Abrégé

A system for conditioning fuel for an air-breathing hydrogen engine (M), comprising: • - at least one hydrogen pump (16) configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, • - one or more heat exchangers (24, 26, 28) configured to increase the temperature of the pressurized hydrogen, • - an air supply circuit (10G), • - at least one combustion device (32) configured to provide partial combustion of the hydrogen with the air coming from the air supply circuit in order to produce a fuel comprising a mixture of gas including gaseous hydrogen and not including oxygen.

Classes IPC  ?

• F02K 9/42 - Moteurs-fusées, c. à d. ensembles fonctionnels portant à la fois le combustible et son oxydant; Leur commande utilisant des propergols liquides ou gazeux
• F02K 9/78 - Moteurs-fusées, c. à d. ensembles fonctionnels portant à la fois le combustible et son oxydant; Leur commande combinés avec un autre ensemble fonctionnel à propulsion par réaction avec un ensemble fonctionnel de propulsion par réaction alimenté par de l'air ambiant

Abrégé

Disclosed is a method of determining an operating condition of a valve of an aircraft system. The method includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the valve. The method includes providing an indication of an altered operating condition associated with actuation of the valve based on the first and second time periods.

Classes IPC  ?

• B64D 37/14 - Remplissage ou vidange
• B64D 37/28 - Commande de ces systèmes
• B64D 37/32 - Mesures de sécurité non prévues ailleurs, p.ex. contre les explosions
• B64F 1/28 - Installations de manutention de liquides spécialement adaptées au remplissage d'aéronefs à l'arrêt
• F02C 7/232 - Soupapes pour combustible; Systèmes ou soupapes de drainage
• F16K 37/00 - Moyens particuliers portés par ou sur les soupapes ou autres dispositifs d'obturation pour repérer ou enregistrer leur fonctionnement ou pour permettre de donner l'alarme

Abrégé

The invention relates to an aircraft comprising a display screen (7) and at least one turbomachine (2), each turbomachine (2) comprising a motor (10), the aircraft (1) comprising the following elements associated with each turbomachine (2): an exhaust fire detection system (30) comprising a detection unit (31) connected to at least one set of photo-detection devices (32) which is arranged outside the turbomachine (2), as well as to the display screen (7), each set of photo-detection devices (32) being configured to detect electromagnetic rays, which are emitted by the turbomachine, in a predetermined infrared wavelength range and in a predetermined ultraviolet wavelength range, the detection unit (31) being configured to transmit a warning signal indicating the presence of a fire outside the turbomachine to the display screen (7) according to data from the at least one set of photo-detection devices (32).

Classes IPC  ?

• F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p.ex. les véhicules routiers dans les avions
• F02C 7/25 - Prévention ou protection contre l'incendie
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

Abrégé

The invention relates to a self-cleaning external layer (22) comprising a self-cleaning aerodynamic surface (S) configured to extract at least some of the oxygen present in the atmosphere (A) in contact with the aerodynamic surface (S) so as to at least partially deprive of oxygen the haemolymph of the insect residue (24) present on the aerodynamic surface (S) after being hit by insects. In this way, the haemolymph remains in a liquid or pasty state for longer, making the insect residue (24) easier to detach from the aerodynamic surface (S). The invention also relates to a vehicle comprising at least one such self-cleaning aerodynamic surface.

Classes IPC  ?

• C09D 5/16 - Peintures antisalissures; Peintures subaquatiques
• C09D 7/40 - Adjuvants
• C09D 183/04 - Polysiloxanes
• C09D 175/04 - Polyuréthanes
• C09D 183/16 - Compositions de revêtement à base de composés macromoléculaires obtenus par des réactions créant dans la chaîne principale de la macromolécule une liaison contenant uniquement du silicium, avec ou sans soufre, azote, oxygène ou carbone; Compositions de revêtement à base de dérivés de tels polymères dans lesquels tous les atomes de silicium sont liés autrement que par des atomes d'oxygène
• C09D 127/18 - Homopolymères ou copolymères du tétrafluoro-éthylène
• B05D 5/08 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces pour obtenir des effets, finis ou des structures de surface particuliers pour obtenir une surface antifriction ou anti-adhésive
• B64C 7/02 - Fuseaux-moteurs
• B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion

Abrégé

The invention relates to a method for manufacturing an aerodynamic structure (34) comprising a first panel (42) having an aerodynamic face (F34) as well as a second reinforced panel (44), characterised in that the manufacturing method comprises a step of stamping the second panel (44) to obtain at least one raised shape (46) which is recessed on the second face (44.2), as well as a step of joining the first and second panels (42, 44) by pressing them against each other outside the raised shape(s) (46). The invention also relates to an aerodynamic structure obtained using said method.

Classes IPC  ?

• B64C 9/32 - Surfaces de freinage aérodynamique
• B64C 9/00 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction
• B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

Abrégé

An apparatus attached near the tip end of a cantilevered aircraft wing for controlling the loads on the wing. The apparatus comprises a first body having a mass rotatable about a first axis by an actuator device; and a second body adjacent to the first body and having a mass rotatable about a second axis by an actuator device. The first and second bodies each have a centre of mass offset from their respective axes and are configured to counter rotate about their respective axes.

Classes IPC  ?

• B64C 3/00 - Voilures
• B64D 47/00 - Equipements non prévus ailleurs
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• F16F 15/22 - Compensation des forces d'inertie

Abrégé

The invention relates to a method for screwing or crimping a ring on a rod (16), characterised in that it comprises: - a step of taking measurements of distances, - a step of reconstructing at least a portion of a virtual outer envelope from the measurements obtained in the step of taking measurements, - a step of establishing the real position and the real orientation of the axis of revolution (A16) of the rod (16) from the reconstructed virtual outer envelope, - steps of positioning and moving the ring relative to the rod (16) according to the established axis of revolution (A16) of the rod (16), the ring being supported by a tool (22) which is moved automatically and autonomously by control and movement systems during the steps of positioning and moving the ring. This method allows insertion of a ring on a rod (16) with increased efficacy using a robot arm with "standard" precision.

Classes IPC  ?

• B23P 19/06 - Machines pour mettre ou retirer les vis ou les écrous
• B25J 9/16 - Commandes à programme
• G01B 11/27 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour tester l'alignement des axes pour tester l'alignement des axes
• G06K 9/00 - Méthodes ou dispositions pour la lecture ou la reconnaissance de caractères imprimés ou écrits ou pour la reconnaissance de formes, p.ex. d'empreintes digitales
• B25J 11/00 - Manipulateurs non prévus ailleurs
• G05B 19/418 - Commande totale d'usine, c.à d. commande centralisée de plusieurs machines, p.ex. commande numérique directe ou distribuée (DNC), systèmes d'ateliers flexibles (FMS), systèmes de fabrication intégrés (IMS), productique (CIM)

Abrégé

The invention relates to a front engine attachment system (150) for an engine of an aircraft, wherein the front engine attachment system (150) comprises an engine pylon (12) with a front rib (62), a front engine attachment (50) with a first link (56) fastened directly to the front rib (62) by two connection points (60a-b), and a second link (70) having a first end (72) fastened to the first link (56) by one connection point (60e), and an engine case (14) for the engine (10), wherein the first link (56) is fastened directly to the engine case (14) by at least two connection points (60c-d), and wherein a second end (76) of the second link (70) is fastened to the engine case (14) by one connection point (73). Such a front engine attachment system thus comprising a direct fastening between the first link and the front rib is simple, has a small space requirement and is easy to manufacture.

Classes IPC  ?

• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur

Abrégé

The system for controlling the idling and power take-off speed has a unit (4) for determining a current value of available power, a unit (5) for determining a current value of consumed power, a unit (6) for determining a value of power variation required at a later time, a unit (7) for calculating a value of estimated total power required at the later time, a unit (8) for calculating a value of estimated available power at the later time, an optimization unit (9) that determines an optimization result by comparing the value of estimated total power required with a value of power associated with an optimization criterion, and a control unit (17) that outputs an order for adapting idling of the engine, an order for adapting the estimated total power required or no order depending on the optimization result.

Classes IPC  ?

• F02C 6/04 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique
• F02C 9/50 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande du flux du fluide de travail

Abrégé

The invention relates to a soundproofing coating with a cellular structure consisting of several structures (11) connected in a transverse direction (D2), each formed by connecting a first longitudinal strip (4) with a second longitudinal strip (5). Each structure (11) has, successively in the longitudinal direction (D1): - a first cavity (6), the cross-section of which narrows gradually in the thickness of the coating until it closes, - a first connection of two walls (71, 72), respectively of the first strip (4) and the second strip (5), in contact with each other over part of the thickness of the coating, which provides a passage (10) between the first cavity (6) and a second cavity (8) that thus form a Helmholtz resonator, - the second cavity (8), the cross-section of which gradually increases in the thickness of the coating and which is closed by a closing sheet, - a second connection of two walls (91, 92). A broadband soundproofing coating that can, in particular, process low frequencies is thus obtained by joining strips that can be obtained by conventional industrial means.

Classes IPC  ?

• B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche discontinue, c. à d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p.ex. structures en nids d'abeilles
• B32B 3/18 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche discontinue, c. à d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche interne formée d'éléments individuels
• B32B 3/26 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche comportant des cavités ou des vides internes
• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
• F02C 7/24 - Isolation thermique ou acoustique
• G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance

Abrégé

The invention comprises an assembly (200) comprising a mast (106) with an upper spar (202) and two lateral blades (230), a wing (104) with a skin (210) and a front spar (208), port/starboard front/rear brackets, each with a housing (218, 220) for a nut (222). The front spar (208) has front/intermediate/rear folds (208a-c), each front bracket (212a-b) being positioned against the front fold (208a) and the intermediate fold (208b) and each rear bracket (214a-b) being positioned against the intermediate fold (208b) and the skin (210), and, for each housing (218, 220), the associated bracket (212, 214) is pierced by a through-bore (224) opening into said housing (218, 220). For each housing (218, 220), the assembly (200) comprises a fastening bolt comprising the nut (222) and a screw (226), the threaded rod of which passes through coaxial bores of the front fold (208a), the skin (210), the top spar (202) and the associated lateral blade (230), and the through-bore (224), and is screwed into the nut (222), and the head of which bears against the lateral blade (230). Such an assembly makes it possible to distribute the fastening bolts on either side of the front spar and thus eliminate the torsional moment in the front spar.

