18results about "Hollow wall articles" patented technology

A latex composition includes a conjugated diene polymer latex and a silicone-based surfactant having a silicon atom content of 1.5 to 10 wt %. A dip-molded article is formed by dip molding the latex composition.

The invention relates to a monolithic structure (1) made of composite material, manufactured starting from a fiber-reinforced prepreg material. The structure comprises two walls (6, 7) facing each other and at least one interconnecting element (8) extending transversely between the walls (6, 7) and connected to them, with which each elongated cavity (9) is defined. The walls (6, 7) extend symmetrically on both sides of a direction (B). The interconnecting element (8) is a rib (10) extending transversely to said direction (B), at least one wall (6, 7) having a sandwich structure and comprising two panels (11, 12) facing each other and at least one spar element (13) extending transversely between the panels (11, 12) and connected to them, with which each elongated cavity (14) is defined, extending transversely to the rib (10).

The invention relates to a method for manufacturing a turbomachine component (2) comprising a wall (3) and a honeycomb structure (4) made of composite material, the honeycomb structure being located on at least a portion of a surface (30) of the wall (3), the honeycomb structure (4) comprising at least one first network of cells (42) and at least one first skin (44) covering the first network of cells (42), the method comprising the steps of: (a) providing the wall (3); and (b) manufacturing the honeycomb structure (4) on the surface, the step (b) of manufacturing the honeycomb structure (4) comprising the sub-steps of: (bl) depositing a first fold of composite material by layup to form the first skin (44); and (b2) forming the first network of cells (42) by additive manufacturing, the sub-step (bl) being performed before or after the sub-step (b2).

A Method (100) for manufacturing a stiffened aerodynamic structure component (10) is provided, comprising the following steps: - Providing (102) an aerodynamic structure component (10), wherein the aerodynamic structure component (10) includes a plurality of spar elements (12) extending spanwise within the aerodynamic structure component (10); wherein the plurality of spar elements (12) is integrally formed with an upper skin section (14) and a lower skin section (16), thereby providing an integrally formed aerodynamic structure component (10), - Generating (104) at least one chordwise reinforcement element (18) by injecting a curable medium (32), preferably via at least one injection hole (20), in the upper skin section (14) and / or the lower skin section (16).

The core material of the wooden honeycomb material proposed in this invention, namely wood fiber paper, is a natural material with a low environmental impact. Furthermore, both the mechanical properties parallel to the longitudinal direction of the wood fibers and the mechanical properties perpendicular to the longitudinal direction of the wood fibers are quite excellent, and the resulting wooden honeycomb material has the advantages of excellent mechanical properties, lightweight design, low cost, and low environmental impact. [Solution] The present invention proposes a wooden honeycomb material. The wooden honeycomb material comprises a wooden honeycomb material and a first resin that adheres to the surface of the wooden honeycomb material. The wooden honeycomb material comprises a plurality of wood fiber paper and a core material adhesive. The plurality of wood fiber paper are bonded together with the core material adhesive. The plurality of composite wood fiber paper comprises unidirectional wood fiber paper and / or composite wood fiber paper. The composite wood fiber paper comprises unidirectional wood fiber paper and a second resin layer and / or fiber reinforcement layer that adheres to the surface of the unidirectional wood fiber paper.

A composite structure assembly (100) includes a composite core (102) including a flexible base (110) and a plurality of cells (108) extending from the flexible base (110). The composite core (102) is conformable to different shapes. The plurality of cells (108) are configured to move in response to movement of the flexible base (110). At least one cell (108) of the plurality of cells (108) may include a central column (160) connected to a first flared end (162) and a second flared end (164) that is opposite from the first flared end (162).

The invention relates to a sealed laminate panel (10), such as a framed laminate panel comprising an open-celled substrate layer (12) within the frame and at least one layer of sheetform material (11) provided over each of opposing surfaces of the framed substrate, which may be prepared by a one-shot process. The invention further relates to a method of forming a laminate panel (10) of the present invention. The laminate panels of the present invention are useful, for example, in buildings, trains, boats, and as architectural components, for example architectural mouldings, although the invention has wide application to a broad range of structures. Aspects of the invention described relate to doors, panels in train carriages and boats, and other panels, in particular those used in buildings.

The invention relates to a method for producing a multicellular body (200), comprising: - arranging strips (100) of thermoplastic material delimiting at least one first row (1a, 2a, 3a) comprising at least first and second shaping blocks (55) spaced apart from one another and a second row (1b, 2b, 3b) comprising at least one third shaping block (55), - moving the at least third shaping block (55) between the at least first and second shaping blocks (55), at least one of the strips (100) being shaped as notches, - bringing the at least first and second shaping blocks (55) closer to the at least third shaping block (55), then - welding the strips (100) to one another so as to obtain a multicellular body (200).

A panel structure manufacturing device includes a shaping device that shapes the surface of a thermoplastic resin into a relief shape and forms a plate-like core member; a heating device that selectively heats the surface of the core member; and a pressurizing device that pressurizes a heated spot of the core member that the heating device has heated and a plate-like face plate, and fuses together the core member and the face plate.

The invention relates to a method for manufacturing a door for a thrust reverser system (60) of an aircraft, said door comprising a wall (74) having long fibers embedded in a thermoplastic resin matrix and a network of ribs (76) overmolded onto one face of the wall (74). This method makes it possible to obtain doors for thrust reverser systems in a simple and economical manner while minimizing waste. The invention also relates to a door obtained from the method of the invention, as well as an aircraft propulsion assembly comprising a thrust reverser system that includes several doors obtained from the method according to the invention.

The invention relates to a method (500) for manufacturing a shell (150) for an aeronautical seat, from a thermoplastic multilayer structure (100), said method being characterized in that it comprises: a step (510) of placing the multilayer structure (100) on a self-heating and self-regulating autonomous mold (300); a step (520) of applying a heating membrane (200) directly onto the multilayer structure; a step (530) of applying a vacuum in the mold by means of the heating membrane, said vacuum producing a compression of the multilayer structure; a step (540) of curing at a predefined temperature, following a cycle regulated by the mold; and a step (550) of demolding and trimming the shell (150) obtained; said method further comprising the integration of a decorative film (40) onto the multilayer structure during molding. The invention also relates to an aircraft seat cover obtained by such a process.Figure for the abbreviation: figure 1.

The present invention relates to the technical field of high-barrier inflatable cushions. Disclosed are a high-barrier inflatable cushion and a preparation process therefor. The preparation process for the high-barrier inflatable cushion comprises the following steps: material feeding, heating, vacuum pressing, spray cooling, air-cooled drying, cutting, and heat sealing. The high-barrier inflatable cushion consists of an airbag forming material and an airbag base material. The airbag forming material is formed by laminating a TPU-EVOH composite material and Lycra fabric, the total thickness of the TPU-EVOH composite material is 0.4-0.8 mm, and the gram weight of the Lycra fabric is 150-230 g / m2. The airbag base material is formed by laminating a TPU-EVOH composite material and non-woven fabric, the total thickness of the TPU-EVOH composite material is 0.1-0.3 mm, and the gram weight of the non-woven fabric is 60-80 g / m2.

The present invention provides lightweight components that have improved energy absorption. The components of the invention comprise a core comprising a plurality of repeats of an open unit cell. Each unit cell comprises intersecting polygonal planes of material and open space. The plurality of open unit cells promote energy absorption by the component from any direction of impact.

The present invention belongs to the field of composites manufacturing, and particularly, it refers to a method for manufacturing an aeronautical panel with improved impact and damping behaviours. The method is applicable not only to flat panels but also to curved or highly curved panels, whatever their size and the shape of their core. The manufactured sandwich panels comprise dry fibre mats made from fabric material and / or non-crimp fabric material. In a particular embodiment, the fabric material and / or the non-crimp fabric material comprise dry fibres which are recycled and / or reused fibres.

The present invention is related to a method for manufacturing a fibre-reinforced composite article (1) having at least one cavity (10), the method comprising the steps of: providing two laminates or preforms (11,12) obtained by coating a fibre reinforcement with a resin, having at least one joining region (13) and at least one cavity defining region (14), and said at least one cavity defining region being covered with a fluid impermeable element in the form of a film attached to the two laminates or preforms, placing the first laminate or preform (11) in a lower mould plate (21) of a mould, placing the second laminate or preform (12) in an upper mould plate (22) of a mould, closing the lower mould plate with the upper mould plate so that the second laminate or preform is placed over the first laminate or preform, so that at least one cavity (10) is created between opposite cavity defining regions of the two laminates or preforms and so that the joining regions of the first and second laminates are in contact and overlapping one another, injecting a fluid to the at least one cavity (10) via at least one fluid injection port (24) of the mould, curing the first and second laminate or preform (11,12) to form a fibre reinforced composite article (1), removing the fluid from the at least one cavity of the fibre-reinforced composite article, opening the mould, and demoulding the fibre-reinforced composite.