154results about "Hollow wall articles" patented technology

The invention discloses a double-injection rubber-coated product assembled in a super-thick plastic part cavity structure mold and a production process of the double-injection rubber-coated product. A molten plastic material is injected into a first injection mold cavity through a first gun barrel of a double-injection injection molding machine to form a first injection molding part and a second injection molding part which are integrated; then the six-axis robot is controlled to drive the part taking and mounting tool to move to grab the insert and fix the insert to the second injection molding part, and at the moment, a closed assembly part with a cavity structure is formed between the second injection molding part and the insert; finally, a molten plastic material is injected to the outer surface of the assembly part of the second injection mold through a second gun barrel of the double-injection injection molding machine to form a third injection molding part; according to the technology, the overall weight of a solid structure product can be greatly reduced, the material use is reduced, the material cost is reduced, the product cooling time is shortened through the design of the cavity structure, the production efficiency is improved, and the product defects such as surface shrinkage marks and internal irregular cavities caused by excessive shrinkage of a plastic material in the cooling and curing process are thoroughly eradicated.

A method of manufacturing a lightweight panel for a vehicle includes a mat fixing operation of manufacturing a first semi-finished product by fixing a mat to each of upper and lower surfaces of a paper honeycomb in a predetermined thickness and a resin spraying operation of manufacturing a second semi-finished product by applying a resin to each of upper and lower surfaces of the first semi-finished product. The method also includes a thermal molding operation of manufacturing a third semi-finished product by thermally molding the second semi-finished product between a heated upper thermal mold and a heated lower thermal mold, a sheet attaching operation of manufacturing a fourth semi-finished product by attaching a sheet molded on an upper surface of the third semi-finished product, and a trimming operation of cutting an unnecessary area of the fourth semi-finished product.

A lightweight panel for a vehicle includes a honeycomb part having a paper honeycomb whose interior is formed in a honeycomb structure and is machined to a predetermined thickness, a reinforcing layer including a reinforcing mat and a reinforcing resin, formed on each of upper and lower surfaces of the honeycomb part, and a plurality of concave portions formed in a lower surface of the honeycomb part.

Composite fuel cell bipolar plates and methods for manufacturing bipolar plates are provided. A method for fabricating a composite fuel cell bipolar plate includes providing a spread-tow woven carbon fiber fabric having an upper layer of fibers and a lower layer of fibers, wherein the fabric has a thickness of less than 200 micrometers (μm); segmenting at least one of the layers of fibers at selected locations to form slits; forming the fabric and resin into a half plate shape to form a plurality of half plates, wherein each half plate comprises a series of lands and walls; and forming the bipolar plate by aligning and bonding respective lands of a first half plate and a second half plate.

The application relates to the technical field of wave-absorbing composite materials, and particularly discloses a honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material based on Ti3C2T x MXene aerogel and a preparation method of the honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material, the honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material is a multilayer structure, and from outside to inside, the multilayer structure comprises a high-temperature-resistant resin-based composite material wave-transparent skin, a honeycomb structure wave-absorbing layer and a high-temperature-resistant resin-based composite material reflecting skin in sequence, and the honeycomb structure wave-absorbing layer is a composite material honeycomb structure filled with a high-temperature-resistant MXene composite aerogel material.The honeycomb sandwich structure high-temperature-resistant wide-frequency wave-absorbing composite material based on Ti3C2T x MXene aerogel, which uses a MXene composite aerogel material (the density is 2 mg / cm 3 ~15 mg / cm 3 ) and a light composite material honeycomb structure carrier, overcomes the defect that existing wave-absorbing materials are large in density, and has an effective absorption frequency band width of more than 10 GHz when the reflectivity is lower than -10 dB, and can simultaneously meet the requirements of wide-frequency wave-absorbing performance and light weight of wave-absorbing materials for aerospace vehicle equipment.

A honeycomb core, formed from a plurality of polygonal cells arranged in an array. Each polygonal cell has lateral cell walls, the lateral cell walls of each polygonal cell forming a polygonal ring, the lateral cell walls being composed of a sheet material, the sheet material being a symmetric three-layer or five-layer thermoplastic co-extruded sheet material having an inner central or core layer and outer layers. The symmetric three-layer or five-layer thermoplastic co-extruded sheet material provides improved mechanical properties compared to a simple sheet material.

The present invention relates to a composite material for producing an extrudate comprising PVC and granules of cereal chaff, such as husks, hulls, awns, seed coats and / or stem parts, wherein the cereal is Pooideae and / or Panicoideae and / or Andropogonoideae.

