• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Methods of molding a fibrous preform and of making a composite part A method of shaping the dry preform material prior to resin infusion is disclosed. the raw material to be modeled is a blank preform (eg flat sheet) of dry, fibrous material. the modeling process is a process that relies on the control of vacuum speed, pressure and deformation to produce a modeled preform with a three-dimensional vacuum configuration. The purpose of the modeling process described here is to allow an automated process to replace the conventional hand of the tray operation.
    公开号:BR112015012130B1
    申请号:R112015012130-6
    申请日:2013-12-19
    公开日:2021-07-13
    发明作者:Robert Blackburn；James EASTBURY；Samuel HILL
    申请人:Cytec Industries Inc；
    IPC主号:
    专利说明:

    FUNDAMENTALS
    [0001] In recent years, the use of fiber reinforced polymer composite materials has become more prevalent in industries such as aerospace and automotive. These composite materials exhibit high strength as well as corrosion resistant properties in harsh environment. Furthermore, its light weight property is particularly advantageous compared to similar parts constructed from metals.
    [0002] Fiber reinforced polymer composites have traditionally been made from prepregs, which are formed from fibers impregnated with a curable matrix resin such as epoxy. The resin content in the prepreg is relatively high, typically 20% - 50% by weight. Multiple pre-impregnated layers can be cut to lay, then later assembled and molded into a molding tool. In the case where the prepreg cannot be easily adapted to the mold shape of the tool, heating can be applied to the prepreg ends to gradually deform with the shape of the mold surface.
    [0003] More recently, fiber reinforced polymer composites are made using liquid molding processes involving resin infusion technologies, which include Resin Transfer Molding (RTM), Liquid Resin Infusion (LRI), Transfer Molding Resin Assisted Vacuum (VARTM), Resin Flexible Tooling Infusion (RIFT), Vacuum Assisted Resin Infusion (VARI), Resin Film Infusion (RFI), Controlled Atmospheric Pressure Resin Infusion (CAPRI), VAP (Vacuum Assisted Process), Single Line Injection (SLI) and Constant Pressure Infusion (CPI) among others. In a resin infusion process, dry binder fibers are first laid out in a mold as a preform and then injected or infused directly in situ with liquid matrix resin. The term "binders" as used herein means that a binder has been applied. The preform typically consists of one or more layers (ie layers) of dry, fibrous material that are assembled in a stacking arrangement where typically a powder, web or film binder is used to maintain the desired geometry prior to infusion. of resin. After resin infusion, the resin-infused preform is cured according to a polymerization cycle to provide a finished composite article. Resin infusion is used not only to manufacture small, complex-shaped parts, but now it is also used to manufacture large aircraft parts like the wing.
    [0004] In resin infusion, manufacturing the preform to be infused with resin is a critical element - the preform is, in essence, the structural part, waiting for the resin. The hand tray has typically been used in the past to create composite preforms with detailed geometry. However, this is considered a time-consuming operation, with a high risk of variation from part to part. Thus, there is still a need for improvements in the fabrication of dry fibrous preforms for subsequent resin infusion. SUMMARY
    [0005] The present disclosure is related to the formation of dry material of the preform before resin infusion. The raw material to be molded is a blank preform (eg, flat sheet) of dry, binder, and fibrous material. The molding process is a process that relies on the control of vacuum speed, pressure and deformation to produce a molded preform with a three-dimensional vacuum configuration. The purpose of the shaping process described here is to allow a highly controlled process to replace the conventional hand of tray operation. BRIEF DESCRIPTION OF THE FIGURES
    [0006] FIGS. 1A-1D illustrate a vacuum forming process for molding a smooth preform according to an embodiment.
    [0007] FIGS. 2A-2C illustrate a method for fabricating a molded preform with an intermediate machining step.
    [0008] FIG. 3 shows a tool housing containing a mold for shaping a preform according to an example.
    [0009] FIG. 4 illustrates the configuration for forming a preform with an L-shaped cross section.
    [00010] FIG. 5 shows a molded preform representing a spar section that was produced by implementing the configuration illustrated in FIG. 4. DETAILED DESCRIPTION
    [00011] The blank preform to be molded is a flat sheet composed of a plurality of fibrous layers (or folds) assembled in a stacking arrangement. The fibrous layers of the preform are held in place (i.e., "stabilized") by bonding using a binder to maintain alignment and to stabilize the fibrous layers. By having the binder, they wear out or separate from the dry fiber material and can be avoided during storage, transport and handling. Additionally, injection or infusion of matrix resin may require pressurized injection, which may result in the local displacement of an unstable preform or fibers. Thus, the binder holds the fibers in position during such a pressurized injection.
