The invention relates to a system (40) for moving a movable flap (16) on the leading edge of an aircraft wing, wherein the system is configured to move the movable flap between an extended position and a retracted position relative to a fixed portion (8) of the wing, and wherein the movement system (40) comprises a movable rail (42) for guiding and/or driving the flap (16), wherein the movable rail, when the movable flap is in the extended position, has an extended portion that projects from the fixed portion (8) of the wing and extends to a connecting end (50). According to the invention, the system comprises an aerodynamic fairing (62) of the movable rail, wherein the system is configured such that, when the movable flap (16) is in the extended position, the fairing (62) extends around at least part of the extended portion (42a).
A transport container is provided for a system for detecting a flow of parts. The container comprises a first holder comprising a first specific shape for receiving a first part type to be transported, a first detector for detecting a state of occupancy of the first holder, and a detector of a geolocation of the container and a controller configured to transmit an identifier of the container together with the state of occupancy of the first holder and the geolocation. A system for detecting a flow of parts is also provided, the system comprising a container as described before. A method for managing the flow of parts implementing said system is also described.
B65D 85/68 - Réceptacles, éléments d'emballage ou paquets spécialement adaptés à des objets ou à des matériaux particuliers pour machines, moteurs ou véhicules assemblés ou en pièces détachées
B65D 90/48 - Aménagements des dispositifs indicateurs ou de mesure
3.
RAPID ATTACHMENT FOR A MOVABLE FLAP MODULE OF AN AIRCRAFT WING
A method for manufacturing a connecting part between a wing box and a leading edge module. The method comprises performing a three-dimensional scanning of a first representative part of the wing box to obtain a first computer model and performing a three-dimensional scan of a second representative part of the leading edge module in order to obtain a second computer model. The first part comprises a first reference region and a first connecting region, the second part comprises a second reference region and a second connecting region. A relative position of the first reference region is defined with respect to the reference region. From the first and second computer model, the connecting part is configured to connect the first and the second connecting region such that the first and the second reference region are located in said relative position. The connecting part is then manufactured.
A profile section for an equipment support panel. The profile section is formed in one piece, comprising a tube suitable for forming a heat pipe by introducing and confining a heat-transfer fluid inside of same, and a groove provided to form a rail along its length for securing at least one piece of equipment supported by the panel, this groove being shaped to form-fittingly engage with an attachment member rigidly connected to the at least one piece of equipment.
A system for protecting a surface of an aircraft against icing by blasting a quantity of warming air against the surface in order to warm it, this quantity of warming air needing to be at a permissible temperature to which the surface can be exposed without compromising the mechanical integrity thereof. The system includes: structures for bleeding a quantity of bleed air from a pneumatic hot source and for conveying this quantity of bleed air, the quantity of bleed air being at a temperature higher than the permissible temperature; structures for capturing and conveying a quantity of collected air corresponding to a portion of the quantity of warming air after it has been blasted against the surface that is to be warmed, this quantity of collected air being at a temperature lower than the permissible temperature; regulating and mixing structures which regulate the quantities of collected and bleed air in order, by mixing these two quantities, to form the quantity of warming air at the permissible temperature; structures for conveying the quantity of warming air towards and blasting it against the aircraft surface that is to be warmed.
The present invention relates to an adjustable guide bushing (10) comprising a first bushing (20) with a first eccentric opening (30) and a second bushing (40) with a second eccentric opening (50), wherein the first bushing (20) is accommodated in the second opening (50) of the second bushing. The invention also relates to a procedure for adjusting the eccentricity of said bushing.
The present invention relates to a transport container for a system for detecting a flow of parts. The container comprises a first holder comprising a first specific shape for receiving a first type of part to be transported, a first detector of a state of occupancy of the first holder, and a detector of a geolocation of the container and a controller configured to transmit an identifier of the container together with said state of occupancy of the first holder and said geolocation. The invention also relates to a system for detecting a flow of parts, the system comprising a container such as described above. A method for managing the flow of parts implementing said system is also described.