Classes IPC  ?

• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
• B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
• B64C 3/32 - Voilures spécialement adaptées pour le montage des groupes propulseurs
• B64C 3/18 - Longerons; Nervures; Lisses

Abrégé

A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly comprises a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

Classes IPC  ?

• B64C 25/04 - Disposition sur l'aéronef
• B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté

Abrégé

The invention relates to an electrical installation (1) that comprises an energy source (2) connected to a user apparatus (3) via two electrical connections (4, 7), each connection comprising a conductor (5) surrounded by an insulating casing (6), an electrical protection device (10a, 10b), comprising a conductive sheath (11) arranged around the insulating casing (6), and a short-circuit (15) able to open said conductor, said device further comprising: - a first current probe (20) arranged to measure a current passing through a first electrical connection (13) connecting, through an impedance (Z1), the sheath (11) to a structure of the aircraft (GND) and a second current probe (21) arranged to measure a current passing through a second electrical connection (14) connecting, through an impedance (Z2), the sheath to the structure of the aircraft; - a detection module (16) connected to each of the two current probes and configured to verify the absence of a current leak out of the conductor (5); - a test module (17) connected to each of the two current probes and configured to verify the reliability of detection; - a central unit (18) configured to control the short-circuit as a function of the result of the verifications performed by the detection and test modules.

Classes IPC  ?

• G01R 31/08 - Localisation de défauts dans les câbles, les lignes de transmission ou les réseaux
• H02H 5/10 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions non électriques normales de travail avec ou sans reconnexion sensibles à une détérioration mécanique, p.ex. rupture de ligne, rupture de connexion de terre
• H02H 7/26 - Protection sectionnelle de systèmes de câbles ou de lignes, p.ex. pour déconnecter une section dans laquelle un court-circuit, un défaut à la terre, ou une décharge d'arc se sont produits

Abrégé

The invention concerns a drive unit (100) for an aircraft, comprising: - a pylon (102) intended to be attached under a wing (14) of the aircraft (1) and having a front face (104) and a lower face (105) and - a turbine engine (10) comprising, from upstream to downstream in a direction (F) of an air flow passing through the turbine engine while the latter is operating, a fan (15) and an engine (14) driving the fan, the fan (15) being ducted by a fan casing (24) and the engine (14) being ducted, from upstream to downstream, by an intermediate casing (30) and an engine casing (28), the intermediate casing (30) having a hub (31) and an outer shroud (32) extending the fan casing (14), said shroud (32) being radially spaced apart from the hub (31) and attached to the latter by arms (33) extending through an air channel (12), the drive unit (100) comprising a front engine attachment (400) attached between the front face (104) of the pylon and the hub (31) and a rear engine attachment (400) attached between the lower face (105) of the pylon and the engine casing (28).

Classes IPC  ?

• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur

Abrégé

In order to bring the primary structure of an aircraft engine attachment pylon as close as possible to a wing box, the invention provides: - an aircraft wing (2) comprising a wing box (14) made partly by means of a front spar (16) and an intermediate spar; - an attachment pylon comprising a primary structure in the form of a box (28) having transverse reinforcement ribs (36, 36a, 36b); and - means for attaching the primary structure (28) of the attachment pylon to the wing box (14). According to the invention, these attachment means comprise a row of bolts (44) along which each bolt passes through a structural part (36, 136a, 136b) of the pylon (4), and a fitting (50) attached to one of the front and intermediate spars.

Classes IPC  ?

• B64C 3/32 - Voilures spécialement adaptées pour le montage des groupes propulseurs
• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur

Abrégé

The invention relates to a method and device for inspecting the structural damage to the skin of an aircraft after a lightning strike, wherein the skin comprises a set of marks caused by the lightning strike, said marks including a visual damage (VD) and a structural damage (SD). The method comprises the following steps: for each mark, measuring the surface area of the paint that has been removed by the lightning strike; comparing the measured surface area with a surface area threshold value, wherein the threshold value relates to the structural damage (SD) of each mark.

Classes IPC  ?

• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

Abrégé

The invention relates to an aircraft including at least one DC electrical network, said network comprising nodes that are interconnected in pairs by branches, each node being connected to at least two branches, said network being protected by a protective system including a plurality of protective elements mounted on the branches, each protective element mounted on a branch including a central processing unit associated with a current sensor, with a current-limiting device and with a circuit-breaker device, for each branch of the network connecting two nodes. The protective system includes two protective elements connected in series on the branch, wherein each protective element adjacent to a node is referred to as being associated with this node, and for each protective element mounted on a branch: the current sensor is, additionally, configured to determine the direction of the current in the branch in relation to the node with which said protective element is associated; the central processing unit is configured to select, depending on the direction of current determined by the current sensor, a threshold value, referred to as the selected threshold value, taken from among a first or a second threshold value greater than the first threshold value in absolute terms, and to compare the current intensity value with the selected threshold value; and the current-limiting device is bidirectional and configured to limit the current flowing through the branch to the threshold value selected by the central processing unit.

Classes IPC  ?

• H02H 7/26 - Protection sectionnelle de systèmes de câbles ou de lignes, p.ex. pour déconnecter une section dans laquelle un court-circuit, un défaut à la terre, ou une décharge d'arc se sont produits
• H02H 7/28 - Protection sectionnelle de systèmes de câbles ou de lignes, p.ex. pour déconnecter une section dans laquelle un court-circuit, un défaut à la terre, ou une décharge d'arc se sont produits pour réseaux maillés

Abrégé

The invention relates to a flight management assembly (1) comprising two guidance chains (2A, 2B), each one provided with a flight management system (3A, 3B), each of said flight management systems (3A, 3B) carrying out at least one calculation of guidance instructions for the aircraft, the flight management assembly (1) also comprising at least one monitoring unit (4A, 4B) designed to monitor the guidance instructions calculated by the two flight management systems (3A, 3B) in such a way as to be able to detect and identify a defective flight management system, the monitoring unit (4A, 4B) comprising a monitoring device (5) which verifies particularly whether the following three conditions are met: a first derivative of extrapolated cross tracks is positive; a second derivative of extrapolated cross tracks is positive; and extrapolated positions of the aircraft are on the same side of an active segment of the flight plan followed by the aircraft as the current position of the aircraft.

Classes IPC  ?

• G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
• G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p.ex. pilote automatique
• G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément

Abrégé

The present invention is a method for controlling message transmission power implemented by a system for preventing collisions of aircraft during flight, said system comprising an anti-collision device (10) and a transponder (20) with which each plane is equipped. According to the present invention, said method comprises - a measurement step (E5) for measuring at least the value, referred to as the quality value, of a quantity representative of the quality at which radio-frequency signals carrying response messages (Rep) transmitted by a transponder (2) of an intruding aircraft are received - a control step (E27) for controlling the power of transmission (Pt) of the radio-frequency signals carrying said response messages (Rep) depending on the quality value or values measured in this way. The present invention also concerns a system for preventing collisions of aircraft during flight.

Classes IPC  ?

• G01S 13/78 - Systèmes utilisant la reradiation d'ondes radio, p.ex. du type radar secondaire; Systèmes analogues dans lesquels des signaux de type pulsé sont transmis effectuant la discrimination entre différents types de cibles, p.ex. radar pour l'identification ami–ennemi
• G01S 13/93 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour prévenir les collisions
• G01S 7/02 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
• G01S 7/40 - Moyens de contrôle ou d'étalonnage

Abrégé

The invention proposes a method and a system of simple, precise, rapid and automatic control to verify the fit between a manufactured device and its digital mock-up modelling it beforehand. The system according to the invention comprises a scanner configured to produce a three-dimensional cloud of points (21) representative of said device (19), as well as a processor and a memory that are configured to: - superpose said cloud of points (21) on said digital mock-up (17), - coordinate said cloud of points (21) with polychrome images (22) captured during the scanning of the device and stored in a memory, - dispersing said cloud of points (21) into several sets of points (21a-21c), each set of points corresponding to an object identified in the polychrome images, - establishing a correspondence between said sets of points and nodes (231) of a treelike structure (23) identifying the digital mock-up, and - evaluating a fit between the cloud of points (21) and the digital mock-up by analysing said correspondence between said sets of points and said nodes of the treelike structure.

Classes IPC  ?

• G06F 17/50 - Conception assistée par ordinateur

Abrégé

The present invention relates to a method for controlling the transmission power of request-response messages implemented by a system to prevent collisions between a first aircraft (1) and a second aircraft (2). According to the invention, said method comprises a measurement step (E22) for measuring at least the value, referred to as the quality value, of a quantity representative of the reception quality of the transponder (20) of the intruding aircraft (2) and, implemented by said anti-collision device (10) of the first aircraft (1), a control step (E8) to control the transmission power of the radio-frequency signals carrying the request-response messages (Req) according to the quality value or values contained in the response messages (Rep) sent by said transponder (20). The present invention also relates to an aircraft anti-collision system for implementing such a method.

Classes IPC  ?

• G01S 13/76 - Systèmes utilisant la reradiation d'ondes radio, p.ex. du type radar secondaire; Systèmes analogues dans lesquels des signaux de type pulsé sont transmis
• G01S 7/282 - Emetteurs
• G01S 7/40 - Moyens de contrôle ou d'étalonnage

Abrégé

In an aircraft (1) comprising a cockpit (3), a unit (14) for monitoring the situation of the aircraft and a radio communication unit (12), the device (10) for aiding the ground rolling is configured to: acquire, from the unit for monitoring the situation of the aircraft, information regarding the situation of the aircraft and determine predicted positions of the aircraft for a set of future instants, and for each vehicle of a set of other vehicles (8, 9a, 9b,9c) situated on the surface of the airport: acquire, from the radio communication unit, information regarding the situation of the vehicle, which information is transmitted by this vehicle, determine predicted positions of the vehicle and calculate a distance between the predicted position of the aircraft and the predicted position of the vehicle for each instant of the set of future instants and compare this distance with a predetermined distance threshold (Sd) and, emit an alert in the cockpit if this distance is less than this distance threshold.

Classes IPC  ?