    [00012] The term "stabilization" or "stabilized" is used herein to mean the stabilization of various sheets, layers or tarpaulins of fibrous layers or fabrics so that they can be molded or deformed without fraying, fraying, crumbling, buckling, wrinkle or otherwise reduce the integrity of the fibrous layers or tissues. Vacuum Formation Process
    [00013] The vacuum forming process involves a double thinning of the membrane, which includes an upper diaphragm and a lower diaphragm, which must be placed over a tool housing (see FIG. 1A). The tooling chamber contains a single (shown) or multiple molds with a three-dimensional, non-polar surface that represents the desired shape of the final structure. In addition, the tool body is connected to a vacuum source via a suction device (eg vacuum pump). Diaphragms are flexible and can be non-elastically deformable or elastic sheets of material such as rubber, silicone, nylon or similar material that have an elongation to failure above 100%. As an initial step, a flat preform is placed between the flexible sheets. Each diaphragm is attached to a frame to maintain the desired diaphragm shape through a supported perimeter.
    [00014] The diaphragms with the preform between them are then placed in the tool housing (FIG. 1B). The diaphragm structures are sealed to the tool housing through a mechanical clamping mechanism to create a sealed chamber, interconnecting the lower diaphragm and tool housing, and define a sealed pocket between the diaphragms. The sealed bag between the diaphragms is connected to a medium suitable for aspiration through a valve connection. Then, the sealed cavity between the diaphragms is partially evacuated to remove air. At this stage, the preform is firmly held between the diaphragms.
    [00015] Vacuum pressure between the diaphragms is applied to achieve stability for the fibrous layers in the preform, to ensure consolidation between the layers and to avoid adverse deformation or wrinkling of the fibrous material during formation. In addition, the vacuum level between the diaphragms is selectively applied to achieve the inter-shear fibrous material layer, maintaining adequate preform stability. Stabilization of the preform is important to maintain good fiber alignment and uniform layer thickness at elevated temperatures. Proper vacuum pressure balances the stability of the preform and the ability to deform the preform to the desired mold. In one embodiment, the vacuum pressure between the diaphragms is defined as less than 1 atmosphere, preferably less than 800 mbar, eg 500 mbar.
    [00016] The term "vacuum pressure" as used herein includes vacuum pressures of less than 1 atmosphere (or less than 1013 mbar).
    [00017] Then, heating is carried out to allow the softening of the binder inside the preform. Heating can be done, for example, by placing the diaphragm assembly and tool housing in an oven, or using an array of infrared heating lamps or a heated mat. The binder in the preform, which is in a solid phase at room temperature (20°C-25°C), softens upon heating and allows fibrous webs to be formed. The forming temperature is dictated by the viscosity of the binder between the layers of fibrous material in the preform. Binder viscosity is optimized to reduce shear stress within the preform to allow movement of layers without creating fiber distortions and/or wrinkles. The binder which is suitable for the purpose in this document contains a mixture of thermosetting resin and thermoplastic resin, and may represent less than 20% of the preform by mass, preferably less than 10% of the preform by mass, more preferably , in the range of 2% - 6% of the preform in bulk. In certain embodiments, the binder composition contains sufficient thermoplastic content to allow successful deformation at elevated temperatures and can be delivered in powder form. The minimum temperature deformation is the temperature at which the binder is softened to a molten state that allows the fibrous preform layer to deform. The viscosity of the preferred binder at this stage may be below 100,000,000 m^Pas, preferably below 10,000,000 m^Pa, more preferably below 3,000,000 m^Pa. Once the preform has reached an optimal temperature deformation, the tool housing is evacuated at a predetermined rate of 1 mbar/15 min or faster, until the housing reaches the desired vacuum level of less than 980 mbar pressure absolute, but less than vacuum pressure in tool housing, more preferably less than 900 mbar absolute pressure and absolute pressure ideally less than 850 mbar, heating is maintained through time of total deformation. As the tool body is being evacuated, the diaphragms with the preform sandwiched between them are pulled into the mold and shaped to the shape of the mold surface.
    [00018] Upon reaching the desired vacuum level of the tool housing, the vacuum pressure between the diaphragms is reduced to a lower vacuum level than between the tool housing to ensure complete compaction of the preform. This also allows the operator to tailor the compaction of the preform and hence the handling characteristics and permeability of the preform. At this point, the preform is cooled.
    [00019] The molded preform is then cooled to below the softening temperature of the binder. At this point, the binder in the preform re-hardens and the preform retains its newly formed geometry. Upon reaching the cooled temperature, the vacuum between the diaphragms is relieved by venting to atmosphere, the upper diaphragm is lifted away from the lower diaphragm, and the molded preform is removed (FIG. 1D). Air is then pre-introduced into the tool housing, and the vacuum formation process is ready to be repeated. The removed preform will retain its desired shape for subsequent resin infusion.
    [00020] The dual arrangement of the diaphragm described above helps in deforming the fibrous preforms, allowing a lower compaction pressure to be set between the diaphragms, thus increasing the mobility of adjacent layers among each other due to lower frictional forces. A reduced pressure between the two diaphragms also minimizes friction from the contact force so the diaphragms can elongate independently of the preform. In the vacuum forming process disclosed in this document, complete compaction with the desired radius shape can be achieved, since the full vacuum level in the tool housing has been applied after deformation. The ability to control the level of compaction in the formation, the rate of formation and the shear behavior of the binder leads to improved radius geometry.
    [00021] The vacuum forming process described above does not require a complex tool with upper and lower shaping parts. Instead, the vacuum formation process is based on controlling the deformation rate, temperature and vacuum pressure. The vacuum rate between the diaphragms and within the tool housing can be optimized to prevent excessive crease formation, fiber distortion and to control radius thickness.
    [00022] Conventionally, post-cure machining of structural parts is done to achieve the geometry of the final part. An 8-axis milling machine is generally used for such operations. This phase of the manufacturing process presents a high level of risk, as it is one of the last processing steps to be carried out. Damage caused during this step can result in the part being demolished. Furthermore, the operation is also usually very time-consuming.
    [00023] Thus, the fabrication of the molded preform can be further optimized by including a machining step after the fabrication of the preform blank, but before modeling through vacuum forming the process described above. This ensures that efficient and easy machining can be done in an automated fashion rather than advanced programming and positioning of the three-dimensional preform within a complex machine, if post-machining curing is done. This machining step can be achieved by pre-consolidating the flat blank preform to a desired level of compaction for stabilization and edge quality.
    [00024] FIGS. 2A-2C illustrates a method for fabricating a molded preform with an intermediate machining step. Referring to FIG. 2A, a large flat sheet of preform material (i.e., blank preform) is manufactured by imposing a plurality of fibrous layers which are either consolidated at the down-depositing point or followed by compaction or consolidation. Preform sheet is then cut to a desired pattern by machining, See FIG. 2B. Referring to FIG. 2C, the patterned sheet is then vacuum molded forming the process described above to produce a non-planar, three-dimensional configuration, for example, an L-shaped cross-sectional structure. The final geometry of the molded preform depends on the configuration of mold is used.
    [00025] The vacuum forming process described here allows for the effective and efficient production of the three-dimensional preforms in an automated way, which allows for greater repeatability and large-scale manufacturing. As an example, this process is suitable for manufacturing aerospace reinforcement structures such as L-shaped curved wing skin spar sections, C-shaped or U-shaped wing spars. Furthermore, rapid deformation is possible through This vacuum forming process, for example, 5-15 minutes of cycle to deform a flat blank preform consisted of 33 layers of carbon fiber fabrics containing 5% by weight of the binder in an L-shaped structure or in U. Preform Material
    [00026] The preform in the present context is a set of dry fibers or layers of dry fibers that constitute the reinforcing component of a composite and is/are a suitable shape for the application of resin infusion as RTM.
    [00027] The blank flat preform to be molded consists of multiple layers or layers of fibrous material, which can include non-woven mats, woven fabrics, knitted fabrics and non-crimped fabrics. A "carpet" is a non-woven fabric made from randomly arranged fibers such as chopped fiber filaments (to produce the chopped fiber mat) or twirled filaments (to produce continuous yarn mat) with a binder applied to maintain its shape. Suitable fabrics include those having directional or non-directional aligned fibers in the form of mesh, tows, ribbons, fabric, braids and the like. The fibers in the fibrous layers or fabrics can be organic or inorganic fibers, or mixtures thereof. Organic fibers are selected from hard or rigid polymers such as aramids (including Kevlar), polyester, high modulus polyethylene (PE), poly-p-phenylenebenzobisoxazole (PBO) and hybrid combinations thereof. Inorganic fibers include fibers made from carbon (including graphite), glass (including E-glass or S-glass fiber), quartz, alumina, zirconia, silicon carbide and other ceramics. To make high-strength composite structures, such as main parts of an airplane, the preform fibers preferably have a tensile strength of > 3500 MPa (or > 500 ksi).