B65D 85/68 - Réceptacles, éléments d'emballage ou paquets spécialement adaptés à des objets ou à des matériaux particuliers pour machines, moteurs ou véhicules assemblés ou en pièces détachées
B65D 90/00 - Parties constitutives, détails ou accessoires des grands réceptacles
B65D 90/48 - Aménagements des dispositifs indicateurs ou de mesure
8.
MOVABLE LEADING-EDGE FLAP WITH MULTIPLE FORCE FLOW PATHS
The invention relates to a movable leading-edge flap (16) comprising an aerodynamic part (19) and at least one drive and guide rail system (42), which system includes two rails (44) each extending over the entire length of the rail system, an intermediate reinforcement (46) provided with a toothed drive track being housed between the two rails (44) in a direction in which these three separate elements are stacked, rail-fastening elements (52) allowing each rail to be fastened to the intermediate reinforcement (46), and each of the two rails (44) having an overall C-shaped cross-section, with the two Cs arranged back-to-back and the recesses (58) thereof open in the spanwise direction (17), the recesses (58) defined by the overall C-shape of the rails being intended to receive elements for guiding the movable flap.
B64C 9/22 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
9.
RAPID ATTACHMENT FOR A MOVABLE FLAP MODULE OF A WING OF AN AIRCRAFT
The present invention relates to a method for manufacturing a connection part (10) between a wing box (20) and a leading edge module (30). The method comprises the steps of carrying out a three-dimensional digitization of a first part representative of the wing box (40) in order to obtain a first digital model (50), and of carrying out a three-dimensional digitization of a second part representative of the leading edge module (60) in order to obtain a second digital model (70). The first part comprises a first reference region (80) and a first connection region (90), and the second part comprises a second reference region (100) and a second connection region (110). A relative position (120) of the first reference region with respect to the second reference region is defined. On the basis of the first and second digital model, the connection part (10) is designed to provide a connection between the first and the second connection region such that the first and the second reference region are situated at the relative position. The connection part is then manufactured. The invention also relates to an assembly comprising a first wing of a first aircraft and a second wing of a second aircraft.
The invention relates to a profile section (34) for an equipment (26) support panel (27). Said profile section is formed in one piece, comprising a tube (38) suitable for forming a heat pipe by introducing and confining a heat-transfer fluid inside of same, and a groove (41) provided to form a rail along its length for securing at least one piece of equipment (26) supported by the panel (27), this groove (41) being shaped to form-fittingly engage with an attachment member (42) rigidly connected to said at least one piece of equipment (26).
A system for suction of the boundary layer of a wing and protection against icing of this wing includes a wall including micro-perforations and delimiting a leading edge extended by a pressure-side wall and by a suction-side wall. The system also includes a perforated tube running along the leading edge, an exhaust duction for sucking air from this tube in order to suck the boundary layer successively via the micro-perforations of the wall and via the perforations of the tube, and a supply duct for blowing hot air into this perforated tube during a phase of protection against icing, this hot air being discharged successively via the perforations of the tube and via the micro-perforations of the wall.
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64C 21/04 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue du soufflage
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
12.
AIRCRAFT ANTI-ICING PROTECTION SYSTEM USING BLOWN HOT AIR WITH REDUCED ENERGY PENALTY
The invention relates to a system for protecting a surface of an aircraft against icing by blasting a quantity of warming air against said surface in order to warm it, this quantity of warming air needing to be at a permissible temperature to which said surface can be exposed without compromising the mechanical integrity thereof. According to the invention, the system comprises: - means for bleeding a quantity of bleed air from a pneumatic hot source and for conveying this quantity of bleed air, the quantity of bleed air being at a temperature higher than the permissible temperature; - means for capturing and conveying a quantity of collected air corresponding to a portion of the quantity of warming air after it has been blasted against the surface that is to be warmed, this quantity of collected air being at a temperature lower than the permissible temperature; - regulating and mixing means which regulate the quantities of collected and bleed air in order, by mixing these two quantities, to form the quantity of warming air at the permissible temperature; - means for conveying the quantity of warming air towards and blasting it against the aircraft surface that is to be warmed.