• G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
• G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
• G08G 5/00 - Systèmes de commande du trafic aérien

Abrégé

In an aircraft (1) comprising a cockpit (3) comprising a display screen (8), a camera (5) configured to acquire images of the environment of the aircraft, as well as a display management system (2), the ground rolling aid system (6) is configured so as to: a) acquire several successive images (20) of the environment of the aircraft by means of the camera, corresponding to various ground positions of the aircraft; b) modify these images by removing at least zones (11) corresponding to the aircraft, so as to produce modified images (22); c) combine several of said modified images to produce a recomposed image (26); d) superpose an image characteristic of the aircraft (16, 18) on the recomposed image so as to produce a reference image (26r); and e) display, on the screen of the cockpit, an image (28) corresponding to the reference image.

Classes IPC  ?

• B64D 47/08 - Aménagements des caméras
• G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol

Abrégé

The subject of the invention is a device for attenuating sound waves forming the wall of a duct, the sound waves spreading in a stream of air passing along the duct. The device comprises a structure (13) constituting a noise attenuator, bounded by a perforated internal wall and a solid external wall. The device comprises fluid tight piping for transporting a heat-transfer fluid on the internal face of the internal wall, the piping constituting a network of piping running substantially in one and the same direction, and such that each length of piping is situated between rows of orifices and is situated substantially in line with the cell partitions. The piping together with the internal wall forms a surface heat exchanger.

Classes IPC  ?

• G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
• B64D 15/02 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit
• B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
• F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
• F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit

Abrégé

The invention relates to a method for determining the collision risk of a taxiing aircraft (1) comprising the steps of: determining the trajectory of the aircraft (1); according to said trajectory, determining at least one protective volume (VR, VP) associated with at least one part of the aircraft; detecting an object inside the protective volume (VR, VP); and generating an alarm in response to the detection of the obstacle.

Classes IPC  ?

• G01S 13/93 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour prévenir les collisions
• G08G 5/00 - Systèmes de commande du trafic aérien
• G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol

Abrégé

The present invention relates to a measurement device which can be attached to an outer wall of a movable object or of a stationary object arranged in a flow of air in order to measure physical quantities. The measurement device comprises a mounting (5) which has recesses (11) having an opening leading to the outside, sensors (6) being provided in said recesses. The device includes a cavity (8) into which the recesses (11) lead and which contains a flexible printed circuit (10), to which the sensors (6) are connected. The method for manufacturing such a device is simplified in the invention by including the following steps: attaching sensors (6) to the flexible printed circuit (10); and attaching the flexible printed circuit (10) provided with sensors (6) to the mounting (5), the sensors (6) being inserted into the recesses (11) and the circuit (10) being inserted into the cavity (8).

Classes IPC  ?

• G01D 11/30 - Supports spécialement adaptés à un instrument; Supports spécialement adaptés à un ensemble d'instruments
• G01L 9/00 - Mesure de la pression permanente, ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments électriques ou magnétiques sensibles à la pression; Transmission ou indication par des moyens électriques ou magnétiques du déplacement des éléments mécaniques sensibles à la pression, utilisés pour mesurer la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent

Abrégé

The present invention relates to a measurement device which can be attached to an outer wall of a movable object or of a stationary object placed in a flow of air in order to measure physical quantities. The measurement device comprises a mounting (5) which has recesses (11) having an opening leading to the outside in which sensors (6) are provided. All of said openings of said recesses (11) are covered by a single film (12). The film (12) thus makes it possible to offer a surface which is as smooth as possible, having very low roughness with no unevenness. It also makes it possible to ensure the tightness of the sensors as well as the air insulation between all the sensors of the mounting.

Classes IPC  ?

• G01D 11/30 - Supports spécialement adaptés à un instrument; Supports spécialement adaptés à un ensemble d'instruments
• G01M 9/06 - Dispositions pour la mesure spécialement adaptées aux tests aérodynamiques

Abrégé

The present invention relates to a measurement device which can be attached to an outer wall of a movable object or of a stationary object placed in a flow of air in order to measure physical quantities. The measurement device comprises a mounting (5) which has recesses (11) having an opening leading to the outside in which sensors (6) are provided. The mounting (5) comprises a cavity (8) in which a flexible printed circuit (10) is housed, on which a single circuit for controlling the sensors (6) is provided. The device according to the present invention has multiple advantages, in particular that of providing a simple measurement device which offers a system for control and interconnection of sensors that is accessible and less complex while offering numerous advantages.

Classes IPC  ?

• G01D 11/30 - Supports spécialement adaptés à un instrument; Supports spécialement adaptés à un ensemble d'instruments
• G01L 9/00 - Mesure de la pression permanente, ou quasi permanente d’un fluide ou d’un matériau solide fluent par des éléments électriques ou magnétiques sensibles à la pression; Transmission ou indication par des moyens électriques ou magnétiques du déplacement des éléments mécaniques sensibles à la pression, utilisés pour mesurer la pression permanente ou quasi permanente d’un fluide ou d’un matériau solide fluent

Abrégé

The invention provides, in order to allow a fan engine (10) to be placed as close as possible to the lower surface of a wing box (21), an assembly (1) for an aircraft including means (8) for attaching a rigid structure (6) of an engine strut to the wing box, said means (8) including an upper wing attachment (8a) comprising a fitting (42) secured to the upper surface (35) of the wing box (21).

Classes IPC  ?

• B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur

Abrégé

The invention relates to an aircraft structure (10), in particular the fuselage, nacelles or wings, comprising, over all or part of an outer surface (21) that may undergo lightning impacts, a layer of flexible polymer (30), a photovoltaic film (40) and a protective layer (50) protecting said photovoltaic film. This aircraft structure primarily has a solar energy capture capacity making it possible to meet the needs of an aircraft as well as an ability to protect against the effects of lightning.

Classes IPC  ?

• B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• H01L 31/048 - Encapsulation de modules

Abrégé

The subject of the invention is a seal interposed between two surfaces (60, 62) of an aircraft propulsion assembly. According to the invention, said seal comprises at least two layers, each one comprising a plurality of strands (68) made of a heat-resistant material, the strands of a first layer being directed in a first direction and the strands of a second layer being directed in a second direction different from the first direction.

Classes IPC  ?

• B64D 29/06 - Fixation des nacelles, carénages ou capotages
• B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères

Abrégé

The invention relates to a stiffener for a fuselage, including a hollow section which can be trapezoidal, which has a base (11) attached to the fuselage or to the floor, relatively high vertical sides (13, 14), and a top side (12) contributing to the rigidity of the stiffener (10) and to the cohesion thereof. A direct assembly to the fuselage (5, 9) is possible. The base consists of two edges (15, 16) arranged one above the other or one in front of the other. Said rigid stiffener, despite the non-continuous cross-section thereof, can be manufactured by simple folding operations of an initially planar metal sheet.

Classes IPC  ?

• B64C 1/06 - Cadres; Lisses; Longerons
• B64C 1/12 - Structure ou fixation de panneaux de revêtement

Abrégé

The invention relates to an aircraft fuselage stiffener (4) comprising a heel (14), a sole (16) and a web (12) connecting the heel and the sole (14, 16), this stiffener comprising a bent metal sheet (18) extending along the heel, the web and the sole. In addition, in order to improve the mechanical behaviour of the stiffener, the bent metal sheet (18) comprises, on the one hand, a main portion (20a) extending along the heel, the web and the sole and, on the other hand, at least one bent‑over portion (20b) forming a liner of the main portion over at least part of the web and/or of the heel and/or of the sole.

Classes IPC  ?

• B64C 1/06 - Cadres; Lisses; Longerons

Abrégé

An aircraft landing gear longitudinal force control system (20) for an aircraft having landing gears with braking and/or driving wheel(s). The system includes an error- based force controller (21) having feedback for minimising any error between the demanded force (Fx*) and the actual force (Fx_LG) achieved by the force control system. The feedback may be derived from force sensors on the landing gear for direct measurement of the landing gear longitudinal force. The force control system may include an aircraft level landing gear total force controller and/or a landing gear level force controller for each actuated landing gear.

Classes IPC  ?

• B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
• B64C 25/46 - Régulateurs de freinage pour empêcher le dérapage ou le capotage des aéronefs
• B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage

Abrégé

The present invention provides a landing gear force and moment distributor system (20) for an aircraft having a landing gear including a pair of bogies arranged symmetrically about the longitudinal axis, each bogie having an actuator arranged to brake and/or drive one or more wheels. The force distribution system comprises a distribution module arranged to: receive an input demand including a longitudinal force input demand corresponding to a desired braking or driving force along the longitudinal axis for the landing gear and a moment input demand corresponding to a desired moment about the vertical axis for the landing gear; and to use the received input demand to calculate an output command comprising, for each bogie, a longitudinal force output command corresponding to a braking or driving force along the longitudinal axis to be applied to said bogie to achieve the longitudinal force input demand, and a moment output command corresponding to a braking or driving force along the longitudinal axis to be applied to said bogie to achieve the moment input demand.

Classes IPC  ?

• B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact
• B64C 25/48 - Mécanismes d'actionnement à fonctionnement différentiel aux fins de gouverner
• B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage

Abrégé

The invention relates to a diagnostic apparatus 1 for detecting delamination in the thickness of a laminated composite panel. The diagnostic apparatus allows inspection of a panel having a non-constant thickness along its length. The diagnostic apparatus comprises an ultrasound probe 30 intended to be placed in contact with the front face of the panel to be inspected, an electronic device 40 for controlling the emission and the reception of ultrasound pulses 51 by the ultrasound probe 30, as well as a visualization device 41 furnished in particular with telltales as to the presence or otherwise of delamination in the panel.

Classes IPC  ?

• G01N 29/07 - Analyse de solides en mesurant la vitesse de propagation ou le temps de propagation des ondes acoustiques
• G01N 29/44 - Traitement du signal de réponse détecté

Abrégé

The invention relates to a process for manufacturing a part (111) made of a composite material, said process comprising the following steps: a step of depositing one or more structural plies (12, 13) impregnated with a thermosetting resin (15) in order to form a structural layer, a step of depositing a surface layer as a stack with the structural plies, said surface layer being formed from an assembly (117) of one or more fibres (118) of thermoplastic resin, said assembly being deformable in at least two directions, said thermoplastic resin having a melting temperature close to a polymerization temperature of said thermosetting resin, then, a step of polymerization of the structural layer at the polymerization temperature, the surface layer then taking the shape of a continuous film that coats the structural layer. Said surface layer may ensure the drainage of air during the polymerization step.