Manufacturing an Acoustic Component with Facilitated Mold Removal. The invention relates to a method for manufacturing an acoustic component comprising a plurality of hollow acoustic elements having a shape that gradually narrows between a base and a top, said method comprising: - positioning and shaping a blank (12) in a shaping tool (500) so as to obtain an acoustic component (120), - opening the shaping tool (500) so that a first face (120a) of the acoustic component (120) is free and a second face (120b) of the acoustic component (120) remains in contact with the shaping tool (500), - spraying a first fluid (601; 701) onto the second face (120a) of the acoustic component (120), - injecting a second fluid (801) onto the first face (120b) of the acoustic component (120) through channels (523) trained in shaping tooling (500).Figure for the abridged version: Fig. 5.

The invention discloses an extrusion die capable of rapidly adjusting die lip gaps and a hollow plate manufacturing method. The extrusion die comprises a die body, two die lips and a die lip adjusting mechanism. The die lip adjusting mechanism comprises two die orifice adjusting blocks mounted on the die body, two groups of fine adjustment mechanisms respectively mounted on the two die orifice adjusting blocks, and two quick adjustment mechanisms for adjusting the positions of the die orifice adjusting blocks relative to the die body. And fine adjustment pieces of the fine adjustment mechanism are respectively connected to different positions of the corresponding die lips. The integral adjustment of the distance between the two die lips can be realized by operating the quick adjustment mechanism, and the local adjustment of the distance between the die lips can be realized by operating the fine adjustment mechanism. According to the method, the mode of fast adjustment and fine adjustment is adopted, overall adjustment and local correction are separated, the problems that a traditional mold is long in adjustment time consumption and high in requirement for skills of operators are solved, overall adjustment of the distance between the mold lips can be fast achieved, meanwhile, the local wall thickness is accurately corrected, and the adjustment efficiency and the product precision are remarkably improved.

A method for producing a torsion box for a structure of an airplane. The method includes providing a first component made of a fiber composite material, the first component has a first planar base having a first inner side and a first outer side, first stiffening elements on the first inner side forming a composite with the first base. A second component is provided of a fiber composite material and has a second planar base having a second inner side and a second outer side. Second stiffening elements are on the second inner side and form a composite with the second base. The method includes superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side. The methods includes connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

A panel for an active laminar flow control arrangement may comprise a longitudinal wall (434) and one or more division walls (428) extending from the longitudinal wall (434) and extending between the first end (491) and the second end (492). The panel may be coupled to a nacelle outer skin (312) via a plurality of adhesive fasteners (326, 322) preinstalled onto an inner surface (314) of the outer skin (312) and onto stiffeners (382) and / or stringers (384) associated with the outer skin (312).

The application discloses a pin-connection large-opening solid rocket engine composite shell forming method, and comprises the following steps: preparing front and rear joints with sealing inserts; preparing a cylinder segment winding tool; assembling a winding core and performing surface treatment; preparing a shell fiber winding layer; curing the shell; and machining the shell, so as to obtain a pin-connection large-opening solid rocket engine composite shell. The forming method has good process performance, and the reliability of the connection between the large-opening composite shell and other cabin segments or end covers is improved by adopting a double-row radial pin connection method. Meanwhile, the sealing performance of the shell is further ensured by arranging the sealing inserts, and the winding process is simple and efficient without the complex operation of circumferential winding and laying-up of the prepreg leveling on the surface of the winding core.

The invention relates to a thermocompression device for producing recyclable honeycomb plates with high mechanical strength, which, by means of the proposed configuration, enables high-speed production with an optimised operating width. For this purpose, the device comprises an area for continuously heating and pressing the supplied sheet, a cooling area, a calendering area and a moulding area. Advantageously, the moulding area comprises forming rollers provided with protuberances arranged in continuous rows distributed on the surface of the forming rollers, such that the rows are arranged cross-wise with respect to the sheet supply direction. Recyclable honeycomb plates are thus obtained. The invention also relates to a method implemented using the described thermocompression device.

Bipolar plates for fuel cells made of composite materials and methods for manufacturing bipolar plates are provided. One method for manufacturing a bipolar plate for fuel cells made of composite material comprises providing a spreading woven carbon fiber fabric with an upper layer of fibers and a lower layer of fibers, wherein the fabric has a thickness of less than 200 micrometers (µm); segmenting at least one of the layers of fibers at selected locations to form slots; forming the fabric and resin into a half-plate mold to form a plurality of half-plates, each half-plate having a series of ribs and walls; and forming the bipolar plate by aligning and joining the respective ribs of a first half-plate and a second half-plate.