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
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
13.
Aircraft wing comprising a mobile leading edge flap guided by a device located at the front of a wing box
An aircraft wing including a mobile leading edge flap associated with a guiding device arranged at the front of a front spar of a wing box, and including: —a pivoting member having one end connected to the spar by an articulated linkage; —a pivoting member connected to one end of the member by an articulated linkage, the end of this member being connected to the flap via an articulated linkage; —a guide rail receiving a tracking member supported by the member, the rail defining a path inscribed on the surface of an imaginary sphere, the centre of which corresponds to a point of convergence of the axes of the three linkages.
The invention relates to a system for suction of the boundary layer of a wing and protection against icing of this wing, comprising a wall (2) comprising micro-perforations (13, 14) and delimiting a leading edge (3) extended by a pressure-side wall (5) and by a suction-side wall (4). The system comprises a perforated tube (15) running along the leading edge (3), means for sucking air from this tube (15) in order to suck the boundary layer successively via the micro-perforations (13, 14) of the wall (2) and via the perforations (16) of the tube (15), and means for blowing hot air into this perforated tube (15) during a phase of protection against icing, this hot air being discharged successively via the perforations (16) of the tube (15) and via the micro-perforations (13, 14) of the wall (2).
B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
The invention concerns an aeraulic turbine (1) with through-flow from upstream to downstream, comprising a squirrel-cage rotor (2) including, at the periphery, a series of blades (6) with an arcuate profile, a frame (3) on which the rotor (2) is rotatably mounted, and flow-guiding walls defining: - a rotor primary intake sector (Xa), - a primary propagation path (Kp) designed to guide, from upstream to downstream, a primary flow Vp of the wind (V) meeting the turbine to the primary intake sector, in order to supply it, - a rotor ejection sector (Xf) that opens onto a discharge space (E), - a rotor auxiliary intake sector (Xb) extending angularly relative to the transverse axis AY between the primary intake sector (Xa) and the ejection sector (Xf), - a scoop (37) designed to guide, from upstream to downstream, an auxiliary flow (Vk) of the wind (V) to the auxiliary intake sector (Xb) in order to supply it, and - a secondary propagation path (Ks) designed to guide, from upstream to downstream, a secondary flow (Vs), this secondary propagation path (Ks) bypassing the rotor to open into the discharge space (E), in the vicinity of the ejection sector (Xf).
F03D 3/00 - Mécanismes moteurs à vent avec axe de rotation sensiblement perpendiculaire au flux d'air pénétrant dans le rotor
F03D 3/04 - Mécanismes moteurs à vent avec axe de rotation sensiblement perpendiculaire au flux d'air pénétrant dans le rotor comportant des moyens fixes de guidage du vent, p. ex. par aubages ou canaux directeurs
16.
Aircraft wing comprising a mobile leading edge flap driven by a linear electric motor
The invention relates to an aircraft wing comprising a stationary central wing body as well as at least one mobile leading edge flap intended for being moved relative to the stationary central body between an extended position and a retracted position, the wing comprising a device for moving the mobile leading edge flap, the device being provided with at least one mobile drive rail including a front end connected to the mobile flap. According to the invention, the movement device comprises a linear electric motor including: a primary assembly provided with at least one stationary carriage comprising coils, the primary assembly being rigidly connected to the stationary central body of the wing; and a mobile secondary assembly including a magnetic track arranged on the drive rail.
The invention relates to an aircraft wing (4) comprising a mobile leading edge flap (16) associated with a guiding device (40) arranged at the front of a front spar (32) of a wing box, and including: - a pivoting member (42) having one end (42a) connected to the spar (32) by an articulated linkage (50a); - a pivoting member (44) connected to one end (42b) of the member (42) by an articulated linkage (50b), the end (44a) of this member (44) being connected to the flap (16) via an articulated linkage (50c); - a guide rail (46) receiving a tracking member (58) supported by the member (44), the rail defining a path (62) inscribed on the surface of an imaginary sphere (64), the centre of which corresponds to a point of convergence of the axes (54a, 54b, 54c) of the three linkages.