Classes IPC  ?

• B29C 63/02 - Garnissage ou gainage, c. à d. application de couches ou de gainages préformés en matière plastique; Appareils à cet effet avec des matières sous forme de feuilles ou de nappes
• B29C 65/02 - Assemblage d'éléments préformés; Appareils à cet effet par chauffage, avec ou sans pressage
• B29C 70/22 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
• B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
• B32B 27/04 - Produits stratifiés composés essentiellement de résine synthétique comme substance d'imprégnation, de collage, ou d'enrobage
• B32B 27/12 - Produits stratifiés composés essentiellement de résine synthétique adjacente à une couche fibreuse ou filamenteuse
• B32B 27/38 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines époxy
• B32B 27/42 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines de condensation d'aldéhydes, p.ex. avec des phénols, des urées ou des mélamines
• C09D 7/12 - Autres adjuvants

Abrégé

The invention relates to a device for the completely automated detection and characterization of a resin flash in a part (100) consisting of a composite material, said device comprising: i) an OCT measuring head (210) including an OCT measuring module; ii) a manipulator (200) capable of moving said OCT head in space; iii) a means (250) for controlling said manipulator; and iv) a computer means (250) including a memory means for acquiring the definition of the geometry of the area (240) to be tested, for recording the measurements, for storing a criterion file, and for performing calculations pertaining to the comparison of the recording with said criterion file. The invention also relates to a method, to be implemented by said device, for the detection and characterization of such a resin flash.

Classes IPC  ?

• G01N 21/84 - Systèmes spécialement adaptés à des applications particulières
• G01N 33/44 - Résines; Matières plastiques; Caoutchouc; Cuir

Abrégé

The invention relates to a method for the nondestructive testing, using laser ultrasonics, of a composite part (100, 500) having a fibrous reinforcement (120) in a resin (110) that optically scatters the laser, characterized in that it includes the steps of: a) taking (720, 820) a measurement of the thickness of the resin of the part on the surface that is illuminated during the laser shot (770, 840), which is capable of generating a thermoelastic effect in said resin and which is referred to as an ultrasonic laser shot; b) adjusting (760, 830) the power of the laser of said ultrasonic shot on the basis of the thickness measurement carried out in step a) so as to eliminate any risk of a flash on the reinforcements; and c) producing the ultrasonic laser shot (770, 840) at the power determined during step b). The device used for implementing said method consists of a combined photoacoustic imaging and low time-coherence interferometry (OCT) system.

Classes IPC  ?

• G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet - Détails
• G01N 29/24 - Sondes
• G01N 29/06 - Visualisation de l'intérieur, p.ex. microscopie acoustique

Abrégé

An electrical core comprising an assembly of power management and distribution contactors. The power management contactors (2) are attached to a first support element (12) and the distribution contactors (4) are carried by a second support element (14) superimposed on the first so as to form a multilayer assembly. The distribution contactors (4) are arranged in double symmetry about two axes perpendicular to one another. They are mechanically linked through a mechanical linkage element extending between two rows of contactors (4) and which carries electrical connection elements (20) connecting the contactors to an element for connecting (22) to a power source. The contactors (2, 4) are assembled in modules (6, 8) according to their type. In particular, the management module (6) comprises at least one modular element common (7, 50, 60) to the power management contactors (2) which is suitable for performing a given secondary function other than the function of establishing a contact.

Classes IPC  ?

• H02B 1/04 - Montage sur ces dispositifs d'interrupteurs ou d'autres dispositifs en général, l'interrupteur ou le dispositif étant muni ou non d'une enveloppe
• H02B 1/056 - Montage sur des tableaux enfichables
• H02B 1/20 - Schémas de barres omnibus ou d'autres fileries, p.ex. dans des armoires, dans les stations de commutation

Abrégé

The device (1) comprises means (3) for emitting an acoustic sequence comprising the repetition of a combination of at least three categories of different synthetic signals, comprising alert noises from birds of prey, interspecies distress signals, and flight signals from various species.

Classes IPC  ?

• A01M 29/16 - CAPTURE OU PIÉGEAGE DES ANIMAUX OU ÉPOUVANTAILS; APPAREILS DE DESTRUCTION D'ANIMAUX OU DE PLANTES NUISIBLES Épouvantails ou dispositifs répulsifs, p.ex. pour oiseaux utilisant des ondes sonores
• G10K 15/02 - Synthèse des ondes sonores

Abrégé

-Method and device for visually scaring animal species, in particular bird species. -The device for scaring comprises means for generating at least one visual signal (S2) comprising at least one image (I2A, I2B), varying in size over time, which simulates approach via an increase in the size of the image (I2A, I2B).

Classes IPC  ?

• A01M 29/06 - CAPTURE OU PIÉGEAGE DES ANIMAUX OU ÉPOUVANTAILS; APPAREILS DE DESTRUCTION D'ANIMAUX OU DE PLANTES NUISIBLES Épouvantails ou dispositifs répulsifs, p.ex. pour oiseaux utilisant des moyens visuels, p.ex. épouvantails, éléments en mouvement, formes spécifiques, motifs ou éléments similaires spécifiques

Abrégé

Improved impact‑resistant and damage‑tolerant aircraft fuselage. The invention relates to a section (32) of the fuselage of an aircraft suffering impacts from external bodies, the fuselage of the aircraft having a curved form with at least one vertical plane of symmetry (A‑A) and a central longitudinal axis, and comprising a skin (35) and a plurality of ring frames (37) arranged perpendicularly to said longitudinal axis, said section (32) of the fuselage also comprising at least one reticular internal structure (51, 53) mounted on a support structure (41, 43), which includes longitudinal beams (39) connected to the skin (35) and interconnected with said ring frames (37), said reticular internal structure (51, 53) being arranged in order to create at least one closed cell (75) with the skin (45) in order to improve the strength thereof and the tolerance thereof to damage from said impacts.

Classes IPC  ?

• B64C 1/06 - Cadres; Lisses; Longerons
• B64D 27/00 - Disposition du montage des groupes moteurs sur aéronefs; Aéronefs ainsi caractérisés

Abrégé

The invention relates to a method for producing a part (10) made of a composite material, comprising a skin (11) and at least one stiffener (12) made of strips, which are in turn made of one or more plies of fibers impregnated with a non-polymerized resin, wherein the method comprises the steps of: producing a preform (15) of the part (10) by pulling the strips through a die (20) for shaping and positioning the skin and the stiffeners, a polymerization core being provided between a first strip and a second strip prior to the passage thereof through the die (20); and pressing the resulting preform (15) in a hot press (30) for a duration dt while applying a pressure P and at a temperature T for polymerizing the resin of the strips in the hot press over a pressing length L that is shorter than the length of the panel.

Classes IPC  ?

• B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.à d. d'objets distincts utilisant des moules opposables, p.ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
• B29C 70/50 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur indéfinie, p.ex. de "prepregs", de préimprégnés [SMC] ou de nappes multiaxiales [XMC]
• B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe

Abrégé

The invention relates to an electrical cabinet for an aircraft, including at least one motherboard (54) comprising, on a first surface thereof, sockets (62) into which PCB boards (56) can be inserted to provide one or more electrical functions, said electrical cabinet being connected to the electrical circuit of the aircraft, which is organized into various electrical harnesses (52) via an electrical connection system, characterized in that the electrical connection system includes at least one additional layer (58) at the second surface (64) of the motherboard (54), the free surface (66) of the last additional layer including sockets (68), each of which ensures the electrical connection to an electrical harness of the aircraft, the additional layer(s) (58) including tracks that enable the reorganization of the electrical circuits from the sockets (62) for the PCB boards (56) so as to make the sockets for the PCB boards consistent with the sockets (68) for the harnesses of the aircraft.

Classes IPC  ?

• H05K 7/14 - Montage de la structure de support dans l'enveloppe, sur cadre ou sur bâti

Abrégé

The invention relates to an electrical center for an aircraft, comprising at least one rack (54) on which at least one module (56) is arranged, said module containing components and including at least one input suitable for being connected to at least one power cable (60) and at least one output suitable for being connected to at least one output cable (64), characterized in that, for one module (56), the output cable(s) (64) pass beneath or into the rack (54) arranged beneath the module.

Classes IPC  ?

• H05K 7/14 - Montage de la structure de support dans l'enveloppe, sur cadre ou sur bâti

Abrégé

An arrangement (2) for selectively making available hydraulic power in separate hydraulic circuits comprises two displacement machines (4, 6), two free-wheels (8, 10) and a drive unit (12) that is preferably arranged between the displacement machines (4, 6). The free- wheels block in opposite directions and are coupled to the displacement machines. Consequently, the first displacement machine (4) is driven in a first rotating direction of the drive unit (12) while the second displacement machine (6) is only driven in a second, opposite rotating direction of the drive unit. This makes it possible to realize an intermittent operation for selectively making available additional hydraulic power in separate hydraulic subsystems by choosing the rotating direction accordingly. This arrangement can reduce the weight and the complexity of a hydraulic system.

Classes IPC  ?

• F15B 11/17 - Systèmes de servomoteurs dépourvus d'asservissement avec plusieurs servomoteurs utilisant plusieurs pompes

Abrégé

The invention relates to a device (1) that comprises a means (4) for adjusting the manoeuvre for adjusting altitude, a means (5) for pre-detecting the transmission of a first type of alarm, a means (6) for determining a first alarm threshold, and a means (7) for establishing an activation height threshold from said first predetermined alarm threshold and from the vertical speed of the aircraft at the time of transmitting the alarm, such that, when the height separating said aircraft (AC) from the set altitude level is strictly greater than said height threshold at the time of transmitting said alarm, said adjusting means (4) is deactivated.

Classes IPC  ?