    [00028] To form the blank preform according to an embodiment, the binder composition is applied to each fibrous layer (eg, fabric plies), and a plurality of coated fibrous layers are then assembled by stacking one desired thickness. The binder can be applied to the fibrous layers before or during the tray of the fibrous layers. The assembly of the fibrous layers can be done by a hand tray process or an automated tray process such as automated tape placement (ATL) and automated fiber placement (AFP) or other automated methods of depositing the fibers or layers in a good shape ample or pre-prepared. The stack of fibrous layers is then consolidated or compacted through the application of heat and pressure. When automated tray is used, compression is performed during tray. During compaction, the binder that is solid at room temperature softens upon heating and allows the fabric of the layer to bond together as it is applied to a setting pressure. Some binders require maintenance of consolidation pressure while the binder cools. Ligand System
    [00029] The binder for binding the fibrous layers in the blank preform can be of various forms, including powder, spray, liquid, paste, film, fibers and non-woven webs. The binding material can be selected from thermoplastic polymers, thermosetting resins and combinations thereof. In certain embodiments, the binder may take the form of polymeric fibers formed from thermoplastic material or thermoset material or a mixture of thermoplastic and thermoset materials. In other embodiments, the binder is a mixture of thermoplastic fibers (ie, formed from the thermoplastic material of the fibers) and thermoset fibers (ie, formed from the thermoset material of the fibers). Such polymeric fibers can be incorporated into the blank preform as a non-woven web composed of polymeric fibers randomly arranged to be inserted between the fibrous layers of the preform.
    [00030] As in the example, the binding material can be an epoxy resin in powder form. As another example, the binder material can be a mixture of one or more thermoplastic and thermoset polymers and one or more resins in a powder form. As another example, the binding material is a non-woven web composed of thermoplastic fibers.
    [00031] If applied in spray form, the binding material can be conveniently dissolved in a solvent such as dichloromethane. When solvent is used, further removal of solvent is required. In film form, a resin binder composition can be deposited (eg, carcass) onto a release paper to form a film, which is then transferred to the fibrous layer of the preform. In powder form, the binder can be spread over the fibrous layer. When the non-woven web of polymeric fibers is used as the binder material, each web is inserted between adjacent fibrous layers during preform placement.
    [00032] Preferably, the amount of binder in the fibrous preform is equal to or less than about 20% by weight, based on the total weight of the preform, preferably 0.5%-10%, by weight, more preferably 0.5%-6% by weight.
    [00033] In a preferred embodiment, the binder is a resin composition that is free of any catalyst, curing or crosslinking agent that can be activated at the preform manufacturing temperature (for example, the temperatures during the tray and modeling), and is still inherently thermally stable at the preform manufacturing temperature.
    [00034] The thermoplastic material suitable as a binder material includes one or more thermoplastic polymers, selected from polyester, polyamide, polyimide, polycarbonate, polyurethane, poly(methyl methacrylate), polystyrene, polyaromatics, polyesteramide, polyamideimide, polyetherimide, polyaramid, polyarylate, polyacrylate, poly(ester) carbonate, poly(butyl acrylate/methyl methacrylate), polysulfone, copolymers and combinations thereof.
    [00035] In one embodiment, the thermoplastic material is a polyarylsulfone polymer having arylsulfone units, represented by:

    [00036] Preferably, the polyarylsufone polymer has an average molecular weight (Mn) in the range of 2000-20,000. The polyarylsulfone polymer can also have reactive end groups such as amine or hydroxyl reactive to epoxide groups or a curing agent. Suitable polyarylsulfones include polyethersulfone (PES), polyetherethersulfone (PEES) and a copolymer thereof (PES-PEES). A particularly suitable polyarylsulfone polymer is a copolymer of PES-PEES with terminal amine groups.
    [00037] The thermoset material suitable as a binding material can be selected from the group consisting of epoxy resin, bismaleimide resin, condensed formaldehyde resin (including phenol-formaldehyde resin), cyanate resin, isocyanate resin, phenolic resin and their mixtures . The epoxy resin can be mono- or poly-glycidyl derived from one or more compounds selected from the group consisting of aromatic diamines, mono-primary aromatic amines, aminophenols, polyfunctional phenols, polyhydric alcohols, and polycarboxylic acids. Particularly suitable are multifunctional epoxy resins, including bifunctional, trifunctional and tetrafunctional epoxies.
    [00038] According to an embodiment, the binder is a resin composition containing one or more multifunctional epoxy resins and a polyarylsulfone polymer with reactive end group(s) and has a softening point of approximately 80°C- 90°C.
    [00039] It has been found that certain combinations of thermoplastic polymer and thermosetting resin(s) operate with a synergistic effect with regard to flow control and mixing flexibility. The thermoplastic component serves to provide flow control for the mixture, dominating typically low viscosity thermoset resins and ensuring that the binder preferentially wets the surface of the fibers in the preform. The thermoplastic component also provides flexibility for mixing, dominating normally fragile thermosetting resins.
    [00040] The binder in the preform is suitable for use with a wide variety of matrix resins to be injected into the preform by liquid resin infusion techniques such as RTM. Additionally, the binder is selected to be chemically and physically compatible with the matrix resin to be injected into the preform.
    [00041] When the dry preform is used in a resin injection process such as RTM, it is desirable that the binder does not form an impermeable film on the surface of the fibrous layers, which can prevent the matrix resin from satisfactorily penetrating the material thickness of the preform during the resin injection cycle.
    [00042] The following example is provided to illustrate a method of modeling a preform according to a modality of vacuum forming the process described here. This example is for illustrative purposes only and should not be construed as limiting the scope of the appended claims. EXAMPLE
    [00043] The flat blank preform (600 x 200 mm) was formed by imposing 33 layers of carbon fiber fabrics. Prior to accumulation, a powder dispersion method was used to deposit 5 gsm of a resin binder in powder form onto each side of the fabric layer. The layers of fabric with the powder spread on it were immobilized and pressed together using heat and pressure, where the dry stack of layers were compacted under atmospheric pressure, applying a vacuum and then heated to 130°C for 15 minutes before be cooled to temperature and the vacuum consolidation removed. This is called a pre-training step.
    [00044] This binder contains a blend of the multifunctional epoxy resins and a PES-PEES copolymer and has a softening point of about 90°C.
    [00045] The blank flat preform was consolidated according to the preforming process described above. The configuration includes a tool housing which contains a molding block, see FIG. 3, and two flexible sheets (top and bottom of diaphragms) made of silicone rubber. This configuration was used to form a molded preform with an L-shaped cross section and is illustrated in FIG. 4. Such a preform configuration is suitable for making a spar section on the wing of an airplane.
    [00046] Initially, the diaphragms with the flat preform sandwiched between them were placed in the tool housing. The diaphragm frame was attached to the perimeter of the tool housing, thus creating a tight vacuum seal interconnecting the low diaphragm and tool housing and a sealed pocket between the upper and lower diaphragms.
    [00047] Next, air was removed between the upper and lower diaphragms by applying a vacuum source, until the vacuum pressure reached 500 mbar. At this point, the flat preform was firmly supported by both diaphragms.
    [00048] The tool setup was then placed in an oven and heated to 140°C at a rate of 5°C/min. During heating, the tool housing was opened to atmospheric pressure to ensure no expansion of air inside the chamber.
    [00049] Once the temperature of the preform had reached 140°C, the tool housing was evacuated. Air was removed at the rate of 100 mbar/min until the vacuum pressure in the tool housing was below 10 mbar. On this occasion, the diaphragms together with the preform were pulled to the mold surface and eventually conformed to them. Heating was maintained throughout this time.
    [00050] On top of the total vacuum in the tool housing (below 10 mbar), the pressure between the diaphragms has been reduced to the stable, the vacuum pressure below 10 mbar. At that point, the heating was off, and the preform was allowed to cool. Vacuum in tool housing was kept below 10 mbar during cool down.
    [00051] When the preform was cooled to 40°C, the vacuum between the diaphragms was relieved by venting to atmosphere and the upper membrane was raised. The molded preform was subsequently removed from the setup installation. After the molded preform was removed, air was re-introduced into the tool housing.
    [00052] The resulting preform is shown in FIG. 5. It has an L-shaped bend section with a radius of curvature of 8.5 m along its length.
    [00053] The cycle time for the modeling process of the pre-consolidated flat preform was 15 minutes - from the start of heating the blank flat preform to the establishment of the final shape.
    权利要求:
    Claims (14)
    [0001]
    1. A method of molding a fibrous preform, characterized in that it comprises: (a) providing a substantially flat fibrous preform, said fibrous preform comprising an array of fibrous materials bonded together by a binder. resin; (b) providing an upper flexible diaphragm and a lower flexible diaphragm, said diaphragms being formed of an elastomeric material and impermeable to gas; (c) providing a housing with a mold positioned thereon, said mold having a non-planar molding surface; (d) hold the fibrous preform between the upper and lower diaphragms tightly, creating a sealed pocket between the diaphragms; (e) positioning the diaphragms with the preform between them over the housing so as to define a sealed chamber interconnecting the lower diaphragm and the housing and such that the lower diaphragm is positioned above the mold surface; (f) removing the air between the diaphragms to establish a vacuum pressure of less than 954 03 Pa (950 mbar) and less than the pressure in the housing; (g) heating the fibrous preform to a temperature above the softening point of the resin binder; (h) create a vacuum within the sealed chamber between the lower diaphragm and the housing, removing air at a rate of 100 Pa/15 minutes (1 mbar/15 minutes) or faster, up to a vacuum pressure of 954 03 Pa (950 mbar) or below is reached, while heating is maintained, whereby the diaphragms with the preform between them are pulled towards the molding surface and eventually conform to it, thus forming a preform. -molded shape; (i) reduce the vacuum pressure between the diaphragms to 1000 Pa (10 mbar) or below; (j) cooling molded preform to a temperature below the softening temperature of the resin binder; (k) relieve the vacuum between the diaphragms; (l) withdraw the upper diaphragm from the cooled preform, maintaining the vacuum inside the sealed chamber between the lower diaphragm and the housing; and (m) removing the cooled and molded preform from the lower diaphragm.
    [0002]
    2. Method according to claim 1, characterized in that the heating step (g) is carried out until the resin binder viscosity is in the range of less than 1.0 x 108 m^Pa.
    [0003]
    3. Method according to claim 1 or 2, characterized in that the total amount of resin binder in the fibrous preform is 0.5% to 10% by weight based on the total weight of the preform. fibrous form.
    [0004]
    4. Method according to any one of claims 1 to 3, characterized in that it further comprises the machining of the substantially flat fibrous preform according to an earlier pattern of step (d).
    [0005]
    5. A method according to any one of claims 1 to 4, characterized in that said fibrous preform comprises a plurality of fibrous layers laid out in a stacking arrangement, and the resin binder is applied to at least one surface of each fibrous layer.
    [0006]
    6. Method according to claim 5, characterized in that said fibrous layers are layers of fabric, tapes or belts.
    [0007]
    7. Method according to any one of claims 1 to 6, characterized in that the resin binder comprises a thermoplastic component or a thermoset component or both.
    [0008]
    8. Method according to claim 7, characterized in that the resin binder comprises a thermoplastic component, and a thermoset component and thermoplastic component comprises a polyarylsulfone polymer and the thermoset component comprises one or more epoxy resins.
    [0009]
    9. Method according to claim 8, characterized in that the polyarylsulfone polymer is a copolymer of polyethersulfone (PES) and polyetherethersulfone (PEES) with amine end groups.
    [0010]
    10. Method according to any one of claims 1 to 7, characterized in that the resin binder comprises a thermoplastic polymer, selected from: polyester, polyamide, polyimide, polycarbonate, polyurethane, poly (methyl methacrylate), polystyrene, polyaromatics, polyesteramide, polyamideimide, polyetherimide, polyaramid, polyarylate, polyacrylate, polyester carbonate, poly(butyl acrylate/methyl methacrylate), polysulfone, copolymers and combinations thereof.
    [0011]
    11. Method according to any one of claims 1 to 10, characterized in that the resin binder is in the form of a powder, liquid, paste or film.
    [0012]
    12. Method according to any one of claims 1 to 9, characterized in that the resin binder is in the form of polymeric fibers, which are a mixture of thermoplastic fibers and thermoset fibers or fibers formed from a mixture of thermoplastic and thermoset polymers.
    [0013]
    13. Method according to any one of claims 1 to 7, characterized in that the resin binder is in the form of a non-woven web comprised of randomly arranged polymeric fibers, which are formed from one or more polymers selected from the thermoplastic polymers, thermoset polymers and combinations thereof.
    [0014]
    14. Method according to any one of claims 1 to 13, characterized in that the fibrous materials comprise the fibers of a material selected from: aramid, high modulus polyethylene (PE), polyester, poly-p-phenylenebenzobisoxazole (PBO), carbon, glass, quartz, alumina, zirconia, silicon carbide and combinations thereof.