Assembly for aircraft comprising a moveable bearing surface supported by a drive shaft passing through a slit provided with a seal with improved sealing efficiency
An assembly for an aircraft including an aircraft wall in which a routing slit is formed. A drive shaft of a bearing surface passes through the slit while remaining free to move along the slit. A seal is provided to seal the slit.
F16J 15/46 - Joints d'étanchéité par bague de garniture dilatée ou comprimée dans son logement par pression d'un fluide, p. ex. garnitures gonflables
F16J 15/3232 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre par joints élastiques, p. ex. joints toriques avec au moins une lèvre ayant plusieurs lèvres
F16J 15/02 - Joints d'étanchéité entre surfaces immobiles entre elles
B64C 9/16 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'arrière de l'aile
An aircraft wing comprising a movable flap which is able to move in rotation relative to a fixed central body, flexible piping and a rail for guiding the movable flap and the flexible piping. The flexible piping-runs along the rail and is secured to the rail close to a distal end of the rail. The wing comprises a structure for holding the flexible piping against or close to the guiding rail, which is borne by the fixed central body. The wing also comprises a housing for accommodating the flexible piping. The housing comprises a wall which is shaped such that the flexible piping coils up inside the housing, being pressed against the wall.
The invention relates to an assembly (20) for an aircraft comprising a fuselage portion (5a) of the aircraft and an adjacent movable trailing edge flap (16), the flap comprising an inner end secured to an actuation shaft (22) for the flap passing through an opening (24) that is provided through the fuselage portion (5a) and is equipped with a seal system (30) comprising a first seal portion (30a) and a second seal portion (30b) arranged opposite one another as seen in a direction of the width (D2) of the opening. According to the invention, at least one of the first and second seal portions (30a, 30b) is segmented in the longitudinal direction into multiple seal sections (34a, 34b), each seal section being associated with elastic return means (36a, 36b) that force the section to move relative to the opening (24) in the direction of the width (D1), toward the other seal portion.
F16J 15/50 - Joints d'étanchéité entre organes mobiles l'un par rapport à l'autre, par étanchéité sans surfaces mobiles l'une par rapport à l'autre, p. ex. des garnitures étanches aux fluides pour transmettre un mouvement au travers d'une paroi
21.
System for dual management of anti-icing and boundary layer suction on an aerofoil of an aircraft, including a function of collecting the anti-icing air
A system for dual management of anti-icing and boundary layer suction for an aerofoil of an aircraft, including: at least one anti-icing channel and at least one suction channel; a device monitoring boundary layer suction and a device monitoring anti-icing; a first duct collecting the suction air communicating with the suction channel and a second duct supplying anti-icing air connected to the device and communicating with the anti-icing channel; a three-way valve to which the first duct, a suction duct, and a duct for discharging the anti-icing air are connected; and a duct collecting anti-icing air connected to the anti-icing channel, and to the first duct.
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables
22.
AIRCRAFT WING COMPRISING A MOBILE LEADING EDGE FLAP DRIVEN BY A LINEAR ELECTRIC MOTOR
The invention relates to an aircraft wing comprising a stationary central wing body as well as at least one mobile leading edge flap (16) intended for being moved relative to the stationary central body between an extended position and a retracted position, the wing comprising a device (50) for moving the mobile leading edge flap, the device (50) being provided with at least one mobile drive rail (20) including a front end connected to the mobile flap. According to the invention, the movement device (50) comprises a linear electric motor (22) including: a primary assembly (52) provided with at least one stationary carriage (52a) comprising coils, the primary assembly being rigidly connected to the stationary central body (8) of the wing; and a mobile secondary assembly (54) including a magnetic track arranged on the drive rail (20).