• G08G 5/04 - Systèmes anticollision

Abrégé

The invention is aimed at effecting rapid, simple protective dome opening, allowing accessibility to the device to be protected (radar and other communication systems, etc.). Accordingly, the invention makes provision for a unique kinematics combining two motions in such a way as to move the dome away while rapidly opening an intervention space. In general, a plane interface (V2) separates, in the initial position before opening, a dome (1) from the entrance face (F1) of a fixed part (10). According to the invention, the opening mechanism consists of two pairs of elements, each pair (21, 22) comprising two connecting elements composed of a rectilinear linkage (2a) and of an arm of greater mechanical strength (20a). The arm (20a) and the linkage (2a) of each pair form a determined angle in lateral view. The ends of the linkages (2a) and of the arms (2b) of each connecting pair (21, 22) are coupled to one and the same fixing support (31, 33) via means of rotational coupling. Each connecting pair (21, 22) forms one of the sides (C1, C2) of a pantograph in the form of an isosceles trapezoid (Tl).

Classes IPC  ?

• H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
• B64C 1/36 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes

Abrégé

The invention relates to a device for transversely supporting a longitudinal test tube and to equipment for determining the mechanical bending properties of such a test tube. According to the invention, the device (1) for transversely supporting a longitudinal test tube (2), comprising a core (2A) and at least one main tab (2B) connected to an end of said core, includes: a body (3) in which a recess (4) is provided, said recess being shaped so as to transversely accommodate said test tube (2) and comprising a main bearing surface (5) with which a surface of said core (2A) is to engage; and mobile clamping means (6) provided so as to press said core (2A) against said main bearing surface (5).

Classes IPC  ?

• G01N 3/04 - Mandrins
• G01N 3/20 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique en appliquant des efforts permanents de flexion

Abrégé

The invention relates to an aircraft including at least one wall (66) defining a first area (I) of the aircraft that is thermally insulated from the outside of the aircraft, and a second area (E) of the aircraft that is not thermally insulated from the outside of the aircraft, and a heat exchanger in which a heat-transport fluid circulates, characterized in that said wall (66) includes at least one pipe (76) in which the heat-transport fluid flows so as to provide the heat-exchanger function.

Classes IPC  ?

• B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret
• B64C 1/10 - Cloisons

Abrégé

The invention relates to an airplane (1) comprising a fuselage (2) which is elongated in a longitudinal direction X of the airplane, a wing (3) attached to the fuselage in a central portion of the fuselage, and a rear fuselage (21) which is located in the rear of the wing (3) and on which the engines (6) are mounted. The airplane further comprises aerodynamic surfaces, a front horizontal stabilizer unit (4), wing end (5) and wing aileron (31) vertical surfaces, which ensure the stability and the aerodynamic control of the airplane and are rigidly connected to the fuselage (2) or the wing (3) in an arrangement such that none of said aerodynamic surfaces is located in a space (62) of potential projection of debris from the engines (6) in case a rotating portion of one of the engines of the airplane breaks.

Classes IPC  ?

• B64D 27/14 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur du fuselage ou fixés à celui-ci
• B64D 27/20 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur du fuselage ou fixés à celui-ci
• B64C 39/12 - Avions canards

Abrégé

The invention aims to secure and control the positioning of the corset on the actuator piston, and also the deployment of the hatches as far as the maximum opening position thereof and the maintenance thereof in this position. To this end, the invention provides the possibility of regulating the length of the corset. A secure corset (4) according to the invention is applied in particular to the immobilization in the maximum opening position of an aircraft landing gear cage hatch (21). The corset (4) has two half-shells (41) that are able to enclose the piston (31) of the actuator (3) having an axis coincident with the common longitudinal axis (A'A) of the half-shells (41) once they are closed around the piston. Locking pins (5) are able to hold the half-shells (41) around the actuator (3). The corset (4) also has a casing (6) secured to at least one of the half-shells (41) and equipped with hooking means (8a) that are able to be coupled to a fixed point (F) on the structure (2). Means (7, 7a, 7b) for varying the distance between the casing (6) and the hooking means (8a) are able to move the hooking means (8a) away from or towards the corset (4) along the common longitudinal axis (A'A) of the half-shells (41).

Classes IPC  ?

• F15B 15/26 - Mécanismes de blocage

Abrégé

The invention relates to a device for implementing a method for pickling/stripping and for simultaneously nondestructively checking a part (100), said device including: a) an energizing laser head capable of generating pulsed energization (212) on the surface of a part (100, 300) according to an energy spectrum adapted for the detachment of the particles (231) adhering to said surface; and b) a detection laser head (220) connected to the energizing laser head and capable of measuring the response of the part to a pulse generated by the energizing head.

Classes IPC  ?

• G01N 29/24 - Sondes
• B23K 26/36 - Enlèvement de matière
• G01N 29/04 - Analyse de solides
• G01N 29/22 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet - Détails
• G01N 29/265 - Dispositions pour l'orientation ou le balayage en déplaçant le capteur par rapport à un matériau fixe

Abrégé

The invention relates to a method and device for automatically managing the separation between two aircraft following one another. The device (1) comprises a means (6, 7) for automatically calculating, prior to performing a function to acquire and maintain separation, orders for controlling speed that enable a trailing aircraft to acquire and maintain a time separation relative to a target aircraft preceding the former.

Classes IPC  ?

• G08G 5/00 - Systèmes de commande du trafic aérien
• G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage

Abrégé

The invention relates to a method for the computer simulation of fluid flows in the environment of an aircraft in order to determine at least one aerodynamic coefficient, in which a first series of aerodynamic coefficient values is obtained. The method also comprises the following steps consisting in: defining a convergence criterion for the aerodynamic coefficient; selecting a predetermined set of terms belonging to the first series; defining a monotonic function in order to apply a relatively expanding transformation to the predetermined set, relative to the complement of said set; applying the aforementioned function to the first series in order to form a second series of aerodynamic coefficient values; determining the aerodynamic coefficient by plotting an evolution curve representing the second series of aerodynamic coefficient values; and displaying said evolution curve including an intrinsic zoom on the convergence area of the aerodynamic coefficient.

Classes IPC  ?

• G06F 17/50 - Conception assistée par ordinateur

Abrégé

The invention aims to produce an instrumentation making it possible to measure the loadings which pass through mechanical joins between two mechanical structures, so as to best evaluate the dimensions and masses without impairing their mechanical properties of a secure transfer of load. To this end, the invention proposes introducing into the zones of transit of the loadings an instrumented component of the form that favours the measurement of shear and its installation. In one embodiment, a zone of transit of loadings consists of an instrumentalized hollow shaft which takes the form of a cylinder (1) able to be introduced into collinear openings (30) in the fittings (20, 25, 26). It comprises a longitudinal housing (10) into which is introduced an insert (2) composed of a central prop (21) in tight contact with the internal wall (1 i) of the shaft (1) and connected, on each side, to a flyweight (31, 32) also in tight contact, by way of multiple tabs (41 to 44) away from contact with said internal wall (1 i). High-temperature gauges (51, 53, 55, 57) are welded to the tabs (41 to 44), so as to measure a variation in electrical resistance corresponding to the bending deformation of the tabs (41 to 44).

Classes IPC  ?

• G01L 1/22 - Mesure des forces ou des contraintes, en général en faisant usage des cellules électrocinétiques, c. à d. des cellules contenant un liquide, dans lesquelles un potentiel électrique est produit ou modifié par l'application d'une contrainte en utilisant des jauges de contrainte à résistance
• G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur

Abrégé

The aim of the invention is to allow the detection and location of electrical faults in a network of metal structures (10) which can receive electric cables and allow the return of current by said cables. The reflectometry-based method involves injecting a probe signal into a cable coupled to the structures (10) and analyzing the signal reflected by the aforementioned anomalies. However, anomaly detection is made difficult by the background noise of the impedance variations of the return signal. To solve this problem, the invention provides a conductive element carrying the probe signal at a constant distance from each structure (10). In one embodiment of the invention, an insulated conductive element (C) is arranged inside the metal structure (10) and is built into a longitudinal groove (50) in a surface (11a) for receiving a longitudinal plastic holder (11) wedged into said structure (10). The reflected signal returned from the conductive element (C) is compared to a threshold above which an anomaly is detected, and said anomaly is located by means of topological correlation. The invention can be used for airplane raceways having a composite skin.

Classes IPC  ?

• G01R 31/08 - Localisation de défauts dans les câbles, les lignes de transmission ou les réseaux
• G01R 31/11 - Localisation de défauts dans les câbles, les lignes de transmission ou les réseaux en utilisant des méthodes de réflexion d'impulsion

Abrégé

The subject of the invention is a device for carrying out a test on a fluid circuit of an aircraft, comprising a test unit (14) which comprises, at the inlet, at least one means of connection (130) to a pressurized gas supply, which means is connected to means (132) for adjusting the pressure of the gas provided by the supply according to the test to be carried out, and, at the outlet, at least two connection means (134) connected to the means (132) for adjusting the pressure of the gas, characterized in that at least two connection means (134) have different dimensions tailored to a range of pressures or a given pressure.

Classes IPC  ?

• G01M 3/02 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide

Abrégé

The subject of the invention is a purge system (22) comprising an open passage (24) and, upstream, a control that allows the hydraulic fluid to flow towards said open passage (24) or prevents it from flowing thereto, said control having a section that can be operated using a given tool, said purge system comprising a removable connection device comprising: coupling means (32) that can be coupled to the purge system, an outlet that can be connected to a pipe (28), a central first part (30) comprising said coupling means (32), a cylindrical bearing surface (34) and a passage (36) extending from the coupling means (32) to the surface (34') of the cylindrical bearing surface (34), an annular second part (38) comprising a bore (40) designed to pivot on the cylindrical bearing surface (34), at least a passage (42) connecting the outlet and the surface (40') of the bore (40), the central part (30) and/or the annular part (38) comprising a groove (62) that allows the hydraulic fluid to flow between the passages (36, 42), characterized in that the central part (30) of the connection device comprises a section (48) to allow said connection device to be coupled to the purge system (22) and which is positioned between the coupling means (32) and the cylindrical bearing surface (34).

Classes IPC  ?

