminage associée, qui est pilotée par un moyen sensible à l'accélération utilisant une masse mobile dans la direction de l'axe de l'élément télescopique et un ressort taré associé à cette masse. Le moyen est agencé pour déclencher l'ouverture de la valve dès que l'accélération détectée dépasse un seuil prédéterminé en fonction du système à protéger, la modification de la longueur de l'élément télescopique maintenant ainsi l'accélération du système en-dessous dudit seuil.

Disk brake with high thermal resistance

The friction device comprises a non-rotary casing (50) in the form of a cage in which there are received a thrust structure (30), a set of friction disks (21, 22, 23, 24, 25) on a common axis, and a backing structure (40), the casing having a peripheral wall provided with ventilation openings (54). The friction device is actuated by a pneumatic actuator (60) mechanically connected to the central portion of the thrust structure through a central opening in an end wall (51) of the casing. Thermal insulation is arranged between the set of disks (21, 22, 23, 24, 25) and the outside of the casing adjacent to the end wall provided with the bearing unit (11) for the rotary shaft (10), and comprises at least one heat barrier (76-77, 78-79) situated at the bearing unit (11).

System zur Betätigung eines Bedienungszylinders für das Fahrwerk eines Flugzeuges.

Axialkolbenpumpe

VERFAHREN UND VORRICHTUNG ZUR VERDICHTUNG PORÖSER SUBSTRATE MITTELS CHEMISCHER DAMPFINFILTRATION

AUFBLASBARE RADANORDNUNG

FAHRWERK MIT SCHWENKBAREN RAEDERN WAEHREND DES EINZIEHENS.

FAHRZEUGRAD AUS VERBUNDWERKSTOFF.

Anlage zur Steuerung mindestens eines Sitzmoduls

Architektur eines hydraulischen Systems zum Manövrieren der Fahrwerke eines Luftschiffs

CARTRIDGE FILTER FOR AIRCRAFT THAT IS SCREWED INTO A DOUBLE THREADED HYDRAULIC BLOCK

L'invention concerne un dispositif de filtrage comprenant un bloc hydraulique recevant un filtre amovi-ble vissé dans un premier taraudage du bloc hydraulique. Le bloc hydraulique reçoit un organe de retenue adapté à retenir axialement le filtre lorsque celui-ci est vissé sur le bloc hydraulique, le bloc hydraulique comportant un deuxième taraudage coaxial au premier taraudage qui reçoit un organe de fixation de l'organe de retenue sur le bloc hydraulique, l'organe de fixation étant vissé dans le deuxième taraudage avec un couple suffisamment important pour empêcher en service toute désolidarisation de l'organe de retenue ...

POWER MANAGEMENT PROCESS OF AN IRREVERSIBLE ACTUATOR OF A VEHICLE'S WHEEL BRAKE

L'invention concerne un frein de roue de véhicule, notamment aéronef, comportant un support (2) qui reçoit au moins un actionneur électromécanique (1) équipé d'un poussoir (8) déplaçable en regard d'éléments de friction (3) sous l'action d'un moteur électrique (6) pour appliquer sélectivement sur les éléments de friction un effort de freinage. Conformément à l'invention, l'actionneur est irréversible de sorte qu'un effort appliqué sur le poussoir ne peut faire tourner le moteur électrique, et l'actionneur est associé à des moyens de coupure (30, 31, 32, 33, 34) sélective d'une alimentation électrique de puissance du moteur électrique qui, en temps normal, autorisent l'alimentation de l'actionneur, et qui coupent cette alimentation si : - la vitesse mesurée de rotation (.omega. mes) du moteur descend en dessous d'un premier seuil prédéterminé (S1), et - la vitesse commandée de rotation (.omega.) du moteur descend en dessous d'un deuxième seuil prédéterminé (S2).

METHOD FOR MANAGING AN AIRCRAFT GROUND CONNECTION

Procédé de gestion d'une liaison au sol d'un aéronef comportant un train d'atterrissage qui porte des roues soumises à des charges statiques dont certaines sont équipées d'un dispositif de freinage et d'autres sont équipées d'un dispositif de déplacement autonome, le procédé comportant l'étape de provoquer une modification d'une répartition des charges statiques auxquelles sont soumises les roues du train d'atterrissage de sorte à : - Surcharger au moins certaines roues équipées d'un dispositif de freinage lors d'une phase de freinage ; - Surcharger au moins certaines roues équipées d'un dispositif de déplacement autonome lors d'une phase de déplacement autonome.

LANDING GEAR ELECTRO-HYDRAULIC BRAKE SYSTEM

L'invention concerne un dispositif de freinage électro-hydraulique d'un train de roues d'aéronef. Le dispositif comporte deux sources de pression hydraulique alimentant chacune un circuit hydraulique menant, par l'intermédiaire de platines de commande de freinage, aux freins des deux groupes de roues. Un circuit relie, par deux clapets navettes, soit une électrovanne commandée électriquement par l'unité de pilotage, soit un double distributeur progressif commandé mécaniquement par les pédales de frein, à une entrée des platines. Un deuxième circuit relie directement une électrovanne à une deuxième entrée de chacune desdites platines. Chaque platine inclut deux circuits internes symétriques ayant une servo-valve par frein concerné, qui sont interconnectés au niveau d'un clapet commandé respectif. En cas de panne sur un circuit, les servo-valves associées à l'autre circuit permettent alors un contrôle du freinage et de l'anti-patinage selon un mode tandem appairé, avec une reconfiguration ...

FOOD AIGUILLETEUSE BY CONTINUOUS SPIRAL BAND

Architecture for a hydraulic circuit

The invention relates to an architecture for a hydraulic circuit associated with actuators ( 100 ), such as actuators for airplane brakes, the architecture comprising a main hydraulic circuit (C) having hydraulic components ( 4, 5 101, 6 ) and adapted to convey hydraulic fluid pressurized by at least one pressure generator ( 2 ) associated with a main supply ( 1 ) to the actuators ( 100 ). The architecture includes an emergency system comprising an auxiliary supply ( 8 ) permanently fed by a return circuit (R) collecting the returns from all of the hydraulic components ( 4, 5,101, 6 ), the auxiliary supply ( 8 ) being connected to the main supply ( 1 ) via a relief valve ( 9 ). The emergency system further comprising an electrically driven pump unit ( 10 ) arranged to take fluid from the auxiliary supply ( 8 ) and to inject it into the main circuit (C) downstream from a general check valve ( 3 ).

Device providing protection against untimely braking

The invention relates to a device for providing protection against untimely braking, the device being specially adapted to an electromechanical brake including at least one actuator having a pusher suitable for being displaced by means of an electric motor controlled by a control module so as to press in controlled manner against a stack of disks, in which the device comprises a safety member suitable for being placed in a first state in which it prevents the pusher from being displaced by the electric motor, and a second state in which it leaves the pusher free to be displaced by the electric motor, the safety member being controlled by a control logic circuit which by default places the safety member in the first state and places the safety member in the second state only in response to the simultaneous presence of an order coming from the control module and a confirmation signal that does not come from the control module and that is independent thereof.

Architecture for the hydraulic braking system of an aircraft

The invention relates to an architecture for a hydraulic braking system suitable for an aircraft of the type having at least one group of main landing gear units, each landing gear unit comprising a determined number of wheels each provided with a hydraulically actuated brake, the or each landing gear group being associated with a hydraulic circuit provided with hydraulic equipment and adapted to deliver hydraulic fluid under pressure to all of the brakes of the landing gear group, the hydraulic fluid being pressurized by at least one aircraft pressure generator system associated with an aircraft hydraulic fluid supply. According to the invention, accumulators are connected on the or each circuit in sufficient number for each accumulator to feed two pairs of brakes, each pair of brakes being mounted on a distinct landing gear unit, and an electrically-driven pump being arranged to maintain a predetermined pressure level in all of the accumulators of the circuit in question.

Flugzeugbremseinheit

Radlenkungsvorrichtung.

Hydraulische Lenkvorrichtung

EINTEILIGES ABSTANDSELEMENT

Method of producing a fibrous preform

Method for producing a fibrous preform, especially by needling a fiber material (e.g., discontinuous pitch-based or PAN-based fiber). A needle-penetrable mold plate (10) having at least one mold cavity (12) therein for receiving the fiber material is provided. The use of a needle-penetrable mold plate allows the mold plate having the fiber material therein to be passed freely through a linear needling device, such as a linear needling loom, without having to take rigorous care to limit a needling path to the discontinuous fiber material, as in the conventional art. The mold plate is moved relative to the needling device one or more times until a desired level of material density (sometimes measured by fiber content percentage) is attained. Preferably, the mold plate is additionally moved and/or allowed to move along a direction generally transverse to the direction along with the mold plate moves relative to the needling device, so as to avoid the conventional problem of needle "tracking ...

Actuator with two operating modes

A shock-absorbing actuator for a vehicle suspension

WATERPROOFING SYSTEM FOR a GAS ENTRY Of a FURNACE OR ANALOGUE

Bistable coupling device for attaching rotating shafts of aircraft, has movable coupler reaching or exceeding unstable intermediate position at critical torque and withdrawn toward stable disengaged position by springs

L'invention est relative à un dispositif d'accouplement bistable comportant deux éléments coupleurs (3, 4 ; 103, 104) pour sélectivement coupler en rotation deux arbres, l'un au moins des éléments coupleurs (4 ; 104) étant mobile entre une position d'embrayage stable dans laquelle les deux éléments coupleurs coopèrent pour lier les deux arbres en rotation, et une position débrayée stable dans laquelle les deux éléments sont éloignés l'un de l'autre pour laisser les deux arbres indépendants en rotation, en lui faisant franchir une position instable intermédiaire, et dans lequel les deux éléments coupleurs coopèrent entre eux selon des surfaces obliques adaptées à provoquer un écartement lors d'un glissement relatif des deux éléments à l'encontre d'une force de rappel vers la position embrayée en réponse à une augmentation du couple transmis, jusqu'à un couple critique pour lequel l'élément coupleur mobile atteint ou dépasse la position intermédiaire instable.

MANAGEMENT SYSTEM AUTOMATISEE OF the SPREADING OUT Of a TEXTILE TABLECLOTH

COUNT Of CIRCULAR TAGGING Of a TEXTILE STRUCTURE FORMEE STARTING FROM an ANNULAR FIBROUS PREFORM

L'invention concerne une table d'aiguilletage circulaire (10) d'une structure textile formée à partir d'une préforme fibreuse annulaire, comprenant un plateau annulaire horizontal (14) sur lequel est destiné à être disposée une préforme fibreuse annulaire (12), des moyens d'entraînement en rotation de la préforme fibreuse autour de l'axe (16) du plateau, un dispositif d'aiguilletage (22) ayant une tête d'aiguilletage (24) s'étendant sur un secteur angulaire du plateau et animée d'un mouvement vertical relatif par rapport au plateau, et des moyens (38a, 38b) pour guider la préforme fibreuse sous la tête d'aiguilletage.

Stellantrieb mit zwei Betriebsarten

Bremse für ein Flugzeugrad, gebremstes Flugzeugrad, sowie Landegestell mit einem solchen Flugzeugrad

Bremsvorrichtung für einen Satz Flugzeugräder

Hydraulische Lenkvorrichtung

METHOD FOR DISTRIBUTING BRAKE PROPORTIONING AMONG AIRCRAFT BRAKES

L'invention concerne un procédé de répartition du freinage entre les freins d'un aéronef, comportant les étapes de: - estimer un objectif d'effort de freinage et un objectif de couple de lacet à réaliser par les freins de l'aéronef ; - définir au moins deux groupes de freins (12,13); - déterminer pour chaque groupe un niveau de freinage à réaliser par ledit groupe, lesdits niveaux de freinage étant calculés de sorte qu'un freinage réalisé selon lesdits niveaux de freinage soit, au moins dans des conditions normales de fonctionnement des freins, conforme à l'objectif d'effort de freinage et l'objectif de couple de lacet.

LANDING GEAR FITTED WITH DEVICE FOR COMMUNICATIONS BETWEEN A WHEEL AND THE LANDING GEAR

L'invention concerne un atterrisseur d'aéronef comportant au moins un essieu sur lequel au moins une roue est montée pour tourner, l'atterrisseur comportant un dispositif de communication pour relier un capteur monté sur une jante de la roue à des moyens de traitement fixes montés sur l'aéronef. Selon l'invention, le dispositif de communication comporte d'une part une antenne solidaire du capteur et donc tournant avec la roue et d'autre part une antenne fixe s'étendant en bout d'essieu et reliée aux moyens de traitement, les deux antennes étant en communication hertzienne au travers d'un capot en matériau non-conducteur solidaire de la roue et recouvrant l'extrémité de l'essieu ...

CIRCULAR MACHINE Of TAGGING PROVIDED With a FLUIDIC DEVICE AUTOMATIQUEDE PREFORMS

Safety locking device for electromechanical equipment and aircraft wheel brake equipped therewith

A safety locking device for electromechanical equipment provided with a rotating shaft, particularly an aircraft wheel brake with a safety locking device. The device comprises a first friction element connected rotationally to the shaft, and a second friction element immobile rotationally and extending opposite the first friction element. One of the two friction elements is able to move in translation, under the action of a controllable actuator, between a locking position and a release position. The locking and release positions correspond to successive angular positions of a selector able to move in rotation and connected in translation to the friction element able to move in translation. The selector is maintained in any one of its angular positions by a resilient member, while the actuator provides solely the passage of the selector from one angular position to the following one, and consequently passage from the locking position to the release position or vice-versa.

Elektrohydraulische Bremsvorrichtung für das Fahrwerk eines Flugzeugs

VERDICHTEN EINER VORFORM UNTER VERWENDUNG EINES FLÜSSIGEN VORLÄUFERS

WHEEL BAR AND SPECIALLY ADAPTED WHEEL

L'invention est relative à une barrette pour roue d'aéronef, comportant un corps oblong prolongé de part et d'autre par deux embouts s'étendant parallèlement au corps et parallèlement entre eux, en étant décalés l'un par rapport à l'autre. L'invention est également relative à une roue spécialement adaptée à recevoir une telle barrette.

POWER DISTRIBUTION ARCHITECTURE FOR THE DISTRIBUTION OF POWER TO THE ELECTROMECHANICAL ACTUATORS OF AN AIRCRAFT

L'invention est relative à une architecture de distribution de puissance pour aéronef, destinée à alimenter des actionneurs électromécaniques d'aéronefs, l'architecture comportant au moins un organe de distribution de puissance pour distribuer la puissance à tel ou tel actionneur électromécanique relié à l'architecture, l'architecture recevant la puissance d'au moins un bus d'alimentation en puissance de l'aéronef. Selon l'invention, un réseau à tension continue variable de façon commandée est interposé entre le bus d'alimentation en puissance de l'aéronef et les organes de distribution de puissance.

MECHANICALLY OPERATED ACTUATOR WITH HYDRAULIC DAMPING

L'invention concerne un actionneur comportant un corps dans lequel une tige est montée pour coulisser, l'actionneur comportant une vis s'étendant à l'intérieur de la tige pour coopérer avec un écrou solidaire de la tige, la vis étant entraînée en rotation par un moteur. Selon l'invention, la tige est associée à un piston qui coulisse dans une cavité du corps pour y définir deux chambres, celles-ci étant remplies de fluide hydraulique et étant mises en communication par des moyens de transvasement de fluide équipés d'au moins un organe de régulation adapté à laminer du fluide expulsé d'une des chambres, au moins pour un sens de déplacement de la tige.

BRAKE POWER ARCHITECTURE FOR AIRCRAFT EQUIPPED WITH ELECTOMECHANICAL ACTUATORS

L'invention est relative à une architecture d'alimentation de freins d'aéronef, pour un aéronef comportant au moins deux atterrisseurs comportant chacun un certain nombre de roues, chacune des roues étant équipée d'un frein comportant un certain nombre d'actionneurs électromécaniques de freinage. L'architecture comporte au moins quatre boîtiers d'alimentation qui alimentent des groupements d'actionneurs pris dans des groupes complémentaires de roues.

WHEEL AND BRAKE ASSEMBLY FOR AIRCRAFT EQUIPPED WITH A DEVICE FOR ROTATING AND HOLDING

L'invention est relative à un ensemble de roue et frein d'aéronef, la roue comportant une jante montée pour tourner sur un essieu de l'aéronef autour d'un axe de rotation, et le frein comportant une pile de disques s'étendant sensiblement dans la jante en service, et un support portant des actionneurs de freinage en regard de la pile de disques pour presser sélectivement ceux-ci, caractérisé en ce que le support porte au moins un organe d'entraînement en rotation de la roue de sorte que l'organe d'entraînement s'étende à l'extérieur de la roue.

LOCKING-IN DEVICE FOR A LANDING GEAR IN LIFTED POSITION

L'invention concerne un dispositif d'accrochage du type comportant un carter principal logeant un crochet articulé, et un levier de verrouillage dont une branche porte un galet d'appui coopérant avec le crochet, l'autre branche étant reliée, par l'intermédiaire d'un embiellage, à la sortie d'un ensemble moto-réducteur d'entraînement. Conformément à l'invention, l'embiellage présente une lumière oblongue de façon à autoriser un pivotement du levier de verrouillage en cas de blocage de l'arbre de sortie de l'ensemble moto-réducteur, et de plus un actionneur indépendant est associé au levier de verrouillage, de façon que son déclenchement en secours provoque un pivotement dudit levier suffisant pour dégager le galet d'appui de la surface de came associée et déverrouiller ainsi le crochet articulé.

PREPARATION OF TEXTILE PREFORMS FOR BRAKE DISCS IN COMPOSITEMATERIAL

A fiber preform for manufacturing a brake disk out of composite material is itself manufactured by superposing and bonding together fiber layers. Structural fiber layers (10) are used to form at least a first preform portion that is to constitute the fiber reinforcement of the brake disk core, while the or each preform portion that is to constitute the fiber reinforcement of a friction portion of the brake disk is constituted by a felt (16, 18), at least in its portion adjacent to the friction face.

A METHOD OF MANUFACTURING CARBON-CARBON COMPOSITE MATERIAL PARTS IN PARTICULAR BRAKE DISKS

A textile three-dimensional structure is formed by superposing felt layers a nd binding them together by needle bonding, then it is compressed so as to obta in a preform having a fibre volume ratio not less than 20 %. The preform is maintained in its compressed state by impregnating it with a liquid composition containing a binding agent for binding the preform fibres together. The resulting consolidated preform is densified for instance by chemical infiltration in vapour phase.

Bremse für ein Flugzeugrad, gebremstes Flugzeugrad, sowie Landegestell mit einem solchen Flugzeugrad

Verfahren zum Schutz eines Bremssystems eines Fahrzeuges mit elektrischen Bremsen

Endanordnung einer Fahrzeugachse, insbesondere für Flugzeuge

Anordnung von Kohlenstoffbremsscheiben für eine Bremseinheit für Luftfahrzeuge sowie Verfahren zur Montage von Scheiben gemäss einer solchen Anordnung

A METHOD FOR BRAKE CONTROL OF AN AIRCRAFT AND CORRESPONDING BRAKING SYSTEM

L'invention est relative à un procédé de gestion du freinage d'un aéronef comportant des atterrisseurs ayant des roues équipées de freins à friction et de freins auxiliaires assurant une dissipation d'énergie par d'autres moyens que la friction, le procédé comportant les étapes de : - lors d'une demande de freinage, tester des paramètres de freinage pour déterminer si l'aéronef est dans une situation de freinage pour laquelle les freins à friction ne sont pas indispensables pour assurer le freinage demandé, - effectuer le freinage demandé en privilégiant un actionnement des freins auxiliaires tant que l'aéronef reste dans ladite situation de freinage, en n'actionnant les freins à friction que si l'aéronef sort de ladite situation de freinage.

JACK ACTIVATING SYSTEM FOR LANDING GEAR

L'invention concerne un système d'actionnement du vérin de manoeuvre d'un train d'atterrissage d'avion, comportant une génération hydraulique capable d'envoyer du fluide sous pression vers l'une ou l'autre des deux chambres du vérin de manoeuvre. Conformément à l'invention, le système d'actionnement comporte un dispositif de sécurité permettant d'eviter toute surcharge sur la tige du verin sous l effet de pointes de pression : ce dispositif comporte deux clapets de surpression , le premier clapet limitant la pression délivrée dans la chambre annulaire étant en outre pilote par la pression de la chambre de pleine section , et le second clapet de surpression , du type différentiel, contrôlant en permanence l'écart de pression entre les deux chambres du vérin. Application à la réalisation de systèmes d'actionnement à haute sécurité pour atterrisseurs d'avion. Figure unique.

DEVICE FOR BRAKING A SET OF AIRCRAFT WHEELS

L'invention concerne un dispositif de freinage d'un train de roues d'aéronef, comportant un circuit hydraulique normal et un circuit hydraulique secours, ces deux circuits menant à chacun des différents freins via une valve de freinage associée. Conformément à l' invention, les valves de freinage du circuit normal et/ou du circuit secours sont constituées par des valves à entraînement direct commandées électriquement par une unité électronique de commande associée.