The invention relates to an aircraft wing comprising a mobile trailing edge flap (16), the wing comprising a device (50) for moving said flap, the device being provided with: a beam (51) supporting a guide rail; a carriage (52a) movably mounted on the rail (20); a rotary joint (40a) between the carriage (52a) and a bracket (30) rigidly connected to the flap; a tilt member (29) for tilting the mobile flap; a rotary joint (40b) between the bracket (30) and the tilt member (29); and a rotary joint (40c) between the tilt member (29) and the beam (51). According to the invention, the device (50) comprises a linear electric motor (22) including: a primary assembly (52) provided with the carriage (52a), which includes coils (55); and a secondary assembly (54) including a magnetic track arranged on the rail (20).
For dual management of anti-icing and boundary-layer suction, a system for an aerofoil of an aircraft, including: a channel having a double function of anti-icing and boundary-layer suction; a double-function main pipe to which a device for monitoring the boundary-layer suction and a device for monitoring anti-icing are connected; an anti-icing air-intake pipe connecting the main pipe and the channel; a non-return valve enabling anti-icing air to go from the main pipe to the pipe; at least one suction-air collection pipe connecting the channel and the main pipe; and a non-return valve enabling suction air to pass from the pipe toward the main pipe.
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
B64C 3/28 - Bords d'attaque ou de fuite fixés aux structures primaires, p. ex. formant des fentes fixes
The invention relates to an aircraft wing. The wing comprises a movable flap which is able to move in rotation relative to a fixed central body, flexible piping (40) and a rail (30) for guiding the movable flap and the flexible piping (40). The flexible piping (40) runs along the rail (30) and is secured to the rail (30) close to a distal end of the rail (31). The wing comprises a means (70) for holding the flexible piping (40) against or close to the guiding rail (30), which is borne by the fixed central body. The wing also comprises a housing (50) for accommodating the flexible piping (40). The housing (50) comprises a wall (61) which is shaped such that the flexible piping (40) coils up inside the housing (50), being pressed against the wall (61).
SYSTEM FOR DUAL MANAGEMENT OF ANTI-ICING AND BOUNDARY LAYER SUCTION ON AN AEROFOIL OF AN AIRCRAFT, INCLUDING A FUNCTION OF COLLECTING THE ANTI-ICING AIR
The invention relates to a system for dual management of anti-icing and boundary layer suction for an aerofoil (4) of an aircraft, including: at least one anti-icing channel (44) and at least one suction channel (46); a device (26) for monitoring boundary layer suction and a device (28) for monitoring anti-icing; a duct (30b) for collecting the suction air communicating with said suction channel and a duct (30a) for supplying anti-icing air connected to the device (28) and communicating with the anti-icing channel. According to the invention, the device (26) comprises a three-way valve (26a, 26b, 26c) to which the duct (30b), a suction duct (29), and a duct for discharging the anti-icing air (31) are connected, the system also comprising a duct for collecting anti-icing air (64) connected to the anti-icing channel (44), and to the duct (30b).
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables
28.
IMPROVED SYSTEM FOR THE DUAL MANAGEMENT OF ANTI-ICING AND BOUNDARY-LAYER SUCTION ON AN AEROFOIL OF AN AIRCRAFT
According to the invention, for the dual management of anti-icing and boundary-layer suction, the invention proposes a system for an aerofoil (4) of an aircraft, including: a channel (42) having a double function of anti-icing and boundary-layer suction; a double-function main pipe (30) to which a device (26) for monitoring the boundary-layer suction and a device (28) for monitoring anti-icing are connected; an anti-icing air-intake pipe (38) connecting the main pipe (30) and the channel (42); a non-return valve (50) enabling the anti-icing air to go from the main pipe (30) to the pipe (38); at least one suction-air collection pipe (56) connecting the channel (42) and the main pipe (30); and a non-return valve (60) enabling the suction air to pass from the pipe (56) toward the main pipe (30).
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
29.