• B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freins; Dispositifs de signalisation
• F16L 27/093 - Raccords avec passages de fluides orientés radialement du type "banjo", c.à d. accouplements pivotants à angle droit
• F16L 41/00 - Tuyaux de branchement; Raccordements des tuyaux aux parois
• F16L 55/07 - Aménagement ou montage de dispositifs, p.ex. soupapes, pour ventiler ou aérer ou purger
• F15B 21/04 - Mesures particulières prises en rapport avec les propriétés du fluide

Abrégé

The invention seeks to allow a remote locking of an element (30) mounted in a structure (3) by a process of pivoting which plans for a lever arm effect (410) to be applied to the element (30). This effect is produced by a control (46) coupled to a linkage engaged with the element (30) to cause it to pivot in a plane (P1) by bearing against the structure (3). An angular offset (A) on this linkage in a plane (P2) then allows the control (46) to become operational remotely. According to one embodiment, a pivot tool (4) comprises a head (41) provided with a lever arm (410), a first rod section (42) coupled to the head (41), an elbow (43) connecting the first section (42) to a second rod section (44), a moving control rod (45) articulated to the second section (44) and a flexible control means (46) connecting the rod (45) to the lever arm (410) via a guiding link (421) connected to the first section (42). Application in particular to a hook that retains a landing gear in the landing gear bay.

Classes IPC  ?

• B25B 9/00 - Outils de serrage tenus à la main autres que ceux prévus au groupe
• B25J 1/04 - Manipulateurs mus dans l'espace manuellement rigides, p.ex. pour atteindre des rayonnages
• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs

Abrégé

The invention belongs to the field of the installation of systems in aircraft. More specifically, the invention relates to the installation of avionics furniture, electrical master boxes and IFE bays. Compared with the arrangements known from the prior art, the invention consists in relocating at least some of the systems furniture toward the front of the aircraft by making use of the space available in the area around the nose gear bay. To do so, the invention uses systems furniture that incorporates a structural function. It thus allows a reduction in the aerodynamic drag of the aircraft.

Classes IPC  ?

• B64C 1/20 - Planchers spécialement adaptés pour recevoir du fret
• B64D 43/00 - Aménagements ou adaptations des instruments
• H05K 7/18 - Structure des bâtis ou des cadres

Abrégé

The stabilizing device (1) comprises auxiliary stabilizers (6) which are mounted on the horizontal tailplane (2) of the aircraft and which generate a lateral stabilizing effect when brought into a deployed position.

Classes IPC  ?

• B64C 5/10 - Surfaces stabilisatrices réglables

Abrégé

A beam (20) comprising first and second flanges (23, 24), the beam (20) having a first region (28, 30) extending between the flanges (23, 24) and a second region (26) extending between the flanges. The first region (28, 30) is designed to support an applied concentrated shear load and the second region (26) is designed to support a predominantly bending load. The first region comprises a fan-shaped truss comprising a hub (36) adjacent the first flange and a plurality of struts (37) which extend substantially radially from the hub (36), and the second region (26) comprises either a truss structure which is substantially regular in the longitudinal beam direction or a shear web. The beam may, for example, be used as a floor beam for an aircraft fuselage.

Classes IPC  ?

• B64C 1/18 - Planchers

Abrégé

The subject of the invention is a method for producing a central wing box comprising an upper panel (32), a lower panel (34), a front spar (36) and a rear spar (38), the upper edges of said spars (36, 38), which are approximately parallel to an axis Y, being connected by the upper panel (32) and the lower edges of said spars (36, 38), which are approximately parallel to the axis Y, being connected by the lower panel (34), characterized in that it consists in making at least one panel and at least one spar as a single piece from a composite material.

Classes IPC  ?

• B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices
• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
• B29C 70/30 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
• B32B 37/14 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches

Abrégé

The aim of the invention is to allow the set of doors to be adjusted without increasing the number of landing gear retraction/extension manoeuvres, by incorporating a specific entrance in the fairing (2) of the landing gear bay (4) that provides access to the different accessories (14, 17a, 17b) used to adjust the doors (21-25). The method of the invention consists in: providing a removable bodywork element (5) which is inserted into the fairing (2) of a landing gear bay, surrounded by a stiffening structure (7) and of sufficient dimension such that the adjustment levers (14, 17a, 17b) can be reached from the outside; accessing the inside of the bay (4) by retracting the removable bodywork element (5); and using the levers (14, 17a, 17b) to adjust the different doors (21 to 25) in a flush aerodynamic position, as well as the clearances between said doors. In one embodiment of the invention, one door (25) comprises a central bodywork portion (5) and a peripheral portion (7) including stiffening means (70). The peripheral portion (7) is surrounded by a seal (30) that bears on the other doors (21-24) via the stiffening means (70) and the central portion (5) is coupled to the peripheral portion (7) by removable separation means (6).

Classes IPC  ?

• B64C 25/16 - Carénages mobiles en liaison avec des éléments de l'atterrisseur
• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs

Abrégé

The invention relates to the field of assembly methods and devices. More particularly, the invention relates to the assembly of two shell elements which are placed side by side along an assembly interface substantially perpendicular to the shell when the two shell elements to be assembled are made from a composite material. For this purpose, the invention provides a device for assembling two structural elements made from a composite material, said device comprising: - two flanged cylindrical receptacles (31, 32) each pierced with a hole (310, 320) perpendicular to the axis of the cylinder; - a shaft (40) that can be inserted into the holes; - bearing means (51, 52, 510, 520) which bear on the internal surfaces of the cylindrical receptacles and can maintain tension in the shaft (40) when the shaft is extending through the holes in the two receptacles; and - means (51, 52, 521) for placing the shaft under tension.

Classes IPC  ?

• F16B 5/00 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles

Abrégé

The invention relates to a positioning device for assembling parts on a structure. Specifically, the invention relates to a positioning device intended for assembling stationary brackets on an aircraft structure. A laser projector is attached directly to the rigid structure of the aircraft and the position of the projector is therefore stable relative to the structure, even if said structure is deformed slightly. The position of the projector is determined in an exact manner via test patterns, which are also attached to the primary structure. The invention also relates to a method for implementing said device.

Classes IPC  ?

• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
• G01C 15/02 - Moyens pour marquer les points de mesure
• B23Q 17/24 - Agencements sur les machines-outils pour indiquer ou mesurer utilisant des moyens optiques

Abrégé

According to the invention, the upper end of the inclined front strut (9i) of the landing gear is connected to the structure (2A) of the fuselage by connecting means (13, 17).

Classes IPC  ?

• B64C 25/12 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté latéralement

Abrégé

The aim of the invention is to reduce the multiple costs of manufacture, assembly, use, and upkeep connected with the assembly of window coaming on aircraft fuselages. To this end, the invention provides a particular shape for the coaming (20) connected to the fuselage skin (30) according to a specific assembly method. Said shape enables, inter alia, the window coaming to be fitted onto the skin by means of adhesion and also coaming to be dispensed with between the fuselage and the window. In one embodiment, composite material window coaming (20) has a wall totally in the shape of a crown (21) that is connected, through co-adhesion, to the inner surface of the fuselage skin (30), also made of composite material. The skin (30) is cut into a window-receiving opening (40), and the coaming (20) has a T-shaped cross-section, wherein the bar of the "T" that forms the crown (21) includes two portions (21a) and (21b) having substantially equal lengths "I".

Classes IPC  ?

• B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise

Abrégé

The invention relates to a device for driving at least one landing gear wheel of an aircraft by means of a wheel motor, which is intended to be used in the stage when the aircraft is traveling on the ground, said aircraft having turbojet engines (1) attached to the main wing. The device comprises at least one power source (6, 8), and one power transmission line between the power source and the wheel motor. The power source (6, 8) is arranged adjacently to a turbojet engine (1) attached to the main wing of the aircraft, and comprises disengageable means (7) enabling the power source to be mechanically connected to the rotating portion of the turbojet engine (1), the power source being sufficient to act as a starter for the turbojet engine (1).

Classes IPC  ?

• B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact

Abrégé

The invention relates to a control member (A) comprising actuation members (F) such as a rudder bar and brakes for a pilot in an aircraft, said actuation members comprising a rotary shaft (2) that is rotatable around an axis (40). Said shaft is rotated during an action of the pilot on the actuation members (F), in particular the brake pedals, by means of mechanical transmission between said shaft and said actuation members. Said control member (A) also comprises a device (1) for generating resistive torque, which is suitable for being attached along the rotary axis of the control member, the device for generating resistive torque comprising a friction disk (3, 4, 5) that is axially mounted and secured to the rotary shaft (2). A first annular track (6, 7, 8) is attached to a frame element (9) of the control member and to bearing means (10, 11, 12).

Classes IPC  ?

• B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
• B64C 13/46 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide avec dispositif artificiel de sensibilité
• G05G 5/03 - Moyens pour attirer l'attention de l'opérateur sur l'arrivée de l'organe de commande dans une position de commande ou de repère; Création d'une sensation, p.ex. moyens pour générer une force antagoniste
• G05G 1/30 - Organes de commande actionnés par le pied

Abrégé

The invention relates to a tool holder device for holding in position and driving a cutting tool on a machine tool. Said tool holder is used as a reliable machining overseeing device, capable of preserving the workpiece, the machine and the tool holder in the event of unforeseen occurrences, and can be used on any machine whatever the tool and whatever the power of said machine. To this end, the tool holder of the invention comprises: a friction coupling (20) with adjustable slipping torque coupling the arbour attachment (11) to the tool attachment (12); detection means (5) for detecting relative slippage between the arbour attachment (11) and the tool attachment (12). Thus, the cutting force, which is manifested in the form of the tool drive torque, cannot exceed a value that has been predetermined through the adjustable slipping torque. The possibility of detecting this slippage allows appropriate action to be initiated.

Classes IPC  ?

• B23B 31/38 - Mandrins de serrage avec des embrayages de surcharge
• F16D 7/02 - Accouplements à glissement, p.ex. glissant en cas de surcharge, pour absorber les chocs du type à friction
• B23Q 15/007 - Commande automatique ou régulation du mouvement d'avance, de la vitesse de coupe ou de la position tant de l'outil que de la pièce pendant l'action de l'outil sur la pièce
• B23B 29/04 - Porte-outils pour un seul outil de coupe
• B23Q 11/04 - Dispositions pour empêcher la surcharge des outils, p.ex. réduisant la charge

Abrégé

The invention relates to an aircraft comprising at least one net for reducing aerodynamic noise from a structural element of said aircraft. According to the invention, the flexible net (5A) associated with the structural element (2) is retractable and capable of occupying at least one position located between the following two end positions: a deployed position, in which the net is placed in a turbulence area (T), and a retracted position, in which said net (5A) is at least partially outside said turbulence area (T).

