A method of cavity honeycomb screen repair

Abstract

The application discloses a cavity honeycomb wire screen repairing method and relates to the technical field of structure repairing. The repairing method comprises the following steps: removing a damaged part of the wire screen to expose a honeycomb area; performing cleaning treatment on the exposed honeycomb area; laying a glue film on the honeycomb area and bonding the glue film to the honeycomb area through heating; laying a replacement wire screen on the honeycomb area with the bonded glue film; arranging an edge lap joint structure on an edge area of the replacement wire screen; and applying pressure to the area with the laid replacement wire screen and edge lap joint structure and performing heating and solidification. The repairing method provided by the application can realize standardized repairing of a complex cavity honeycomb wire screen, has high repairing precision, good structural integrity, high connection strength and good durability, is strong in process controllability and stable in quality, is strong in universality, low in implementation cost, high in reassembling precision and strong in assembling reliability.

Description

Technical Field

[0001] This application relates to the field of structural repair technology, specifically to a method for repairing cavity honeycomb mesh. Background Technology

[0002] Complex honeycomb wall structures are widely used in critical components such as aero-engine air intakes and noise reduction structures. Composed of a honeycomb core, wire mesh, fiberglass reinforcement layers, metal gaskets, partitions, pins / boobs, etc., they are prone to damage under high temperature, vibration, and airflow erosion conditions, including wire mesh breakage, honeycomb crushing, adhesive detachment, and fastener loosening. This directly affects structural strength, aerodynamic performance, and service safety. Current repair methods for such structures primarily rely on manual gluing, partial patching, simple application, and edge sealing with sealant. These methods generally suffer from non-standard processes, loose adhesion, uneven curing, insufficient edge strength, and poor reassembly accuracy, failing to meet aerospace airworthiness and long service life requirements. While the industry possesses technologies such as honeycomb repair, composite material application, and vacuum curing, these are mostly designed for flat or simple curved surfaces. A complete repair process is lacking, adaptable to complex cavities, integrating wire mesh-honeycomb-edge overlap, and featuring refined pretreatment and precise reassembly. This results in delamination, detachment, and insufficient strength after repair, hindering repair quality and efficiency.

[0003] At present, the repair of complex wall honeycomb structures is mainly concentrated in the field of aviation honeycomb sandwich structure and air intake repair. Typical technologies and defects are as follows: (1) Conventional honeycomb wire mesh manual repair (industry common practice): simply remove the old wire mesh, apply glue and lay the new mesh, without special filling of honeycomb cavity, preheating and shrinkage of adhesive film distribution, edge glass fiber overlap reinforcement and other processes. The adhesive layer is uneven in thickness and has weak bonding force with the honeycomb. Hollows and detachment occur at complex surfaces. After repair, air tightness and structural strength are difficult to guarantee. (2) Patent CN114379121A discloses the honeycomb repair of engine thrust reverse sliding door: using adhesive bonding and vacuum-assisted curing, it is a planar or near-planar repair method, but it does not design for the repair of complex surface metal wire mesh, honeycomb cell adhesive film shrinkage, and precise reassembly of pins / boobs / pads. The filling of deep cavity defects is insufficient, and there is no edge overlap reinforcement, which easily leads to stress concentration and early failure. (3) Patent CN116476418A discloses a rapid repair method for the intake duct muffler panel: focusing on damage cutting and panel replacement is also a planar or near-planar repair method. It does not involve the replacement of metal mesh, fine processing of honeycomb edges, use of multiple types of adhesives in different areas, vacuum pressure and high temperature curing parameter control. It cannot achieve reliable integrated bonding of mesh-honeycomb-glass fiber, and the reassembly size accuracy is difficult to control.

[0004] As can be seen from the above, existing technologies all systematically address key issues in the repair of complex cavity honeycomb structures, such as: refined surface pretreatment, precise bonding of adhesive film and honeycomb, reliable adhesion of metal mesh, edge overlap reinforcement, uniform pressure curing, and precise fastener reassembly. However, these technologies suffer from poor repair consistency, low pass rate, and short lifespan. Therefore, a complex cavity repair process is urgently needed to overcome these shortcomings. Summary of the Invention

[0005] In view of this, this application provides a method for repairing the honeycomb mesh of an aero-engine cavity. This method can solve the problems of weak edge strength, easy stress cracking, and misalignment during repair and reassembly of traditional processes.

[0006] To address the aforementioned technical problems, this application provides the following technical solution: A method for repairing a cavity with a honeycomb mesh, wherein the cavity has a honeycomb region and the honeycomb region is covered with a mesh, the repair method comprising: (1) Remove the damaged portions of the wire mesh to expose the honeycomb area; (2) Clean the exposed honeycomb area; (3) Lay an adhesive film on the honeycomb area and heat it to bond the adhesive film to the honeycomb area; (4) Lay a replacement wire mesh on the honeycomb area where the adhesive film is bonded; (5) An edge overlap structure is provided in the edge area of ​​the replacement wire mesh; (6) Apply pressure to the area where the replacement wire mesh and the edge overlap structure are laid, and heat to cure.

[0007] Preferably, step (3) of bonding the adhesive film to the honeycomb region includes: The honeycomb region on which the adhesive film is laid is heated to a first temperature range, so that the adhesive film is initially adhered to the honeycomb region; Perforations are made on the adhesive film corresponding to the honeycomb grid. The temperature is then reheated to the first temperature range, causing the adhesive film to sink into and adhere to the inner wall of the honeycomb pores.