Provided is an extrusion molding apparatus capable of producing a multi tube with which an outer shape of a cross section is close to a perfect circle. The multi-lumen tube extrusion molding apparatus includes a resin supplying portion, a die that has an extrusion port at a lower end portion and molds the multi-lumen tube as the resin supplied from the resin supplying portion is extruded vertically downward, and an outer surface molding apparatus that molds an outer surface of the extruded tube. In a state in which the resin is supplied from the resin supplying portion to the die, the outer surface molding apparatus depressurizes a molding space of circular cylindrical shape in a state in which the extruded tube is contained in the molding space to mold an outer surface of the contained multi-lumen tube to a circular cylindrical shape.

The present invention relates to a method for manufacturing a multi-layer component, in particular a sandwich component, wherein the method comprises at least: providing a first and a second cover layer element (102, 104) in a tool unit (100), wherein the first and the second cover layer element (102, 104) are arranged next to each other and / or are in contact with each other in the tool unit (100), in particular directly; and introducing a plastic material (108) between the first and the second cover layer element (102, 104), wherein the first and the second cover layer element (102, 104) are spaced apart from each other before and / or during the introduction of the plastic material (108) and / or by the introduction of the plastic material (108). Furthermore, the present invention relates to a tool unit (100) and a production plant for manufacturing a multi-layer component, in particular a sandwich component.

A method for forming a fiber-reinforced thermoplastic control surface (600) includes forming first and second skins (610, 612) from a fiber-reinforced thermoplastic resin. The method further includes overmolding fiber-reinforced thermoplastic features onto the first skin (610) and / or second skin (612), including stiffener structures (614), sidewalls (633), and / or hinges. The method further comprises welding or consolidating the first and second skins (610, 612) together, along with the associated internal features overmolded thereon to form a single-piece, stiffened, fiber-reinforced thermoplastic control surface (600).

The present application relates to the technical field of high polymer material additive manufacturing, in particular to a processing and manufacturing process of seamless double-plastic high-cavity pipe, which uses additive manufacturing process to manufacture the seamless double-plastic high-cavity pipe. The prefabricated plastic inner pipe is clamped on the rotatable clamp below the printing head, a base plate is arranged at the starting printing position and the outer pipe main pipe section is printed layer by layer on the base plate, the printing operation and the angle adjustment operation are alternately performed until the printing of the outer pipe main pipe section is completed, then the angle of the prefabricated plastic inner pipe is adjusted, and the outer pipe sealing section is printed layer by layer at the unprinted gap part of the hollow outer wall plastic outer pipe, during which a special disintegrable support sheet is used to support the formation of the overhanging upper bottom of the outer pipe sealing section. The prepared seamless double-plastic high-cavity pipe is used for structural analysis or performance test, and the application of additive manufacturing technology avoids the manufacturing of complex co-extrusion die head and the occupation of production equipment, which provides convenience for enriching the number of experimental groups and developing more mature products.

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.

To provide a method for manufacturing a lay-up (600) of a composite honeycomb core sandwich structure.SOLUTION: Laying up a first group of unidirectional tows (602) on a tool (100) for layup of the composite honeycomb core sandwich structure using an automated fiber placement process to form a stack of under-core composite plies (604) secured to a rough surface (102) adhered to the tool (100), placing a honeycomb core (606) on the stack of under-core composite plies (604) in the rough surface (102), and laying up a second group of unidirectional tows (608) on the honeycomb core (606) using the automated fiber placement process to form a stack of over-core composite plies (610) securing the honeycomb core (606) to the rough surface (102).SELECTED DRAWING: Figure 6A

The invention discloses a method for manufacturing composite fibreboard products, which includes the steps of providing double-faced corrugated paper sheets as raw material; of feeding the double-faced corrugated paper sheets through a coater; of gluing the double-faced corrugated paper sheets together to form a honeycomb block; of cutting the honeycomb block into honeycomb wafers each having two outer layers; of laminating the outer layers of the honeycomb wafers with paper to form a flat sandwiched composite fibreboard; and of cutting and trimming the flat sandwiched composite fibreboards to form composite fireboard products. The honeycomb block is cured to ensure dimensional stability. The honeycomb block is cut into honeycomb wafers by means of big saw means.