Classes IPC  ?

• B64C 23/00 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs

Abrégé

The invention relates to an aircraft nacelle comprising an air inlet (110) with a lip (114) extended to the back by a passage (116) that makes it possible to channel an air flow to a drive (112), said passage (116) comprising at least one acoustic treatment panel (120) that includes, from the outside to the inside: an acoustically resistant porous layer (122); at least one cell-like structure (124), the cells of which are sized for acoustic treatment; and a reflective or sealed layer (126). Said reflective layer (126) comprises, near the end thereof that is oriented toward the lip (114), a surface (130) that is angled so as to be connected to the lip (144). A cell-like structure (136) is in contact with the angled surface (130) of the reflective layer, and the angled surface (130) forms an angle less than 30° with the tangent on the acoustically resistant layer. Said aircraft nacelle is characterized in that the cell-like structure (136) is inserted between said angled surface (130) of the reflective layer and an acoustically resistant porous layer. Said aircraft nacelle is also characterized in that the cells of the cell-like structure (136) are sized for acoustic treatment.

Classes IPC  ?

• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion

Abrégé

The invention relates to an aircraft nacelle including a first subassembly consisting of a pipe (112) channeling an airflow in the direction of an engine having a covering or panel (118) for acoustic treatment, including, from the inside to the outside, a reflecting layer (120), at least one cellular structure (122), and at least one acoustically resistive structure (124) forming the aerodynamic surface of the pipe (112), as well as a second subassembly consisting of a lip (116) and a front frame (126), characterized in that it includes at least one connection element (134) which is separate from the two subassemblies and connected to a portion of the pipe (112) and to a portion of the lip forming an extension of said portion of the pipe at different points so as to be capable of enabling a relative movement between the two subassemblies.

Classes IPC  ?

• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion

Abrégé

The invention relates to the jet propulsion unit of an aircraft, which comprises a turbofan engine (3), faired by a nacelle, comprising a thrust reverser device in two parts: one part including a means for feeding back air (15) towards the outside of the propulsive unit, on a first angular sector of the nacelle; one part including internal deflectors which can be removed and controlled, suitable for channelling the secondary air flow, circulating in a secondary jet between the propulsive unit and the fairing in a second angular sector of the nacelle, such as to offset the latter angularly in the secondary jet towards a certain external thrust reversal means. The internal deflectors consist of at least two mobile surfaces (22, 23), each rotatably hinged between an inoperative position, in which the mobile surface is continuous with the inner surface of the fairing of the nacelle, and a thrust reversal position, in which said mobile surfaces (22, 23) locally interrupt the longitudinal secondary air flow, and channel the latter gradually towards some of the air feedback means.

Classes IPC  ?

• F02K 1/70 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante

Abrégé

The invention relates to a blade (5) for a double-curved surface (1), said blade including a flexible longitudinal scraper (6) and a means (8) for exerting a bearing force on at least one point of the scraper in a direction Z mainly normal to the surface. The invention also comprises: a longitudinal part (7) solidly connected to the scraper at a plurality of points (10); and means for changing the flexural rigidity of the longitudinal rod over time, in least at one segment thereof, in a plane XZ that is normal to the surface and between preselected values. The longitudinal part is a metal blade having very different inertia values on the two axes of the cross-section thereof.

Classes IPC  ?

• B60S 1/38 - Balais d'essuie-glaces

Abrégé

The invention relates to a method for repairing aircraft primary structures. In particular, the invention relates to a method for repairing damage to the coating (1) of an aircraft fuselage, said coating comprising a fiber-reinforced composite material. The method includes a step consisting in: making a substantially parallelepiped cut (11) in the fuselage around the damage, and piercing a substantially circular opening (10) centered on the intersection between the sides of the parallelepiped contour of the cut and each of the vertices of said contour prior to the cutting operation.

Classes IPC  ?

• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs

Abrégé

The device intended for double glazing comprising at least one outer glazing (1) and one inner glazing (2), which glazings are separated by a gas-filled intermediate space (3), used for insulating an interior environment against an exterior environment, there being likely to be a variation in pressure between these environments, for example in the case of an aircraft in flight, comprises means for keeping the outer glazing and the inner glazing of this double glazing chiefly parallel, independently of this variation in pressure. The invention also relates to double glazing comprising this device, to the method for maintaining parallelism and to software for implementing the method.

Classes IPC  ?

• B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise
• E06B 3/677 - Vidage ou remplissage de l'espace entre les vitres; Prévention de la condensation dans l'espace entre les vitres; Nettoyage de l'espace entre les vitres

Abrégé

The invention relates to a method for designing repair kits for a predefined area of the external/internal structure of an aircraft, said repair kits each including an external/internal structural part having predefined shape and size, suitable for being placed within the existing external/internal structure, instead of an equivalent shape comprising a damaged area, which can be removed or not, said method comprising a step of creating a range of standardised repair kits, optimised according to an estimate of the most likely types of accidental damage in the studied area.

Classes IPC  ?

• G06F 17/50 - Conception assistée par ordinateur
• B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs

Abrégé

The invention relates to an air inlet of an aircraft nacelle including a pipe, extending over the circumference of said air inlet and defined in the back by a front frame, and a means for the localized injection of hot air into said pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. Said inlet is characterized in that it includes at least one vortex generator (38) in the pipe (22), said generator being plate-shaped or shaped in a manner projecting from the wall of the pipe (22), in order to disrupt the hot air flow so as to compensate the effect of the centrifugal force and reduce the temperature gradient between the inside and outside of said pipe (22).

Classes IPC  ?

• B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud

Abrégé

The subject of the invention is an aircraft nacelle air intake comprising a duct extending around the circumference of said air intake and means (24) for the localized injection of hot air into said duct to make the hot air circulate in the duct along its circumference, characterized in that the injection means (24) comprise a collector tank in a plane secant with the direction of the stream of air flowing through the duct comprising at least one hole (44) allowing the air stream flowing in the duct to pass through it and a plurality of injection orifices (46) which are connected to a hot air supply and arranged around the passage hole or around and/or between the passage holes (44).

Classes IPC  ?

• B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
• F02C 7/047 - Chauffage pour prévenir le givrage

Abrégé

The invention relates to a device for drilling and/or boring large complex panels. Said device includes: a template positioned and stationary relative to said panel; an effector (40) suitable for communicating a rotary cutting movement and an advance movement to a tool, which can be described according to at least three linear axes and two rotary axes in relation to a marker attached to the effector, referred to as the effector origin; a means suitable for positioning the effector origin relative to the panel including relative locking of the template and the effector.

Classes IPC  ?

• B23B 45/02 - Perceuses tenues à la main ou perceuses analogues portatives, p.ex. en forme de pistolet; Equipement à cet effet entraînées électriquement
• B23B 47/28 - Gabarits de perçage de pièces
• B23Q 1/54 - Supports mobiles ou réglables d'outils ou de pièces utilisant des mécanismes particuliers avec des guidages en rotation uniquement avec deux guidages en rotation uniquement
• B23Q 15/26 - Commande ou régulation de la position de l'outil ou de la pièce de la position angulaire
• B23B 49/02 - Gabarits ou douilles d'alésage
• B23C 1/20 - Dispositifs ou machines portatifs; Dispositifs ou machines à commande manuelle
• B23B 35/00 - Méthodes d'alésage ou de perçage ou autres méthodes de travail impliquant l'utilisation de machines à aléser ou à percer; Utilisation d'équipements auxiliaires en relation avec ces méthodes

Abrégé

The invention relates to a fluid ejection device which is used specifically as an extinguisher, the ejected fluid then being an extinguishing agent in liquid or powdered form. Said device comprises: a cylindrically-shaped tank (1), which is sealingly separated perpendicularly to the axis thereof, into two chambers (11, 12), by means of a so-called piston (10) element capable of sliding axially inside the tank; a first chamber (11) containing a non-gaseous fluid (110), which is in communication with an ejection opening (13) closed by a cap (30) capable of opening at a pressure greater than or equal to a pre-determined pressure in said first chamber; a second so-called pressurization chamber (12) capable of being connected to means (40) for increasing the pressure in said chamber; and a means (101) linking the piston to the tank in complete connection in a first axial so-called storage position, which means are capable of breaking and releasing the piston in axial translation at a pressure greater than or equal to a pre-determined pressure in the pressurization tank (12), so as to cause the fluid (110) to be ejected.

Classes IPC  ?

• A62C 13/66 - Extincteurs portatifs sous pression permanente ou mis sous pression immédiatement avant l'emploi la substance extinctrice et le gaz comprimé étant emmagasinés dans des récipients distincts
• A62C 35/02 - Matériel installé à demeure avec des réservoirs pour délivrer la substance extinctrice

Abrégé

The invention relates to a method for manufacturing a composite material curved part, during which the composite material fiber layers (110) that should form said part are kept tensioned at least during the folding step, the movement of said layers relative to each other being moreover monitored. The invention also relates to a device capable of implementing said method.

Classes IPC  ?

• B29C 70/30 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
• B29C 70/56 - Tensionnage des renforcements avant ou pendant le façonnage
• B29C 53/02 - Cintrage ou pliage
• B29C 53/04 - Cintrage ou pliage de plaques ou de feuilles

Abrégé

The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.

Classes IPC  ?

• B64C 7/02 - Fuseaux-moteurs
• B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
• B64D 29/02 - Nacelles, carénages ou capotages des groupes moteurs montés dans les ailes

Abrégé

The invention relates to a mounting (1) for holding an elongate object (13) such as an electric cable in position relative to a structure (12). According to the invention, said mounting comprises: two parts for connecting the mounting to the structure (2, 3, 21, 22) each of which has a bearing surface (2a, 3a, 21a, 22a) suitable for resting each side of the structure against a bearing surface (12a, 12b) of the structure, said two connecting parts being assembled together by a clamping means (7, 8, 10), at least one supporting part (4, 23, 24) suitable for maintaining said elongate object (13) via a holding means (50, 31, 37, 69), characterised in that said mounting part is provided in the form of a substantially cylindrical railing (23, 24), secured to a connecting part.

Classes IPC  ?

