Aircraft front portion including a concave bulkhead separating a non-pressurized radome area and a pressurized area

An aircraft front portion includes a sealed bulkhead separating a non pressurized radome area from a pressurized area. The sealed bulkhead is delimited by two surfaces opposite to each other, one being substantially concave when seen from the radome area and the other being substantially convex when seen from the pressurized area.

Ventilated smoking article

A cigarette includes a rod comprising a wrapped tobacco column that is joined to an axially aligned filter by a band of air impermeable tipping paper. The filter end of the rod is inserted into a mouthpiece having an air impermeable outer surface that comprises a ventilation tube and a second filter, separated by a mixing chamber. The ventilation tube has an air permeable annular wall that defines a central axial passage through which the rod extends. In use, the end surface of the annular wall at the rod end of the ventilation tube, which extends radially outward around the rod, acts as a ventilation surface through which air is drawn into the mixing chamber, where it mixes with mainstream smoke from the burning tobacco rod. The air/smoke mixture is drawn through the second filter into the consumer's mouth.

Tools For Manufacturing A Composite Panel, In Particular Of An Aircraft Fuselage

A tool equipment for manufacturing a panel in a composite material, in particular for an aircraft fuselage. The tool equipment (1) comprises a mould (2) including a fixed part (4) and a plurality of removable modules (6) which are able to be mounted on this fixed part (4).

Primary structure for aircraft of composite material with improved crash resistance and associated energy-absorbing structural element

The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.

Methods for manufacturing a tool equipment including a plurality of removable modules and for molding a fuselage panel

A method for manufacturing a tool equipment used in molding a panel for a fuselage of an aircraft from a composite material is provided. The method includes manufacturing a mold such that a fixed part includes a hub and an intermediary member. A plurality of removable modules which are able to be mounted on this fixed part are also manufactured and then fastened to the fixed part so as to modify an external surface upon which composite material is laid-up or draped during the molding of the panel.

AIRCRAFT FRONT PORTION INCLUDING A CONCAVE BULKHEAD SEPARATING A NON-PRESSURIZED RADOME AREA AND A PRESSURIZED AREA

The invention relates to an aircraft front portion (1) including a sealed bulkhead (10) separating a non-pressurized radome area (20) from a pressurized area (30), whereof the volume of the pressurized area (30) is optimized. For this, said sealed bulkhead (10) is delimited by two surfaces (11,12) opposite to each other, one (11) being substantially concave when it is seen from said radome area (20) and the other one (12) being substantially convex when it is seen from said pressurized area (30).

Device and method for assembling brackets in an aircraft structure

The invention relates to a positioning device for assembling parts on a structure. More specifically, the invention relates to a positioning device designed for assembling fixed brackets to an aircraft structure. A laser projector is fastened directly on the rigid aircraft structure; its position is therefore stable in relation to the latter, even if said structure undergoes slight deformations. The position of the projector is determined accurately by utilizing targets, which are also fastened to the primary structure. The invention also relates to a method for implementing this device.

Smoking article with front-plug and method

There is provided a smoking article that includes a plurality of elements, including a front-plug and an aerosol-forming substrate, assembled in contact with a cigarette paper to form a rod. The front-plug is located upstream from the aerosol-forming substrate. In use, a heating element is inserted into the smoking article and the aerosol-forming substrate is heated to generate an aerosol. When the heating element is subsequently withdrawn from the smoking article, the front-plug acts to retain the aerosol-forming substrate within the rod.

Smoking article with front-plug and aerosol-forming substrate and method

A smoking article is provided, including a plurality of elements including a front-plug and an aerosol-forming substrate. A hole or slit is defined through the front-plug, through which a heating element may be inserted. In use, a heating element is inserted into the smoking article through the hole or slit and the aerosol-forming substrate is heated to generate an aerosol. When the heating element is subsequently withdrawn from the smoking article, the front-plug acts to retain the aerosol-forming substrate within the smoking article.

Heated aerosol generating article with thermal spreading wrap

A heated aerosol-generating article is provided, including an aerosol-forming substrate radially encircled by a sheet of thermally-conductive material. The heated aerosol-generating article is for use with an electrically-operated aerosol-generating device comprising a heating element, for example an insertable heating element. The aerosol-forming substrate may be a rod comprising a gathered sheet of aerosol-forming material circumscribed by a wrapper, in which the wrapper is a sheet of thermally-conductive material. The thermally-conductive material acts as a thermally-conducting flame barrier for spreading heat and mitigating against the risk of a user igniting the aerosol-forming substrate by applying a flame, or other ignition source, to the heated aerosol-generating article.

Aerosol-generating article having a flavour-generating component

An aerosol-generating article (10) comprises a plurality of elements assembled in the form of a rod (11). The plurality of elements includes an aerosol-forming substrate (20), and a mouthpiece filter (50) located downstream from the aerosol-forming substrate (20) within the rod (11). The aerosol-generating article (10) further comprises a volatile flavour-generating component (45) disposed between the aerosol-forming substrate (20) and the mouthpiece filter (50) within the rod (11). In some embodiments the volatile flavour-generating component (45) is supported by a low resistance support element (40) located between the aerosol-forming substrate (20) and the mouthpiece filter (50). In some embodiments the volatile flavour-generating component (45) is menthol.

Aerosol-generating article having an aerosol-cooling element

An aerosol-generating article (10) comprises a plurality of elements assembled in the form of a rod (11). The elements include an aerosol-forming substrate (20) and an aerosol-cooling element (40) located downstream from the aerosol-forming substrate (20). The aerosol-cooling element (40) comprises a plurality of longitudinally extending channels and has a porosity of between 50% and 90% in the longitudinal direction. The aerosol-cooling element may have a total surface area of between 300 mm 2 per mm length and 1000 mm 2 per mm length. An aerosol passing through the aerosol-cooling element (40) is cooled, and in some embodiments, water is condensed within the aerosol-cooling element (40).

Smoking article with front-plug and aerosol-forming substrate and method

Aerosol-generating article with rigid hollow tip

Aerosol-generating article with low resistance air flow path

Thermal laminate rods for use in aerosol-generating articles

Heated aerosol generating article with thermal spreading endpiece

DEVICE AND METHOD FOR ASSEMBLING SUPPORTS IN AN AIRCRAFT STRUCTURE

METHOD FOR MANUFACTURING AN AIRCRAFT FUSELAGE TRUNK OF COMPOSITE MATERIAL

L'invention concerne un procédé de fabrication d'un tronçon de fuselage d'aéronef en matériau composite, comportant les opérations suivantes : - fabrication d'un tronçon d'une seule pièce (4); - découpe longitudinale du tronçon ; - écartement de deux lèvres (5a, 5b) situées de part et d'autre de la découpe ; - réassemblage du tronçon (4b) et réalisation d'une jonction longitudinale avec recouvrement des deux lèvres. L'invention concerne également un tronçon réalisé suivant ce procédé. The invention relates to a method of manufacturing an aircraft fuselage section of composite material, comprising the following operations: - manufacture of a one-piece section (4); - longitudinal cutting of the section; - spacing of two lips (5a, 5b) located on either side of the cutout; - Reassembly of the section (4b) and realization of a longitudinal junction with overlap of the two lips. The invention also relates to a section made according to this method.

METHOD FOR MANUFACTURING AN AIRCRAFT FUSELAGE TRUNK OF COMPOSITE MATERIAL

The disclosed embodiments relate to a method for manufacturing an aircraft fuselage section of composite material that comprises the following operations manufacturing a one-piece section; cutting the section longitudinally; spreading apart two edges located on the two sides of the cut; reassembling the section and making a longitudinal joint with the two edges overlapping. The disclosed embodiments also relate to a section made in accordance with this method.

SMOOTH CHEST AND ORBITAL JUNCTION DEVICE

L'invention concerne une éclisse de lisses (100) destinée à relier deux lisses (101, 102) adjacentes, caractérisée en ce qu'elle comporte au moins trois pièces indépendantes (106, 111, 112, 222, 201, 202), une tige de jonction (106) étant destinée à être fixée par deux extrémités opposées (107, 110) aux deux lisses adjacentes, et au moins deux plaques de jonction (111, 112, 201, 202), chaque plaque de jonction étant destinée à être solidaire par une première extrémité d'une des deux lisses, et par une deuxième extrémité d'une traverse (116) disposée entre les deux lisses. L'invention concerne également un dispositif de jonction orbitale comportant au moins une éclisse de lisses selon l'invention. The invention relates to a bar plate (100) for connecting two adjacent rails (101, 102), characterized in that it comprises at least three independent parts (106, 111, 112, 222, 201, 202), a junction rod (106) being intended to be fixed by two opposite ends (107, 110) to the two adjacent rails, and at least two connecting plates (111, 112, 201, 202), each connecting plate being intended to be secured by a first end of one of the two smooth, and a second end of a cross member (116) disposed between the two rails. The invention also relates to an orbital junction device comprising at least one stringer of heddles according to the invention.

PRIMARY STRUCTURE FOR AIRCRAFT IN COMPOSITE MATERIAL HAVING IMPROVED CRASH AND STRUCTURAL COMPONENT WITH ENERGY ABSORBER.

La présente invention concerne essentiellement une structure primaire d'un fuselage d'aéronef comportant au moins une première bielle (15) reliée par une extrémité (16) à une traverse (10) et par une autre extrémité (17) à un cadre (9) de renfort. Une deuxième bielle (19) présente une extrémité (20) fixée à la structure en dessous de l'extrémité (17) de la première bielle (15), et une autre extrémité (21) reliée à la première bielle (15) par l'intermédiaire d'une liaison glissière. Un organe (25) déformable est relié aux bielles (15, 19), de sorte qu'en cas de crash, les forces de compression appuient sur la deuxième bielle (19), de sorte que l'extrémité (21) de la deuxième bielle (19) coulisse le long de la première bielle (15) de manière à étirer longitudinalement l'organe (25) déformable pour absorber le choc. The present invention essentially relates to a primary structure of an aircraft fuselage comprising at least a first connecting rod (15) connected at one end (16) to a crossmember (10) and at another end (17) to a frame (9). ) reinforcement. A second connecting rod (19) has one end (20) fixed to the structure below the end (17) of the first connecting rod (15), and another end (21) connected to the first connecting rod (15) by the intermediate of a slide link. A deformable member (25) is connected to the connecting rods (15, 19) so that, in the event of a crash, the compression forces press on the second connecting rod (19), so that the end (21) of the second connecting rod (19) slides along the first connecting rod (15) so as to longitudinally stretch the deformable member (25) to absorb the impact.

PRIMARY STRUCTURE FOR AIRCRAFT IN COMPOSITE MATERIAL HAVING IMPROVED CRASH AND STRUCTURAL COMPONENT WITH ENERGY ABSORBER.

FRONT AIRCRAFT PART COMPRISING A CONCAVE CLOSURE SEPARATING AN UNPRESSURIZED RADOME ZONE AND A PRESSURIZED AREA

L'invention concerne une partie avant (1) d'aéronef comportant une cloison étanche (10) séparant une zone de radôme (20) non pressurisée d'une zone pressurisée (30), dont le volume de la zone pressurisée (30) est optimisé. Pour cela, ladite cloison étanche (10) est délimitée par deux surfaces (11,12) opposées l'une à l'autre, l'une (11) étant sensiblement concave lorsqu'elle est vue depuis ladite zone de radôme (20) et l'autre (12) étant sensiblement convexe lorsqu'elle est vue depuis ladite zone pressurisée (30). The invention relates to a front part (1) of an aircraft comprising a bulkhead (10) separating an unpressurized radome zone (20) from a pressurized zone (30), the volume of the pressurized zone (30) being optimized. For this, said watertight partition (10) is delimited by two surfaces (11,12) opposite to each other, one (11) being substantially concave when viewed from said radome zone (20) and the other (12) being substantially convex when viewed from said pressurized zone (30).

Center fuselage section for airplane, has ventral fairing partially surrounding fuselage and wing and directly fixed on wing and fuselage by structural elements that enable fairing to work, and wing box for joining wing and fuselage

The section has a central wing box (16) partially installed in a central part of a fuselage of an aircraft to join a wing (14) and the fuselage. A ventral fairing partially surrounds the fuselage and the wing, and is directly fixed on the wing and the fuselage by structural elements that enable the fairing to work. The structural elements have battens (33) fixed on stiffeners (32) of the wing and on feet (31) of frames of the fuselage, and connection elements e.g. C-shaped sectioned frames, fixed on the fuselage frames. The structural elements are made of composite material or titanium.

TOOLING FOR MANUFACTURING A PANEL OF COMPOSITE MATERIAL, PARTICULARLY AN AIRCRAFT FUSELAGE

Tool for manufacturing composite material panel of fuselage of aircraft, has detachable modules fixed on external face of intermediate element, so that external surface of module and element assembly is adapted to internal surface of panel

The tool (1) has a male type mold (2) comprising a hub (3) and an intermediate element (5) that surrounds the hub partially. Detachable modules (6) are juxtaposed with each other and fixed on an external face of the intermediate element, so that an external surface (7) of the module and element assembly is adapted to an internal surface of the composite material panel. One of the detachable modules is fixed on the intermediate element using mechanical fixation units or a magnetic system. (Incomplete specification, abstract based on available information published by the patent office). An independent claim is also included for a method for realizing a tool for manufacturing a composite material panel of a fuselage of an aircraft.

STRUCTURAL PANEL WITH INTEGRATED RAIDISSEMENT

The panel has a longitudinal stiffener (4) extending from one end to another end of the panel, where the panel is made of fiber reinforced composite material. Trace of the stiffener follows a non-null geodesic curvature between the ends of the stiffener, over a surface of a skin of the panel. The stiffener is formed of folds. The stiffener is formed by overlapping edges of the folds when the folds are draped with an intermediate ply arranged between the edges of the folds. An independent claim is also included for an aircraft comprising a fuselage.

Composite structure e.g. wing box, optimization draping method for aircraft, involves modifying variables to be optimized for model finite elements of structure, where variables include geometrical dimensions of elements

Le procédé d'optimisation de drapage d'une structure composite du type comportant une "peau" sensiblement bidimensionnelle formée d'un assemblage de plis superposés, ladite optimisation étant réalisée vis à vis d'au moins un critère sous la forme d'une fonction d'un ensemble de contraintes externes, ledit procédé comportant des étapes : de mémorisation des zones élémentaires d'un modèle éléments finis représentatif de cette structure, de découpage de l'assemblage de plis formant la structure en un ensemble initial d'éléments de caractéristiques données, chaque élément possédant des variables susceptibles d'être optimisées, de calcul de tenue aux charges externes de la structure, et, tant que les résultats de calcul de tenue aux charges externes sont incompatible pour au moins une zone élémentaire de calcul, à au moins un critère préalablement fixé, de modification d'au moins certaines variables susceptibles d'être optimisées pour au moins certains éléments et d'itération, le procédé étant tel que les variables susceptibles d'être optimisées comprennent les dimensions géométriques des éléments.

Thermal laminate rods for use in aerosol-generating articles

A rod is formed from a gathered sheet of material circumscribed by a metal foil wrapper. The sheet of material is a co-laminated sheet comprising a layer of an aerosol-forming material and a layer of a thermally-conductive material. The rod may be used as a component part of an aerosol-generating article.

AIRCRAFT CENTRAL TRONCON WITH WORKING VENTRAL CARENAGE

L'invention concerne un tronçon central d'aéronef comportant : - une partie centrale (15) d'un fuselage d'aéronef - une voilure (14), - un caisson central de voilure (16) installé au moins partiellement dans le fuselage et assurant une jonction entre la voilure et le fuselage, et - un carénage ventral (20) enveloppant partiellement le fuselage et la voilure, ledit carénage ventral étant fixé directement sur la voilure et sur le fuselage au moyen d'éléments structuraux aptes à rendre ledit carénage ventral travaillant. The invention relates to a central aircraft section comprising: - a central part (15) of an aircraft fuselage - an airfoil (14), - a central airfoil box (16) installed at least partially in the fuselage and providing a junction between the airfoil and the fuselage, and - a ventral fairing (20) partially enveloping the fuselage and the airfoil, said ventral fairing being fixed directly to the airfoil and to the fuselage by means of structural elements capable of rendering said fairing ventral working.

Fuselage element comprising a fuselage segment and junction means, fuselage portion, fuselage and aircraft

Un élément de fuselage (1) comporte un premier tronçon de fuselage (2a) comportant une peau (3a), et des moyens de jonction (4) aptes à raccorder le premier tronçon (2a) à un second tronçon de fuselage adjacent (2b), le premier tronçon (2a) s'étendant le long de l'axe longitudinal (X) du fuselage, l'élément de fuselage (1) comportant des éléments raidisseurs (5a) s'étendant selon l'axe (X). L'extrémité (5a1) d'au moins un élément raidisseur (5a) dépasse un bord libre (7) de la peau (3a) d'une longueur prédéterminée (L). A fuselage element (1) comprises a first fuselage section (2a) comprising a skin (3a), and junction means (4) capable of connecting the first section (2a) to a second adjacent fuselage section (2b) , the first section (2a) extending along the longitudinal axis (X) of the fuselage, the fuselage element (1) comprising stiffening elements (5a) extending along the axis (X). The end (5a1) of at least one stiffening element (5a) exceeds a free edge (7) of the skin (3a) by a predetermined length (L).

Aerosol-generating article for use with an aerosol-generating device

Proizvod za proizvodnju aerosola (10) za upotrebu sa uređajem za proizvodnju aerosola koji sadrži grejni element za umetanje u aerosolni supstrat (20) proizvoda za proizvodnju aerosola (10), pri čemu se proizvod za proizvodnju aerosola (10) sastoji od: - supstrata za formiranje aerosola (20); i - potpornog elementa (30) postavljenog odmah iza supstrata za formiranje aerosola (20), pri čemu potporni element (30) dodiruje aerosolni supstrat (20); naznačen time što proizvod za proizvodnju aerosola (10) sadrži element za hlađenje aerosola (40) postavljen iza potpornog elementa (30), spoljnji omotač (60) koji obavija aerosolni supstrat (20), potporni element (30) i element za hlađenje aerosola (40) i time što je aerosolni supstrat (20) postavljen na samom gornjem kraju (80) proizvoda za proizvodnju aerosola (10), aerosolni supstrat (20) koji sadrži sakupljen list homogenizovanog duvanskog materijala. Prijava sadrži još 12 patentnih zahteva. Aerosol product (10) for use with an aerosol device comprising a heating element for insertion into the aerosol substrate (20) of the aerosol product (10), wherein the aerosol product (10) consists of: - a substrate for aerosol formation (20); and - a support element (30) placed immediately behind the aerosol-forming substrate (20), wherein the support element (30) touches the aerosol substrate (20); characterized in that the aerosol production product (10) comprises an aerosol cooling element (40) arranged behind the support element (30), an outer shell (60) enveloping the aerosol substrate (20), a support element (30) and an aerosol cooling element 40) and wherein the aerosol substrate (20) is placed at the very upper end (80) of the aerosol production product (10), an aerosol substrate (20) comprising a collected sheet of homogenized tobacco material. The application contains 12 more patent claims.

Device for assembling brackets in an aircraft structure

A positioning device for assembling parts on a structure is disclosed. More specifically, the positioning device is designed for assembling fixed brackets to an aircraft structure. A laser projector is fastened directly on the rigid aircraft structure; its position is therefore stable in relation to the latter, even if the structure undergoes slight deformations. The position of the projector is determined accurately by utilizing targets, which are also fastened to the primary structure. A method for implementing the positioning device is also disclosed.

Device and method for assembling brackets in an aircraft structure

L'invention concerne un dispositif de positionnement pour l'assemblage de pièces sur une structure. Plus particulièrement, l'invention concerne un dispositif de positionnement destiné à l'assemblage de supports fixes sur une structure d'aéronef. Un projecteur laser est fixé directement à la structure de l'aéronef, rigide, sa position est donc stable par rapport à celle-ci même si ladite structure subit de petites déformations. La position du projecteur est déterminée de manière exacte par l'intermédiaire de mires fixées, elles aussi, sur la structure primaire. L'invention concerne également un procédé de mise en uvre de ce dispositif. The invention relates to a positioning device for assembling parts on a structure. More particularly, the invention relates to a positioning device intended for the assembly of fixed supports on an aircraft structure. A laser projector is fixed directly to the structure of the aircraft, rigid, its position is therefore stable with respect to the latter even if said structure is subjected to small deformations. The position of the projector is determined exactly by means of sights which are also fixed on the primary structure. The invention also relates to a method of implementing this device.

Aerosol-generating article having an aerosol-cooling element

An aerosol-generating article (10) comprises a plurality of elements assembled in the form of a rod (11). The elements include an aerosol-forming substrate (20) and an aerosol-cooling element (40) located downstream from the aerosol-forming substrate (20). The aerosol-cooling element (40) comprises a plurality of longitudinally extending channels and has a porosity of between 50% and 90% in the longitudinal direction. The aerosol-cooling element may have a total surface area of between 300 mm2 per mm length and 1000 mm2 per mm length. An aerosol passing through the aerosol-cooling element (40) is cooled, and in some embodiments, water is condensed within the aerosol-cooling element (40).

METHOD FOR DESIGNING THE DRAPING OF COMPOSITE PLY

Heated aerosol generating article with thermal spreading wrap

A heated aerosol-generating article comprises an aerosol-forming substrate radially encircled by a sheet of thermally-conductive material. The heated aerosol-generating article is for use with an electrically-operated aerosol-generating device comprising a heating element, for example an insertable heating element. The aerosol-forming substrate may be a rod comprising a gathered sheet of aerosol-forming material circumscribed by a wrapper, in which the wrapper is a sheet of thermally-conductive material. The thermally-conductive material acts as a thermally-conducting flame barrier for spreading heat and mitigating against the risk of a user igniting the aerosol-forming substrate by applying a flame, or other ignition source, to the aerosol-generating article. Figure 2

Aerosol-generating article having an aerosol-cooling element

Zagrevani proizvod (10) za proizvodnju aerosola koji sadrži mnoštvo elemenata sklopljenih u obliku štapića (11), mnoštvo elemenata obuhvata supstrat (20) za formiranje aerosola, element (40) za hlađenje aerosola postavljen nizvodno od supstrata (20) za formiranje aerosola unutar štapića (11) i filter postavljen nizvodno od elementa (40) za hlađenje aerosola unutar štapića (11), element (40) za hlađenje aerosola je napravljen od nabranog lista koji sadrži mnoštvo podužno protežućih kanala, naznačen time da je element (40) za hlađenje aerosola napravljen od nabranog i skupljenog polimernog lista tako da se element za hlađenje aerosola sastoji od mnoštva podužno protežućih kanala i ima podužnu poroznost od između 50% i 90% u podužnom pravcu, podužna poroznost je dobijena iz odnosa površine poprečnog preseka materijala od kojeg je napravljen element za hlađenje aerosola i površine unutrašnjeg poprečnog preseka proizvoda za proizvodnju aerosola na delu koji sadrži element za hlađenje aerosola.Prijava sadrži još 5 patentnih zahteva. A heated aerosol product (10) comprising a plurality of rod-shaped elements (11), a plurality of elements comprising an aerosol-forming substrate (20), an aerosol cooling element (40) positioned downstream of the aerosol-forming substrate (20) (11) and a filter mounted downstream of the aerosol cooling element (40) inside the rods (11), the aerosol cooling element (40) is made of a pleated sheet comprising a plurality of longitudinally extending channels, wherein the cooling element (40) is aerosol made of pleated and shrunk polymer sheet such that the aerosol cooling element consists of a plurality of longitudinally extending channels and has a longitudinal porosity of between 50% and 90% in the longitudinal direction, the longitudinal porosity obtained from the cross-sectional area of the material of which it is made element for cooling the aerosol and the surface of the inner cross-section of the aerosol production product on the part which ...

COVER PANEL OF AN AIRCRAFT FUSELAGE INTEGRATING THERMAL AND ACOUSTIC INSULATION

L'invention a pour objet un panneau d'habillage isolant configuré pour être positionné contre une face intérieure (18) d'une peau (12) d'un fuselage d'un aéronef. Selon l'invention, ce panneau d'habillage isolant (26) est monobloc, comprend au moins une couche isolante (32) positionnée au niveau d'une première face (28) et une couche d'habillage (34) positionnée au niveau d'une deuxième face (30) et a une densité croissante de la première face (28) à la deuxième face (30). Selon un mode de réalisation, ce panneau d'habillage isolant (26) est obtenu par impression tridimensionnelle. The invention relates to an insulating cladding panel configured to be positioned against an inner face (18) of a skin (12) of a fuselage of an aircraft. According to the invention, this insulating cladding panel (26) is in one piece, comprises at least one insulating layer (32) positioned at a first face (28) and a cladding layer (34) positioned at the level of a second face (30) and has an increasing density of the first face (28) to the second face (30). According to one embodiment, this insulating covering panel (26) is obtained by three-dimensional printing.

COVER PANEL OF AN AIRCRAFT FUSELAGE INTEGRATING THERMAL AND ACOUSTIC INSULATION

Ventilated smoking article

A cigarette 2 includes a rod 4 comprising a wrapped tobacco column 8 that is joined to an axially aligned filter 12 by a band of air impermeable tipping paper 14. The filter end of the rod 4 is inserted into a mouthpiece 6 having an air impermeable outer surface that comprises a ventilation tube 16 and a second filter 18, separated by a mixing chamber 20. The ventilation tube 16 has an air permeable annular wall 26 that defines a central axial passage 28 through which the rod 4 extends. In use, the end surface 30 of the annular wall 26 at the rod end of the ventilation tube 16, which extends radially outward around the rod 4, acts as a ventilation surface through which air is drawn into the mixing chamber 20, where it mixes with mainstream smoke from the burning tobacco rod. The air/smoke mixture is drawn through the second filter 18 into the consumer's mouth.

Aerosol-generating article having a biodegradable flavour-generating component

An aerosol-generating article comprises a plurality of elements assembled in the form of a rod. The plurality of elements includes an aerosol-forming substrate, and a mouthpiece filter located downstream from the aerosol-forming substrate within the rod. The aerosol-generating article further comprises a volatile flavour-generating component disposed between the aerosol-forming substrate and the mouthpiece filter within the rod. The volatile flavour-generating component is supported by a low resistance support element located between the aerosol-forming substrate and the mouthpiece filter. The construction of the aerosol-generating article reduces the rate at which the volatile flavour-generating component is consumed during use. The volatile flavour-generating component may be menthol.

Stiffened panel for fuselage in aircraft, has stiffener extending from one end to another end of panel, where trace of stiffener follows non-null geodesic curvature between ends of stiffener, over surface of skin of panel

The panel has a longitudinal stiffener (4) extending from one end to another end of the panel, where the panel is made of fiber reinforced composite material. Trace of the stiffener follows a non-null geodesic curvature between the ends of the stiffener, over a surface of a skin of the panel. The stiffener is formed of folds. The stiffener is formed by overlapping edges of the folds when the folds are draped with an intermediate ply arranged between the edges of the folds. An independent claim is also included for an aircraft comprising a fuselage.

Shisha device for heating a substrate without combustion

A shisha device for use with a cartridge containing an aerosol-generating substrate includes a vessel, a receptacle, and an electrical heating element. The cartridge comprises a housing surrounding the aerosol-generating substrate. The vessel defines an interior configured to contain liquid and defines an outlet in communication with the interior of the vessel. The receptacle is configured to receive the cartridge. The heating element is configured to heat the aerosol-generating substrate in the cartridge to generate an aerosol when the cartridge is received by the receptacle. Preferably, the heating element is configured to heat the tobacco substrate to an extent sufficient to generate the aerosol without combusting the aerosol-generating substrate.

Heated aerosol generating article with thermal spreading wrap

A heated aerosol-generating article comprises an aerosol-forming substrate radially encircled by a sheet of thermally-conductive material. The heated aerosol-generating article is for use with an electrically-operated aerosol-generating device comprising a heating element, for example an insertable heating element. The aerosol-forming substrate may be a rod comprising a gathered sheet of aerosol-forming material circumscribed by a wrapper, in which the wrapper is a sheet of thermally-conductive material. The thermally-conductive material acts as a thermally-conducting flame barrier for spreading heat and mitigating against the risk of a user igniting the aerosol-forming substrate by applying a flame, or other ignition source, to the aerosol-generating article.

Central section of aircraft with ventral or belly fairing capable of movement

An aircraft center section includes a center part of an aircraft fuselage, a wing section, a center wing box installed at least partly in the fuselage and providing a junction between the wing section and the fuselage, and a ventral fairing partly enveloping the fuselage and the wing section, with the ventral fairing being attached directly to the wing section and to the fuselage by means of structural elements that can make the ventral fairing a working fairing.

Device and method for assembling brackets in an aircraft structure

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.

Manufacturing process for a section of aircraft fuselage in composite material

The disclosed embodiments relate to a method for manufacturing an aircraft fuselage section of composite material that comprises the following operations manufacturing a one-piece section; cutting the section longitudinally; spreading apart two edges located on the two sides of the cut; reassembling the section and making a longitudinal joint with the two edges overlapping. The disclosed embodiments also relate to a section made in accordance with this method.

Smoking article with front-plug and method.

Un artículo (1, 100, 200, 300) para fumar que comprende una pluralidad de elementos, que incluye un tapón (2, 102, 202, 302) frontal y un substrato (7) formador de aerosol ensamblado en contacto con el papel (5) para cigarro para formar una barra (15). El tapón (2, 102, 202, 302) frontal está ubicado corriente arriba del substrato (7) formador de aerosol. Durante el uso, el elemento (8) de calentamiento se inserta dentro del artículo (1, 100, 200, 300) para fumar y el substrato (7) formador de aerosol se calienta para generar el aerosol. Cuando el elemento (8) de calentamiento se extrae del artículo (1, 100, 200, 300) para fumar, el tapón (2, 102, 202, 302) frontal actúa para retener el substrato (7) formador de aerosol dentro de la barra (15).

FUSELAGE ELEMENT COMPRISING A FUSELAGE STRING AND JUNCTION MEANS, FUSELAGE PORTION, FUSELAGE AND AIRCRAFT

Section of aircraft fuselage in composite material with a constant internal profile

The disclosed embodiments concern an aircraft fuselage section made of composite material with an internal skeleton having frames that form the radial structure of the fuselage and stringers that form the longitudinal structure of said fuselage, and a skin made of composite material, surrounding the internal skeleton, with said skin having an evolving thickness along a longitudinal axis X, with an approximately constant, regular interior profile. The disclosed embodiments also concern a process for manufacturing the skin of an aircraft fuselage section made of composite material, having a draping operation for strips of fibers precoated with resin around a mold, with the number of strips of fibers varying longitudinally depending on the area of the fuselage being considered so as to create a skin with an evolving thickness.

Aerosol-generating article for use with an aerosol-generating device

Smoking article with front-plug and aerosol-forming substrate and method

A smoking article (1, 100, 300) comprises a plurality of elements including a front-plug (2, 102, 302) and an aerosol-forming substrate (7). A hole (103,303) or slit (23) is defined through the front-plug(2, 102, 302), through which a heating element (8) may be inserted.In use, a heating element (8) is inserted into the smoking article (1, 100, 300) through the hole (103,303) or slit (23) and the aerosol-forming substrate(7) is heated to generate an aerosol. When the heating element (8) is subsequently withdrawn from the smoking article (1, 100, 300), the front-plug (2, 102, 302) acts to retain the aerosol-forming substrate (7)within the smoking article (1, 100, 300).

Aerosol-generating article for use with an aerosol-generating device

An aerosol-generating article (10) comprises: an aerosol-forming substrate (20);a support element (30) located immediately downstream of the aerosol-forming substrate (20); an aerosol-cooling element (40) located downstream of the support element (30); and an outer wrapper(60) circumscribing the aerosol-forming substrate (20), the support element(30) and the aerosol-cooling element (40). The support element (30) abuts the aerosol-forming substrate (20). The aerosol-forming substrate (20) is penetrable by a heating element (110) of an aerosol-generating device(120).

Smoking article with front-plug and aerosol-forming substrate and method

FUSELAGE ELEMENT COMPRISING A FUSELAGE STRING AND JUNCTION MEANS, FUSELAGE PORTION, FUSELAGE AND AIRCRAFT

Un élément de fuselage (1) comporte un premier tronçon de fuselage (2a) comportant une peau (3a), et des moyens de jonction (4) aptes à raccorder le premier tronçon (2a) à un second tronçon de fuselage adjacent (2b), le premier tronçon (2a) s'étendant le long de l'axe longitudinal (X) du fuselage, l'élément de fuselage (1) comportant des éléments raidisseurs (5a) s'étendant selon l'axe (X). L'extrémité (5a1) d'au moins un élément raidisseur (5a) dépasse un bord libre (7) de la peau (3a) d'une longueur prédéterminée (L). A fuselage element (1) comprises a first fuselage section (2a) comprising a skin (3a), and connecting means (4) capable of connecting the first section (2a) to a second section of adjacent fuselage (2b). , the first section (2a) extending along the longitudinal axis (X) of the fuselage, the fuselage element (1) having stiffening elements (5a) extending along the axis (X). The end (5a1) of at least one stiffening element (5a) protrudes beyond a free edge (7) of the skin (3a) by a predetermined length (L).

Heated aerosol generating article with thermal spreading wrap

Aerosol-generating article having a flavour-generating component

Smoking article with front-plug and method

Heated aerosol generating article with thermal spreading endpiece

SMOOTH CHEST AND ORBITAL JUNCTION DEVICE

Heated aerosol generating article with air-flow barrier

Splice plate for stringers and orbital joining device

A splice plate for stringers designed to connect two adjacent stringers at least three independent pieces, a connection rod being designed to be fixed by two opposite extremities to two adjacent stringers, and at least two connecting plates, each connecting plate being designed to be fixedly joined to a first extremity of one of the two stringers, and by a second extremity of a cross bar disposed between the two stringers. The disclosed embodiment also relate to a device for orbital fixation including at least one stringer splice plate splice bar.

Aerosol-generating article having a flavour-generating component

An aerosol-generating article (10) comprises a plurality of elements assembled in the form of a rod (1 1 ). The plurality of elements includes an aerosol-forming substrate (20), and a mouthpiece filter (50) located downstream from the aerosol-forming substrate (20) within the rod (1 1 ). The aerosol-generating article (10) further comprises a volatile flavour-generating component (45) disposed between the aerosol-forming substrate (20) and the mouthpiece filter (50) within the rod (1 1 ). In some embodiments the volatile flavour-generating component (45) is supported by a low resistance support element (40) located between the aerosol-forming substrate (20) and the mouthpiece filter (50). In some embodiments the volatile flavour-generating component (45) is menthol.

ARTICLE AND HEATED AEROSOL GENERATING SYSTEM, AND METHOD FOR SMOKING A HEATED AEROSOL GENERATING ARTICLE

artigo e sistema gerador de aerossol aquecido, e método para fumar um artigo gerador de aerossol aquecido. a presente invenção refere-se a um artigo gerador de aerossol aquecido para uso com um dispositivo gerador de aerossol tendo um elemento de aquecimento que compreende um substrato formador de aerossol sólido e uma barreira de fluxo de ar violável montada dentro de um envoltório para formar uma coluna. a coluna tem uma extremidade da boca e uma extremidade distal a montante da extremidade da boca. a barreira de fluxo de ar violável é posicionada, quando intacta, para impedir substancialmente que o ar seja tragado através do substrato formador de aerossol sólido quando um usuário tragar pela extremidade da boca da coluna. isso reduz a propensão para a ignição do substrato formador de aerossol. article and heated aerosol generating system, and method of smoking a heated aerosol generating article. The present invention relates to a heated aerosol generating article for use with an aerosol generating device having a heating element comprising a solid aerosol forming substrate and a breachable airflow barrier mounted within a wrapper to form a column. the column has a mouth end and a distal end upstream of the mouth end. the tamper-evident airflow barrier is positioned, when intact, to substantially prevent air from being drawn through the solid aerosol forming substrate when a user swallows through the mouth end of the column. this reduces the ignition propensity of the aerosol forming substrate.

Aerosol-generating article with rigid hollow tip

A heated aerosol-generating article (10) for use with an aerosol- generating device comprises a plurality of components including an aerosol-forming substrate (20) assembled within a wrapper (60) to form a rod having a mouth end (70) and a distal end (80) upstream from the mouth end (70). A rigid hollow tube (30) is disposed upstream from the aerosol-forming substrate (20) within the wrapper. A pierceable film (31), for example a pierceable polymer film or metallic film, spans one end of the rigid hollow tube (30). The rigid hollow tube (30) is substantially non-flammable and acts to lower the risk of the aerosol-forming substrate (20) being ignited if a flame is held to the distal end of the article.

Device and method for assembling brackets in an aircraft structure

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.

DEVICE FOR ASSEMBLING BY SEPARATING MULTIPLE ELEMENTS AND METHOD FOR ASSEMBLING PANELS, IN PARTICULAR AIRCRAFT FUSELAGE USING THE SAME

Shisha device for heating a substrate without combustion

A shisha device (100) for use with a cartridge (20) containing an aerosol-generating substrate (302) includes a vessel, a receptacle, and an electrical heating element. The cartridge comprises a housing surrounding the aerosol-generating substrate. The vessel defines an interior configured to contain liquid (19) and defines an outlet in communication with the interior of the vessel. The receptacle is configured to receive the cartridge. The heating element is configured to heat the aerosol-generating substrate in the cartridge to generate an aerosol when the cartridge is received by the receptacle. The heating element is configured to heat the tobacco substrate to an extent sufficient to generate the aerosol without combusting the aerosol-generating substrate.

Aerosol-generating article having an aerosol-cooling element

An aerosol-generating article (10) comprises a plurality of elements assembled in the form of a rod (11). The elements include an aerosol-forming substrate (20) and an aerosol-cooling element (40) located downstream from the aerosol-forming substrate (20). The aerosol-cooling element (40) comprises a plurality of longitudinally extending channels and has a porosity of between 50% and 90% in the longitudinal direction. The aerosol-cooling element may have a total surface area of between 300 mm 2 per mm length and 1000 mm 2 per mm length. An aerosol passing through the aerosol-cooling element (40) is cooled, and in some embodiments, water is condensed within the aerosol-cooling element (40).

Thermal laminate rods for use in aerosol-generating articles

A rod is formed from a gathered sheet of material circumscribed by a metal foil wrapper. The sheet of material is a co-laminated sheet comprising a layer of an aerosol-forming material and a layer of a thermally-conductive material. The rod may be used as a component part of an aerosol-generating article.

Heated aerosol generating article with thermal spreading endpiece

A heated aerosol-generating article (1000, 3000) for use with an aerosol-generating device (2010) is in the form of a rod having a mouth end (1012, 3012) and a distal end (1013, 3013) upstream from the mouth end. An aerosol-forming substrate (1020, 3020) is located upstream of the mouth end within the rod and the distal end of the heated aerosol-generating article is spanned by a non-flammable thermally-conductive material to reduce the propensity for ignition of the article.

Equipment for manufacturing a composite panel, particularly for aircraft fuselage

- Outillage pour la fabrication d'un panneau en matériau composite, en particulier d'un fuselage d'aéronef. L'outillage (1) comporte un moule (2) muni d'une partie fixe (4) et une pluralité de modules (6) amovibles susceptibles d'être agencés sur cette partie fixe (4).

Method of using a smoking article with front-plug and aerosol-forming substrate

Method of using a smoking article with front-plug and aerosol-forming substrate

Nietverbindung mehrerer elemente und verfahren zum verbinden von schalen, insbesondere eines flugzeugrumpfes, mit hilfe dieser nietverbindung

Artigo gerador de aerossol aquecido com peça terminal de propagação térmica

具有濾嘴的吸煙消耗品

【物品用途】;本設計所應用之物品係一種具有濾嘴的吸煙消耗品。;【設計說明】;本設計具有濾嘴的吸煙消耗品，在其中一端被形塑為裝有消耗性菸草材料的特殊菸草構造(如俯視圖所示)，看起來像摺疊的菸草層。菸草結構的另一端，在圓柱形外表面中包含凹陷的濾嘴(如仰視圖所示)。菸草結構之長度可比傳統香菸的長度略短一點。;吸煙消耗品可與可攜式的電子加熱裝置一起使用。在這樣的情況下，吸煙消耗品係在香菸端先被裝入電子加熱器，使得有著凹陷濾嘴的另一端仍從電子加熱器突出而可被吸菸者的嘴唇含著的狀態下被消耗。;上述電子加熱裝置不像習知的電子香菸使液體揮發，而將在吸煙消耗品中加的菸草加熱至菸草會散發出香味和氣態物質的特定溫度，卻不會完全燃燒，如同以傳統香菸來吸菸一樣，香味以及其他物質可以藉由在凹陷之濾嘴抽吸而被吸菸者吸入。在前述使用中，吸煙消耗品可被視為搭配上述的可攜式電子加熱器使用的單次使用性料匣。;左側視圖與右側視圖相同，省略左側視圖。

Dispositif d'assemblage par rivetage de plusieurs elements et procede d'assemblage de panneaux notamment de fuselage d'aeronef a l'aide dudit dispositif

L'objet de l'invention est un dispositif d'assemblage de plusieurs éléments (T1, T2) par rivetage caractérisé en ce qu'il est constitué, de rivets ou analogues (1) dont le fût (3) présente une section elliptique ou analogue , reçus et rivetés dans des trous (7) de section elliptique ou analogue correspondant à celle dudit fût (3), ménagés dans lesdits éléments à assembler.

Nietverbindung mehrerer Elemente und Verfahren zum Verbinden von Schalen, insbesondere eines Flugzeugrumpfes, mit Hilfe dieser Nietverbindung

Nietverbindung mehrerer Elemente und Verfahren zum Verbinden von Schalen, insbesondere eines Flugzeugrumpfes, mit Hilfe dieser Nietverbindung

Aerosol-generating article with low resistance air flow path