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WO2013025115A1 - Structure composite à mailles renforcées en trois dimensions (3d) et procédé de production - Google Patents

Structure composite à mailles renforcées en trois dimensions (3d) et procédé de production Download PDF

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Publication number
WO2013025115A1
WO2013025115A1 PCT/PT2011/000027 PT2011000027W WO2013025115A1 WO 2013025115 A1 WO2013025115 A1 WO 2013025115A1 PT 2011000027 W PT2011000027 W PT 2011000027W WO 2013025115 A1 WO2013025115 A1 WO 2013025115A1
Authority
WO
WIPO (PCT)
Prior art keywords
resin
dimensional
knitted
composite structure
reinforced composite
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/PT2011/000027
Other languages
English (en)
Inventor
Raul Manuel Esteves Sousa Fangueiro
João Carlos VELOSA PEREIRA
Hélder Filipe DA CUNHA SOUTINHO
Sérgio Manuel PINHEIROS MARQUES
Jorge Miguel PINHEIRO MARQUES
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Castros & Marques Lda
Original Assignee
Castros & Marques Lda
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Castros & Marques Lda filed Critical Castros & Marques Lda
Priority to PCT/PT2011/000027 priority Critical patent/WO2013025115A1/fr
Publication of WO2013025115A1 publication Critical patent/WO2013025115A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/026—Knitted fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two or more layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin

Definitions

  • the present invention relates to a three-dimensional (3D) composite structure reinforced by a 3D knitted structure, produced using the resin infusion process, comprising to independent composite sheets connected by a core composed by impregnated cross-threads.
  • the product can be used as a prefabricated structure and more particularly, as fiber- reinforced sandwich panels, for ease of manufacture of prefabricated structures.
  • This product presents added strength, better finishing, low cost manufacturing flexibility, light-weight, excellent acoustic and thermal insulation properties.
  • Textile structures play an important role in the performance of the global textile system.
  • Three- dimensional structures (3D) are organized and integrated set of fibres with multiaxial orientation. Due to the different orientations of the fibres, this type of structures present a high performance behaviour being suitable for a wide range of applications, such as reinforcement of composite structures, for specific applications .
  • Three-dimensional (3D) fabrics may be produced using then most common textile techniques including braiding, nonwovens, weaving or knitting.
  • Three-dimensional (3D) fabrics may be divided into solid three-dimensional (3D) structures or near-net-shaped three-dimensional (3D) structures.
  • Three-dimensional (3D) solid fabrics are usually composed by two separate layers interconnected by- piles or new textile structures. These types of structures are commonly used as reinforcements for composite materials due to their good delamination resistance and impact properties. In the last few years, great efforts have been performed in warp knitting technology to produce a wide range of three-dimensional (3D) fabrics being able to be applied in several conditions, like car seat foam replacement.
  • Materials used in these types of structures are mostly polyester, either texturized or monofilament yarns. Fabrics produced are mono material based, varying just the type of pattern in each separate layer and the density and yarn count of the interconnecting piles.
  • Metals and concrete are the preferred materials for use in buildings constructions or in the transportation industry. These materials are used generally as thick, heavy, and difficult to transport. Also present poor insulation properties. Accordingly, there exists a need for a lightweight and relatively low-cost prefabricated structure .
  • Typical composite sandwich structures have a fundamental pattern, which includes two faceplates, comparatively thin with high strength and stiffness, enclosing a core structure, relatively thick but light, with high stiffness. The components are bonded together. The efficiency of a sandwich material is measured by the strength to weight ratio and proper adhesion between the layers .
  • Textile reinforced laminated structures made of oriented threads are well known in the art.
  • 2-D textile reinforcement and recently 3-D fibrous structures are known ways to improve composite materials in general and particularly mechanical properties of sandwich structures.
  • One problem with texrile threads is thar their best properties are in one direction - tensile (stretch) . Bending and buckling usually are their weak points.
  • Patent WO 2007/098241 A3 refers to a system, method and apparatus for producing fire rated doors.
  • the fire rated doors are made from two panels “sandwich” together.
  • An optional interior layer e.g., fire resistant material
  • Patent US 6869669 B2 presents a prefabricated structure, more particularly a fiber reinforced sandwich panel, for the manufacture of prefabricated buildings.
  • the sandwich panel includes first and second face panels, a support frame, and a core material for insulation.
  • Each of the first and second face panel has a first predetermined thickness and is formed of a fiber reinforced cementitious material.
  • the support frame supports the first and second face panels in a spaced apart configuration.
  • the support frame is formed of a fiber-reinforced cementitious material that is continuous with the cementitious material of the first and second face panel.
  • the block of embedded insulation defines a structure of the support frame.
  • Patent WO/2006/033101 refers to a textile sandwich structure with textile core that comprises two faceplates and a filament core, wherein the core filament is bonded to the faceplates at a plurality of contact points of the filament with said faceplates, the number of said bonded contact points being selected such that it provides a desired resistance to compression of the filament when a force is applied to one of the faceplates.
  • the contact between the faceplates and core may take place in three of the following forms: the core filament is physically bonded to the faceplates in a plurality of contact bonding points; The bonding of the core filament is achieved by integrating the bonded contact points into the faceplates; The faceplates become in contact with the core filament upon application of compression loading.
  • Patent WO 2009/022022 Al presents a method and unit for producing polymer sandwich panels.
  • the unit comprise three lines: a line in which a foam core is produced by extrusion; another line in which the structural skins are obtained, said skins comprising a glass-fibre-reinforced polypropylene base sheet, to which base sheet is applied a surface coating layer also based on polypropylene reinforced with wood fibres or other natural fibres; and a third line in which the structural skins are affixed to the foam core using heat and pressure.
  • Patent US 7048985 B2 presents a technique and a material, a three-dimensional spacer fabric interiamina infusion media and reinforcing composite lamina with the purpose of increasing the resin distribution rate and uniformity throughout the lay up while improving mechanical properties .
  • the present invention has novelty and implicates an inventive step regarding all the others described above in the prior art.
  • the infusion process differs from the ones presented in the patents described, because the mould is open before the resin is totally cured. In this way, it is possible to obtain a composite material with the thickness of the reinforced structure, and there ' s no need to use thermoplastic fibre to create a stiff sandwich product. Moreover, using the vacuum infusion process the resin is just impregnating the connecting fibres of the core leaving the empty space among them completely empty, providing light-weight.
  • the production method has been developed to permit the introduction of various accessories in predefined points of the 3D reinforced composite panel during the vacuum infusion process, like joints, edges, fastenings, corners, screws, locks and others.
  • the final product developed using this method presents important characteristics when comparing to other products used currently in the market such as: low weight, easy and quick production, versatility according to thickness and dimensions required and good performance for different kind of specific applications.
  • the present invention relates to a three-dimensional (3D) knitted reinforced composite structure comprising two independent composite sheets (1 and 3), top and bottom, connected by a core composed by resin impregnated cross- threads (2) being able to be applied for example as soundproofing or as fire rated doors, facades, walls and in the transportation industry.
  • the composite is produced in a single step using knitted fabrics as reinforcing structure and the resin vacuum infusion process with special modifications as method to apply the resin.
  • the composite presents the thickness of the reinforcing structure, due to the aperture of the mould before total curing of the resin.
  • the present invention relates also to the use of closed molded resin infusion for the production cf the composite structure. More specifically it relates to the use of three-dimensional spacer fabrics in resin infusion.
  • closed mould processing fiber and/or other reinforcement ( s ) , collectively referred to as the "preform" are placed in the mould.
  • a method of enclosing and compressing the pre-form against the mould is then employed.
  • Resin is introduced into the pre-form by ports through the enclosure. Upon resin curing the enclosure is first removed, followed by the finished part.
  • Vacuum infusion is one of the principal closed molded resin infusion techniques. Vacuum infusion uses one hard rigid mould and one flexible bag or membrane that when joined are sealed to form a "closed" mould.
  • a disposable barrier layer commonly referred to as peel ply is placed on top of the pre-form.
  • a disposable infusion medium and/or perforated injection tubing is then placed on top of the peel ply to aid in the delivery and distribution of the liquid resin down through the laminate stack.
  • the distribution channels may be incorporated into the bag.
  • Vacuum pressure is then applied and draws resin through feed-lines into the mould and through the fiber pre-form.
  • the production process permits to obtain an extremely light weight composite panel due to the empty spaces left between the fibers in the core that are not occupied by the resin. Resin is only impregnating the fibers in the core, since the mould is open before the resin is completely cured.
  • the production method has been developed to permit the placement, in the 3D reinforced composite panel, of various accessories that can be important for different specific functionalities. These accessories include joints, edges, fastenings, corners, screws, locks and others.
  • Figure 1 - represents the three-dimensional (3D) knitted reinforced composite structure comprising twc independent composite sheets (1 and 3) connected by a core composed by resin impregnated cross-threads (2) .
  • Figure 2 - shows the impregnation process to obtain a three-dimensional knitted reinforced composite structure.