• H02G 3/22 - Installations de câbles ou de lignes à travers les murs, les sols ou les plafonds, p.ex. dans les immeubles
• H02G 3/32 - Installations de câbles ou de lignes sur les murs, les sols ou les plafonds utilisant des colliers de fixation
• F16L 3/16 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger
• F16L 3/24 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers avec un élément spécial pour fixation à des poutres profilées

Abrégé

An adjustable, or all -moving, horizontal stabiliser (4) for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake (7) fixed with respect to the stabiliser (4) and attached to, or integrally formed with, the stabiliser leading edge adjacent the root.

Classes IPC  ?

• B64C 5/02 - Plans fixes horizontaux
• B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons

Abrégé

The invention relates to a device and a method for producing long textile preforms for the production of structural composite parts by means of a resin infusion method. The device and the method according to the invention are suitable for producing essentially circular preforms for, for example, producing frames or sections of frames of aircraft fuselage. The invention relates to a method for progressive and continuous placement over the length of a long form of a fibrous strip (21) comprising a small quantity of a binding agent for forming a preform (12) having a section comprising at least two non-coplanar wings.

Classes IPC  ?

• B29C 70/22 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
• B29C 70/38 - Empilage automatisé, p.ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
• B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement

Abrégé

The invention relates to an automated device for the use of a drape-forming step in order to form a laminated fibrous preform that is then soaked with resin so as to produce a composite material part. The invention also relates more specifically to the creation of preforms for manufacturing parts, such as optionally high-thickness panels, that essentially extend in two dimensions. The device of the invention includes a master controller (1) capable of spatially moving and positioning a drape-forming head (10), said drape-forming head including: a drum comprising a vacuum opening that leads to the surface thereof and is capable of individually gripping a length of fabric on a mounting outside the equipment and the drape-forming head (10); and a means suitable for subsequently placing said length of fabric down on the preform (70), said fabric-placing means including a compacting means and a means for heating the length of fabric.

Classes IPC  ?

• B29C 70/38 - Empilage automatisé, p.ex. utilisant des robots, par application de filaments selon des modèles prédéterminés

Abrégé

The invention relates to a radome (1) for an aircraft and, specifically, to a device for connecting said radome to the structure of said aircraft. The radome that is the subject matter of the invention includes a plurality of locking units suitable for engaging the opposing surfaces of the fuselage (10) of the aircraft and the radome (1), each unit comprising: a locking means (20) suitable for exerting a tractive force on the surface of the fuselage, substantially normal to the latter, by means of the attachment means; a centring means suitable for passing on the shearing forces substantially tangential to the opposing surfaces of the fuselage and the radome; the locking means (20) being placed so as to be located inside the resulting stress cone on the centring means in order to minimise the bending strain generated by assembly in the radome (1).

Classes IPC  ?

• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p.ex. radome
• B64C 1/36 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes

Abrégé

The invention relates to a method for dimensioning, by an analytical method, an essentially plane panel consisting of a homogeneous and isotropic material, said panel consisting of a skin reinforced by a set of three parallel bundles of stiffeners built into the panel. The pockets determined on the skin by said groups of stiffeners are triangular, the stiffeners are blade-shaped, and the stiffened panel must comply with specifications of mechanical resistance to pre-determined external loads, the angles between bundles of stiffeners being such that the triangular pockets have any kind of isosceles form.

Classes IPC  ?

• G06F 17/50 - Conception assistée par ordinateur

Abrégé

The invention relates to an interface device (1) between an injection tube (2) and a mold (3) provided with an injection hole (4), characterized in that the interface device (1) comprises a terminal element for an injection tube, comprising an end piece (5a, 5b) inserted into one end of the tube (2) and a sealing ring (6) that slides onto the tube, and a means (7, 8) for holding and clamping the terminal element. Said means (7, 8), which is to be screwed into a mounting (9) that is rigidly connected to the mold and is arranged around the injection hole (4), forms a seal between an injection end of the end piece and a sealing surface (10, 11) of the mold at the injection hole. The dismantlable assembly comprises a screw-on socket (7) that has a supporting surface (7a) for the sealing ring (6).

Classes IPC  ?

• B29C 33/00 - Moules ou noyaux; Leurs détails ou accessoires
• F16L 41/08 - Raccordements des tuyaux aux parois ou à d'autres tuyaux, dans lesquels l'axe du tuyau est perpendiculaire au plan de la paroi ou à l'axe de l'autre tuyau
• F16L 41/14 - Raccordements des tuyaux aux parois ou à d'autres tuyaux, dans lesquels l'axe du tuyau est perpendiculaire au plan de la paroi ou à l'axe de l'autre tuyau par vissage d'une pièce intermédiaire contre l'intérieur ou l'extérieur de la paroi

Abrégé

The invention relates to a device for protecting piping from lightning, characterized in that the piping consists of tubular metal sections (1, 2, 3) connected to each other by connection parts (6a, 6b, 4a, 4b, 51, 52), a first portion (4a, 4b, 51) of the connection parts being plastic material parts and a second portion (6a, 6b, 52) of the connection parts being metal parts.

Classes IPC  ?

• B64D 45/02 - Dispositifs de protection contre la foudre; Déperditeurs de potentiel
• F16L 25/02 - Structure ou détails de raccords de tuyaux non prévus dans les groupes ou présentant in intérêt autre que celui visé par ces groupes spécialement adaptés pour isoler électriquement l'une de l'autre les extrémités raccordées des tuyaux
• F16L 27/12 - Raccords réglables; Raccords permettant un déplacement des parties raccordées permettant réglage ou déplacement sensiblement longitudinal
• F16L 39/04 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux permettant réglage ou déplacement

Abrégé

The present invention relates to a tapped insert for cylindrical plain bore (30) of a part A1 comprising a cylindrical body (10), characterized in that said cylindrical body (10) comprises an inner bore (11) of frusto-conical shape, and at least one longitudinal slot (12, 12') extending into the cylindrical body (10) and communicating with said frusto-conical inner bore (11) and characterized in that the tapped insert also comprises a core (20) of frusto-conical shape complementary with said frusto-conical inner bore (11) of the cylindrical body (10), said core (20) comprising a inner tapped aperture (21), said cylindrical body (10) and said core (20) being such that said tapped insert can be holded in position and locked in said cylindrical bore (30) to equip said cylindrical bore with an inner taping.

Classes IPC  ?

• F16B 13/06 - Chevilles ou autres dispositifs fixés à des parois ou autres emplacements par insertion dans des trous préparés à cet effet avec parties s'agrippant dans le trou ou derrière la paroi après insertion et combinées avec un manchon extensible
• F16B 2/04 - Brides ou colliers, c. à d. dispositifs de fixation dont le serrage est effectué par des forces effectives autres que la résistance à la déformation inhérente au matériau dont est fait le dispositif internes, c. à d. agissant par expansion

Abrégé

The present invention relates to a device for mechanically linking with rotating axis at least two parts (P1, P2), which is adapted to extend in a longitudinal direction (X) in coaxial bores (A1, A2) formed respectively in said at least two parts (P1, P2) hinged in relation to each other around the axis (X), wherein it comprises: - a cylindrical body (10) comprising at least one end portion (13) provided with at least one longitudinal slot (13a), said cylindrical body (10) comprising in said longitudinal direction (X) a cylindrical bore extended by a frusto-conical bore (12) extending in said at least one end portion (13) intended to be located in the bore (A2) of part (P2); - an insert (20) of frusto-conical shape substantially complementary to said frusto-conical bore (12), said insert (20) including a tapped aperture (21) extending in said longitudinal direction (X) when said insert (20) is accommodated in said frusto-conical bore (12), and - a screw (30) with a threaded end (31) adapted to cooperate by screwing with said tapped aperture (21) of said insert (20) allowing to lock the cylindrical body (10) in the bore (A2) and making a rotoide joint around axis (X).

Classes IPC  ?

• F16B 5/02 - Jonction de feuilles ou de plaques soit entre elles soit à des bandes ou barres parallèles à elles par organes de fixation utilisant un filetage
• F16B 13/06 - Chevilles ou autres dispositifs fixés à des parois ou autres emplacements par insertion dans des trous préparés à cet effet avec parties s'agrippant dans le trou ou derrière la paroi après insertion et combinées avec un manchon extensible

Abrégé

The invention relates to a frame for a door provided at an opening provided in an aircraft fuselage defined by a skin, said frame including an upper longitudinal stiffener and a lower longitudinal stiffener connecting two vertical substructures (62) together, which are arranged on either side of the opening at which at least one abutment (56) is provided for transferring the radial forces exerted by the door, characterized in that each vertical substructure (62) includes at least three walls made of a composite material and connected together so as to form a closed and hollow profile in order to obtain a shell structure.

Classes IPC  ?

• B64C 1/14 - Fenêtres; Portes; Trappes d'évacuation ou panneaux de visite; Structures de cadres environnants; Verrières; Pare-brise

Abrégé

The invention relates to a method for making a profile section made of fibers (32) and intended for filling a space, having a cross-section in the shape of a nail head or of a half of a nail head resulting from the assembly of preforms in a T shape, at least one of said performs having a radius of curvature at the junction area of said preforms, characterized in that the method consists of feeding fibers (28) coated with a powder to a preforming station (30) at which said powder is activated and said fibers (28) move in a passage, the shapes of which are adapted to those of the desired profile section, and then moving said preformed fibers in a shaping station (34) at which said fiber profile section (32) is cooled and shapeed by passing into a cavity, the shapes of which are adapted to those of the desired profile section.

Classes IPC  ?

• B29C 70/20 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans une seule direction, p.ex. mèches ou autres fibres parallèles
• B29C 70/52 - Pultrusion, c.à d. façonnage et compression par traction continue à travers une matrice

Abrégé

The invention relates to a system for attaching an element (3) capable of vibrating onto an aircraft structure (2), comprising at least one pair of scoops (10) attached onto the element capable of vibrating, as well as onto the structure, each scoop (10a, 10b) of the pair of scoops comprising: an outer rigid element (12) attached onto the structure; an inner rigid element (13) mounted inside the outer rigid element and rigidly connected to the element capable of vibrating; and a flexible element (14) placed along each outer rigid element flank, between the outer rigid element and the inner rigid element.

Classes IPC  ?

• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur