The invention relates to a movable flap (16) for the leading edge of an aircraft wing, the flap being intended to be mounted on a fixed part (8) of the wing and comprising two flap ends (16a, 16b) positioned opposite one another along the span (17) of the flap, the flap defining a leading edge zone from which a lower surface and an upper surface extend, the surfaces being spaced apart from one another over the height (21) of the flap. According to the invention, the flap has a generally upwardly concave shape in its nominal state in order to limit fatigue stresses on the flap during flight.
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 - Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
B65D 90/48 - Arrangements of indicating or measuring devices
4.
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 - Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
B65D 90/48 - Arrangements of indicating or measuring devices
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 - Containers, packaging elements or packages, specially adapted for particular articles or materials for machines, engines or vehicles in assembled or dismantled form
B65D 90/00 - Component parts, details or accessories for large containers
B65D 90/48 - Arrangements of indicating or measuring devices
11.
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.
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.
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 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).
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.
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.
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.
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).
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 - Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
F03D 3/04 - Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor having stationary wind-guiding means, e.g. with shrouds or channels
23.
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.
B64C 7/00 - Structures or fairings not otherwise provided for
26.
ASSEMBLY FOR AIRCRAFT INCLUDING A MOBILE LOAD-BEARING SURFACE, BORNE BY AN OPERATING SHAFT CROSSING A SLIT EQUIPPED WITH A SEALED JOINT WITH IMPROVED SEALING EFFICIENCY
L'invention concerne un ensemble pour aéronef comprenant une paroi d'aéronef (5a) dans laquelle une fente de cheminement (24) est formée, un arbre d'actionnement (22) d'une surface portante (16) qui traverse la fente en étant mobile le long de celle-ci, et un joint d'étanchéité (30) pour sceller cette fente.Selon l'invention, le joint d'étanchéité est formé en deux parties, en comprenant une partie inférieure de joint (30a) et une partie supérieure de joint (30b) agencées en vis-à-vis de part et d'autre de la fente, chacune des deux parties comprenant une lèvre (33a, 33b) formant pistes de contact entre lesquelles l'arbre d'actionnement est enserré et se déplace en les déformant durant une mise en mouvement de la surface portante, ces lèvres présentant une forme en oreilles de lapin permettant leur enroulement autour de l'arbre afin de limiter les espaces d'ouverture parasites et empêchant leur désalignement.
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 - Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall
29.
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.
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).
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).
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.
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).
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).
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).
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 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B64C 9/22 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
40.
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).
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
41.
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 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
E04C 2/32 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure formed of corrugated or otherwise indented sheet-like materialBuilding elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of such layers with or without layers of flat sheet-like material
E04C 2/36 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
44.
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 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap
B64C 13/30 - Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
45.
PROCESS FOR MANUFACTURING A PANEL COMPRISING AT LEAST ONE HONEYCOMB BODY AND A FIRST SKIN MADE FROM A COMPOSITE MATERIAL
The invention relates to a process for manufacturing a sandwich panel comprising a step to bake a stacked structure provided with a honeycomb body; a film pre-impregnated with a first resin with a polymerisation temperature T1 and a first stack of fibre layers pre-impregnated with a second resin with a polymerisation 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, to create a rigid barrier providing a seal from the second resin by polymerisation of said first resin, followed by a second phase designed to produce the skin starting from the stack, by polymerisation of the second resin.
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
E04C 2/36 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
46.
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 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
E04C 2/36 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
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 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 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.
The invention relates to 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 means for setting the riveting head (38) in motion relative to a carriage (34) of the riveting system, where these means 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. Particular application in the field of aeronautic construction.
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 (.alpha.1) with a value of less than 45.degree..
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