Method for producing a leading edge skin by baking a stack incorporating heating elements and layers of pre-impregnated fibres
A method for producing a skin of a leading edge for an aircraft wing element, including an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge. The method includes curing a stack in a mold between two molding surfaces facing each other. The stack includes the resistive heating elements assembly, two adhesive films arranged respectively on either side of the assembly so that the heating elements adhere to each of these two adhesive films, two layers of electrically insulating pre-impregnated fibers adhering respectively to the two adhesive films on the sides opposite those receiving the heating elements, and a plurality of layers of pre-impregnated carbon fibers.
B29C 70/48 - 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" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 70/68 - 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 en incorporant ou en surmoulant des parties préformées, p. ex. des inserts ou des couches
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B64C 9/22 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
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 70/88 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts caractérisées principalement par des propriétés spécifiques, p. ex. électriquement conductrices ou renforcées localement
B29C 70/02 - 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 des combinaisons de renforcements et de matières de remplissage dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées ou non remplies
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
30.
METHOD FOR PRODUCING A LEADING EDGE SKIN BY BAKING A STACK INCORPORATING HEATING ELEMENTS AND LAYERS OF PRE-IMPREGNATED FIBRES
The invention relates to a method for producing a leading edge skin for an aircraft, comprising an assembly of resistive heating elements (26) for a system for de-icing and/or anti-icing of the leading edge, the method comprising a step of baking a stack (14) in a mould between two moulding surfaces facing each other, said stack comprising: - the assembly of elements (26); - two adhesive films (24, 28) arranged on either side of the assembly (26); - two layers of pre-impregnated fibres (22, 30) adhering to the two adhesive films; and - a plurality of layers of pre-impregnated carbon fibres (20).
A device (1) for assembling panels using riveting which includes a riveting system (6) together with a drilling system (4). According to the invention, the device includes components for setting the riveting head (38) in motion relative to a carriage (34) of the riveting system, where these components are designed to be capable of moving this riveting head (38) between an at-rest position in which the drilling head axis and the riveting head axis (16, 40) are distinct, and a working position in which the same axes (16, 40) coincide.
The invention relates to a process for manufacturing a sandwich panel comprising a step to bake a stacked structure (16) provided with: a honeycomb body (2); a film (12) pre-impregnated with a first resin with a polymerization temperature T1; and a first stack (18) of fiber layers pre-impregnated with a second resin with a polymerization temperature T2 greater than T1, the film being arranged between the first stack and the body. The baking step comprises a first phase designed to use the film (12), to create a rigid barrier providing a seal from the second resin by polymerization of said first resin, followed by a second phase designed to produce the skin starting from the stack (18), by polymerization of the second resin.
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa 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
B29C 43/36 - Moules pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
E04C 2/32 - Éléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux caractérisés par la forme ou la structure formés d'un matériau ondulé ou cannelé analogue à des feuillesÉléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux caractérisés par la forme ou la structure composés de couches de ce genre avec ou sans couches d'un matériau plat en feuilles
E04C 2/36 - Éléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux caractérisés par la forme ou la structure composés de plusieurs éléments séparés analogues à des feuilles séparés par des bandes de matériaux disposées transversalement, p. ex. panneaux alvéolaires
33.
Cable carrier chain for leading edge mobile slat for an aircraft wing
An aircraft wing comprising a wing fixed central body, and a leading edge mobile slat (16) designed to be moved in rotation relative to the fixed central body along a circular trajectory inscribed on a sphere with center (C). According to the invention, the wing also comprises a cable carrier chain (30) comprising links (34) articulated to each other through articulation axes (44) that converge towards a single point, the chain being connected at its two ends to the fixed central body and to the mobile slat. Furthermore, the single point is the center (C) of the sphere, located on a rotation axis (42) of the leading edge mobile slat relative to the wing fixed body.
B64C 9/24 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile par volet unique
B64C 13/30 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des mécanismes à câbles, chaînes ou tiges
34.