Rocking beam landing system

Regelungsverfahren für die Kraft der Parkbremse in einem Bremssystem eines Fahrzeuges mit elektrischen Bremsen

Verfahren zur Steuerung der Bremsung eines Luftschiffs mittels Vorhersage von dessen Bewegung auf der Flughafenplattform

Verriegelungsvorrichtung einer schwenkbaren Radhalterung.

Regelungsverfahren eines Sitzes und Durchführung dieses Verfahrens

Regelungsverfahren eines Sitzes und Durchführung dieses Verfahrens

PILOTING NETWORK FOR SINGLE- OR MULTI-ENGINE ACTUATORS, SPECIFICALLY ADAPTED TO AERONAUTICAL APPLICATIONS SUCH AS FEEDING LATCHING ASSEMBLY MOTORS

L'invention est relative à un réseau de puissance de secours pour aéronef, destiné à alimenter des moteurs d'actionneurs reliés à ce réseau, le réseau comportant un bus de puissance adapté à convoyer une puissance triphasée alternative générée par un convertisseur continu/alternatif alimenté par une source de tension continue de l'aéronef, le convertisseur étant équipé de moyens de modulation de la tension et/ou de la fréquence de la puissance triphasée ainsi générée.

METHOD FOR MOVING AN AIRCRAFT ON THE GROUND

L'invention est relative à un procédé de déplacement d'un aéronef comportant au moins un atterrisseur auxiliaire à l'avant de l'aéronef et des atterrisseurs principaux, chacun des atterrisseurs portant des roues, comportant les étapes de : - équiper au moins l'une des roues portées par l'atterrisseur auxiliaire d'un organe moteur de déplacement principal, et équiper au moins l'une des roues portées par les atterrisseurs principaux d'un organe un moteur de déplacement d'appoint; - en réponse à un ordre de déplacement, solliciter l'organe moteur de déplacement principal pour déplacer l'aéronef, et au moins dans une situation où l'effort d'entraînement de l'aéronef développé à l'aide de l'organe moteur de déplacement principal s'avère insuffisant pour déplacer l'aéronef, solliciter l'organe moteur de déplacement d'appoint en complément de l'organe moteur de déplacement principal.

FILTRATION DEVICE FOR AIRCRAFT WITH FOOLPROOF DEVICE AND CARTRIDGE DRIVE

L'invention concerne un dispositif de filtrage pour aéronef comprenant un bloc hydraulique adapté à recevoir un filtre amovible qui comporte une cuve recevant une cartouche, dans lequel la cuve est équipée intérieurement d'une épingle en matériau élastiquement déformable comportant d'une part un détrompeur qui s'étend vers l'ouverture de la cuve et qui comporte une extrémité recourbée qui dépasse d'un bord de la cuve, et d'autre part un doigt qui s'étend vers le fond de la cuve en étant orienté vers le centre de celle-ci, de façon que, lorsqu'une cartouche est mise en place dans la cuve, le doigt est repoussé par la cartouche et force le détrompeur à se rétracter de sorte que son extrémité recourbée ne déborde radialement de la cuve plus, la cartouche étant équipée d'un obstacle externe qui coopère avec une extrémité du doigt pour empêcher le retrait de la cartouche de la cuve.

FILTRATION DEVICE FOR AIRCRAFT WITH FILTER ROTATION STOP

L'invention concerne un dispositif de filtrage pour aéronef comprenant un bloc hydraulique adapté à recevoir un filtre amovible qui comporte une cuve recevant une cartouche. Conformément à l'invention, un insert est vissé avec serrage dans un taraudage du bloc hydraulique, l'insert comportant lui-même un taraudage dans lequel la cuve est vissée, le dispositif comportant en outre des moyens d'arrêt en rotation de la cuve une fois celle-ci vissée dans l'insert.

LANDING GEAR, BRAKE FOR AIRCRAFT WHEEL, AIRCRAFT BRAKE WHEEL ASSEMBLY AND MAINTENANCE PROCESS FOR SAID LANDING GEAR

L'invention concerne un atterrisseur d'aéronef, comprenant au moins un essieu pour porter au moins un ensemble de roue freinée qui comporte une jante montée pivotante sur l'essieu et une pile de disques et un support portant des actionneurs électromécaniques modulaires démontables unitairement, l'atterrisseur et l'ensemble de roue freinée étant conformés de sorte que chaque actionneur soit dans l'une au moins des configurations suivantes : - un espace libre de dimensions suffisantes pour recevoir l'actionneur s'étend, suivant une trajectoire de démontage, directement en regard de l'actionneur lorsqu'il est en position d'opération ; - l'actionneur est associé à des moyens de son déplacement depuis une position en opération à une position de démontage, un espace libre de dimensions suffisantes pour recevoir l'actionneur s'étendant, suivant une trajectoire de démontage, directement en regard de l'actionneur lorsqu'il est en position de démontage.

TOGETHER HAS INFLATABLE WHEEL

PROCESS AND INSTALLATION FOR THE MANUFACTURE OF ANNULAR FIBROUS PREFORMS

Actuator with torque limiter

An actuator includes: at least one drive motor; an outlet ( 22 ); an adjustable torque limiter which is disposed between the/each motor and the outlet ( 22 ), the torque limiter having a mobile element ( 100 ) which is used to set the maximum torque transmitted; and a case which houses the motor and the torque limiter. The case is provided with an opening ( 110 ) for accessing the mobile element ( 100 ) used to set the maximum torque transmitted and the torque limiter is mounted in the case.

Sicherheitsblockiervorrichtung für ein elektromechanisches Gerät sowie hiermit ausgerüstete Bremse eines Flugzeugs

Sperreinrichtung und zugehöriges Betriebsverfahren, insbesondere für ein Flugzeugfahrwerk

Elektromagnetische Bremse mit einer Parkbremse

METHOD OF CONTROLLING THE YAWING MOVEMENT OF AN AIRCRAFT RUNNING ALONG THE GROUND

The invention relates to a method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. According to the invention, the method comprises the steps of: 1. Method of controlling a yawing movement of an aircraft running along the ground , the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels , the method comprising the steps of:{'sub': c', 'p, 'on the basis of a yaw rate setpoint {dot over (φ)}, determining a wheel-steering prepositioning angle θ;'}{'sub': c', 'p', 'z', 'c', 'm', 'c, 'using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle θequal to the sum of this prepositioning angle θand of an angle θwhich is determined taking account of an error between the yaw rate setpoint {dot over (φ)}and the measured yaw rate {dot over (φ)}when the steerable bottom part is steered by the steering angle θ.'}2. Method according to claim 1 , in which the steering angle θis equal to the sum of the prepositioning angle θand of the angle θwhich is further determined taking account of an error between the required steering angle θand a measured steering angle θ.32. Method according to claim 1 , applied to an aircraft further comprising at least two main landing gears positioned respectively one on the left and one on the right of the fuselage and the wheels of which are associated with torque application members claim 1 , the method comprising the step of generating claim 1 , for the attention of the torque application members of the left and right main landing gears claim 1 , two acceleration setpoints Γ claim 1 , Γso that the members thus stimulated generate claim 1 , on the aircraft claim 1 , a yaw moment Mthat complements the yaw moment Mgenerated by the first landing gear () claim 1 , so that the ...

METHOD FOR MANUFACTURING A COMPOSITE MATERIAL CONNECTING ROD

The present invention relates to a method of fabricating a rod of composite material from a fiber preform comprising a certain number of primary fiber plies connected together by links allowing plies to slide relative to one another while the preform is being shaped, the preform including a central portion for constituting the body of the rod and including two opposite side portions, together with extensions for forming lugs of the rod, which method includes the step of shaping the fiber preform so as to give it a hollow shape while keeping the two opposite side portions spaced apart so as to give the fiber preform an open profile in its central portion, followed by injecting resin and causing it to polymerize. 128679. A method of fabricating a rod of composite material from a fiber preform () comprising a certain number of primary fiber plies connected together by links allowing plies to slide relative to one another while the preform is being shaped , the preform including a central portion () for constituting the body of the rod and including two opposite side portions ( , ) , together with extensions () for forming lugs of the rod , which method includes the step of shaping the fiber preform so as to give it a hollow shape while keeping the two opposite side portions spaced apart so as to give the fiber preform an open profile in its central portion , followed by injecting resin and causing it to polymerize.2. A method according to claim 1 , wherein the fiber preform is wrapped around a shaper mandrel before injecting resin and polymerizing it.3. A method according to claim 1 , wherein the side portions are stiffened to increase local buckling strength.467. A method according to claim 3 , wherein the stiffening comprises using a preform of varying stiffness that increases perpendicularly to a plane of symmetry of the preform on going from the center thereof towards the side portions ( claim 3 , ).523. A method according to claim 1 , wherein the preform is shaped ...

METHOD OF MANAGING MOVEMENT OF AN AIRCRAFT ON THE GROUND

The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels. 1. A method of managing movement of an aircraft on the ground , the aircraft having at least one left main undercarriage and at least one right main undercarriage , each having wheels associated with torque application members for applying torque to the wheels in response to a general setpoint , the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint , wherein the method comprises the successive steps of:from the general setpoint, determining for each of the undercarriages an undercarriage acceleration setpoint in such a manner that the undercarriage acceleration setpoints together enable the general setpoint to be satisfied;for each of the undercarriages, determining from the undercarriage acceleration setpoint and for each of the wheels of said undercarriage, a wheel acceleration setpoint in such a manner that the wheel acceleration setpoints together correspond to the undercarriage acceleration setpoint; andfor each of the wheels, determining from the wheel acceleration setpoint a general torque setpoint for the torque to be generated by the torque application member associated with said wheel in such a manner that the general torque setpoint enables the wheel acceleration setpoint to be satisfied, and in such a manner that the torques applied to the wheels by the torque application members in response to the ...

METHOD FOR OPERATING A LANDING GEAR ASSEMBLY WITH A BREAKER STRUT

A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut () and the stabilizer member () in such a manner that at least one of the links () of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator () to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg. 1. An aircraft landing gear comprising:a leg hinged to the aircraft and operable between a deployed position and a retracted position, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links, themselves held in alignment by a locking member,wherein the strut and the stabilizer member are arranged in such a manner that at least one of the links of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, andwherein an operating actuator is attached to said link in order to cause the link to pivot against the locking member and exert thereon a force tending simultaneously to bring the links of the stabilizer member out of alignment against the locking member, to bring the links of the strut out of alignment, and to move the leg.2. A landing gear according to claim 1 , wherein the operating actuator is of the rotary type and is attached to the associated link by means of a rod.3. A landing gear according to claim 1 ...

Selective force transmission device and an undercarriage consisting of an application thereof

The invention relates to a device for selectively transmitting force, the device comprising a first element and a second element that is movably mounted on the first element, a friction member being arranged between the first element and the second element to exert a friction force between them, which force presents a maximum value that depends on prestress imparted by a presser member. The device includes control means for varying the prestress imparted by the presser member to the friction member and arranged, where appropriate, to substantially release the prestress imparted by the presser member so that the prestress becomes substantially zero.

DEVICE FOR REDUCING AERODYNAMIC NOISE FROM AN AIRCRAFT UNDERCARRIAGE

In the field of aviation, a device for limiting aerodynamic noise from a deployed aircraft undercarriage during landing and/or takeoff. The device comprises two end plates () for closing respective ends () of a hollow pin () of the undercarriage, such as a hinge pin between two rods of the undercarriage, together with at least one tie () for engaging inside the hollow pin () to connect the two end plates () together so as to hold them pressed against the ends () of the pin (). 1442216144221a,bababab. A device for limiting aerodynamic noise from a deployed aircraft undercarriage while landing and/or takeoff , the device comprising two end plates () for closing respective ends ( , ) of a hollow pin () of the undercarriage , such as a hinge pin between two rods of the undercarriage , together with at least one tie () for engaging inside the hollow pin () to connect the two end plates ( , ) together so as to hold them pressed against the ends ( , ) of the pin ().2446a,b. A device according to claim 1 , wherein the end plates () and/or the tie () are made of natural fibers such as hemp or flax fibers agglomerated in a resin of reusable type.3449966441a,ba,ba,b. A device according to claim 1 , wherein at least one end plate () includes a central orifice () for having the tie () pass therethrough in order to secure the tie () to the end plate () by means of the end of the tie () passing through the end plate.464499997744a,ba,ba,ba,ba,b. A device according to claim 3 , further including at least one locking means such as a staple for securing rigidly to an end of a tie () passing through an end plate () via its orifice () claim 3 , the locking means presenting a section greater than that of the orifice () so as to bear against an outer face () of the end plate ().5446a,b. A device according to claim 3 , wherein the end plate () is provided with means for locking an end of the tie () passing through the central orifice thereof.6664466559944a,ba,ba,ba,ba,b. A device according ...

HYDRAULIC CIRCUIT FOR ACTUATING AN UNDERCARRIAGE, AND METHODS OF DEPLOYING AND RAISING AN UNDERCARRIAGE USING SUCH A CIRCUIT

A hydraulic circuit for actuating an undercarriage, the circuit comprising: a feed line for feeding fluid and a return line; at least one door selector connected to the feed and return lines, the selector feeding door service lines, including an opening line and a closing line for opening and closing the doors; at least one undercarriage selector connected to the feed and return lines, feeding undercarriage service lines including a deployment line and a raising line for deploying and raising the undercarriage; and a door unhooking line and an undercarriage unhooking line. The door unhooking line is connected to at least one undercarriage service line while the undercarriage unhooking line is connected to at least one door service line, the circuit also including means for connecting the door service lines together during a door opening stage, and means for connecting the undercarriage service lines together during an undercarriage deployment stage. 1. A hydraulic circuit for actuating an undercarriage , the circuit comprising:a fluid feed line and a return line;at least one door selector connected to the feed and return lines, the selector feeding door service lines, including an opening line and a closing line for opening and closing the doors;at least one undercarriage selector connected to the feed and return lines, the selector feeding undercarriage service lines including a deployment line and a raising line for deploying and raising the undercarriage; anda door unhooking line and an undercarriage unhooking line;wherein the door unhooking line is connected to at least one undercarriage service line while the undercarriage unhooking line is connected to at least one door service line, the circuit also including means for connecting the door service lines together during a door opening stage, and means for connecting the undercarriage service lines together during an undercarriage deployment stage.2. A hydraulic circuit according to claim 1 , wherein the means ...

METHOD FOR MANUFACTURING A COMPOSITE MATERIAL CONNECTING ROD HAVING REINFORCED ENDS

In the field of aviation, a method of fabricating a composite-material rod. The method comprises a first step of fabricating a mandrel comprising a sleeve of composite material and solid inserts of composite material secured to the ends of said sleeve to constitute a rigid whole. Then, one or more layers of braided fibers are applied around the mandrel by using a fiber-braiding machine. Next, a resin is injected into the layers of braided fibers so as to establish cohesion rigidly bonding the braided fiber layers and at least the ends of the mandrel in order to form a rod body out of composite material having reinforced ends. Finally, respective holes are drilled at each end of the rod body, each hole passing through the layers of braided fibers and also through the corresponding insert. 1. A method of fabricating a composite-material rod having reinforced ends , the method comprising the steps of:fabricating a mandrel comprising a sleeve and reinforcing inserts secured to the ends of said sleeve in order to constitute a rigid whole;applying one or more layers of braided fibers around the mandrel with a machine for braiding reinforcing fibers;injecting and polymerizing resin into the layers(s) of braided fibers in order to establish cohesion rigidly bonding the layers of braided fibers and at least the ends of the mandrel together in order to form a rod body having reinforced ends; anddrilling to make a through orifice at each end of the rod body, each orifice passing through the layers of braided fibers and through the corresponding insert.2. A method according to claim 1 , wherein the sleeve and the inserts are fabricated out of a composite material comprising a resin of the same type as the resin injected into the layers surrounding the mandrel.3. A method according to claim 1 , wherein the sleeve and the inserts are made of a composite material comprising fibers of the same type as the fibers of the layers surrounding the mandrel.4. A method according to claim 1 ...

Nose gear of an aircraft comprising a single control device for retraction and steering

A landing gear of an aircraft, including a strut including two arms forming a rotational axis for retracting the gear, a rotating tube mounted in a mobile manner such that it rotates inside the strut about a pivoting axis, a sliding rod that is mobile in a translatory manner in the rotating tube along the pivoting axis, and carries wheels of the gear at one of its ends, and at least one bearing point that is located on one of the elements of the gear at a distance from the retraction axis and can bear necessary efforts for the retraction, the bearing point being located on the rotating tube.

METHOD OF FABRICATING A METAL PART INCLUDING FIBROUS ANNULAR REINFORCEMENT

A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part. 16-. (canceled)7. A method of fabricating an axisymmetric annular metal part reinforced by including coaxial annular reinforcement therein in a form of a winding of composite material , the method comprising:preparing an annular metal blank for the part;making or finishing off a cavity that opens out into a coaxial inside face of the blank and that possesses a right cross-section of axial extent that decreases going radially outwards over at least a portion of its height;winding a reinforcing yarn in the cavity so as to fill substantially all of the space therein with a winding;closing the cavity by putting into place a metal cylindrical wall in register with the opening of the cavity; thensubjecting the assembly to a hot isostatic compression process; andmachining the blank to obtain a final shape of the part.8. A method according to claim 7 , wherein the reinforcing yarn includes a core of composite material or of ceramic claim 7 , sheathed in metal claim 7 , and the winding that is being formed is stabilized by welds bonding together certain turns via their metal sheaths.9. A method according to claim 7 , wherein the winding of the reinforcing yarn is started by fixing one end thereof to a bottom of the cavity claim 7 , and winding is continued by causing the blank to turn about its axis while feeding the yarn at a speed that is controlled relative to a speed of rotation of the blank.10. A method according to claim 9 , wherein the yarn is fed at a speed that is ...

METHOD OF MAKING A THREE-DIMENSIONAL FIBER PREFORM FOR FABRICATING AN ANNULAR PART OUT OF CARBON/CARBON COMPOSITE MATERIAL

A method of making a three-dimensional fiber preform for fabricating an annular part out of carbon-carbon composite material, the method including stacking layers of a fiber sheet made up of carbon yarns or tows, needling the layers one by one as they are superposed so as to bond them together, and locally modifying the electromagnetic properties of the fiber preform by increasing the fiber density of the layers of the fiber sheet that are situated at half-thickness of the fiber preform. 1. A method of making a three-dimensional fiber preform for fabricating an annular part out of carbon-carbon composite material , the method comprising:stacking layers of a fiber sheet made up of carbon yarns or tows;needling the layers one by one as they are superposed so as to bond them together, andlocally modifying the electromagnetic properties of the fiber preform by increasing the fiber density of the layers of the fiber sheet that are situated at half-thickness of the fiber preform.2. A method according to claim 1 , wherein the layers of the fiber sheet in which the fiber density is increased are subjected to needling with parameters that are different from those of the needling to which the other layers are subjected.3. A method according to claim 2 , wherein the layers of the fiber sheet in which the fiber density is increased are subjected to needling with needling density greater than that of the needling to which the other layers are subjected.4. A method according to claim 3 , wherein the layers of the fiber sheet in which the fiber density is increased are subjected to needling with a needling density of about 60 strokes/cm claim 3 , the other layers being subjected to needling with a needling density of about 30 strokes/cm.5. A method according to claim 2 , wherein the layers of the fiber sheet in which the fiber density is increased are subjected to needling with the needles having a penetration depth greater than that of the needling to which the other layers are ...

TOOL FOR REMOVING ANNULAR ELEMENTS TIGHTLY MOUNTED IN HOLES, IN PARTICULAR BLIND HOLES, OF PARTS

A removal tool which exerts an axial pull on an annular element including a tie rod with a widened end head adapted to be inserted in the coaxial passage of the annular element, beyond the annular element, and a mechanism for engaging with the element in a form of an annular cage with lateral prongs capable of deforming elastically in the radial direction, passing through the axial passage to engage via the elastic prongs thereof with the distal transverse surface of the element and to allow the element to be removed by the engagement of the widened head with the prongs, following the axial movement of the tie rod outside of the hole by a control mechanism. 19-. (canceled)10. A tool for removal of annular elements or rings , tightly mounted in holes , or in blind holes , in parts , of type exerting axial traction on the annular element , the tool comprising:a tie-rod adapted to be engaged coaxially in the axial passage of the annular element and terminating at its distal end passing through the axial passage of the annular element in an enlarged head having a diameter less than the inside diameter of the axial passage of the element and which is fed into the hole beyond a distal transverse face of the annular element;means for contact with the annular element, taking a form of an annular cage with lateral claws that are elastically deformable in the radial direction, which cage surrounds the tie-rod and passes through the axial passage of the annular element such that the claws come to be pressed against the distal transverse face of the annular element; anddrive means for acting on the tie-rod to extract the annular element from the hole through action of the claws of the contact means driven by the enlarged head of the tie-rod,wherein the lateral claws of the annular cage are in a position deformed radially inwards when they pass through the axial passage of the annular element and, on exiting the passage, spontaneously resume their initial position with an ...

ELECTROMECHANICAL TELESCOPIC ACTUATOR

The invention relates to a telescopic actuator comprising: 1. A telescopic actuator comprising:a cylinder having means for coupling it to a first external element;a rod mounted to slide telescopically in the cylinder along a sliding axis and including means for coupling it to a second external element;a lead screw mounted to rotate in the cylinder about the sliding axis and extending inside the rod to co-operate with a nut secured to the rod, such that rotating the lead screw causes the rod to slide;drive means for driving the lead screw in rotation; andretention means for axially retaining the lead screw, which means hold a bearing of the lead screw captive in an axial direction, the retention means being arranged to retain the bearing of the lead screw with axial clearance suitable for absorbing movements imparted to the rod relative to the cylinder;wherein the drive means for driving the lead screw in rotation are controllable to move the bearing of the lead screw axially until it is centered in the retention means so as to benefit from substantially half of the clearance on either side of the bearing.2. A telescopic actuator according to claim 1 , wherein the retention means are controllable in selective manner to release the bearing of the lead screw in response to a release order.3. A telescopic actuator according to claim 1 , wherein the drive means for driving the lead screw in rotation comprise:a fluted shaft mounted to rotate in the cylinder about the sliding axis and extending inside the screw to drive it in rotation via a fluting connection; anda motor member for driving the fluted shaft in rotation.4. A method of actuating an actuator according to claim 1 , wherein claim 1 , when the length of the actuator is “frozen” by the rod being held stationary relative to the cylinder claim 1 , the drive means for driving the lead screw are actuated to move the bearing of the lead screw until it is centered in the retention means so as to benefit from ...

DEVICE FOR BRAKING/DRIVING AN AIRCRAFT WHEEL

The invention relates to a device for braking/driving an aircraft wheel mounted tO rotate on an undercarriage axle, the device comprising: a stack of disks comprising disks that are constrained in rotation with the wheel and that alternate with disks that are constrained in rotation with a torsion tube; a support member mounted to rotate on the axle and constrained in rotation with the torsion tube; braking actuators carried by the support member for selectively pressing the disks together; and a drive member for selectively driving the support member in rotation; the support member carrying a secondary of a transformer having a primary arranged facing the support member while being stationary in rotation, the secondary being electrically connected to the actuators and the primary being adapted to being connected to a non-DC voltage source. 1. A device for braking/driving an aircraft wheel mounted to rotate on an undercarriage axle , the device comprising:a stack of disks comprising disks that are constrained in rotation with the wheel and that alternate with disks that are constrained in rotation with a torsion tube;a support member mounted to rotate on the axle and constrained in rotation with the torsion tube;braking actuators carried by the support member for selectively pressing the disks together; anda drive member for selectively driving the support member in rotation;wherein the brake actuators are electromechanical actuators and in that the support member carries a secondary of a transformer having a primary arranged facing the support member while being stationary in rotation, the secondary being electrically connected to the actuators and the primary being adapted to being connected to a non-DC voltage source.2. A device according to claim 1 , wherein each actuator comprises:a brushless DC electric motor;a pusher that is movable linearly and that is mechanically connected to the motor so as to move in response to rotation of the motor;a static contactor ...

METHOD OF CONTROLLING A BRUSHLESS DC MOTOR

The invention relates to a method of powering at least one brushless DC electric motor having a plurality of phases for powering, the method including the steps of associating a static contactor with the motor for taking input voltage pulses and delivering polyphase voltage pulses to the motor in a manner that is servo-controlled to the angular position of the rotor of the motor, and for generating from a DC voltage source voltage pulses of frequency that is fixed and at a duty ratio that is controllable, thereby forming the input voltage pulses to the static contactor. 1. A method of powering at least one brushless DC electric motor having a plurality of phases for powering , the method comprising the steps of:associating a static contactor with the motor for the purpose of taking an input voltage and delivering to the motor a polyphase voltage in a manner that is servo-controlled to the angular position of the rotor of the motor; andusing a DC voltage source to generate voltage pulses of frequency that is fixed and of duty ratio that is controllable so as to form the input voltage to the static contactor.2. An integrated electromechanical brake actuator comprising:a brushless DC electric motor;a linearly-movable pusher mechanically connected to the motor to move in response to rotation of the motor;a static contactor for delivering a polyphase voltage to the motor by interrupting and sequencing input voltage pulses as a function of information relating to the angular position of the rotor of the motor; andan angle position sensor for sensing the angular position of the rotor and delivering said information.3. An aircraft undercarriage including at least one axle receiving at least one wheel fitted with an electromechanical brake claim 2 , the brake including at least one brake actuator according to .4. An aircraft undercarriage according to claim 3 , wherein the brake includes a ring receiving the brake actuator(s) and mounted to rotate on the axle claim 3 , the ...

DEVICE FOR CONTROLLING TRAPDOORS CLOSING THE HOLD OF AIRCRAFT LANDING GEAR

A device for driving at least one door () of an aircraft undercarriage bay, the device comprising a permanent mechanical linkage () between the door and the undercarriage. The permanent linkage is arranged to transform a movement of the undercarriage between a stowed position and a deployed position, or vice versa, into a go-and-return movement suitable for causing the door to open and then to close during the movement of the undercarriage between said positions. 1442023242525201222a,ba,b. A device for driving at least one door () of an aircraft undercarriage bay , the device comprising a permanent mechanical linkage ( , , , ) coupled to the door and to the undercarriage and arranged to transform a movement of the undercarriage between a stowed position and a deployed position , or vice versa , into a go-and-return movement suitable for opening and then closing the door during the movement of the undercarriage between said positions , wherein the permanent linkage comprises a generator lever () hinged to an element () of the undercarriage and coupled to a stationary point () of the aircraft so as to present a go-and-return movement relative to the undercarriage element.22023. A device according to claim 1 , wherein the go-and-return movement of the generator lever () is transmitted to a rocker lever () claim 1 , also pivotally mounted on the undercarriage element claim 1 , the rocker lever being coupled to the door. The invention relates to a device for driving the doors that close the bay of an aircraft undercarriage.In general, the undercarriage and the doors of the corresponding bay are driven by distinct actuators. Sequential logic means guarantee that the doors open before the undercarriage is moved, and then that the doors close. In certain aircraft, such as the DC3, the doors of the main undercarriages are urged towards the open position by a resilient member that holds the doors open when the undercarriage is in the deployed position. On the undercarriage ...

METHOD FOR MANUFACTURING A FIBER-REINFORCED METAL CONNECTING ROD, AND RESULTING CONNECTING ROD

The present invention relates to a method of fabricating a metal link rod () that is longitudinally reinforced in its thickness by fiber reinforcement (), the method comprising the following steps: 162. A method of fabricating a metal link rod () that is longitudinally reinforced in its thickness by fiber reinforcement () , the method comprising the following steps:{'b': 11', '12, 'making a metal blank having at least one longitudinal housing (, ) leading into an edge face of the blank;'}{'b': '2', 'inserting fiber reinforcement () into the housing;'}{'b': '2', 'bonding the fiber reinforcement to the blank by metal diffusion around the fibers of the fiber reinforcement (); and'}{'b': '6', 'finishing the blank to obtain a link rod ();'}wherein the fiber reinforcement is inserted by means of the following operations:previously placing the fiber reinforcement on a support in the form of an angle bar; andinserting the angle bar carrying the corresponding fiber reinforcement in the housing.262. A method of fabricating a metal link rod () that is longitudinally reinforced in its thickness by fiber reinforcement () extending parallel to a longitudinal direction of the link rod , the method comprising the following steps:{'b': 1', '11', '12, 'making a metal section member () of constant section and including at least two longitudinal housings (, );'}{'b': '2', 'inserting a respective piece of fiber reinforcement () in each of the housings, the insertion of the fiber reinforcement comprising initially placing fiber reinforcement on a support in the form of an angle bar and then inserting each angle bar carrying the corresponding fiber reinforcement in one of the housings;'}applying hot isostatic compression to the assembly in order to obtain a reinforced bar;cutting up the reinforced bar in order to make a plurality of link-rod blanks; andfinishing each blank in order to obtain reinforced link rods.36. A link rod () suitable for being obtained by the method according to ...

Electromechanical actuator with dual excitation

A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

METHOD OF LIMITING A CURRENT SUPPLIED BY A DC POWER SUPPLY

The invention relates to a method of limiting a current isupplied by a DC power supply, the method comprising: 2. A method according to claim 1 , wherein the image current i is a current I obtained by differential filtering of the power supply current.3. A method according to claim 1 , wherein the switch control signal is an output from a comparator that compares the output from a resettable integrator with a current setpoint equal to the threshold current i claim 1 , the integrator receiving as input the current that is an image of the power supply current.4. A method according to claim 1 , applied to a power converter including a plurality of arms claim 1 , each of which arm comprises two switching cells in series claim 1 , each cell comprising a controlled switch connected in parallel with a diode claim 1 , and wherein claim 1 , for the duration of the period T claim 1 , a switch in one of the cells of one of the arms is kept closed while a switch of another one of the cells in another one of the arms is controlled in application of the periodic control step of . The invention relates to a method of limiting a current supplied by a direct current (DC) power supply.For various reasons, in particular for reasons of saving energy or protecting powered equipment, it is desirable to limit the current from a DC power supply.In particular, aircrafts are known that are provided with a power bus for delivering alternating current (AC) power generated by the alternators of the aircraft to electromechanical actuators that may consume said power. A converter transforms the AC power into DC power, and it is appropriate to ensure that the power consumed by the actuators is limited in order to save power.Various types of power limitation are known. In general, they rely on servo-control based on a model of the load to be powered. The servo-control seeks to limit the torque setpoint of the motor as a function of the speed of rotation of the motor, or else to limit the speed ...

HYDRAULIC BRAKE ARCHITECTURES FOR AIRCRAFTS FOR BRAKING AT LEAST ONE WHEEL OF THE AIRCRAFT

Aircraft hydraulic parking architecture, including a brake with a wheel braking hydraulic actuator, a pressure source (Alim) of high-pressure fluid, a normal braking hydraulic circuit (C) including at least pressure control servo valve with a supply port (P) connected to the pressure source (Alim), a return port (R), a utilization port (U) connected to the actuator, the brake architecture further including a parking hydraulic circuit (C) including a parking brake valve (PkBV) having an outlet port (Ps) selectively connected either to the pressure source (Alim) or a low-pressure return circuit (CR). 1) Hydraulic brake architecture for aircrafts , including at least one wheel , the architecture including:at least one brake provided with at least one hydraulic actuator for braking the wheel,at least one pressure source (Alim) adapted to deliver a hydraulic fluid at high pressure; and{'b': '1', 'a normal braking hydraulic circuit (C) includingat least one pressure control servo valve (BCV) including:a supply port (P) connected to the pressure source (Alim);a return port (R);a utilization port (U) connected to the braking hydraulic actuator; anddistribution means mounted so as to be mobile so as to connect the utilization port (U) either with the supply port (P) or with the return port (R);{'b': '2', 'the brake architecture further including a parking hydraulic circuit (C) including{'b': '1', 'a parking brake valve (PkBV) having an outlet port (Ps) adapted to be connected selectively either to the pressure source (Alim) or to a return circuit (CR) at a pressure that is low relative to said high pressure;'}{'b': '1', 'characterized in that the outlet port (Ps) of the parking brake valve (PkBV) is connected to the return port (R) of the pressure control servo valve (BCV).'}2) Brake architecture according to claim 1 , wherein the pressure source (Alim) includes a supply of hydraulic fluid at a pressure that is high relative to said low pressure and an accumulator of ...

METHOD OF CONTROLLING A COOLING DEVICE FOR A MACHINE TOOL

A method of controlling a cooling device for cooling a cutting tool in a machine tool. The method comprising the steps of: 1. A method of controlling a cooling device for cooling a cutting tool for a machine tool fitted with such a cutting tool , the cooling device comprising:a supply of machining fluid;a pump connected to the supply;a drive motor for driving the pump;a cooling nozzle for cooling the tool; andat least one machining fluid transfer duct connecting the pump to an input of the nozzle;the method comprising the steps of:{'b': '1', 'controlling the motor to drive the pump in such a manner that the pump feeds the nozzle with machining fluid at a constant flow rate D that is equal to a first flow rate setpoint (D) ;'}measuring a parameter P representative of a fluid outlet pressure from the nozzle; and{'b': 1', '1', '1, 'comparing an estimated outlet pressure Pestim as estimated from the parameter P with a first predetermined pressure threshold Ps, and controlling the motor so as to increase the fluid flow rate D as delivered by the pump if the estimated output pressure drops below the first pressure threshold Ps.'}2212. A method according to claim 1 , including the step of comparing the outlet pressure Pestim as estimated from the parameter with a second predetermined pressure threshold Ps claim 1 , and generating a worn nozzle alarm Alarm if the estimated outlet pressure Pestim drops below the second predetermined pressure threshold Ps.3323. A method according to claim 1 , including the step of comparing the outlet pressure Pestim as estimated from the parameter P with a third predetermined pressure threshold Ps claim 1 , and generating a clogged nozzle alarm Alarm if the estimated outlet pressure Pestim drops below the third predetermined pressure threshold Ps.4. A method according to claim 1 , including a step of determining the first flow rate setpoint D from a database B that contains claim 1 , for a plurality of given nozzle flow sections S claim 1 , ...

HYDRAULIC ACTUATOR WITH AUTOMATIC PURGING AT THE END OF ITS STROKE

A hydraulic actuator comprising a hollow body () defining a cylindrical cavity and a rod () which is mounted to slide within the body along a sliding axis between two end positions and which is integral with a piston sliding in a sealed manner within the cylindrical cavity in order to define two chambers (C, C). The rod defines an interior passage, connecting the two chambers, which has a valve () comprising a shut-off member () which is returned towards a seat () and closes the passage. The rod receives a push member () which can move relative to the rod between a position apart from the shut-off member () and a position forcing the shut-off member to open. The push member is constrained, when the rod reaches the end of its stroke, by the push member engaging with a portion () of the hollow body. 215262615133. Actuator according to claim 1 , wherein the push member ( claim 1 , ) comprises a needle () which is mounted so as to be able to slide within the rod in a direction parallel to the sliding axis of the rod claim 1 , the needle having a distal end close to the valve and a proximal end close to a crosspiece () which is floatingly mounted across the rod in a longitudinal slot () therein so as to project to either side of the rod such that claim 1 , when the rod reaches the end of its stroke claim 1 , ends of the crosspiece will bear against the facing portion () of the hollow body claim 1 , pushing the crosspiece relative to the needle such that said crosspiece in turn pushes the needle claim 1 , which in turn pushes the shut-off member of the valve to force it to open. The invention has for its subject a hydraulic actuator with automatic purging, allowing the air contained in one of the chambers thereof to be purged at least when the rod reaches the end of its stroke.Accordingly, what is proposed is a hydraulic actuator comprisingThus, the opening of the purge valve takes place automatically and systematically each time the rod reaches the end of its stroke. The ...

Metallic part provided with fibrous reinforcements and having a bevelled edge

The invention relates to a mechanical part made from a metal preform presenting at least one housing ( 5 ) that extends longitudinally relative to a preferred direction for the application of forces to the mechanical part in service, and into at least one piece of fiber reinforcement is inserted and then bonded to the blank by hot isostatic compression, wherein the piece of fiber reinforcement ( 10 ) presents a chamfered end ( 12 ).

METHOD FOR MANUFACTURING COMPOSITE PARTS COMPRISING BRAIDED FIBERS

A method of fabricating a composite material part such as a link. The method comprises the successive operations of applying reinforcing fiber layers () that are braided around a mandrel over all or part of the length of the mandrel, the layers being superposed one on another. The method includes a step of cutting an intermediate reinforcing fiber layer () after it has been applied, a step of withdrawing a cut portion prior to applying the following braided layer (), thereby locally building up an extra thickness of reinforcing layers on each portion of the cut layer that has remained in place, the extra thickness constituting local reinforcement of the part. Resin is subsequently injected into the various braided layers prior to the resin being polymerized in order to prepare a blank. The method applies in particular to the field of aviation. 1. A method of fabricating a composite material part , in particular a link , the method comprising successive operations ofapplying reinforcing fiber layers that are braided around a mandrel over all or part of the length of the mandrel, the layers being superposed one on another,cutting an intermediate reinforcing fiber layer after it has been applied,withdrawing a cut portion prior to applying the following braided layer, thereby locally building up an extra thickness of reinforcing layers on each portion of the cut layer that has remained in place, the extra thickness constituting local reinforcement of the part, andsubsequently injecting resin into the various braided layers prior to the resin being polymerized in order to prepare a blank.2. A method according to claim 1 , including claim 1 , prior to applying each intermediate layer for cutting claim 1 , applying a protective band arranged along the outline of the cutting so as to protect the previously-applied braided layer during the operation of cutting the intermediate layer.3. A method according to claim 1 , wherein the cutting is performed with equipment including ...

METHOD FOR DISTRIBUTING BRAKING TORQUE BETWEEN BRAKED WHEELS FITTED TO AT LEAST ONE UNDERCARRIAGE OF AN AIRCRAFT

A method for distributing braking energy between a group of braked wheels 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels comprising a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with means for measuring a thickness of the stack of discs, and in which: 2. Method according to claim 1 , in which the wheels are all fitted to the same undercarriage (N=1).3. Method according to claim 1 , in which claim 1 , for at least one of the brakes claim 1 , the individual braking setting Cis corrected with the aid of a torque correction (ΔC) dependent on an initial temperature (T) of the stack of discs before braking is applied claim 1 , so that the individual braking setting of the said brake is decreased if the initial temperature of the latter (C) is higher than a reference temperature.4. Method according to claim 3 , in which the reference temperature is the mean of the temperatures of the other brakes.6. Method according to claim 1 , in which the torque correction is bounded.7. Method according to claim 1 , in which the general braking setting is a braking torque setting. The invention relates to a method for distributing braking torque between braked wheels fitted to at least one undercarriage of an aircraft.On certain aircraft, and despite identical braking setting application, a heterogeneous distribution of the braking energy dissipated by the brakes may be observed, leading to heterogeneous disc stack heating and wear.Moreover, certain brakes may attain or exceed a critical temperature threshold forcing the airline operating the aircraft to wait until these brakes have fallen in temperature before being able to commence a new rotation. This waiting time represents a loss of earnings for the airline.The invention is aimed at proposing a method for distributing the braking energy between the brakes, allowing maximum avoidance of ...

AIRCRAFT BRAKING SYSTEM ARCHITECTURE

An aircraft braking system architecture having brakes with electromechanical actuators () for selectively applying a braking force to respective stacks of disks () in order to exert a braking torque on respective wheels. Included is at least one power module () that sends phase currents to the electromechanical actuators so that the latter can exert a braking force and at least one control module () for controlling the power module in response to a braking command such that appropriate phase currents are sent to the actuators so that these can develop the desired braking force. At least one power supply unit (), comprising means () of generating a high voltage (HVDC), supplies the power module with the high power it needs for powering the actuators. The unit () also has means () for generating a low voltage (LVDC) for powering at least the control module at a low voltage. 1. Aircraft braking system architecture comprising:{'b': 3', '2, 'brakes with electromechanical actuators () for selectively applying a braking force to respective stacks of disks () in order to exert a braking torque on respective wheels;'}{'b': '7', 'at least one power module () designed to send phase currents to the electromechanical actuators so that the latter can exert a braking force;'}{'b': '8', 'at least one control module () for controlling the power module in response to a braking command such that appropriate phase currents are sent to the actuators so that these can develop the desired braking force;'}{'b': 20', '21, 'at least one power supply unit () comprising means () of generating a high voltage (HVDC) to supply the power module with the high power it needs for powering the actuators;'}{'b': '22', 'characterized in that the power supply unit further comprises means () for generating a low voltage (LVDC) for powering at least the control module at a low voltage.'}2229. Braking system architecture according to claim 1 , in which the means () of generating a low voltage also power a ...

NON-DESTRUCTIVE METHOD FOR DETECTING MACHINING BURNS OF A VERY-HIGH-STRENGTH STEEL, AND COLOUR CHART FOR CALIBRATING MACHINING BURNS OF SAID STEEL

A method for efficient, industrialisable detection of machining burns of VHS steel. Machined steel is immersed in an aqueous solution of acids including hydrofluoric acid and nitric acid. To define a burn degree, a color chart for calibrating machining burns of VHS steel detected using the method is prepared. The color chart can include studs of the examined steel subjected to deliberate damage by excessive resurfacing actions (or other machining modes), then submerged in the acid solution. The resurfacing actions can be simulated by overheated thermal treatment, between an ageing temperature (for example 510° C. for steel) and a solution annealing temperature (950° C. for the steel). The samples are classified according to the grey level thereof resulting from the immersion and corresponding to a predetermined hardness and thus to a predetermined level of damage.

METHOD FOR POWERING AUTONOMOUS DRIVE MOTORS FOR AN AIRCRAFT

The invention relates to a method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated, characterized in that the method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator. 1456218. Method for powering an autonomous drive device () in an aircraft comprising a certain number of drive motors () for the wheels () for selectively driving the said wheels at least when the jet engines of the aircraft are not activated , the aircraft comprising an auxiliary power unit or APU () driving a first generator () for supplying power to the devices on the aircraft that need to be powered when the jet engines are not activated , characterized in that the method comprises the use of a second generator () dedicated to the power supply of the autonomous drive device , the second generator being disposed in parallel with the first generator so as to be driven by the APU and , when it operates as a motor under the action of power recovered by the autonomous drive device , so as to help the APU to drive at least the first generator.2. Method according to claim 1 , comprising the step for controlling the speed of the aircraft over the ground by powering the autonomous drive motors in order to accelerate the aircraft up to a requested speed if the speed of the aircraft is lower than the said requested speed claim 1 , and conversely claim 1 , to make the ...

TELESCOPIC ACTUATOR

The invention relates to a telescopic actuator comprising a body () defining a cylindrical cavity of longitudinal axis (X); a rod () mounted to slide telescopically in the cylinder along the said axis; a nut () secured to the rod; a lead screw () mounted on the cylinder to extend along and rotate about the said axis (X) and collaborate with the nut in such a way that a rotation of the lead screw causes a telescopic movement of the rod in the cylinder; means () for driving the rotation of the lead screw. 236135341. Actuator according to claim 1 , in which the actuating member comprises a linkage () extending longitudinally and mounted with the ability to move on the body () so that it can be moved parallel to itself in an orthoradial direction claim 1 , the linkage collaborating with a pin () secured to the locking sleeve () to carry the pin with it as it moves so as to cause the sleeve to rotate claim 1 , this being so regardless of the axial position of the rod relative to the body ().3361136. Actuator according to claim 2 , in which the linkage () is mounted with the ability to move on the body () by means of two cranks pivot-mounted on the body () and having ends connected to ends of the linkage ().41520. Actuator according to claim 1 , further comprising hydraulic damping means ( to ) for at least regulating the speed at which the rod enters the body when the nut has been disconnected from the rod.515431321819. Actuator according to claim 4 , in which the hydraulic damping means comprise a diaphragm () carried at the end of the lead screw () and collaborating in a fluidtight fashion with the rod () to define within the actuator two hydraulic chambers claim 4 , these being one chamber C in a hollow of the rod () and one chamber C in the remainder of the actuator claim 4 , the chambers being placed in fluidic communication by passage means ( claim 4 , ) that allow fluid to pass across the diaphragm.618192112. Actuator according to claim 5 , in which the passage ...

DEVICE FOR ROTATIONALLY COUPLING A RING WITH A WHEEL AND AIRCRAFT LANDING GEAR EQUIPPED WITH SUCH A DEVICE

The invention relates to a device () for rotationally coupling a wheel () with a ring () for driving the wheel () mounted so as to rotate coaxially with the wheel (). 1. A device for rotationally coupling a wheel with a ring for driving the wheel mounted so as to rotate coaxially with the wheel , the device comprising:a plurality of connecting members each extending in a direction contained in a plane perpendicular to the axis of rotation and forming an angle with a radial direction, the connecting members being pivotably mounted, on the one hand, on the wheel and, on the other hand, on the ring, each connecting member being elastically deformable in compression and in traction along an axis that passes through its two pivot-mounted ends.2. The device according to claim 1 , wherein each connecting member has a length which varies when subject to a force acting on the connecting member in opposition to a internal dissipative force.3. The device according to claim 2 , wherein each connecting member is a telescopic linkage which comprises two sliding parts connected respectively to the wheel and to the ring claim 2 , Belleville washers being arranged between the parts so as to generate a resilient and dissipative force during relative displacement of the parts.4. Landing gear comprising at least one axle for receiving at least one wheel associated with a member for driving the wheel comprising a ring mounted so as to rotate coaxially with the wheel and connected to controlled means for rotational driving thereof claim 1 , characterized in that the wheel and the ring are coupled together by a coupling device according to . The invention relates to a device for rotationally coupling a ring with a wheel and to aircraft landing gear equipped with such a device.In order to reduce fuel consumption as well as the noise levels and pollution produced by the operation of jet engines on the ground, it has been proposed to motorize the wheels of the aircraft so as to allow it to ...

METHOD FOR MAKING A CONNECTING ROD MADE OF A COMPOSITE MATERIAL COMPRISING A REINFORCED YOKE

The invention relates to a method for making a connecting rod () made of a composite material and including a yoke () for receiving a mechanical axis, said yoke () including two parallel arms () perpendicular to the mechanical axis, wherein the method comprises the steps of: making a mandrel () defining a single piece sufficiently rigid for receiving fiber layers (--); applying onto said mandrel () base fiber layers (-) and additional layers (-) interleaved between the base layers (-) at the yoke () in order to form an additional thickness thereon; inserting lugs () extending through the intermediate layers (-) and the base layers (-); injecting resin into the base layers (-) and the intermediate layers (-) and polymerizing said resin. 167777ab. A method for fabrication of a composite material connecting rod () comprising a yoke () adapted to receive a mechanical shaft , this yoke () comprising two parallel arms ( , ) perpendicular to the orientation (AZ) of the mechanical shaft , the method comprising the steps of:{'b': 11', '8', '8', '9', '9, 'i': a', 'e', 'a', 'd, 'fabricating a mandrel () forming a whole sufficiently rigid to receive layers of fibers (-, -);'}{'b': 11', '8', '8', '6', '9', '9', '8', '8', '7', '7', '7, 'i': a', 'e', 'a', 'd', 'a', 'e', 'a', 'b, 'applying to this mandrel () base layers (-) of reinforcing fibers constituting the connecting rod () and additional layers (-) interleaved between the base layers (-) at the level of the yoke (, , ) to constitute increased thicknesses there;'}{'b': 7', '7', '7', '13', '13', '9', '9', '8', '8', '7, 'i': a', 'b', 'a', 'b', 'a', 'd', 'a', 'e, 'at the level of each arm (, ) of the yoke (), inserting lugs (, ) passing through the interleaved layers (-) and the base layers (-) according to the orientation (AZ) of the mechanical shaft on which this yoke () is to be mounted;'}{'b': 8', '8', '9', '9, 'i': a', 'e', 'a', 'd, 'injecting resin into the base layers (-) and into the interleaved layers (-) and ...

METHOD OF PROTECTING AN AIRCRAFT LANDING GEAR WHILE THE AIRCRAFT IS BEING TOWED, AND PIN FOR COUPLING A TOWING BAR TO AN ORIENTABLE LOWER PART OF A LANDING GEAR

A method of protecting an aircraft undercarriage () while it is being towed by means of a tow bar () hitched to a steerable bottom portion of the undercarriage, the method including the step of generating an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold. The threshold is caused to vary as a function of an orientation of the steerable bottom portion of the undercarriage. 181. A pin () for coupling a tow bar to a steerable bottom portion of an undercarriage () having a pivot axis that is inclined relative to the vertical , wherein the pin comprises:{'b': '9', 'means () for measuring the forces to which the pin is subjected;'}{'b': '10', 'means () for measuring the angle of inclination of the pin relative to the horizontal;'}{'b': '11', 'means () for calculating a force threshold as a function of the orientation of the bottom portion of the undercarriage as deduced from the angle of inclination of the pin; and'}{'b': '11', 'means () for comparing a measured force with a force threshold and for generating an alarm if the measured forces reach or exceed a force threshold.'}2810. A pin () according to claim 1 , wherein the means for measuring the angle of inclination of the pin relative to the horizontal comprise an accelerometer () claim 1 , in particular a three-axis accelerometer.3113. A method of protecting an aircraft undercarriage () having a pivot axis that is inclined relative to the vertical claim 1 , while the undercarriage is being towed by means of a tow bar () hitched to the steerable bottom portion of the undercarriage claim 1 , the method including the step of using a pin according to either preceding claim in order to generate an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold.4. A method according to claim 3 , wherein said threshold is caused to vary as a function of the orientation of the steerable bottom ...

Method of controlling the steering of a steerable portion of an aircraft undercarriage

The invention relates to a method of controlling the steering of a steerable portion of an aircraft undercarriage that is fitted both with a steering member for steering the steerable portion and also with at least two angular position sensors for sensing the angular position of the steerable portion in order to deliver respective signals representative of the angular position of the steerable portion, wherein the steering member is controlled by means of servo-control using information that is representative of the angular position of the steerable portion. According to the invention, the information representative of the angular position that is used is a mean of the angular positions sensed by the at least two angular position sensors.

METHOD FOR MANAGING A BRAKING SYSTEM FOR AN AIRCRAFT FITTED WITH ELECTROMECHANICAL BRAKES

A braking system for an aircraft with electric brakes comprising plural electromechanical actuators (). The system comprises a braking control unit () delivering a normal braking setpoint () for one or more controllers () of the actuators, and selection means () for causing the braking system to operate in a plurality of modes. The system includes: a normal braking mode where the control unit generates a normal braking setpoint () for the controller(s); an ultimate braking mode, having priority over the normal braking mode, being responsive to a parking control member, and controlling actuators to respond to the actuation of the parking control member; and a parking braking mode, applied in response to the parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked in position. 1220211015. A braking system for an aircraft with electric brakes comprising a certain number of electromechanical actuators () , the systems comprising a braking control unit () delivering a normal braking setpoint () for one or more controllers () of the actuators , and selection means () for causing the braking system to operate in a plurality of modes , including:{'b': '21', 'a normal braking mode during which the braking control unit generates a normal braking setpoint () for the controller(s);'}an ultimate braking mode, having priority over the normal braking mode, that is applied in response to actuation of a parking control member, and in which the actuators are controlled to apply a force in response to the actuation of the parking control member, but in which they are not blocked in position; anda parking braking mode, applied in response to actuation of a parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked ...

METHOD OF MANAGING THE STEERING OF AIRCRAFT WHEELS, IN PARTICULAR IN THE EVENT OF A TIRE BURSTING OR DEFLATING

The invention relates to a method of managing the steering of aircraft undercarriage wheels carried by a steerable bottom portion of the undercarriage, the bottom portion being associated with steering control including a steering member suitable for steering the bottom portion of the undercarriage in response to a steering order. According to the invention, the method comprises the steps of: 1. A method of managing the steering of aircraft undercarriage wheels carried by a steerable bottom portion of the undercarriage , the bottom portion being associated with steering control including a steering member suitable for steering the bottom portion of the undercarriage in response to a steering order , wherein the method comprises the steps of: the pressure of one of the tires is less than a first predetermined threshold; and', 'the difference between the pressures of two of the tires is greater than a second determined threshold;, 'monitoring the pressures of the tires carried by the wheels, and in response to detecting at least one of the following eventsactivating the steering control if the steering control is not activated; andimplementing a steering control relationship that is modified compared with a nominal control relationship used when the tires are properly inflated.2. A method according to claim 1 , wherein the modified steering control relationship is modified relative to the nominal control relationship in application of one or more of the following actions:limiting the steering angle of the steerable portion of the undercarriage, preferably to ±45 degrees;limiting the maximum speed of the aircraft at which the wheels can be steered, preferably to less than 5 knots;limiting the angular speed at which the wheels can be steered, preferably to ±5 degrees per second;increasing the sensitivity of the control at small angles, preferably by a factor of 2;increasing the dead region around 0 degrees; andreducing the dynamics of the control. In general, aircraft ...

Aircraft landing gear of the rocker-arm and deformable-parallelogram type

The invention relates to an aircraft landing gear of deformable-parallelogram type, including: a leg including a casing ( 1 ) having a lower end on which a rocker arm ( 3 ) carrying at least one wheel is hinged by means of a pivot ( 2 ), a shock absorber ( 5 ) being connected between the rocker arm and the casing; two panels ( 10, 11 ) each hinged on the one hand on the structure of the aircraft and on the other hand on the leg, about parallel axes; According to the invention, one of the panels ( 11 ) is hinged on the leg whilst being connected to the casing by a pin on one end of the pivot ( 2 ) of the rocker arm.

METHOD FOR MAKING AN ARM FOR A HINGED STRUCTURE SUCH AS A ROCKER ARM FOR AN AIRCRAFT LANDING-GEAR STRUCTURE

The invention relates to a method for making an arm for a hinged structure such as an aircraft landing gear structure, this arm comprising a main body () extending in a longitudinal direction (AP; BP; CP), and including an interface () such as a yoke radially protruding from the main body, this method including the steps of: 212212. The method claimed in claim 1 , wherein the base (; ) has a generally tubular shape.310110172172324. The method claimed in claim 1 , wherein the mandrel (; ) is formed in line with the external face of the base (; ) with at least one sleeve (; ).42526122122324. The method claimed in claim 3 , wherein a sealed junction ( claim 3 , ) is made between the base (; ) and each sleeve ( claim 3 , ).512212192030130230. The method claimed in claim 4 , wherein the tubular base (; ) has a longitudinal section of beveled shape ( claim 4 , ) adapted to distribute the forces on the internal walls of the main body (; ; ).610110172172324. The method claimed in claim 2 , wherein the mandrel (; ) is formed in line with the external face of the base (; ) with at least one sleeve (; ). The present invention concerns a method for making an arm for a hinged structure such as rocker arm for an aircraft landing gear structure.A landing gear rocker arm takes the form for example of a link having at each of its ends an interface in the form of a bearing and at least one other, so-called intermediate, interface situated between its ends and taking the form of a yoke.In there is shown diagrammatically landing gear equipped with such a rocker arm. The landing gear comprises a main leg at the lower end of which is mounted a front end of a rocker arm comprising a bearing so that this rocker arm is able to pivot relative to the leg about a horizontal transverse axis.Two wheels of the landing gear are carried by a transverse shaft or axle mounted at the rear end of the rocker arm, i.e. at the level of its rear bearing , these wheels thus being mounted on either side of ...

MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS JOINED TO THE STRUCTURE OF THE AIRCRAFT IN AN ARTICULATED MANNER

An aircraft undercarriage comprising two rocker beams () carrying wheels and mounted to pivot on a common pivot (Y), the undercarriage including a shock-absorber device comprising two connecting rods (), each coupled to a respective one of the rocker beams, at least one of the connecting rods being telescopic and forming a shock absorber, the two connecting rods also being coupled to a rocker () pivotally mounted on a central pivot (). The common pivot of the rocker beams is secured to the structure of the aircraft and is mounted in a fixed position thereon, while the central pivot of the rocker is movable between a first position in which the rocker beams are in a landing position, and a second position in which the rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position. 11215678. An aircraft undercarriage comprising two rocker beams ( , ) carrying wheels and mounted to pivot on a common pivot (Y) , the undercarriage including a shock-absorber device comprising two connecting rods ( , ) , each coupled to a respective one of the rocker beams , at least one of the connecting rods being telescopic and forming a shock absorber , the two connecting rods also being coupled to a rocker () pivotally mounted on a central pivot () , wherein the common pivot of the rocker beams is secured to the structure of the aircraft and is mounted in a fixed position thereon , while the central pivot of the rocker is movable between a first position in which the rocker beams are in a landing position , and a second position in which the rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position.29. The aircraft undercarriage according to claim 1 , wherein the pivot of the rocker is mounted at the end of a panel () that is pivotally mounted on the structure of the aircraft to pivot between an active position in which the pivot of the rocker is substantially vertically in register with the ...

DEVICE FOR MANOEUVRING, ON THE GROUND, A DOOR OF AN AIRCRAFT LANDING GEAR

The invention relates to a device for manoeuvring, on the ground, a door of an aircraft landing gear, the door being linked with door manoeuvring means and uplock means for locking the door when it reaches the closed position, at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means which can be operated by an operator on the ground in order to control at least: 13123573407317. A device for manoeuvring , on the ground , a door () of an aircraft () landing gear () , the door () being linked with door manoeuvring means () and uplock means () for locking the door () when it reaches the closed position , at least one unlocking electromechanical actuator () arranged to act upon the uplock means () with a view to deactivating them during opening of the door () in flight , characterised in that the device comprises control means () which can be operated by an operator on the ground in order to control at least:{'b': 40', '7, 'an opening sequence during which the unlocking electromechanical actuator () is actuated in order to deactivate the uplock means (),'}{'b': '5', 'a closing sequence during which the manoeuvring means () are actuated in order to close the door again.'}217242526405. The device according to claim 1 , wherein the control means () comprise at least two control members ( claim 1 , claim 1 , ) arranged such that they must both be actuated to enable control of the unlocking electromechanical actuator () or control of the manoeuvring means ().32425262829. The device according to claim 2 , wherein at least one of the control members ( claim 2 , claim 2 , ) is arranged to control a state display member ( claim 2 , ) of the device.4242526242526. The device according to claim 3 , wherein the control means include at least three control members ( claim 3 , claim 3 , ) claim 3 , including the state ...

Device for connecting a gearmotor to an aircraft wheel in order to enable the wheel to be driven selectively by the gearmotor

A device for connecting a gear motor to an aircraft wheel, the device comprising: a casing rotatably carrying a shaft that is to be driven by the gear motor, and on which a pinion is mounted idle by means of a rolling bearing; a toothed ring for being constrained in rotation with the aircraft wheel and arranged to mesh permanently with the idle pinion; and rotation securing means for selectively constraining the idle pinion in rotation with the shaft. With this structure, a smooth bearing is interposed between the shaft and the rolling bearing of the idle pinion.

HYDRAULICALLY REGULATED ELECTROMAGNETIC ACTUATOR, AND LANDING GEAR FITTED WITH SUCH AN ACTUATOR FOR CONTROLLING SAME

The present invention relates to an electromechanical actuator comprising an electric motor () for driving an output shaft () in rotation via a reduction gear () and passive regulation means () allowing for control of the speed of rotation of the output shaft, and comprising a braking member (), arranged between an output of the reduction gear and the output shaft to be driven, said braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft, characterized in that the braking member is of hydraulic type and comprises fluid decantation means () between two chambers () decanting under the effect of the rotation of the output shaft through a selective drawing member () which, depending on the direction of rotation of the actuator, opposes two distinct resistances to the decantation of the fluid from one chamber to the other. 111420303033343541. Electromechanical actuator comprising an electric motor () for driving an output shaft () in rotation via a reduction gear () and passive regulation means () allowing for control of the speed of rotation of the output shaft , and comprising a braking member () , arranged between an output of the reduction gear and the output shaft to be driven , said braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft , characterized in that the braking member is of hydraulic type and comprises means () for transferring fluid between two chambers ( , ) , under the effect of the rotation of the output shaft through a selective drawing member () which , depending on the direction of rotation of the actuator , opposes two distinct resistances to the transfer of the fluid from one chamber to the other.23138333435. Actuator according to claim 1 , in which the braking member comprises a cylindrical casing () in which a fixed segment () and a rotating paddle () extend to define the two chambers ( claim 1 , ) and provoke the ...

METHOD FOR MANUFACTURING AN ARM IN COMPOSITE MATERIAL COMPRISING A TRANSVERSAL BEARING DESIGNED TO RECEIVE A FIXED OR ROTATING SHAFT

The invention relates to a method for manufacturing an arm () in composite material, this arm comprising a main body incorporating a bearing () designed to receive a shaft passing through it transversely, this method comprising the steps of: 1162216. A method for manufacturing an arm () in composite material comprising at least one bearing () designed to receive a fixed or rotating shaft passing through the arm () transversely , this method comprising the steps of:{'b': 11', '12, 'manufacturing at least one hub () by winding reinforcing fibres around a generally tubular support ();'}{'b': '14', 'manufacturing at least one sleeve ();'}{'b': 15', '11', '11', '14, 'manufacturing a mandrel () by attaching each hub () to at least one sleeve end so that each hub () extends transversely to each sleeve ();'}{'b': 21', '15', '17', '19, 'applying one or more braided reinforcing fibres () around this mandrel () and over its whole length with a machine () for braiding reinforcing fibres ();'}{'b': 21', '11', '21', '11, 'injecting and polymerizing resin into the layer or layers of braided fibres () and optionally into the wound fibre or fibres of the hub () in order to establish a cohesion rigidly binding at least the layers of braided fibres () with the hub () that they surround;'}{'b': 21', '12', '12, 'machining the layers of braided reinforcing fibres () at each end of the generally tubular support () in order to clear each end of this support ().'}21413121521. The method according to claim 1 , in which each sleeve () is manufactured with pieces of fabric of reinforcing fibres preimpregnated with resin claim 1 , in which the reinforcing fibres () wound around the generally tubular support () are also preimpregnated with resin claim 1 , and in which the mandrel () is prepolymerized before application of the layers of braided reinforcing fibres ().312. The method according to claim 1 , in which the reinforcing fibres are wound around the generally tubular support () so as to ...