  • the manufacturing system to produce the three-dimensional (3D) knitted reinforced composite structure presents in Figure 1 is composed by a mould, sandwich knitted structure (1, 2 and 3), and the resin vacuum system (5, 11, 12, and 14), according to Figure 2.
  • the impregnation cycle using the special infusion process developed includes different steps.
  • step 1 the mould (10), made out of glass, wood, plastic, among other materials, is completely clean and the tacky tape (7) placed around the edges of the mould and overlapped where the two pieces of the mould are into contact.
  • a release agent is applied to the mould in order to allow easy composite removing. Depending on the release agent, 5-10 min is required before start the lay-up process.
  • a variety of release products are available based in wax or polyvinyl alcohol (PV7A) .
  • the 3D knitted structure (1, 2 and 3) is placed into the mould.
  • peel-ply (6) is placed larger than the spacer 3D dimensions in order to, after infusion, be possible to easily grab the peel-ply (6) to pull it off.
  • the peel ply material is generally used to allow the builder to have a "re-bondable" surface, which requires no additional preparation once the peel ply is removed.
  • the peel ply serves other important functions as well. When applied over " the wet lay-ups, will allow squeegeeing trapped air out without allowing the fibrous layers to move and shift around. When the resin/fiber layup is cured and the peel ply is removed, the surface will be free of harmful, sharp edges and spurs.
  • Peel plies are usually made from polyamide (nylon) or polyester fibres. Polyamide fabrics are more commonly used, though polyesier fabrics must be used with phenol-based resin systems. In vacuum infusion, peel ply fabric of polyamide or polyester can be used, to obtain excellent surface finish and release characteristics that are required for production of high quality composite.
  • a resin distribution mesh (5) is applied as shown in Figure 2.
  • the flow provides enhanced resin flow over the laminate, enabling transport of resin to the whole mould surface.
  • the peel ply (6) provides means of removal of the distribution mesh after cure, good resin flow through itself into the tool laminate and provides a textured surface for a subsequent bonding of a support structure.
  • a number of resin distribution meshes are available offering different properties. Flow, drape and ease of placement are the main criteria for selection.
  • the pressure gradient is created by vacuum on the outlet port.
  • the resin injection tank (13) and inlet port (8) are at room pressure, as opposed to resin injection techniques where the resin injection tank is pressurized.
  • the injection of resin is made through the runner.
  • the outlet (9) and inlet (8) of the resin and runners are positioned.
  • Tacky tape is placed around the inlet tube (15) and outlet tube (14), so that when resin is applied it is possible to squeeze/push the tacky tape, otherwise leaks may be created in this area when vacuum is applied.
  • the vacuum foil (4) a thin transparent plastic foil which is resistant to diffusion of resin particles, is used to close up the mould.
  • the foil When the foil is almost totally closed and the last seam is about to be done, the foil is pulled to allow the definition of the dimensions of the last seam. After this procedure, the tacky tape can be stick to the foil.
  • step 8 vacuum is applied and leaks are checked. Most often, leaks are found at inlet, outlet and seams.
  • the resin is mixed (and degassed) and the inlet hose is in the resin it is important open slowly the clamp in order to prevent resin mixture with the small amount of air still present in the hose.
  • the pressure needs to be increased to a desired value (80-90 kPa) .
  • a desired value 80-90 kPa
  • 90 kPa absolute pressure is used.
  • the inlet is closed.
  • the resin in excess will slowly keep flowing out of the outlet.
  • foam is used to help the bubbles get out easily. Degassing occurs at 90 - 100 kPa, taking care that the foam doesn't flow over and leave polyesters /epoxies for 5-10 minutes.
  • the mould is open before the resin is cured allowing the resilient 3D knitted structure to recovers to its initial thickness.
  • the resin at this stage flows from the upper to the lower structure impregnating just the cross-threads of the core, keeping the free space among them as in the reinforcing knitted fabric.
  • the resin is finally cured it is possible to start the de-molding.
  • Different materials can be used to produce the three- dimensional sandwich composite.
  • the variation in the type of fibre used and in the resin type can occur, according to the requirements of the specific application.
  • the 3D reinforcing structure may be designed to control the final performance of the composite panel, presents in Figure 1.
  • This 3D reinforcing structure composed by two independent layers connected by cross-threads, may be produced using weaving or knitting, warp or weft, technologies, but preferably knitting technology.
  • the connecting threads may be sufficiently stiff to allow fabric recover after compression allowing the required resilience to permit fabrics to recover after resin impregnation before curing, during the vacuum infusion process.
  • Different materials may be used for this purpose including polyester, polyamide or polypropylene monofilaments. Different monofilament yarn counts can be applied in a range from 2 to 500 tex (g/km) .
  • connection threads in the structure may be also designed according to the limitations of the technology used, in a range from 10/cm" to 500/cm .
  • the three- dimensional (3D) knitted reinforced composite structure has a density of the cross-threads which varies according to the specific requirements of the application from 1 dtex to 1000 dtex.
  • the independent layers of the 3D structure may be also designed to control composite panel properties according to the requirements of the application.
  • Different material fibers can be used including all types of non-natural fibers, including polyester, glass, carbon, and natural fibers like sisal, hemp, banana, among others.
  • the yarns using these fibers may be spun or multi ilament yarns, but preferably multifilament, in a yarn count varying from 100 dtex to 100 tex.
  • Different arrangements of the fibers in these independent layers may be achieved depending on the type of loops used to produce them in the corresponding technology.
  • the density of loops can also be designed according to the number of needles per length used in the production equipment (gauge), in a range from 5 to 60 needles/cm.
  • Viscosity is a measurement of how fast a fluid will flow against a stationary surface, or how resistant a fluid is to flowing against a surface. High viscosity fluids are more resistant to flow than low viscosity fluids. Any obstacle that fluid must move around during its flow increases the effective area of stationary surface resistance, decreases the effective open cross sectional flow area, and therefore decreases the overall fluid flow rate. Generally the denser and less uniform the fiber the better it is as a reinforcement material for composites. Vacuum infusing standard fibrous lamina is therefore quite challenging without the use of infusion media. The ideal infusion medium maximizes available cross sectional area with minimal flow " restrictions.
  • thermoset resins may be used including polyester, vinyl ester and epoxy.
  • Polyester resin tends to have yellowish tint and is suitable for most backyard projects. Its weaknesses are that it is UV sensitive and can tend to degrade over time, and thus generally is also coated to help preserve it. It is often used in the making of surfboards and for marine applications.
  • Its hardener is a MEKP, and is mixed at 14 drops per oz.
  • MEKP is composed of methyl ethyl ketone peroxide, a catalyst. When MEKP is mixed with the resin, the resulting chemical reaction causes heat to build up and cure or harden the resin.
  • Vinyiester resin tends to have a purplish to bluish to greenish tint. This resin has lower viscosity than polyester resin and is more transparent. This resin tends to be more resistant over time to degradation than polyester resin, and is more flexible. It uses the same hardener as polyester resin (at the same mix ratio) and the cost is approximately the same.
  • Epoxy resin is almost totally transparent when cured. In the aerospace industry, epoxy is used as a structural matrix material or as structural glue.
  • thermosets are liquid at their required curing temperature allowing more viscouses resin systems to be impregnated at higher temperatures .
  • thermosets resins it is important to control the viscosity during the curing cycle.
  • the resins need to have a certain yield tension for flow, to prevent resin from dripping down to the bottom skin.
  • Flow control agents can be added to produce the requirement viscosity profile.
  • sandwich fabric structure has a lower density than full laminate structures and thus a lower curing exothermic (temperature), which is needed for full core.
  • the sandwich fabric of the about 95 % air in between the piles, which has to be heated. Also, heat is lost to the environment due to air flow.
  • the three-dimensional (3D) knitted reinforced composite panel When comparing to other products in the market the three-dimensional (3D) knitted reinforced composite panel present a very low weight, good resistance and compression properties as well as significantly thermal and acoustical insulation performance.
  • the three-dimensional (3D) knitted reinforced composite structure can be manufactured with any desirable width, length and thickness between 10 mm to 1000 mm..
  • Example 1 Three-dimensional (3D) knitted reinforced composite structure using an epoxy resin
  • a three-dimensional (3D) knitted reinforced composite structure has been prepared using an epcxy resin with the processing parameters indicated in Table 1.
  • Table 4 The compressive properties of the 3D knitted fabrics reinforcing a composite material impregnated with epoxy resin.

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  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

La présente invention concerne une structure composite à mailles renforcées en trois dimensions (3D) comportant deux toiles composites indépendantes (1 et 3) reliées par un cœur composé de filets croisés imprégnés de résine (2), qui peut être utilisée, par exemple, comme isolation sonore ou sur des portes, des façades ou des parois anti-feu, ainsi que dans l'industrie des transports. Le matériau composite est produit en une seule étape en utilisant des textiles à mailles en 3D et un procédé d'infusion de résine. Ce procédé permet d'imprégner totalement les couches extérieures et le cœur de manière partielle, où sont disposés les filets croisés, en conservant les espaces vides entre eux, qui font office de pièges, sans résine, car le moule est ouvert avant que la résine ne soit totalement déposée. De plus, cette méthode de production a été développée pour permettre le placement, dans la couche composite 3D renforcée, de différents accessoires pouvant être utilisés pour diverses utilisations spécifiques. Parmi ces accessoires se trouvent des joints, des cales, des dispositifs de fixation, des coins, des vis, des dispositifs de blocage, et d'autres encore.
PCT/PT2011/000027 2011-08-16 2011-08-16 Structure composite à mailles renforcées en trois dimensions (3d) et procédé de production Ceased WO2013025115A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/PT2011/000027 WO2013025115A1 (fr) 2011-08-16 2011-08-16 Structure composite à mailles renforcées en trois dimensions (3d) et procédé de production