    类似技术:
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    同族专利:
    公开号 | 公开日
    RU2015129498A|2017-01-25|
    JP6161175B2|2017-07-12|
    KR20150096484A|2015-08-24|
    MX361646B|2018-12-13|
    JP2016503098A|2016-02-01|
    CN104812556A|2015-07-29|
    KR102085014B1|2020-03-05|
    BR112015012130A2|2017-07-11|
    MX2015007284A|2015-08-12|
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    US9259859B2|2016-02-16|
    EP2909014A1|2015-08-26|
    WO2014100328A1|2014-06-26|
    EP2909014B1|2016-09-07|
    AU2013361406B2|2017-05-04|
    GB201223032D0|2013-02-06|
    TW201433433A|2014-09-01|
    RU2635623C2|2017-11-14|
    AU2013361406A1|2015-04-16|
    CA2895813C|2020-04-07|
    CA2895813A1|2014-06-26|
    US20140175709A1|2014-06-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4065340A|1977-04-28|1977-12-27|The United States Of America As Represented By The National Aeronautics And Space Administration|Composite lamination method|
    SU1685738A1|1988-09-26|1991-10-23|Саратовское электроагрегатное производственное объединение|Drape-and-forming machine for fabricating thermoplastic articles|
    US5037599A|1989-06-26|1991-08-06|Basf Aktiengesellschaft|Single diaphragm forming of drapeable thermoplastic impregnated composite materials|
    GB8916909D0|1989-07-24|1989-09-06|Ici Plc|Method of forming thermoformable composite material|
    US5578158A|1994-03-01|1996-11-26|Massachusetts Institute Of Technology|Method and system for forming a composite product from a thermoformable material|
    US5817265A|1995-10-03|1998-10-06|Dow-United Technologies Composite Products, Inc.|Method for precision preforming of complex composite articles|
    GB9709166D0|1997-05-06|1997-06-25|Cytec Ind Inc|Preforms for moulding process and resins therefor|
    GB9907204D0|1999-03-30|1999-05-26|Woolstencroft David H|A composite|
    US20050008862A1|1999-12-02|2005-01-13|Joseph Brian E.|Carbon foam composite tooling and methods for using the same|
    GB2364266B|2000-07-04|2004-04-28|Kevin John Channer|Improvements in and relating to the moulding of composite materials|
    US7300894B2|2002-12-30|2007-11-27|University Of Maine|Composites pressure resin infusion system |
    EP1600271A1|2004-05-11|2005-11-30|Nestlé Waters Management & Technology|Process and apparatus for making preforms of polymeric material|
    US7306450B2|2004-09-29|2007-12-11|The Boeing Company|Apparatuses, systems, and methods for manufacturing composite parts|
    FR2880016B1|2004-12-23|2007-04-20|Messier Bugatti Sa|PROCESS FOR PRODUCING A FIBROUS PREFORM FOR THE MANUFACTURE OF CARBON / CARBON COMPOSITE MATERIAL PARTS INCORPORATING CERAMIC PARTICLES, AND PRODUCT PRODUCED THEREBY|
    US20060266472A1|2005-05-06|2006-11-30|Kipp Michael D|Vacuum bagging methods and systems|
    JP5017358B2|2006-03-28|2012-09-05|シーアールシーフォーアドバンストコンポジットストラクチャーズリミテッド|Welding of functional members to polymer composite members|
    US7862322B2|2006-04-25|2011-01-04|Florida State University Research Foundation|Resin infusion between double flexible tooling system|
    GB0702781D0|2007-02-13|2007-03-21|Airbus Uk Ltd|Method of processing a composite material|
    GB2452298B|2007-08-30|2010-01-13|Gkn Aerospace Services Ltd|Composite structure|
    JP5315713B2|2008-02-12|2013-10-16|東レ株式会社|Method for manufacturing preform for FRP member|
    JP2009286006A|2008-05-29|2009-12-10|Toyota Motor Corp|Vacuum molding device|
    US8652371B2|2008-11-20|2014-02-18|Cytec Technology Corp.|Constant pressure infusion process for resin transfer molding|
    FR2950833A1|2009-10-01|2011-04-08|Airbus Operations Sas|METHOD AND DEVICE FOR THE AUTOMATED MANUFACTURE OF CIRCULAR DRY PREFORMS|EP2676780B1|2012-06-18|2017-08-02|Technische Universität Dresden|Method for manufacture of a layered semi-finished product|
    DE102013019806B4|2013-11-27|2015-06-03|Daimler Ag|Method for forming a two-dimensional semi-finished fiber product|
    CN106470825A|2014-06-30|2017-03-01|塞特工业公司|For manufacturing the dry fibers band of preform|
    FR3027546B1|2014-10-24|2017-07-21|Porcher Ind|POWDERED MACHINES BY ELECTROSTATIC PROCESS|
    FR3027839B1|2014-10-31|2017-09-08|Plastic Omnium Cie|PLASTIC SHEET PREFORMING SYSTEM WITH SEQUENTIALLY ACTUATING PLATING MEANS|
    WO2016100365A1|2014-12-18|2016-06-23|Cytec Industries, Inc.|Modified resin systems suitable for liquid resin infusion|