METHOD FOR PRODUCING A MECHANICAL MEMBER FROM COMPOSITE MATERIAL, HAVING AN IMPROVED MECHANICAL PERFORMANCE UNDER TRACTION-COMPRESSION AND BENDING

The invention relates to a method for manufacturing a mechanical member in composite material, such as a connecting rod (), comprising successive operations of applying layers of reinforcing fibres braided all about a mandrel, comprising, between two operations of applying layers of braided reinforcing fibres, a step: 1. A method for manufacturing a mechanical member in composite material , such as a connecting rod in composite material , comprising successive operations of applying layers of reinforcing fibres braided all about a mandrel and over all or some of the length of this mandrel while being superposed radially one on top of the other , comprising , between two operations of applying layers of braided reinforcing fibres , a step:of placing, on the last layer of braided fibres, at least one element formed of pultruded reinforcing fibres, each pultruded element being oriented longitudinally and extending over at least one portion of the length of the mandrel;and of at least temporary attachment of each pultruded element to the last layer of braided reinforcing fibres,and in which once all the pultruded elements have been put in place and all the braided layers have been applied, a resin is injected into the various braided layers before the assembly is polymerized in order to form a rough part.2. The method according to claim 1 , in which each pultruded element is of the solid rod type.3. The method according to claim 1 , in which the attachment of each pultruded element applied against one and the same layer of reinforcing fibres is carried out with a product of the adhesive or resin type.4. The method according to claim 1 , in which the attachment of each pultruded element applied against one and the same layer of reinforcing fibres is carried out with a binding passed around the assembly formed by the mandrel with the layers that it supports and the pultruded elements to be attached.5. The method according to claim 1 , in which several pultruded elements ...

A DEVICE FOR UNLOCKING AN UNDERCARRIAGE IN A DEPLOYED POSITION, AND AN UNDERCARRIAGE FITTED WITH SUCH A DEVICE

A simple device for blocking and unblocking the locking member of an undercarriage having a breaker strut and including an unlocking device. The device comprises. a rotary actuator of axis parallel to the hinge axis of the links of the stabilizing member; a crank connected to a shaft of the actuator; a pawl hinged to the end of the crank and including a step; a pin secured to and at a distance from one of the links of the stabilizing member; and return means for urging the pawl towards the pin. The actuator is actuatable between a first angular position in which the pin is in contact with the pawl facing the step while the links are substantially in alignment, and a second angular position that the crank reaches when the step of the pawl has pushed back the pin, taking the links of the stabilizer member out of alignment. 17522233333336a,ba,baba,b. An aircraft undercarriage comprising a leg () hinged to the aircraft about a raising axis () , the leg being stabilized in the deployed position by a strut () comprising two hinged-together connecting rods () , the strut being maintained in its aligned position by a stabilizing member () comprising two hinged-together links () , one of the links () being hinged to the strut and another link () being hinged to the leg or to the aircraft , said links () being held in a substantially aligned and locked position , wherein the undercarriage includes an unlocking device () comprising:{'b': 3', '3, 'i': a,', 'b, 'a rotary actuator of axis parallel to the hinge axis of the links () of the stabilizing member;'}{'b': 63', '62, 'a crank () connected to a shaft of the actuator ();'}{'b': 64', '65, 'a pawl () hinged to the end of the crank and including a step ();'}{'b': 31', '3', '3, 'i': 'b', 'a pin () secured to and at a distance from one of the links () of the stabilizing member (); and'}{'b': 64', '31, 'return means for urging the pawl () towards the pin ();'}{'b': 63', '31', '64', '65', '63', '65', '64', '31', '3', '3', '3, 'i': ...

METHOD FOR OPERATING A MACHINE FOR PLAITING REINFORCING FIBERS

The invention relates to a method for the operation of a plaiting machine () that comprises a ring () carrying fiber spools () for plaiting layers () of fibers () about a mandrel () carried by a carrier () capable of movement along the axis (AX) of the ring (), wherein after plaiting the fibers () are cut in order to withdraw the mandrel (), and that comprises: a hub () carried by the carrier () and secured to the mandrel () while being mounted upstream therefrom; an operation for tightening the fibers () around the hub (; IS) with a link () surrounding said fibers () after the mandrel () has passed through the ring (); and in which the fibers () are cut between the mandrel () and the hub () before withdrawing the mandrel (). 1. A method of operating a braiding machine including a ring carrying spools of reinforcing fiber for successively braiding a plurality of layers; of reinforcing fibers around a unique mandrel moved several times through the ring or around a plurality of mandrels moved one after the other through the ring , each mandrel being carried by a support movable through the ring along an axis of the ring , in which method , after passing the mandrel through the ring , the reinforcing fibers are cut downstream of this mandrel to be able to remove it , characterized in that:a hub carried by the support and fastened to the mandrel is mounted downstream of the latter;the reinforcing fibers are tightened around the hub by means of a tie around these reinforcing fibers after passing the mandrel through the ring; andthe reinforcing fibers are cut between the mandrel and the hub before removing the mandrel.2. The method claimed in claim 1 , wherein a hub is used including at least one circumferential groove forming an imprint in which is accommodated the tie for attaching the reinforcing fibers.3. The method claimed in claim 1 , wherein a hub is used having a shape that is at least partly conical.4. The method claimed in claim 1 , wherein a hub is used having ...

METHOD OF MANAGING PARKING BRAKING IN A BRAKING SYSTEM FOR A VEHICLE FITTED WITH ELECTRIC BRAKES

The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of: 1. A method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake , the method comprising the steps of:establishing a series of direct adjustment tables for parking braking, corresponding to braking situations at different energy levels;when applying parking braking, selecting a direct adjustment table corresponding to a braking situation preceding the application of parking braking; anddirectly adjusting a parking braking force in application with the selected direct adjustment table;wherein the method comprises the steps of:selecting a first direct adjustment table and applying it for a predetermined initial application time;making a first adjustment;comparing a real change in position of the pusher with a theoretical change in position of the pusher obtained from the direct adjustment tables after an application time equal to the initial application time; andselecting a second direct adjustment table for which the theoretical change in position of the pusher is the closest to the real change in position.2. A method according to claim 1 , wherein the first direct adjustment table is a high energy level table.3. A method according to claim 2 , wherein the first direct adjustment table is the table having the highest energy level.4. A method according to claim 1 , comprising the steps of:establishing for each braking energy level different direct adjustment tables as a function of ambient temperature; andselecting the direct adjustment ...

MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS AND A DEFORMABLE PARALLELOGRAM STRUCTURE

An aircraft landing gear, characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear, the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams, and at least one of the connecting rods being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocking crossbar pivotally mounted on a central pivot, the pivots of the rocker beams and the central pivot of the crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system. 1. An aircraft landing gear , characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear , the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams , and at least one of the connecting rods being telescopic and forming a shock absorber , the two connecting rods also being coupled to a rocking crossbar pivotally mounted on a central pivot , the pivot of the rocker beams and the central pivot of the rocking crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system.2. The aircraft landing gear according to claim 1 , wherein the rocker beams are hinged to the leg via two distinct respective pivots.3. The aircraft landing gear according to claim 1 , wherein the connecting rod that forms a shock absorber includes a cylinder that is coupled ...

LATCHING BOX WITH AN UNLOCKING ACTUATOR HAVING A CYLINDRICAL CAM

The invention relates to a latching box for selectively retaining a movable element such as an undercarriage or a hatch in position, the box comprising a body carrying: 1. A latching box for selectively retaining a movable element such as an undercarriage or a hatch in position , the box comprising a body carrying:a hook pivotally mounted about a first pivot axis between an engaged position and a disengaged position relative to the movable element;a locking member pivotally mounted about a second pivot axis parallel to the first pivot axis to pivot between a position for blocking the hook in the engagement position and a release position for releasing the hook; andat least one cam actuator in which the cam co-operates operationally with the locking member to move it towards the release position;wherein the cam of the actuator is a cylindrical cam rotatable about an axis of rotation orthogonal to the first and second pivot axes.2. A latching box according to claim 1 , wherein the cylindrical cam co-operates with a first arm of a rocker pivotally mounted on the box about a third pivot axis parallel to the first and second pivot axes claim 1 , the rocker having a second arm co-operating with the unlocking member to push it back when the cam is rotated.3. A latching box according to claim 1 , wherein the actuator includes claim 1 , in addition to the cylindrical cam claim 1 , a certain number of rotary elements including at least one motor claim 1 , said rotary elements all rotating about axes of rotation parallel to the axis of the cam.4. A latching box according to claim 3 , wherein the actuator has two freewheels linked in rotation with a shaft carrying the cam claim 3 , the freewheels being driven by respective electric motors.5. A latching box according to claim 4 , wherein the cam is carried by a shaft that includes a toothed wheel engaged by stepdown gearing itself engaged by the freewheels. The invention relates to a latching box for retaining undercarriages ...

Process for manufacturing a mechanical member made of a composite having increased mechanical strength

The invention relates to a method of fabricating a mechanical member, the method including a plurality of operations of braiding and depositing layers of braided reinforcing fibers on a mandrel ( 11 ) by using braiding machine. Each operation comprises braiding a braided layer and depositing it by moving the mandrel ( 11 ) along a central axis of the braiding machine. Each of the various superposed braided layers comprises both longitudinal fibers ( 12, 12 G) that are parallel to a main direction of the mandrel ( 11 ), and interlacing fibers that are inclined. At least one operation is configured to form and deposit a braided layer having, in at least one cross-section of the member, a density of longitudinal fibers that differs depending on whether consideration is given to one angular region (S 1 ) or another angular region (S 2 ) of the same extent around the center of gravity (G) of the mandrel ( 11 ) in the section under consideration. The invention applies to fabricating structural elements in the field of aviation.

DEVICE FOR SELECTIVELY CONNECTING A GEARMOTOR TO AN AIRCRAFT WHEEL TO ENABLE THE WHEEL TO BE DRIVEN SELECTIVELY BY THE GEARMOTOR

A device, which connects a gearmotor to an aircraft wheel, comprising: a casing rotatably carrying a shaft driven by the gearmotor, the shaft having a fluted portion on which a gearwheel is mounted to slide along a longitudinal axis of the shaft without rotating relative to the shaft; a toothed ring for constraining to rotate with the aircraft wheel; and means for moving the gearwheel axially between a retracted position (disengaged from the toothed ring) and an engaged position (gearwheel meshes with the toothed ring). The means for moving comprises a hollow screw-and-nut assembly extending around the shaft, one of the elements being axially secured to the gearwheel but prevented from rotating by an anti-rotation member, and the other element of the screw-and-nut assembly being rotatably mounted inside the casing to be driven selectively by an electric motor so that rotating the electric motor causes the gearwheel to move axially. 1. A device for connecting a gearmotor to an aircraft wheel , the device comprising:a casing rotatably carrying a shaft that is to be driven by the gearmotor, the shaft having a fluted portion on which a gearwheel is mounted to slide along a longitudinal axis of the shaft without rotating relative to the shaft;a toothed ring for constraining to rotate with the aircraft wheel; andmeans for moving the gearwheel axially between a retracted position in which it is disengaged from the toothed ring and an engaged position in which the gearwheel meshes with the toothed ring;wherein the means for moving the gearwheel axially comprise a hollow screw-and-nut assembly extending around the shaft, one of the elements of the screw-and-nut assembly being axially secured to the gearwheel but prevented from rotating by an anti-rotation member, and the other element of the screw-and-nut assembly being rotatably mounted inside the casing to be driven selectively by an electric motor so that rotating the electric motor causes the gearwheel to move axially.2. ...

CONTROL BOX

The invention provides a control box for selectively delivering orders to receivers (), the control box comprising: 1812. A control box for selectively delivering orders to receivers ( , ) , the control box comprising:{'b': 14', '24, 'a shaft () mounted to turn about an axis of rotation (X), while being capable of sliding along said axis (X) between a rest position towards which it is urged by return means (), and an active position;'}{'b': 16', '11', '14', '14, 'order delivery means (, ) co-operating with the shaft () to deliver orders as a function of the angular position of the shaft ();'}{'b': '15', 'rotary drive means () for causing the shaft to turn; and'}{'b': 23', '27', '28', '27', '28', '15, 'safety actuation means () for causing the shaft to slide from the rest position in which anti-rotation means (, ) prevent the shaft from turning to the active position in which the anti-rotation means (, ) leave the shaft free to turn under drive from the rotary drive means ().'}22728271428282714282714. A control box according to claim 1 , wherein the anti-rotation means ( claim 1 , ) comprise longitudinal grooves () formed in a portion of the shaft () and co-operating with a stationary finger () of the control box so that the finger () is engaged in one of the grooves () when the shaft () is in the rest position and the finger () is disengaged from the grooves () when the shaft () is in the active position.3412714. A control box according to claim 2 , also including at least one retractable finger () adapted to penetrate selectively into one of the grooves () in order to prevent the shaft () from turning.44140. A control box according to claim 3 , wherein the retractable finger () is a moving portion of an electromechanical solenoid actuator ().53637381414. A control box according to claim 1 , further including detector means ( claim 1 , claim 1 , ) adapted to co-operate with the shaft () in order to detect whether the shaft () is in the rest position or in the active ...

METHOD OF EXTENDING AIRCRAFT UNDERCARRIAGES IN EMERGENCY MODE

A method of actuating undercarriage latching boxes and associated hatch latching boxes of an aircraft in an emergency mode, the latching boxes having at least one feed port and at least one unlatching member that is operable when the port is fed with fluid under pressure, the aircraft also being provided with a hydraulic braking circuit. The method includes connecting at least one tapping circuit to the braking circuit of the aircraft in association with an isolation valve that is kept, in a normal mode, in an isolation state and that can be controlled to be placed in an open state in which at least some of the feed ports of the latching boxes are fed by the tapping circuit connected to the braking circuit. 1. A method of actuating undercarriage latching boxes and associated hatch latching boxes of an aircraft in an emergency mode , the latching boxes having at least one feed port and at least one unlatching member that is operable when the port is fed with fluid under pressure , the aircraft also being provided with a hydraulic braking circuit , wherein the method includes connecting at least one tapping circuit to the braking circuit of the aircraft in association with an isolation valve that is kept , in a normal mode , in an isolation state and that can be controlled to be placed in an open state in which at least some of the feed ports of the latching boxes are fed by the tapping circuit connected to the braking circuit.2. The method according to claim 1 , wherein the isolation valve is located directly in the tapping circuit.3. The method according to claim 1 , wherein the aircraft has a single braking circuit claim 1 , and wherein the single tapping circuit that is connected thereto feeds the ports of all of the latching boxes.4. The method according to claim 1 , in which the aircraft has two hydraulic circuits defining two braking circuits claim 1 , wherein a single tapping circuit is connected to one of the braking circuits in order to feed the ports of all ...

ELECTRIC BRAKE FOR AN AIRCRAFT WHEEL, THE BRAKE INCLUDING AN ELECTROMECHANICAL ACTUATOR FITTED WITH A TEMPERATURE SENSOR

An electric brake for an aircraft wheel comprising a support formed by a torsion tube and by an actuator-carrier , a stack of disks mounted around the torsion tube , electromechanical actuators carried by the actuator-carrier , each actuator comprising an electric motor and a pusher , the electric motor being adapted to move the pusher facing the stack of disks in order to apply a braking force selectively to the stack of disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stack of disks. The temperature measurement means comprises at least one temperature sensor arranged in the pusher of one of the electromechanical actuators so as to be located in the immediate proximity of the stack of disks when the pusher is brought into contact therewith. 1. An electric brake for an aircraft wheel , the brake comprising:{'b': 4', '5', '6, 'a support () that may be formed by a torsion tube () and by an actuator-carrier ();'}{'b': 7', '5, 'a stack () of disks mounted around the torsion tube ();'}{'b': 8', '6', '12', '14', '12', '14', '7', '7, 'at least one electromechanical actuator () carried by the actuator-carrier (), each actuator comprising an electric motor () and a pusher (), the electric motor () being adapted to move the pusher () facing the stack () of disks in order to apply a braking force selectively to the stack () of disks; and'}{'b': '7', 'temperature measurement means for measuring a temperature representative of a temperature that exists in the stack () of disks;'}{'b': 18', '14', '8', '7', '14, 'the electric brake being characterized in that the temperature measurement means comprise at least one temperature sensor () arranged in the pusher () of one of the electromechanical actuators () so as to be located in the immediate proximity of the stack () of disks when the pusher () is brought into contact therewith.'}281814. An electric brake according to claim 1 , wherein each actuator () is ...

METHOD OF RESETTING THE ORIENTATION OF AN AIRCRAFT UNDERCARRIAGE HAVING A STEERABLE BOTTOM PORTION

The invention provides a steering resetting method for an aircraft undercarriage that includes a leg in which a steerable bottom portion is mounted to slide against a suspension force generated by a shock absorber, the undercarriage being provided with a controllable steering member for causing the steerable bottom portion to swivel in response to an angular position setpoint, the undercarriage also including at least one angular position sensor adapted to generate an electrical signal representative of the angular position of the steerable bottom portion and suitable for use in controlling the steering member; the method comprises the step, performed when the steerable bottom portion is in an indexed angular position while the aircraft is in flight and the undercarriage is fully extended, of setting the electrical signal from the sensor to a determined reset value. 1. A steering resetting method for an aircraft undercarriage that includes a leg in which a steerable bottom portion is mounted to slide against a suspension force generated by a shock absorber , the undercarriage being provided with a controllable steering member for causing the steerable bottom portion to swivel in response to an angular position setpoint , the undercarriage also including at least one angular position sensor adapted to generate an electrical signal representative of the angular position of the steerable bottom portion and suitable for use in controlling the steering member; the method comprising the step , performed when the steerable bottom portion is in an indexed angular position while the aircraft is in flight and the undercarriage is fully extended , of setting the electrical signal from the sensor to a determined reset value.2. A method according to claim 1 , wherein the reset value is equal to the difference between a value of the non-reset signal as measured while the steerable bottom portion of the undercarriage is in the indexed angular position and a value of the non-reset ...

DEVICE FOR GUIDING AND HOLDING A CABLE WITHIN A PIPE

The invention provides a device () for guiding a cable () in a duct (), the device () being characterized in that it comprises at least one guide tube () receiving the cable () and at least one expandable clamp () secured to one end () of the tube (), the expandable clamp () being deployed so as to be blocked against the inside wall of the duct () in order to hold the tube () in the duct (). The device serves to guide and hold the cable in the duct without damaging the duct. 128842a,b. A device () for guiding a cable () in a duct () , the device () comprising:{'b': 12', '8', '8, 'i': a,', 'b, 'at least one guide tube () receiving the cable (); and'}{'b': 13', '12', '12, 'i': 'a', 'at least one expandable clamp () secured to one end () of the tube (),'}{'b': 13', '4', '12', '4, 'wherein the expandable clamp () being deployed so as to be blocked against an inside wall of the duct () in order to hold the tube () in the duct ().'}213204. The device according to claim 1 , wherein the expandable clamp () includes at least one movable pad () arranged to exert a force on the wall of the duct ().3. The device according to claim 1 ,{'b': 13', '18', '25, 'wherein the expandable clamp () comprises a frame () including a central opening (), and'}{'b': 12', '4', '2', '4', '13, 'wherein the tube () is arranged substantially against the wall of the duct () so that the device () allows access to the inside of the duct () through the expandable clamp ().'}4191920214ab,. The device according to claim 2 , wherein the pads ( claim 2 , ) have soles () made of elastomer that bear against the inside wall of the duct ().51328338812a,b. The device according to claim 1 , wherein the expandable clamp () includes blocking means ( claim 1 , ) for blocking the cable () relative to the tube ().6. An aircraft landing gear including a device according to .788410a,b. A method of guiding a cable () in a duct () having an entry and an outlet orifice () for the cable claim 1 , the method comprising the ...

Electromechanical braking system for an aircraft

The invention relates to an aircraft braking system having brakes with electromechanical braking actuators (103) adapted to press selectively against associated stacks of disks in order to generate a braking torque on associated wheels of the aircraft; at least one control module (130) receiving braking setpoints and responding by generating a braking command (121); and at least one power module (120) responding to the braking command by delivering AC power to the motors of actuators connected to the power module so that the motors develop a braking force corresponding to the braking setpoints. According to the invention, the control module includes a digital processor stage (131) and an analog processor unit (135).

COUPLING DEVICE BETWEEN TWO ROTARY ELEMENTS

The invention relates to a device for coupling together two elements mounted to rotate about a common axis of rotation (X) in order to enable one of the elements to be selectively driven in rotation by the other, the device comprising two members (), each secured to a respective one of the elements for coupling together, the elements being axially movable relative to each other between a remote position in which the members do not co-operate and the elements are decoupled, and an engaged position in which the members co-operate with each other in order to provide a rotary connection between the two elements. According to the invention, one of the members forms a plate () having a face (P) perpendicular to the axis of rotation and in which a plurality of housings () are formed, the housings extending in radial directions; the other one of the elements carrying rollers () that are mounted to rotate about radial axes to project from said element so that each of them can penetrate into any one of the housings when the members are engaged and can co-operate with the side faces () of the housing in order to provide a rotary connection between the two members. 1343152314. A device for coupling together two elements mounted to rotate about a common axis of rotation (X) in order to enable one of the elements to be selectively driven in rotation by the other , the device comprising two members ( , ) , each secured to a respective one of the elements for coupling together , the elements being axially movable relative to each other between a remote position in which the members do not co-operate and the elements are decoupled , and an engaged position in which the members co-operate with each other in order to provide a rotary connection between the two elements , the device being characterized in that one of the members forms a plate () having a face (P) perpendicular to the axis of rotation and in which a plurality of housings () are formed , the housings extending in radial ...

METHOD OF USING AND RENOVATING A DISK FROM A STACK OF DISKS OF A VEHICLE BRAKE

The invention relates to a method of using and renovating a disk () from a stack of disks () of a vehicle brake, the method comprising the steps of using the disk during a plurality of lives and of compensating for loss of thickness after each life by assembling the disk with a complementary portion. 171072073079. A method of using and renovating a disk from a stack of disks ( , , , ) of a vehicle brake , the method comprising the steps of using the disk during a plurality of lives () and of compensating a reduction in thickness after each life by assembling the disk with a complementary portion , in compliance with the following arrangements:{'b': '12', 'after a first life, at the end of which the disk has a thickness lying in the range 60% to 90% of an initial thickness of the disk, surfacing both faces of the disk and assembling it on one side with a first complementary portion () so that the assembly has a thickness substantially equal to the initial thickness of the disk;'}{'b': '14', 'after a second life, at the end of which the disk has a thickness greater than 50% of the initial thickness, surfacing the disk to a thickness substantially equal to 50% of the initial thickness and assembling it with a second complementary portion () so that the assembly has a thickness substantially equal to the initial thickness of the disk;'}{'b': '16', 'after a third life, at the end of which the disk has a thickness lying in the range 40% to 10% of the initial thickness, surfacing the disk and assembling it with a third complementary portion () so that the assembly has a thickness substantially equal to the initial thickness of the disk; and'}after a fourth life, discarding the disk.29. A method according to claim 1 , wherein the disk () presents thicknesses at the beginning of the second life and at the beginning of the fourth life that are complementary.312. A method according to claim 2 , wherein the first complementary portion () is another disk at the beginning of its ...

METHOD OF MANAGING SYSTEMS ASSOCIATED WITH THE LANDING GEAR OF AN AIRCRAFT

The invention relates to a method of managing an aircraft having undercarriages carrying a certain number of braked wheels, the aircraft including: 1. A method of managing an aircraft having undercarriages carrying a certain number of braked wheels , the aircraft including:a system for operating the undercarriages including raising actuators and latching actuators for the undercarriages and the associated hatches;a braking system including braking actuators for braking the wheels of the aircraft;at least one control unit for controlling the operation of the undercarriages and the braking; andat least one maintenance unit for selectively controlling at least some of the actuators of said systems while the aircraft is in a switched-off state during maintenance operations on one or another of the systems;wherein the method includes the step of activating the maintenance unit while the aircraft is not in the switched-off state in order to use the maintenance unit for actuating actuators connected to the maintenance unit, in particular in the event of a failure of the control unit.2. A method according to claim 1 , wherein the maintenance unit is activated in response to at least:a manual activation order; and/ora signal coming from a control unit indicating that the control unit has failed.3. A method according to claim 1 , including the use of a plurality of control units suitable for controlling the operating and braking actuators claim 1 , in which the maintenance unit is activated in response at least to:a manual activation order; and/oran AND combination of signals coming from all of the control units and indicating that each corresponding control unit has failed.4. A method according to claim 1 , wherein the maintenance unit is powered with the help of the battery of the aircraft.5. A method according to claim 1 , wherein the actuators controlled by the maintenance unit are connected thereby by specific power supply channels. The invention relates to a method of ...

METHOD OF MANAGING THE BRAKING OF AN AIRCRAFT TO LIMIT ITS PITCH

The invention relates to a method of managing the braking of an aircraft having at least one controllable brake for braking the aircraft when the aircraft is on the ground and as a function of a braking setpoint C, wherein the method includes correcting the braking setpoint as a function of the pitch angle θ of the aircraft during braking. 1. A method of managing the braking of an aircraft having at least one controllable brake for braking the aircraft when the aircraft is on the ground and as a function of a braking setpoint , the method including correcting the braking setpoint as a function of a pitch angle of the aircraft during braking , and wherein said correction is performed by subtracting a correction value from the braking setpoint , which correction value is:calculated as a function of the pitch angle if the aircraft is running at a ground speed less than a threshold speed; andset to zero if the ground speed is greater than or equal to the threshold speed.2. A method according to claim 1 , wherein the correction of the braking setpoint includes a step of limiting any variation to the correction of the setpoint. The invention relates to a method of managing the braking of an aircraft so as to limit its pitch.Most aircraft have landing gear with a plurality of undercarriages having the essential functions firstly of absorbing a large portion of the kinetic energy due to the vertical component of the speed of the aircraft on landing, and secondly of enabling the aircraft to travel on the ground, in particular during the braking stage to which the present invention relates.A distinction is generally made between so-called “main” landing gear that supports the major portion of the weight of the aircraft, and so-called “auxiliary” landing gear that serves to balance the aircraft on the ground and to make it more maneuverable. On most modern aircraft, the main landing gear is situated close to the center of gravity of the airplane under the wing or under the ...

BRAKE FOR AN AIRCRAFT WHEEL

A brake for an aircraft wheel comprising an actuator-carrier that carries at least one electromechanical actuator having a pusher that is movable along a direction parallel to an axis of rotation X of the wheel and facing friction elements in order to apply a braking force selectively against the friction elements The actuator-carrier and the actuator include guide means for guiding the actuator while being installed on the actuator-carrier in a radial direction Y until it reaches a service position. The guide means forms a bearing surface for transmitting braking forces from the actuator to the actuator-carrier. Position-holder means holds the position of the actuator in its service position and comprises a strap fastened to the actuator-carrier to prevent the actuator from moving on the actuator-carrier in the service position. 11415192710710141525321514373737141514. A brake for an aircraft wheel , the brake comprising an actuator-carrier () that carries at least one electromechanical actuator () having a pusher () that is movable along a direction parallel to an axis of rotation (X) of the wheel () and facing friction elements ( , ) in order to apply a braking force selectively against the friction elements ( , ) , the actuator-carrier () and the actuator () including guide means ( , ) for guiding the actuator () while it is being installed on the actuator-carrier () in a radial direction (Y) until it reaches a service position , said guide means forming a bearing surface suitable for transmitting braking forces from the actuator to the actuator-carrier , and position-holder means () for holding the position of the actuator in its service position , the brake being characterized in that the position-holder means () comprise a strap () fastened to the actuator-carrier () in order to prevent the actuator () from moving on the actuator-carrier () in the service position.237143939. A brake according to claim 1 , wherein the strap () is removable radially and is ...

DEVICE FOR BRAKING AND ROTATING AN AIRCRAFT WHEEL

The invention relates to a device for braking and driving rotation of a wheel () mounted to rotate on an aircraft landing gear axle, the device comprising: a torsion tube () adapted to be mounted to rotate on the axle that carries the wheel; a stack of disks () including first disks having means for constraining them in rotation with the wheel and second disks arranged in alternation with the first disks and including means for constraining them in rotation with the torsion tube; a ring () carrying braking actuators () that are adapted to act selectively to press the disks against one another, the ring being constrained in rotation with the torsion tube in order to form a rotary portion () of the device; a rotary drive member () for driving rotation of the rotary portion (); and finally blocking means () for selectively blocking rotation of the rotary portion, which means are independent of the rotary drive member. 11. A device for braking and driving rotation of a wheel () mounted to rotate on an aircraft landing gear axle , the device comprising:{'b': '26', 'a torsion tube () adapted to be mounted to rotate on the axle that carries the wheel;'}{'b': '30', 'a stack of disks () including first disks having means for constraining them in rotation with the wheel and second disks arranged in alternation with the first disks and including means for constraining them in rotation with the torsion tube;'}{'b': 23', '24', '20, 'a ring () carrying braking actuators () that are adapted to act selectively to press the disks against one another, the ring being constrained in rotation with the torsion tube in order to form a rotary portion () of the device; and'}{'b': 40', '20, 'a rotary drive member () for driving rotation of the rotary portion ();'}{'b': 51', '52, 'the device being characterized in that it also includes blocking means (, ) for selectively blocking rotation of the rotary portion, which means are independent of the rotary drive member.'}2202040. A device ...

METHOD OF FABRICATING A FRICTION PART BASED ON C/C COMPOSITE MATERIAL

A fiber preform made of carbon fibers is densified with a carbon matrix in a plurality of separate stages. After a first densification stage and before the end of carbon matrix densification, ceramic particles are introduced in order to be dispersed within the composite material part. The introduced particles have a mean size of less than 250 nm and are made at least of a ceramic compound of an element selected from titanium, yttrium, tantalum, and hafnium, the ceramic compound being selected from oxides, nitrides, and mixed oxide, carbide, and/or nitride compounds that do not react with carbon at a temperature of less than 1000° C. and that have a melting point higher than 1800° C. 1. A method of fabricating a friction part based on carbon/carbon composite material , the method comprising:making a fiber preform out of carbon fibers;densifying the preform with a carbon matrix, densification being performed in a plurality of separate stages, and during the fabrication process, introducing ceramic particles into the partially densified preform, wherein the introduction of ceramic particles takes place after a first stage of densifying the fiber preform with the carbon matrix and before the end of densifying with the carbon matrix, and comprises impregnating with a colloidal solution of at least one ceramic compound, or impregnating with a sol-gel type solution containing at least one ceramic compound precursor, followed before continuing with the densification by means of the carbon matrix, by a treatment for transforming the precursor into a ceramic compound by reacting with the carbon of the matrix without complete transformation into carbide,wherein in order to obtain ceramic compound particles having an average size of less than 250 nm, the ceramic compound constituting the particles being at least one compound of an element selected from titanium, yttrium, tantalum, and hafnium, and being selected from oxides, nitrides, and mixed oxide, carbide, and/or nitride ...

EQUIPMENT FOR MEASURING THE INFLATION PRESSURE OF A TIRE OF A VEHICLE WHEEL

The invention provides measurement equipment for measuring the inflation pressure of a tire of a vehicle wheel , the equipment comprising: 11. Measurement equipment for measuring the inflation pressure of a tire of a vehicle wheel () , the equipment comprising:{'b': '16', 'a body () defining an internal volume;'}{'b': 19', '16', '6', '2', '4, 'a communication orifice () for putting the inside volume of the body () into communication with an inflation chamber () situated between a rim () and a tire () of the wheel and containing an inflation gas;'}{'b': 25', '125', '325', '16', '26', '27', '19', '25', '125', '325, 'an indicator member (; ; ) slidably mounted in the body () so as to define a gastight separation between a first chamber () containing a given quantity of a reference gas and a second chamber () into which the communication orifice () leads, such that the indicator member (; ; ) is subjected to opposing pressures that exist in each of the chambers; and'}{'b': 30', '143', '243', '244', '345', '451', '30, 'position-identification means (; ; , ; ; ) for identifying the position of the indicator member in the body, the position-identification means including a sensor () for sensing the position of the indicator member.'}2450. Tire pressure measurement equipment according to claim 1 , wherein the position-identification means comprise a window () in the body enabling the position of the indicator member to be viewed.3345325. Tire pressure measurement equipment according to claim 1 , wherein the position-identification means comprise a dial comparator () arranged on the body and including a reference mark and a pointer mechanically connected to the indicator member () so that the position of the pointer relative to the mark indicates the inflation pressure.430. Tire pressure measurement equipment according to claim 1 , wherein the position sensor () comprises a passive linear movable sensor of the inductor claim 1 , or capacitor claim 1 , or potentiometer type. ...

DEVICE AND METHOD FOR SPREADING A CABLE OF CARBON FIBERS OR CARBON YARNS

A device for spreading a cable of carbon fibers or carbon yarns, includes a disk mounted on a rotary shaft and provided with at least one comb adapted to comb a cable of carbon fibers or carbon yarns in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable. The comb includes a plurality of teeth protruding radially toward the outside of the disk, and a device for rotating the disk around its rotary axis. Furthermore, a method for spreading a cable of carbon fibers or carbon yarns, includes at least making the teeth of the comb of the device flush with the cable in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable. 1. A device for spreading a cable of carbon fibers or carbon yarns , comprising:a disk mounted on a rotary shaft and provided with at least one comb adapted to comb a cable of carbon fibers or carbon yarns in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable, said comb including a plurality of teeth protruding radially toward the outside of the disk;means for rotating the disk around its rotary axis; andmeans for adjusting the orientation of the teeth of the comb.2. The device according to claim 1 , further comprising means for adjusting the radial position of the comb on the disk.3. The device according to claim 2 , wherein the comb is mounted on the disk in a radial groove and is capable of sliding inside the latter so as to allow adjustment of the radial position of said comb on the disk.4. The device according to claim 1 , wherein the comb is mounted on the disk by means of a pivoting link so as to make it possible to adjust the orientation of the teeth of said comb.5. A method for spreading a cable of carbon fibers or carbon yarns claim 1 , comprising at least making the teeth of the comb of the device according to flush with the cable in a direction substantially parallel to the longitudinal direction of ...

METHOD OF FASTENING AN AIRCRAFT WHEEL DRIVE MEMBER ON AN UNDERCARRIAGE CARRYING A WHEEL

The invention provides a method of mounting an aircraft wheel drive member () on an undercarriage having an axle () that carries the wheel and that is provided with a torque plate () having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support () that bears against an inside face of the torque plate opposite from its outside face against which a brake () is fitted, and of fitting the drive member on the support. 1301310110210. A method of mounting an aircraft wheel drive member () on an undercarriage having an axle () that carries the wheel and that is provided with a torque plate () having an outside face against which a brake can be fitted , the method comprising the steps of fitting a support (; ; ) that bears against an inside face of the torque plate opposite from its outside face , and of fitting the drive member on the support.210. A mounting method according to claim 1 , wherein the support () comprises two half-supports claim 1 , each of which is fitted against the inside face of the torque plate in order to be bolted thereto.320212225. A mounting method according to claim 1 , wherein the support is fastened on the torque plate by using at least one bolt () inserted in an orifice of the torque plate and having a threaded bolt shank () on which a nut () is fitted to clamp together the support and the torque plate between a head () of the shank and the nut.423. A mounting method according to claim 3 , wherein the bolt shank includes a smooth portion () for centering it in the orifice of the torque plate.525. A mounting method according to claim 4 , wherein the head () of the bolt is received in the spot face of the brake with a small amount of circumferential clearance in order to position the brake relative to the torque plate.6110210. A mounting method according to claim 1 , wherein the support is made as a single piece (; ) and has an opening to enable it to be put into place against the inside face of ...

AIRCRAFT WHEEL WITH A UNIVERSAL DRIVE DOG

The invention relates to an aircraft wheel comprising a rim adapted to receive a tire, and a hub connected to the rim () in order to receive bearings for guiding the wheel in rotation about an axis of rotation (X) on an axle of the aircraft, the wheel including at least one dog () that projects laterally from the rim in order to present two parallel faces () and that is pierced by an orifice () extending from one face to the other along a generally orthoradial direction (Y). 12101112. An aircraft wheel comprising a rim adapted to receive a tire , and a hub connected to the rim () in order to receive bearings for guiding the wheel in rotation about an axis of rotation (X) on an axle of the aircraft , the wheel being characterized in that it includes at least one dog () that projects laterally from the rim in order to present two parallel faces () and that is pierced by an orifice () extending from one face to the other along a generally orthoradial direction (Y).2101010. An aircraft wheel according to claim 1 , having three dogs ( claim 1 , claim 1 , ) that are circumferentially spaced apart at 120° from one another.3100203343. A method of driving a wheel according to in rotation claim 1 , wherein the aircraft is fitted with a rotary drive member () provided with drive means (; ; ) suitable for co-operating with the dog(s).420. The method according to claim 3 , wherein the drive member is provided with one or more drive forks () suitable for fitting astride a respective dog in order to transmit rotary torque by the fork bearing against one of the parallel faces of the dog.5100333010. The method according to for driving a wheel in rotation claim 3 , wherein the rotary drive member () is provided with a drive link () having one end coupled to a lug () fitted to the dog ().631. The method according to claim 5 , wherein the lug is fitted with a shank () having a threaded end claim 5 , the shank being engaged in the orifice of the dog in order to fasten the lug to the dog ...

Electromechanical braking system architecture

The invention relates to a braking system architecture for an aircraft having wheels 1 braked by means of respective brakes 2, each brake having a plurality of electromechanical actuators 3 a, 3 b, the braking system having controllers 8 a, 8 b for distributing electric power Ps to the actuators 3 a, 3 b in response to a braking setpoint, each controller 8 a, 8 b being associated with some of the actuators of any given brake. According to the invention, each controller 8 a, 8 b has an input Ev for receiving information about the rotary speed of the wheel 1 braked by the actuators associated with said controller, the controller including processor means 13 for modulating the power transmitted to the actuators as a function of the speed of rotation of the wheel in order to provide anti-skid protection.

RACK STEERING CONTROL PISTON

The invention relates to a steering actuator piston with a rack () for an aircraft landing gear () characterized in that the piston comprises a body () made of a lightweight alloy having an externally threaded main span () terminated on one side by a shoulder () and extended on the other side by a skirt (), the body having screwed to it a tapped bronze bushing having on its outer wall at least one groove for receiving a seal, the skirt having a drilling to receive a pin for securing the piston to the rack, the bushing extending in service between the shoulder and the pin so that it is retained axially between the shoulder and the pin. 16110111213. A steering actuator piston with a rack () for an aircraft landing gear () , characterized in that the piston comprises a body () made of lightweight alloy having an externally threaded main span () terminated on one side by a shoulder () and extended on the other side by a skirt () , the body having screwed to it a tapped bronze bushing having on its outer wall at least one groove for receiving a seal , the skirt having a drilling to receive a pin for securing the piston to the rack , the bushing extending in service between the shoulder and the pin so that it is retained axially between the shoulder and the pin.222. The piston as claimed in claim 1 , in which a groove is formed in an upright face of the shoulder facing the bushing in order to receive a seal () which bears against the bushing when the latter is screwed onto the body.32118115. The piston as claimed in claim 1 , comprising a shoe () bearing on a bottom () of the body () in order to cooperate with a hemispherical end of the rack such that a pressure applied to the piston generates a force which is transmitted to the rack by thrust on its spherical end claim 1 , without stressing the pin ().43357810111213. An aircraft landing gear comprising a steerable part () and also a rack steering actuator for steering the steerable part () claim 1 , the actuator ...

METHOD OF USING AND RENOVATING A DISK FROM A STACK OF DISKS

The invention relates to a method of using and renovating a brake disk (), the method comprising steps of using the disk in a plurality of lives and compensating for a reduction in the thickness of the disk after each life by assembling the disk with a complementary portion or by associating the disk with another disk of rotor or stator type if the disk is itself respectively of stator or rotor type.

METHOD OF DETECTING A LEAK PAST A DYNAMIC SEAL IN AIRCRAFT LANDING GEAR

A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear () comprising: a strut (); a rod () slidably mounted in the strut; and a bearing () fitted to an end () of the strut to guide the rod (). The bearing includes a bushing () having a seal () arranged to rub against the rod () to provide sealing between the strut and the rod, defines a fluid chamber (), and a stop nut () for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut () without a wiper seal in the place of the stop nut (), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface () of the rod (). 1100. A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear () comprising at least:{'b': '10', 'a strut ();'}{'b': '20', 'a rod () slidably mounted in the strut; and'}{'b': 70', '11', '20', '50', '62', '20', '2', '40', '64, 'a bearing () fitted to an end () of the strut to guide the rod (), said bearing including at least one bushing () having at least one dynamic seal () arranged to rub against the rod () in order to provide sealing between the strut and the rod, thereby defining a chamber () filled with hydraulic fluid between the strut and the rod, and a stop nut () for preventing the bushing from moving in translation relative to the strut and provided with at least one wiper seal () arranged to wipe hydraulic fluid on the rod;'}{'b': 3', '40', '22, 'the method being characterized in that it includes a step of installing a test nut () without a wiper seal in the place of the stop nut (), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak, if any, of hydraulic fluid on the outside surface () of the rod.'}210062. A method according to for detecting a leak in aircraft landing gear () claim 1 , wherein ...

ELECTROMECHANICAL ACTUATOR

An electromechanical actuator comprising an actuator member and an electric motor () adapted to drive the actuator member. The electric motor () comprises a rotor portion (), a stator portion () comprising a yoke-forming body () and a set of coils received in slots () in the body (), and at least one electrical module (). The electrical module is adapted to generate an electrical power supply current (Ia) for the electric motor (), which current flows in the set of coils. The electrical module () is carried by the body (). 122. An electromechanical actuator comprising an actuator member and an electric motor () adapted to drive the actuator member , the electric motor () comprising:{'b': '4', 'a rotor portion ();'}{'b': 5', '105', '9', '109', '112', '9', '109, 'a stator portion (, ) comprising a yoke-forming body (, ) and a set of coils received in slots () in the body (, ); and'}{'b': 17', '117', '2, 'at least one electrical module (, ) adapted to generate an electrical power supply current (Ia) for the electric motor (), which current flows in the set of coils;'}{'b': 17', '117', '9', '109, 'the actuator being characterized in that the electrical module (, ) is carried by the body (, ).'}21716. An electromechanical actuator according to claim 1 , wherein the electrical module () is positioned at least in part against a portion of the set of coils forming a winding overhang ().3117116. An electromechanical actuator according to claim 1 , wherein the electrical module () is positioned at least in part over a portion of the set of coils forming a winding overhang ().41716. An electromechanical actuator according to claim 1 , wherein the electrical module () is arranged so as to surround claim 1 , at least in part claim 1 , a portion of the set of coils forming a winding overhang ().5117111109. An electromechanical actuator according to claim 1 , wherein the electrical module () is positioned at least in part inside a housing () in the body ().6111112. An ...

AIRCRAFT LANDING GEAR PROVIDED WITH AN ADJUSTABLE ROLLER

The invention relates to an aircraft undercarriage intended to be mounted so as to be able to move on the aircraft between a deployed position and a retracted position, the undercarriage comprising a roller () carried by a support () secured to the undercarriage while being able to be moved with respect thereto, characterised in that the support is mounted pivotally on the undercarriage.

CONTROL BOX

The invention provides a control box for selectively delivering orders to receivers (), the control box comprising: 1. A device for operating an aircraft landing gear hatch on the ground , the device comprising:{'b': 5', '12', '4, 'means (, ) for operating the hatch ();'}{'b': 6', '7', '10', '4', '6', '7', '10', '8', '6', '7', '10, 'hooking means (, , ) enabling the hatch () to be locked when it reaches a closed position, the hooking means (, , ) including at least one unlocking actuator () arranged to act on the hooking means (, , ) in order to deactivate them; and'}{'b': 9', '16', '9', '5', '12', '8, 'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'claim-text': [{'b': 8', '6', '7', '10, 'an opening sequence during which the unlocking actuator () is actuated to deactivate the hooking means (, , ); and'}, {'b': 5', '12', '4, 'a closing sequence during which the operating means (, ) are actuated to reclose the hatch ().'}], 'a control box () according to , the order delivery means () of the control box () optionally being connected to the operating means (, ) of the hatch and to the unlocking actuator () in order to run the following sequences selectively28. A device for operating a landing gear hatch on the ground according to claim 1 , wherein the unlocking actuator () is an electromechanical actuator. This application is a Divisional of U.S. application Ser. No. 13/761,767, filed Feb. 7, 2013, which claims priority to French Application No. 12 51189, filed Feb. 8, 2012, the disclosure of each is incorporated herein by reference.The invention relates to a control box, in particular one that is suitable for use in operating an aircraft landing gear hatch on the ground.Most modern aircraft have retractable landing gear, wheel wells for receiving the landing gear while the aircraft is in flight, and hatches for closing the wheel wells. The hatches are opened and closed with the help of hatch operating actuators, e.g. hydraulic actuators.When the hatch reaches the ...

METHOD OF RESTORING A WHEEL TO COMPLIANCE AND TOOLING FOR PERFORMING THE METHOD

A method of restoring a wheel () to compliance, the wheel having a plurality of ovalized bores (). The method is characterized in that it includes at least a step of boring a first ovalized bore () with the help of a reamer () presenting a longitudinal pilot portion () and a longitudinal cutter portion (), the cutter portion () presenting teeth () defining a cutting diameter (D), and the pilot portion () presenting a pilot diameter (D) strictly less than the cutting diameter (D), the step of boring this first ovalized bore () consisting in inserting the reamer () into the first ovalized bore (), beginning with the pilot portion () and followed by the cutter portion (), the pilot diameter (D) being such that it enables the reamer () to be guided in translation inside the first ovalized bore () for boring. 112233334231223233132abbaab. A method of restoring a wheel () to compliance , the wheel having a plurality of ovalized bores () , the method being characterized in that it includes at least a step of boring a first ovalized bore () with the help of a reamer () presenting a longitudinal pilot portion () and a longitudinal cutter portion () , the cutter portion () presenting teeth () defining a cutting diameter (D) , and the pilot portion () presenting a pilot diameter (D) strictly less than the cutting diameter (D) , the step of boring this first ovalized bore () consisting in inserting the reamer () into the first ovalized bore () , beginning with the pilot portion () and followed by the cutter portion () , the pilot diameter (D) being such that it enables the reamer () to be guided in translation inside the first ovalized bore () for boring.233535. The method of restoring compliance according to claim 1 , wherein the reamer () extends along a longitudinal axis of symmetry (X-X) of the reamer claim 1 , and during the boring step claim 1 , the reamer () is assembled to a rotary drive machine () arranged to drive the reamer () in rotation about said longitudinal axis ...

METHOD OF PREPARING A METAL ALLOY PART

A method of converting an alloy comprising a majority of titanium, the method comprising: 1. A method of converting an alloy that comprises , in percentage by weight of alloy , a majority of titanium , the alloy presenting a β transus temperature beyond which a transition is observed from α phase alloy structures to β phase alloy structures , the method comprising:{'b': '1', 'a step of fabricating an ingot () made of said alloy;'}at least first, second, and third steps of a first type (A, B, C) consisting in plastically deforming the alloy from said ingot while it is at a current temperature strictly higher than the β transus temperature (Tβ); andat least first and second steps of a second type (A′, B′) consisting in plastically deforming the alloy from said ingot while it is at a current temperature strictly lower than the β transus temperature (Tβ);the method being characterized in that the steps of the first and second types (A, A′, B, B′, C) are applied in the following sequence:{'b': '1', 'performing the first step of the first type (A) while the alloy is at a first temperature (T); followed by'}performing the first step of the second type (A′); followed by{'b': 2', '1, 'performing the second step of the first type (B) while the alloy is at a second temperature (T) strictly lower than said first temperature (T); followed by'}performing the second step of the second type (B′); followed by{'b': 3', '2, 'performing the third step of the first type (C) while the alloy is at a third temperature (T) strictly lower than said second temperature (T).'}2. An alloy conversion method according to claim 1 , wherein:{'b': '1', 'the first temperature (T) is higher than the β transus temperature (Tβ) by at least 200° C. and at most 300° C.;'}{'b': '2', 'the second temperature (T) is higher than the β transus temperature (Tβ) by at least 100° C. and at most 200° C.;'}{'b': '3', 'the third temperature (T) is higher than the β transus temperature (Tβ) by at least 50° C. and at ...

DEVICE FOR DRIVING AN AIRCRAFT WHEEL IN ROTATION

The invention relates to a device for driving rotation of an aircraft wheel comprising a rim () mounted to rotate on an axle () of landing gear about an axis of rotation (X), the device comprising a drive ring gear () and a drive actuator () having an outlet pinion () that co-operates with the drive ring gear to drive the wheel in rotation. The drive ring gear is mounted to rotate about the axis of the rim of the wheel, the drive device including selective coupling means () that are operable to link the rim and the drive ring gears together in rotation, or to disconnect them.

PROCESS FOR FABRICATING AN AIRCRAFT PART COMPRISING A SUBSTRATE AND A SUBSTRATE COATING LAYER

A method of fabricating a part () comprising a metal substrate (Sub) at least partially covered in a coating layer (Rev). The method comprises: preparing (A) a surface of the substrate (Sub) to obtain a prepared surface of roughness Ra lying in the range 0.6 μm to 1.6 μm, and; forming (C) the coating layer (Rev) on the prepared surface of the substrate, this coating layer (Rev) being formed by spraying, using an HVOF type spraying method to spray a powder mixture containing grains (G) of metal carbide, the grains (G) having dimensions that are strictly less than 1 μm and the thickness (Epmin) of the coating layer (Rev) as formed in this way being less than 50 μm; then finishing at least one surface of said coating layer (Rev) by polishing (D) in such a manner as to ensure that its roughness Ra is less than 1.6 μm. 11. A method of fabricating a part () comprising a metal substrate (Sub) at least partially covered in a coating layer (Rev) , the method comprising:preparing (A) a surface of the substrate (Sub) for covering in order to obtain a prepared surface of roughness Ra lying in the range 0.6 μm to 1.6 μm, and preferably in the range 0.8 μm to 1.6 μm;forming (C) the coating layer (Rev) on the prepared surface of the substrate, this coating layer (Rev) being formed by spraying, using an HVOF type spraying method to spray a powder mixture containing grains (G) of metal carbide, the grains (G) having dimensions that are strictly less than 1 μm and the thickness (Ep min) of the coating layer (Rev) as formed in this way being less than 50 μm; thenfinishing at least one surface of said coating layer (Rev) by polishing (D) in such a manner as to ensure that its roughness Ra is less than 1.6 μm.2. A method according to claim 1 , wherein the preparation (A) of the substrate surface (Sub) for covering is performed by sand blasting.3. A method according to claim 1 , wherein the coating layer that is formed has thickness lying in the range 30 μm to 50 μm and the size of the ...

ELECTROMECHANICAL BRAKING METHOD FOR REDUCING VIBRATION

The invention relates to an electromechanical braking method for an aircraft having at least one electromechanical brake fitted to at least one braked wheel of the aircraft, the brake having friction members and a plurality of electromechanical actuators each actuator comprising a pusher suitable for being moved by means of an electric motor to selectively apply a pressing force on the friction members According to the invention, for a given braking operation, a total braking force to be applied against the friction members of the brake is distributed in non-uniform manner amongst the actuators of the brake, such that at least two actuators apply respective different forces. 12123445633444. An electromechanical braking method for an aircraft having at least one electromechanical brake () fitted to at least one braked wheel () of the aircraft , the brake () having friction members () and a plurality of electromechanical actuators () , each actuator () comprising a pusher () suitable for being moved by means of an electric motor () to selectively apply a pressing force on the friction members () , the method being such that , for a given braking operation , a total braking force to be applied against the friction members () of the brake is distributed in non-uniform manner amongst the actuators () of the brake , such that at least two actuators () apply respective different forces , the method being characterized in that the distribution among the actuators () is modified after a predetermined or random number of braking operations.24. A braking method according to claim 1 , wherein claim 1 , for a given braking operation claim 1 , each actuator () delivers a predefined contribution to the total force claim 1 , and wherein claim 1 , on each modification of the distribution claim 1 , the predefined contributions are permutated between the actuators so that each actuator delivers successively each of the predefined contributions to the total force.34. A braking method ...

SYSTEM FOR MAINTAINING A PRESSING FORCE BY THE COMBINED ACTION OF TWO MEMBERS

An aircraft electromechanical braking system comprising a braking control unit and at least one electromechanical brake the brake being fitted with at least one electromechanical actuator having a pusher suitable for being moved by means of an electric motor The actuator also has a blocking member for blocking the pusher in position. The control unit is adapted to cause the braking system to operate in an additional braking mode referred to as “combined” mode, in which the motor is activated to bring the pusher into a position in which it exerts a given holding force, and then the blocking member is activated, while activation of the motor is maintained. 11013124672486107762. An aircraft electromechanical braking system comprising braking control means () and at least one electromechanical brake () fitted to at least one braked wheel () of the aircraft , the brake () being fitted with friction members () and with at least one electromechanical actuator () having a pusher () suitable for being moved by means of an electric motor () in order to selectively apply a pressing force against the friction members () , the actuator () also having a blocking member () for blocking the pusher () in position , the control means () being adapted to cause the braking system to operate at least in a controlled mode in which the electric motor () is controlled to selectively apply a pressing force in response to a braking setpoint , or in a parking mode in which the motor () is controlled to bring the pusher () into a position in which it exerts a parking force on the friction members () , and then the blocking member is activated and the motor is deactivated ,{'b': 10', '7', '6', '8', '7', '6, 'the system being characterized in that the control means () are adapted to cause the braking system to operate in an additional braking mode referred to as “combined” mode, in which the motor () is activated to bring the pusher () into a position in which it exerts a given holding force, ...

MECHANICAL ACTUATOR WITH A HYDRAULIC DAMPER DEVICE

The invention relates to an actuator comprising a cylinder () in which a rod () is mounted to slide, the actuator having a screw () extending inside the rod to co-operate with a nut () secured to the rod, the screw being driven in rotation by a motor (), the actuator being characterized in that a hydraulic chamber (CH) filled with hydraulic fluid is arranged inside the actuator by means of a floating piston () sliding in sealed manner against the rod inside of the actuator, the hydraulic chamber being in fluid flow communication with an accumulator () via a solenoid valve () that is controllable between a closed state in which the chamber is isolated from the accumulator, and a fluid-passing state in which the hydraulic chamber and the accumulator are in communication, calibrated resistance being exerted against the passage of fluid from the chamber towards the accumulator. 1110121028108710710110201202112122122. An actuator comprising a cylinder (; ) in which a rod (; ) is mounted to slide , the actuator having a screw (; ) extending inside the rod to co-operate with a nut (; ) secured to the rod , the screw being driven in rotation by a motor (; ) , the actuator being characterized in that a hydraulic chamber (CH) filled with hydraulic fluid is arranged inside the actuator by means of a floating piston (; ) sliding in sealed manner against the rod inside of the actuator , the hydraulic chamber being in fluid flow communication with an accumulator (; ) via a solenoid valve (; ) that is controllable between a closed state in which the chamber is isolated from the accumulator , and a fluid-passing state in which the hydraulic chamber and the accumulator are in communication , calibrated resistance being exerted against the passage of fluid from the chamber towards the accumulator as obtained when movement of the rod inside the actuator leads to a reduction in the volume of the hydraulic chamber.22102109103. An actuator according to claim 1 , wherein the floating ...

PORTABLE EQUIPMENT FOR MACHINING A LOWER PORTION OF AN AIRCRAFT LANDING GEAR CASING

Portable tooling for machining a bottom portion of an aircraft landing gear strut having a plurality of orifices. The portable tooling comprising a collar for positioning it on the bottom portion of the strut, at least one indexing member for angularly indexing the collar on the strut and for preventing it from moving, and a support that is removably fitted on the collar and that is fitted with a motor-driven machining spindle that carries a tool mounted to move on the support along a direction converging on the strut in order to machine an orifice extending in register with the tool. The collar is arranged in such a manner as to be capable of receiving the support in a plurality of angular positions, in each of which the tool extends in register with one of the orifices to be machined. 1. A portable tooling for machining a bottom portion of an aircraft landing gear strut having a plurality of orifices , the portable tooling being characterized in that said portable tooling comprises a collar for positioning said portable tooling on the bottom portion of the strut , at least one indexing member for angularly indexing the collar on the strut and for preventing said collar from moving , a support that is removably fitted on the collar and that is fitted with a motor-driven machining spindle that carries a tool mounted to move on the support along a direction converging on the strut in order to machine an orifice extending in register with the tool , the collar being arranged in such a manner as to be capable of receiving the support in a plurality of angular positions , in each of which the tool extends in register with one of the orifices to be machined.2. The portable tooling according to claim 1 , wherein the support includes a carriage movably mounted on the support claim 1 , the carriage receiving the reaming spindle that moves together with the carriage.3. The portable tooling according to claim 1 , wherein the collar has a plurality of guides claim 1 , each ...

TELESCOPIC ACTUATOR

The invention relates to a telescopic actuator comprising a rod (), a hollow lead screw (), a fixed piston () comprising a first tail () which extends in the lead screw () and a head (). According to the invention, the actuator comprises a first hydraulic connection channel () extending through the first tail () to fluidically connect a first chamber (C) with a source of hydraulic fluid (), and the channel () comprises first damping means suitable for slowing down the rod () when the latter is depressed by regulating a hydraulic fluid flow rate in the first channel provoked by the depression of the rod. 2. Telescopic actuator according to claim 1 , in which the first damping means comprise restriction means suitable for laminating the hydraulic fluid when the latter is discharged from the first chamber when the rod is depressed in the body.3194. Telescopic actuator according to claim 2 , in which the restriction means comprise a check valve () arranged in the first channel to block the latter and to open in response to an overpressure in the first chamber when the rod () is depressed.44. Telescopic actuator according to claim 3 , in which the check valve is calibrated and adapted to open to admit fluid into the first chamber when the rod () is extended.544. Telescopic actuator according to claim 1 , further comprising second means for damping the rod () suitable for slowing down the rod () at the end of depression.6261191126228262162611. Telescopic actuator according to claim 5 , in which the second damping means comprise a sliding piston () cooperating in a seal-tight manner with an internal wall of the head () of the fixed piston () to define claim 5 , between the head () and the bottom of the sliding piston () claim 5 , a second chamber (C) claim 5 , a second connecting channel () being formed in the sliding piston () to fluidically connect the second chamber (C) with the first connecting channel () claim 5 , the sliding piston () being arranged in such a way ...

METHOD OF MANAGING A STEERING COMMAND FOR A STEERABLE PORTION OF AIRCRAFT LANDING GEAR

The invention relates to a method of managing a steering command for a steerable portion of nose landing gear of an aircraft the method implementing servo-control to servo-control a steering actuator to an angle position setpoint θset for the steerable portion , the servo-control including calculating an error ε by subtracting a reference angle θest from the angle position setpoint θset. According to the invention, the reference angle θest is an angle determined by calculation as a function of a longitudinal speed Vlong and a yaw rate τ of the aircraft 1321631. A method of managing a steering command for a steerable portion () of nose landing gear () of an aircraft () , the method implementing servo-control to servo-control a steering actuator () to an angle position setpoint (θset) for the steerable portion () , the servo-control including calculating an error (ε) by subtracting a reference angle (θest) from the angle position setpoint (θset) , the method being characterized in that the reference angle (θest) is an angle determined by calculation as a function of a longitudinal speed (Vlong) and a yaw rate (τ) of the aircraft ().3186. A method of managing a steering command according to claim 1 , wherein the servo-control is performed by a servo-control loop including a PID controller () for generating a steering command (Icomm) for the actuator () as a function of the error (ε).413113126. A method of managing a steering command according to claim 1 , wherein the servo-control is implemented in a controller () arranged in the aircraft () claim 1 , the controller () delivering a command current (Icomm) to a command member () for delivering calibrated power to the steering actuator (). The invention relates to a method of managing a steering command for a steerable portion of aircraft landing gear.Most modern aircraft have nose landing gear situated under the nose of the fuselage of the aircraft.Generally, steering of the aircraft on the ground is controlled by ...

PROXIMITY SENSOR FOR AIRCRAFT, PROVIDED WITH A SPECIAL SEALED ASSEMBLY

Sensor () comprising: 11. A sensor () comprising:{'b': 2', '3', '31', '1, 'a casing () delimiting an internal volume () internal to the casing and having a passage () extending between this internal volume and a first external zone (Z) external to the casing;'}{'b': 4', '3, 'a moving part () able to move inside the said internal volume () of the casing;'}{'b': 5', '4', '2', '5', '51', '31', '1', '3', '51', '52', '51', '52', '1', '3', '14', '51', '31', '14', '3', '1', '2', '52, 'detection means () for detecting a movement of the said moving part () with respect to the casing (), these detection means () comprising a detection portion () extending in the passage (), between the said first external zone (Z) external to the casing and the said internal volume () internal to the casing, this detection portion () also having a groove () open to the outside of the detection portion (), this groove () extending between the said first external zone (Z) external to the casing and the said internal volume () internal to the casing, characterized in that it comprises first sealing means () positioned around the detection portion () and placed inside the passage (), these first sealing means () being arranged in such a way as to prevent fluid from passing between the internal volume () and the first external zone (Z) external to the casing () via said groove ().'}2152533152. The sensor () according to claim 1 , in which at least one portion of the length of the groove () is filled with a sealant () arranged to oppose the said passage of fluid between the internal volume () and the first external zone (Z) external to the casing via the said groove ().314141315131251141141315114131. The sensor according to claim 2 , in which these first sealing means () comprise an annular ring () assembled in a sealed manner inside the passage () to form a guide sleeve guiding the translational movement of the detection portion () inside the passage () and with respect to the casing () claim 2 , ...

AIRCRAFT LANDING GEAR

An aircraft landing gear comprising an axle () intended to receive a wheel () comprising a rim () mounted to rotate on the axle () by means of at least one rolling bearing (). The rolling bearing () comprises an inner ring () mounted around the axle () and an outer ring () rotationally secured to the rim () of the wheel (). The landing gear further comprising a measurement device () intended to perform measurements of at least one operating parameter of the landing gear. The measurement device () is incorporated in the rolling bearing () by being secured to one of the inner or outer rings of the rolling bearing (). 13463881131264212188. Aircraft landing gear comprising an axle () intended to receive a wheel () comprising a rim () mounted to rotate on the axle () by means of at least one rolling bearing () , said rolling bearing () comprising an inner ring () mounted around the axle () and an outer ring () rotationally secured to the rim () of the wheel () , the landing gear further comprising measurement means () intended to perform measurements of at least one operating parameter of the landing gear , characterized in that the measurement means () are incorporated in the rolling bearing () by being secured to one of the inner and outer rings of the rolling bearing ().221304. Aircraft landing gear according to claim 1 , in which the measurement means () comprise at least one sensor () intended to measure the speed of rotation of the wheel () of the aircraft.330328. Aircraft landing gear according to claim 2 , in which the sensor () is a magnetic sensor cooperating with a measurement crown ring () mounted rotationally secured to the other of the outer and inner rings of the rolling bearing ().432. Aircraft landing gear according to claim 3 , in which the measurement crown ring () is in the form of a toothed wheel.532. Aircraft landing gear according to claim 3 , in which the measurement crown ring () comprises at least one magnet.630. Aircraft landing gear according ...