The invention relates to a method for manufacturing a honeycomb structure for a part, in particular for an aircraft turbomachine, this honeycomb structure comprising a grid of cells (86), a first skin (82) of composite material covering the grid (86), and optionally a second skin (84) of composite material having the grid (86) positioned between the first and second skins, the method being characterized in that it comprises the steps of: (a) creating a first stack (820) of fiber layers by draping so as to form the first skin, (b) depositing at least one first interface film (800) by draping onto the first skin, (c) positioning the grid of cells (86) on the first interface film, (d) optionally depositing at least one second interface film (802) by draping onto the grid (86), and (e) optionally creating a second stack (840) of fiber layers by draping so as to form the second skin.Figure for the abbreviation: Figure 11.

The present invention is directed to a 3D printed mold for creating three dimensional pulp products from a fibrous pulp slurry. Transverse filaments are integrated into an infill structure with an open-cell pattern. The transverse filaments form channels through the interior matrix of the mold. The open cell infill pattern and channels allow for the movement of vacuumed materials through the interior matrix of the 3D printed mold when vacuum pressure is applied. The product surface of the mold comprises an array of beads formed from the over-extrusion of melted material at the ends of the transverse filaments. The beaded array narrows the opening of the channels created by the transverse filaments, preventing the fibers from entering the matrix of the mold and clogging the flow of materials. This causes the fibers to aggregate on the product surface of the mold, forming the three dimensional pulp product.

The invention relates to a method for manufacturing a turbomachine part, comprising a wall and a honeycomb structure made of composite material on at least a portion of one face of the wall, the honeycomb structure having at least one first grid of cells and at least one first skin covering this first grid of cells, the method comprising the following steps of: (a) supplying the wall, and (b) creating the honeycomb structure on the face, wherein step (b) of creating the honeycomb structure comprises the following substeps of: (b1) laying first plies of composite material by draping to form the first skin, and (b2) forming the first grid of cells by additive manufacturing, substep (b1) being carried out before or after substep (b2). Figure for the abstract: Figure 10

The present invention relates to a method of processing a composite component comprising one or more types of fibers and a thermoplastic. The method comprising: arranging a preliminary composite component (10) comprising a floodable hollow lattice structure (12) within a shaping cavity (116) of a mold (110); injecting a fluid medium into the floodable hollow lattice structure (12) of the preliminary composite component (10); and increasing the temperature of the fluid medium to a processing temperature, thereby: yielding the thermoplastic, and increasing a pressure within the shaping cavity (116) such that a shell surface (14) of the preliminary composite component (10) presses against a surface of the shaping cavity (116) while maintaining a lattice structure within the preliminary composite component (10) and such that both the shell and lattice structures of the preliminary composite component are consolidated. A system for processing the composite component is also presented.

A method for manufacturing a lightweight panel for a vehicle, comprising fixing a mat (22) to each of an upper and a lower surface of a paper honeycomb (P) of a predetermined thickness during a mat fixing operation (S120) to produce a first semi-finished product (20-1), applying a resin (24) to each of the upper and the lower surface of the first semi-finished product (20-1) during a resin spraying operation (S130) to produce a second semi-finished product (20-2), thermoforming the second semi-finished product (20-2) between a heated upper thermoforming tool (53) and a heated lower thermoforming tool (51) during a thermoforming operation (S150) to produce a third semi-finished product (20-3), and attaching a shaped plate (23) to an upper surface of the third semi-finished product (20-3) during a plate attachment operation (S160).to produce a fourth semi-finished product (20-4), and separating an unnecessary area from the fourth semi-finished product (20-4) during a separation process (S170).

Composite fuel cell bipolar plates and methods of making bipolar plates are provided. A method for manufacturing a composite fuel cell bipolar plate, comprising: providing a spread tow-woven carbon fiber fabric having an upper fiber layer and a lower fiber layer, where the fabric has a thickness of less than 200 microns ([mu] m); dividing at least one of the fiber layers at a selected location to form a slit; forming the fabric and the resin into a half-plate shape to form a plurality of half-plates, where each half-plate includes a series of platforms and walls; and forming the bipolar plate by aligning and bonding the respective lands of the first and second half-plates.

Sandwich-structured noise-attenuating and / or structural panels and methods of manufacturing such panels using ultrasonic welding are described. The method includes: receiving a backing member, a sheet and a cellular structure; assembling the cellular structure between the backing member and the sheet; and ultrasonically welding the backing member and the sheet together.