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Application Number Priority Date Filing Date Title
PCT/PT2011/000027 WO2013025115A1 (fr) 2011-08-16 2011-08-16 Structure composite à mailles renforcées en trois dimensions (3d) et procédé de production

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Cited By (5)

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Publication number Priority date Publication date Assignee Title
GB2533934A (en) * 2015-01-07 2016-07-13 Cotech Inc Composite decorative material with micro 3D surface and a method for making same
WO2021099476A1 (fr) 2019-11-22 2021-05-27 Saint-Gobain Performance Plastics France Matériaux composites comprenant un mode de liage de renforcement et une résine, et procédé de production
CN113696509A (zh) * 2021-08-06 2021-11-26 南京航空航天大学 一种超混杂面板/三维编织中空夹层复合材料的一体化成型方法
CN115091780A (zh) * 2022-05-18 2022-09-23 南京玻璃纤维研究设计院有限公司 一种利用三轴成型工装制备中空织物复合材料的方法
US12434431B2 (en) 2017-08-28 2025-10-07 Harris Corporation Method for making a metal isolator body and associated device including the same

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US6869669B2 (en) 2001-11-14 2005-03-22 Advanced Wall Systems Llc Fiber-reinforced sandwich panel
WO2006033101A2 (fr) 2004-09-22 2006-03-30 Escom Composite Materials Ltd. Structure sandwich a noyau textile
WO2007098241A2 (fr) 2006-02-21 2007-08-30 Polymer-Wood Technologies, Inc. Systeme, procede et appareil pour produire des portes resistantes au feu
WO2009022022A1 (fr) 2007-07-27 2009-02-19 Ulma C Y E, S. Coop. Procédé et installation destinés à la production de panneaux de type sandwich de nature polymérique et panneau obtenu

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US20030077965A1 (en) * 2001-07-23 2003-04-24 Mack Patrick E. Three-dimensional spacer fabric resin infusion media and reinforcing composite lamina
US7048985B2 (en) 2001-07-23 2006-05-23 Vrac, Llc Three-dimensional spacer fabric resin infusion media and reinforcing composite lamina
US6869669B2 (en) 2001-11-14 2005-03-22 Advanced Wall Systems Llc Fiber-reinforced sandwich panel
WO2006033101A2 (fr) 2004-09-22 2006-03-30 Escom Composite Materials Ltd. Structure sandwich a noyau textile
WO2007098241A2 (fr) 2006-02-21 2007-08-30 Polymer-Wood Technologies, Inc. Systeme, procede et appareil pour produire des portes resistantes au feu
WO2009022022A1 (fr) 2007-07-27 2009-02-19 Ulma C Y E, S. Coop. Procédé et installation destinés à la production de panneaux de type sandwich de nature polymérique et panneau obtenu

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2533934A (en) * 2015-01-07 2016-07-13 Cotech Inc Composite decorative material with micro 3D surface and a method for making same
US12434431B2 (en) 2017-08-28 2025-10-07 Harris Corporation Method for making a metal isolator body and associated device including the same
WO2021099476A1 (fr) 2019-11-22 2021-05-27 Saint-Gobain Performance Plastics France Matériaux composites comprenant un mode de liage de renforcement et une résine, et procédé de production
FR3103409A1 (fr) 2019-11-22 2021-05-28 Saint-Gobain Performance Plastics France Structure tricotee pour renforcement de materiaux composites.
CN115003870A (zh) * 2019-11-22 2022-09-02 法国圣戈班高性能塑胶公司 包括针织增强结构和树脂的复合材料以及制造方法
CN115003870B (zh) * 2019-11-22 2024-04-26 法国圣戈班性能塑料公司 包括针织增强结构和树脂的复合材料以及制造方法
CN113696509A (zh) * 2021-08-06 2021-11-26 南京航空航天大学 一种超混杂面板/三维编织中空夹层复合材料的一体化成型方法
CN115091780A (zh) * 2022-05-18 2022-09-23 南京玻璃纤维研究设计院有限公司 一种利用三轴成型工装制备中空织物复合材料的方法

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