METHOD FOR MAKING A PANEL INCLUDING AT LEAST ONE CELLULAR BODY AND A FIRST SKIN MADE OF A COMPOSITE MATERIAL
The invention relates to a method for making a sandwich panel, that comprises baking a stacked structure (16) including: a first cellular body (2); a film (12) pre-impregnated with a first resin having a polymerisation temperature T1; and a first stack (18) of webs of fibres pre-impregnated with a second resin having a polymerisation temperature T2 higher than T1, the film being arranged between the first stack and the body. The baking includes a first phase for producing, from the film (12), a rigid barrier that is sealed relative to the second resin by polymerisation of the first resin, followed by a second phase for producing the skin from the stack (18) by polymerisation of the second resin.
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa 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
E04C 2/36 - Éléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux caractérisés par la forme ou la structure composés de plusieurs éléments séparés analogues à des feuilles séparés par des bandes de matériaux disposées transversalement, p. ex. panneaux alvéolaires
The invention relates to a method for assembling sheets by riveting, comprising a step for piercing a hole through the sheets, followed by a step for placing a rivet in the pierced hole, the step for piercing a hole being executed by supplying an advance speed instruction of a piercing tool as well as a rotation speed instruction of this tool. According to the invention, a previous step for determining information on the local stiffness of the sheets (Info_stiffness) is also carried out at the level of the hole to be pierced, the advance speed instruction and rotation speed instruction of the tool being a function of this information on the local stiffness of the sheets.
Application most suited to the field of aircraft construction.
The invention relates to an aircraft wing comprising a fixed wing central body and a leading edge mobile flap shutter (16) intended to be rotated with respect to the fixed body in a circular path that lies within a sphere of centre (C). According to the invention, the wing further comprises a cable-carrying chain (30) comprising links (34) that are articulated to one another about axes of articulation (34) that converge to a single point, the chain being connected at its two ends to the fixed central body and to the mobile flap shutter. In addition, the said single point is the centre (C) of the sphere, located on an axis (42) about which the leading edge mobile flap shutter rotates with respect to the wing fixed body.
The invention relates to a leading edge mobile flap (16) for a main wing of an aircraft, this flap including an aerodynamic skin (18) that has a bird impact-sensitive frontal area (24), and a rear skin (28) integral with the aerodynamic skin (18), the flap also comprising a plurality of ribs (34) spaced out along a leading edge longitudinal direction (X′). According to the invention, the flap additionally includes, between two directly consecutive ribs, a single rigid bird trajectory-deflecting wall (42) anchored to the skins (18, 28). Furthermore, in a cross-section taken along any plane orthogonal to the direction (X′), the wall (42) forms with a geometric chord (26) of the flap an angle (α1) with a value of less than 45°.
The invention concerns an assembly method using plate riveting including a step of drilling a hole through the plates followed by a step of placing a rivet in the drilled hole, the hole drilling step being performed by delivering a set feed rate of a drilling tool as well as a set rotational speed of said tool. According to the invention, the method further consists in performing a prior step of determining an information concerning the local stiffness of the plates (info-stiffness) at the hole to be drilled, the set feed rate and the set rotational speed of the tool being based on said information concerning the local stiffness of the plates. The invention is particularly applicable to aircraft construction.
G05B 19/416 - Commande numérique [CN], c.-à-d. machines fonctionnant automatiquement, en particulier machines-outils, p. ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'un programme sous forme numérique caractérisée par la commande de vitesse, d'accélération ou de décélération
39.
DEVICE AND METHOD FOR JOINING METAL SHEETS BY MEANS OF RIVETING
The invention relates to a device (1) for joining metal sheets by means of riveting, comprising a riveting system (6) and a drilling system (4). According to the invention, the device comprises means for moving the riveting head (38) relative to a carriage (34) belonging to the riveting system, these means being designed to be able to move this riveting head (38) between a rest position in which the drilling head axis and riveting head axis (16, 40) are separate, and a working position in which the same axes (16, 40) coincide with each other. Primary application: aircraft manufacture.
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