    US11155046B2|2016-01-21|2021-10-26|Cytec Industries Inc.|Fabrication of complex-shaped composite structures|
    FR3047196B1|2016-02-02|2018-09-28|Coriolis Group|METHOD FOR MAKING THREE DIMENSIONAL PREFORMS BY FORMING INITIAL PREFORMS WITH SAILS|
    FR3055574B1|2016-09-02|2018-10-05|Porcher Ind|FIBROUS STRUCTURE AND 3D PREFORM FOR COMPOSITE PIECE|
    GB2554476A|2016-09-21|2018-04-04|Suzlon Energy Ltd|A method of forming a component|
    GB201620227D0|2016-11-29|2017-01-11|Cytec Ind Inc|Automated fabrication of fibrous preform|
    AU2018217915A1|2017-02-08|2019-08-29|Cytec Engineered Materials Ltd.|Double diaphragm shaping of composite materials, assemblies for such shaping, and resulting composite materials|
    CN109795137A|2017-11-16|2019-05-24|中国商用飞机有限责任公司|For fixing the method and device of reinforcing fibre in the molding of resin material workpiece|
    DE102017220899A1|2017-11-23|2019-05-23|Bayerische Motoren Werke Aktiengesellschaft|Method for producing a fiber composite component and fiber composite component|
    DE102018201902A1|2018-02-07|2019-08-08|Ford Global Technologies, Llc|Apparatus and method for mass production of at least partially fiber-reinforced injection-molded components|
    RU2688716C1|2018-05-24|2019-05-22|Общество с ограниченной ответственностью "Композит Сольюшен"|Method of making large-size composite articles by vacuum infusion and composite power beam of bridge section for collapsible bridge structure|
    EP3587091A1|2018-06-25|2020-01-01|The Boeing Company|Ply location templates for double diaphragm vacuum bagging system|
    US10875263B2|2018-06-25|2020-12-29|The Boeing Company|Ply location templates for double diaphragm vacuum bagging systems|
    US10875264B2|2018-06-25|2020-12-29|The Boeing Company|Ply location templates for double diaphragm vacuum bagging systems|
    CN109111089B|2018-07-30|2021-08-13|东莞市轩驰智能科技有限公司|Molding apparatus and molding method|
    NL2021422B1|2018-08-03|2020-02-12|Boeing Co|Ply location templates for double diaphragm vacuum bagging systems|
    FR3085131B1|2018-08-27|2020-11-13|Safran|PROCESS FOR SHAPING BY COMPACTING A FIBROUS PREFORM FOR THE MANUFACTURE OF A PART FROM COMPOSITE MATERIAL|
    EP3927527A1|2019-02-22|2021-12-29|Cytec Industries, Inc.|Fabrication of three-dimensional structures from preform blanks|
    FR3094265B1|2019-03-27|2022-01-28|Safran Aircraft Engines|TOOL FOR PREFORMING A FIBER PREFORM AND METHOD FOR PREFORMING A FIBER PREFORM|
    WO2020242777A1|2019-05-31|2020-12-03|Cytec Industries Inc.|Controlled shear vacuum forming for shaping preforms|
    FR3098749A1|2019-07-19|2021-01-22|Institut De Recherche Technologique Materiaux, Mettalurgie, Procedes|Manufacturing process of preforms for composite materials|
    CN110774613B|2019-09-17|2021-08-17|北京玻钢院复合材料有限公司|Bismaleimide resin matrix composite material, antenna housing and preparation method thereof|
    WO2021132752A1|2019-12-24|2021-07-01|코오롱데크컴퍼지트 주식회사|Preform molding apparatus for manufacturing composite material and preform molding method for manufacturing composite material|
    US11220072B2|2020-01-02|2022-01-11|The Boeing Company|Molding system and methods for forming structures|
    FR3108871A1|2020-04-07|2021-10-08|Airbus Operations|PROCESS FOR MANUFACTURING A PREFORM PACKAGED WITH A COMPONENT IN COMPOSITE MATERIAL AND PROCESS FOR MANUFACTURING THE SAID COMPONENT|
    法律状态:
    2018-03-06| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2018-03-13| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2018-03-20| B06I| Publication of requirement cancelled [chapter 6.9 patent gazette]|Free format text: ANULADA A PUBLICACAO CODIGO 6.6.1 NA RPI NO 2462 DE 13/03/2018 POR TER SIDO INDEVIDA. |
    2019-12-10| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-02-23| B06A| Notification to applicant to reply to the report for non-patentability or inadequacy of the application [chapter 6.1 patent gazette]|
    2021-06-22| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-07-13| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 19/12/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    GB1223032.2|2012-12-20|
    GBGB1223032.2A|GB201223032D0|2012-12-20|2012-12-20|Method for forming shaped preform|
    PCT/US2013/076378|WO2014100328A1|2012-12-20|2013-12-19|Method for forming shaped preform|
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