DEVICE FOR MEASURING THE ROTATIONAL SPEED OF A WHEEL

The invention relates to a measurement device for measuring the rotational speed of a vehicle wheel, the measurement device comprising a body () incorporating: 1. Measurement device for measuring the rotational speed of a vehicle wheel , the measurement device comprising a body incorporating:a rotor which can be rotated by the wheel and on which at least one permanent magnet is mounted;a stator comprising a winding generating a measurement voltage (Vmes) when the wheel and therefore the permanent magnet turn, the measurement voltage being indicative of the rotational speed of the wheel;{'b': '6', 'an electronic board comprising processing means for processing the measurement voltage;'}power supply means designed to generate, from the measurement voltage, a power supply voltage (Vali) intended to power the electronic board;the electronic board comprising first voltage-matching means intended to drop the power supply voltage when the latter is above a predetermined first voltage threshold and to raise the power supply voltage when the latter is below a predetermined second voltage threshold.2. Measurement device according to claim 1 , in which the first voltage-matching means comprise a first converter of the Buck-Boost type.3. Measurement device according to claim 2 , in which the first voltage-matching means comprise a control circuit intended to adjust a control law of pulse width modulation type to operate the first converter of Buck-Boost type.4. Measurement device according to claim 1 , in which the electronic board further comprises energy-storage means intended to store electrical energy when the rotational speed of the wheel is above a predetermined first speed threshold and to release the stored electrical energy to power the electronic board when the rotational speed of the wheel is below a predetermined second speed threshold.5. Measurement device according to claim 4 , in which the energy-storage means collaborate with second voltage-matching means ...

AIRCRAFT UNDERCARRIAGE

An undercarriage comprising at least: 1. An aircraft undercarriage comprising at least:{'b': 4', '3, 'a wheel () mounted on an axle () to rotate about an axis of rotation X;'}{'b': 7', '9', '3', '11', '9', '9', '4', '13, 'a brake () comprising a torsion tube () extending around the axle (), friction members () mounted around the torsion tube () and extending between the torsion tube () and the wheel (), and at least one brake actuator () for selectively exerting a braking force on the friction members; and'}{'b': 14', '5', '4', '15, 'drive means for driving rotation of the wheel, the drive means comprising an electric motor () connected to the rim () of the wheel () by a coupler member ();'}{'b': 15', '3', '9, 'the undercarriage being characterized in that the coupler member () extends at least in part around the axle () between the axle and the torsion tube () of the brake.'}21535. An aircraft undercarriage according to claim 1 , wherein the coupler member () comprises a clutch member () for selectively connecting together the electric motor and the rim of the wheel claim 1 , the clutch member facing the torsion tube.33637. An aircraft undercarriage according to claim 2 , wherein the clutch member includes clutch disks comprising at least one first clutch disk () constrained to rotate with the coupler member and at least second clutch disk () constrained to rotate with the rim of the wheel.4813404040. An aircraft undercarriage according to claim 2 , wherein the brake includes an actuator carrier () carrying the brake actuator () claim 2 , and wherein the clutch member is actuated by a clutch actuator (; ′; ″) carried by the brake actuator.5418. An aircraft undercarriage according to claim 4 , wherein the clutch actuator is mounted on an inside face () of the actuator carrier () and extends between the axle and the torsion tube of the brake.651. An aircraft undercarriage according to claim 4 , wherein the clutch actuator is mounted on an outside face () of the ...

AIRCRAFT WHEEL FITTED WITH DRIVEKEY-BOLTS

An aircraft wheel comprising two half-wheels () assembled together by means of bolt fasteners () clamping together disks of the half-wheels, each bolt fastener comprising a bolt () with an end forming a screw head () and a threaded end () for receiving a nut (), the wheel also being fitted with drive keys () that are fitted to one of the half-wheels for driving brake disks in rotation, the wheel being characterized in that each drive key has a first end () that is shaped to co-operate with the screw head of one of the bolts so that said first end is held and prevented from moving when the key is in place on the wheel. 11210110111111211213113141142012023123. An aircraft wheel comprising two half-wheels ( , ) assembled together by means of bolt fasteners (; ) clamping together disks of the half-wheels , each bolt fastener comprising a bolt (; ) with an end forming a screw head (; ) and a threaded end (; ) for receiving a nut (; ) , the wheel also being fitted with drive keys (; ) that are fitted to one of the half-wheels for driving brake disks in rotation , the wheel being characterized in that each drive key has a first end (; ) that is shaped to co-operate with the screw head of one of the bolts so that said first end is held and prevented from moving when the key is in place on the wheel.22312. A wheel according to claim 1 , wherein the first end () is cylindrical in shape and penetrates into a central orifice formed in the screw head () of the bolt.3242526. A wheel according to claim 1 , wherein the key has a second end () that is pierced to receive a bolt () for fastening said end to an extension () projecting axially from the half-wheel.4111120. A wheel according to claim 1 , wherein the bolts () of the fastener bolts and the drive keys () are made integrally.5. A wheel according to claim 4 , wherein the first end of the drive key is formed integrally with the screw head of the bolt.6125. A wheel according to claim 4 , wherein each key has a second end carrying ...

AIRCRAFT LANDING GEAR

The invention relates to an aircraft landing gear equipped with a steering device () for orienting the wheels (), the steering device () comprising a body () in which is incorporated an electromechanical actuator () equipped with an electric motor (). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel () to the rest of the landing gear () when the aircraft is on the ground. The body () of the steering device () is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body () of the steering device () and the strut assembly () of the landing gear to damp the vibration between the body () of the steering device () and the strut assembly (). 123254643175784142435587872872. Aircraft landing gear comprising a strut assembly () articulated to the structure of the aircraft , a strut () sliding along an axis of sliding X in the strut assembly () and a free end of which carries at least one wheel () , a steering tube () mounted with the ability to rotate about the axis (X) , and a torque link () connecting the steering tube () and the strut () in terms of rotation , the landing gear () additionally being equipped with a steering device () for orienting the wheel () about the axis X , the steering device () comprising a body () in which is incorporated an electromechanical actuator () equipped with an electric motor () intended to drive the rotation of the steering tube () and therefore of the strut () in order to steer the wheel () , the landing gear being further equipped with damping means intended to limit the transmission of vibration from the wheel () to the rest of the landing gear when the aircraft is on the ground , characterized in that the body () of the steering device () is mounted with the ability to rotate about the axis (X) with a limited amplitude of rotation , and in that the damping means extend between the body () of the steering ...

METHOD OF MANAGING THE BRAKING OF AN AIRCRAFT

The invention relates to a method of managing the braking of an aircraft, the aircraft having a plurality of wheels R R each fitted with a brake F F adapted to generate a braking force in response to brake pedals being depressed, the management method comprising the steps of: 11121125. A method of managing the braking of an aircraft , the aircraft having a plurality of wheels (R , . . . , R) , each fitted with a brake (F , . . . , F) adapted to generate a braking force in response to brake pedals () being depressed , the management method comprising the steps of:distributing the wheels fitted with respective brakes in at least two distinct groups (G1, G2, G3, G′1, G′2, G′3); andallocating respective relationships (L1, L2, L3) to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals;the method being characterized in that it further comprises the step of modifying the distribution of the wheels in response to a predetermined event occurring.2. A braking management method according to claim 1 , wherein each relationship (L1 claim 1 , L2 claim 1 , L3) defines a different minimum threshold (E1 claim 1 , E2 claim 1 , E3) for brake pedal depression from which a braking force is applied.3. A braking management method according to claim 1 , wherein the step of modifying the distribution is performed in response to detecting claim 1 , on at least one wheel referred to as a “singular” wheel:unavailability of the brake; orthe brake having a temperature that is high compared with the temperatures of the other brakes; orthe brake having a high degree of wear compared with the wear of the other brakes; ora tire having a temperature that is high compared with the temperatures of other tires; ora tire having a pressure that is high compared with the pressures of other tires.4. A braking management method according to claim 3 , wherein a wheel of a group including a singular wheel having its brake unavailable is ...

METHOD OF MANAGING THE BRAKING OF AN AIRCRAFT

A method of managing the braking of an aircraft, the aircraft having a plurality of wheels R, . . . , R, each fitted with a brake F, . . . , F adapted to generate a braking force in response to brake pedals being depressed. The management method comprising the steps of (1) distributing the wheels fitted with respective brakes in at least two distinct groups G, G, G, G′, G′, G′; (2) allocating respective braking relationships to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals; and (3) acting at predetermined intervals to permutate the allocation of the relationships to the groups in application of a predefined permutation relationship. The method also includes a step of modifying the permutation relationship in response to the occurrence of a predetermined event. 11121125. A method of managing the braking of an aircraft , the aircraft having a plurality of wheels (R , . . . , R) , each fitted with a brake (F , . . . , F) adapted to generate a braking force in response to brake pedals () being depressed , the management method comprising the steps of:{'b': 1', '2', '3', '1', '2', '3, 'distributing the wheels fitted with respective brakes in at least two distinct groups (G, G, G, G′, G′, G′);'}{'b': 1', '2', '3, 'allocating respective braking relationships (L, L, L) to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals; and'}acting at predetermined intervals to permutate the allocation of the relationships to the groups in application of a predefined permutation relationship;the method being characterized in that it further comprises the step of modifying the permutation relationship in response to the occurrence of a predetermined event.2112. A braking management method according to claim 1 , wherein the predetermined event is detecting on at least one wheel (R claim 1 , . . . claim 1 , R):{'b': 1', '12, 'the unavailability ...

PROCESS FOR MANUFACTURING A COMPOSITE, GENERALLY TRIANGULAR, STRUCTURAL PART

A method of fabricating an element () out of composite material, the element comprising three arms () arranged in a triangle. The method comprises the operations of: fabricating a three-dimensionally woven preform from reinforcing fibers and including through slots defining two arms () and two half-arms that are all parallel and contiguous in pairs, each arm () having one end whereby it is connected to a half-arm and another end whereby it is connected to the other arm (); shaping the preform by deploying it and by uniting its two half-arms in order to give it a triangle configuration; securing together the half-arms by stitching with reinforcing fibers; and injecting resin into the preform and polymerizing the resin. 125222324. A method of fabricating a structural element () out of composite material , the element comprising three arms ( , , ) arranged in a triangle and connected to one another via their respective ends , the method comprising the operations of:{'b': 19', '13', '14', '15', '21', '22', '23', '24', '24', '22', '23', '24', '24', '22', '23, 'i': a,', 'b', 'a,', 'b, 'using a fabric three-dimensionally woven from reinforcing fibers to fabricate a preform () having through slots (, , , ) defining two arms (, ) and two half-arms () that are all parallel and contiguous in pairs, each arm (, ) having one end whereby it is connected to a half-arm () and another end whereby it is connected to the other arm (, );'}{'b': 19', '24', '24', '22', '23', '19', '24', '24, 'i': a,', 'b', 'a,', 'b, 'shaping the preform () by deploying it and by uniting its two half-arms () to give it a triangle configuration with two sides corresponding to the two arms (, ) of the preform () and with its third side corresponding to uniting the two half-arms () of the preform;'}{'b': 24', '24', '24', '24, 'i': a,', 'b', 'a,', 'b, 'securing together the two half-arms () by stitching reinforcing fibers through both half-arms (); and'}{'b': '19', 'injecting resin into the preform () and ...

AIRCRAFT WHEEL COMPRISING A DUCT ESTABLISHING A LEAKAGE PATH IN THE WHEEL

The invention relates to an aircraft wheel comprising a rim and a tyre () received on the rim, the rim comprising two parts () assembled with one another by means of assembly bolts (), one of the parts comprising a recess () in which is arranged a seal () which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct () extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tyre, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent. 120120121011025105310341046106. Aircraft wheel comprising a rim and a tyre (; ) received on the rim , the rim being in two parts ( , ; , ) assembled with one another by means of assembly bolts (; ) , one of the parts comprising a recess (; ) in which is arranged a seal (; ) which is interposed between the two parts , the wheel being characterized in that at least one of the parts comprises at least one duct (; ) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tyre , and on the other hand a space between the two parts , the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.212. Wheel according to claim 1 , in which the rim comprises two half-rims ( claim 1 , ) claim 1 , each half-rim forming respectively one of the parts of the rim.363. Wheel according to claim 2 , in which the duct () is cut into the half-rim comprising the recess () claim 2 , the duct opening into the recess.46. Wheel according to claim 3 , in which the duct () has a bottom which is inclined relative ...

BRAKE ACTUATOR FOR AIRCRAFT WHEEL HYDRAULIC BRAKE

A brake actuator for an aircraft hydraulic brake, insertable in a cavity of a brake ring. The actuator comprises a liner () designed to be housed sealingly in the cavity of the ring, a piston () mounted to slide sealingly in the liner along an axis of sliding (X) so as to apply a braking force when a fluid is introduced under pressure into the cavity, and a wear compensation device () which defines a position to which the piston retreats into the liner by means of mobile stop () that can be moved forward by the piston as a braking force is applied. An elastic return member () returns the piston towards the position of retreat bearing against the mobile stop. The wear compensation device extends between the liner and the piston, downstream of a seal extending between the liner and the piston so as not to be bathed in the fluid in the cavity, the stop being held still by friction on the liner. 1. Brake actuator for an aircraft hydraulic brake , which is intended to be added into one of the cavities of a brake ring , the actuator comprising{'b': '1', 'a liner () designed to be housed sealingly in the cavity of the ring;'}{'b': '3', 'a piston () mounted to slide sealingly in the liner along an axis of sliding (X) so as to apply a braking force when a fluid is introduced under pressure into the cavity;'}{'b': 10', '11, 'a wear compensation device () which defines a position to which the piston retreats into the liner by means of mobile stop () that can be moved forward by the piston as a braking force is applied;'}{'b': '16', 'an elastic return member () returning the piston towards the position of retreat bearing against the mobile stop;'}characterized in that the wear compensation device extends between the liner and the piston, downstream of a seal extending between the liner and the piston so as not to be bathed in the fluid in the cavity, the stop being held still by friction on the liner.212. Brake actuator according to claim 1 , in which the mobile stop comprises ...

BRAKING ACTUATOR FOR A HYDRAULIC BRAKE OF AN AIRCRAFT WHEEL

A braking actuator for a hydraulic aircraft brake, received in a cavity of a ring of the brake. The actuator comprises a liner structure () sealed in the cavity of the ring, and a piston () slidably mounted in the liner structure to apply a braking force. A wear-compensating device () defines a retreated position of the piston in the liner structure by an axially movable stop () which can be advanced by the piston during the application of a braking force and in frictional relationship with a fixed part () of the wear-compensating device secured to the liner. An elastic member () returns the piston to the retreated position defined by the piston bearing against the movable stop, the movable stop being in frictional relationship with the fixed part via at least one telescopic intermediate element () interposed between the movable stop () and the fixed part (). 1. Braking actuator for a hydraulic aircraft brake , intended to be received in one of the cavities of a ring of the brake , the actuator comprising{'b': '1', 'a liner () adapted to be received in a sealed manner in the cavity of the ring;'}{'b': '3', 'a piston () slidably mounted in a sealed manner in the liner along a sliding axis in order to apply a braking force when a pressurized fluid is introduced into the cavity;'}{'b': 10', '11', '18, 'a wear-compensating device () which defines a retreated position of the piston in the liner by means of an axially movable stop () which can be advanced by the piston during the application of a braking force and in frictional relationship with a fixed part () of the wear-compensating device secured to the liner;'}{'b': '24', 'an elastic member () for returning the piston to the retreated position defined by the piston bearing against the movable stop;'}{'b': 16', '11', '18, 'characterized in that the movable stop is in frictional relationship with the fixed part via at least one telescopic intermediate element () interposed between the movable stop () and the fixed part ...

DEVICE FOR COUPLING AN ACTUATOR FOR CONTROLLING THE LANDING GEAR OF AN AIRCRAFT

A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated. 1. A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure , the device comprising:a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged;pre-loading means acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; andabutment means pour defining at least one working position for the lever when the actuator is activated.2. A device according to claim 1 , wherein the pre-loading means and the abutment means are arranged to define distinct rest and working positions.3. A device according to claim 2 , wherein the pre-loading means comprise two pushers arranged on either side of the lever to co-operate therewith and to urge the lever towards the rest position situated between two working positions defined on either side of the rest position by the abutment means.4. A device according to claim 1 , wherein the pre-loading means urge the lever towards the abutment means so that the rest position and the working position coincide.5. A device according to claim 1 , wherein the pre-loading means comprise a spring acting on a crank hinged to the structure of the aircraft claim 1 , the crank being coupled to the lever by means of a connecting rod.6. An aircraft having a device according to for coupling an actuator for operating an aircraft undercarriage.7. ...

Electromechanical actuator for vehicle brake and braking system comprising such an actuator

The invention relates to an electromechanical actuator for a vehicle brake comprising a body ( 4 ) in which are arranged an electric motor ( 5 ) and a threaded plunger cooperating via a helical link with a nut ( 8 ) driven in rotation by the electric motor ( 5 ). According to the invention, the nut ( 8 ) is mounted to move axially in the body ( 4 ) of the actuator between a rest position towards which the nut ( 8 ) is pushed back by elastic means, and an active position towards which the nut is displaced against the elastic means when a braking force is applied, the actuator further comprising means for detecting the axial displacement of the nut.

METHOD FOR THE RECONDITIONING AND USE OF BRAKE DISCS OF THE REAR STATOR TYPE WITH STUDS, ASSEMBLED DISC AND CORRESPONDING STACK OF DISCS

The invention relates to a method for the reconditioning and use of brake discs of the rear stator type with studs, the method comprising the steps of using a first disc () during a first life, using a second disc () during a first life, after the first life of the first disc and the first life of the second disc, machining a friction surface on one of the discs and a rear surface on the other of the discs so that one of said surfaces comprises at least one shoulder () and the other of said surfaces comprises at least one notch (), and nesting the first disc in the second disc such that the notch and the shoulder cooperate so as to centre the discs. 1. Method for the reconditioning and use of aircraft brake discs of the rear stator type with studs , the method comprising the steps of:{'b': '12', 'using a first disc () during a first life as the rear stator disc with studs from a first stack of brake discs, the first disc having an initial thickness at the start of the first life,'}{'b': '112', 'using a second disc () during a first life as the rear stator disc with studs from a second stack of brake discs, the second disc at the start of the first life being substantially identical to the first disc at the start of the first life,'}{'b': 13', '114', '17', '118, 'after the first life of the first disc and the first life of the second disc, machining a friction surface () on one of the discs and a rear surface () on the other of the discs so that one of said surfaces comprises at least one shoulder () and the other of said surfaces comprises at least one notch () capable of cooperating with said shoulder,'}nesting the first disc in the second disc such that the notch and the shoulder cooperate so as to centre the discs,{'b': '212', 'fixing the two discs to one another to form an assembled disc (), the assembled disc having a thickness which is substantially identical to the initial thickness,'}fixing studs to the assembled disc,using the assembled disc during an ...

AIRCRAFT WHEEL

An aircraft wheel which is provided with rotational driving unit (). The driving unit comprises a driving ring () which is associated with structure () for attaching the ring to a rim of the wheel. The attachment structure is fixed to treads () of the rim which further serve to retain removable brake blocks () with which the rim is provided. 11011011111121121911921121. Aircraft wheel which is provided with rotational driving means (; ) , the driving means comprising a driving ring (; ) which is associated with means (; ) for attaching the ring to a rim of the wheel , the wheel being characterised in that the attachment means are fixed to treads (; ) of the rim which further serve to retain removable brake blocks (; ) with which the rim is provided.220120. Aircraft wheel according to claim 1 , wherein the same bolt (; ) extends in order to retain both one of the attachment members of the driving ring and a brake block on one of the treads of the rim.3111314. Aircraft wheel according to claim 1 , wherein the ring comprises a chain () and the attachment members each comprise jaws ( claim 1 , ) which are capable of clamping links of the chain.41719. Aircraft wheel according to claim 3 , wherein at least one of the jaws comprises a lug () which extends in order to enable it to be fixed to one of the treads () of the rim.5111. Aircraft wheel according to claim 1 , wherein the ring () is a rigid toothed ring and the attachment members are integral with the ring. The invention relates to an aircraft wheel which is provided with means for the rotational driving thereof by means of a driving actuator.The advantage of motorising aircraft wheels in order to be able to move the aircraft without the use of the power units thereof has recently been recognised. In this regard, there are known aircraft wheels which are provided with means for the rotational driving thereof by means of a driving actuator which is fitted to the lower portion of the landing gear. These driving means ...