[0008] Preferably, the first temperature range is 110℃~130℃.

[0009] Preferably, the edge overlap structure in step (5) includes a support film layer and a fiber prepreg layer. The support film layer is disposed on the replacement mesh, and the fiber prepreg layer is disposed on the support film layer. Adjacent fiber prepreg layers are butted together with a butt joint gap of 0 to 0.03 inches.

[0010] Preferably, the fiber prepreg layer is a glass fiber prepreg layer.

[0011] Preferably, the heating and curing temperature in step (6) is 170℃~182℃ and the curing time is 110min~130min.

[0012] Preferably, the pressure applied in step (6) includes: applying mechanical pressure under the clamping of a clamp coated with a separating agent; or, covering the area where the replacement mesh and the edge overlapping structure are laid with a vacuum bag and evacuating the vacuum bag to a predetermined vacuum level.

[0013] Preferably, the separating agent is an epoxy separating agent, the clamping plate is an aluminum clamping plate, and the predetermined vacuum degree is at least 22 inches of mercury.

[0014] Preferably, step (3) further includes: filling the cavities between the honeycombs in the honeycomb region and the mounting area for mounting fasteners with a filler.

[0015] Preferably, the cavity includes an upper cavity and a lower cavity, and the steps of removing, cleaning, laying adhesive film, laying replacement mesh, setting edge overlapping structure, applying pressure and heating curing are performed on the upper cavity and the lower cavity respectively.

[0016] Compared with the prior art, the beneficial effects of this application are: (1) High repair precision and good structural integrity: This invention effectively avoids secondary damage such as honeycomb crushing and deformation by finely removing damaged wire mesh, lightly repairing honeycomb edges with diamond sandpaper, and filling honeycomb cavities and installation areas in sections, thus ensuring the integrity of the substrate structure. Combined with the adhesive film distribution preheating and shrinkage process, the adhesive film is completely attached to the inner wall of the honeycomb cell, eliminating voids and gaps, which can improve the adhesive density and interface bonding strength, and solve the problems of poor adhesion and easy detachment in traditional repair.

[0017] (2) High connection strength and good durability: The composite reinforcement structure of metal wire mesh, supporting film and glass fiber prepreg overlap tape is adopted. Through precise size control and joint tolerance guarantee, a multi-layer reliable bond is formed. Combined with vacuum pressure or aluminum plate uniform pressure and high temperature curing system, the repair layer and the substrate form an integral whole. The interface strength is high, the delamination resistance is strong, and the debonding resistance is strong. It makes up for the shortcomings of traditional process with weak edge strength and easy stress cracking, and greatly improves the service life after repair.

[0018] (3) Strong process controllability and stable quality: This application clearly defines key parameters such as heating temperature, curing time, vacuum degree and drilling size, and adopts standardized operating procedures to replace manual operation that relies on experience; through the dual process selection of hot air gun / heating furnace, two-cloth cleaning method and separation agent protection, etc., the consistency of each process is guaranteed, human error is reduced, and high-quality, high-pass-rate repair is achieved to meet the airworthiness and reliability requirements of aviation equipment.

[0019] (4) High versatility and low implementation cost: The process does not require large special equipment and can be completed with conventional tools, vacuum bags and heating furnaces, making it highly operable on site; at the same time, the use of partitioned glue and precise reassembly reduces material waste and rework costs, and reduces maintenance costs while ensuring strength; it can be adapted to the repair of multiple components such as upper and lower cavities, partitions, pins, bosses, and metal gaskets, and has good versatility and economy.

[0020] (5) High reassembly accuracy and strong assembly reliability: This invention strictly specifies the drilling size tolerance of pins, bosses and inserts, and reassembles partitions and accessories according to the standard specifications to ensure accurate installation position and reasonable fit clearance; special structural adhesive is used to bond metal gaskets and standard curing is used to ensure that the fasteners are firmly connected and do not loosen, solving the defects of misalignment, loosening and poor fit in traditional repair and reassembly, and restoring the original assembly performance of the parts. Attached Figure Description

[0021] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 A schematic diagram of the cavity honeycomb mesh provided in an embodiment of this application is shown; Figure 2 This is a top view of the upper cavity provided in an embodiment of the present application, between the damaged wire meshes. Figure 3 A schematic diagram of the cross-sectional structure of the cavity honeycomb mesh provided in an embodiment of this application is shown; Figure 4 This illustration shows a schematic diagram of the honeycomb region structure after removing damage from the wire mesh, as provided in an embodiment of this application. Figure 5 This illustration shows a schematic diagram of the structure of the honeycomb area after the adhesive film is laid, as provided in an embodiment of this application. Figure 6 This illustration shows a cross-sectional diagram of the upper and lower cavities after the replacement wire mesh has been laid, as provided in an embodiment of this application. Figure 7 A cross-sectional schematic diagram of the overlapping structure of the upper and lower cavities provided in the embodiment of this application is shown.

[0022] Figure label: 100-Cavity, 101-Upper cavity, 102-Lower cavity, 103-Honeycomb area, 104-Wire mesh, 105-Replacement wire mesh, 106-Mounting edge, 107-Supporting adhesive film layer, 108-Fiber prepreg layer, 109-Edge overlap structure, 110-Honeycomb pores, 111-Mating gap. Detailed Implementation

[0023] The following detailed embodiments are provided to help the reader gain a full understanding of the methods, apparatus, and / or systems described herein. However, various changes, modifications, and equivalents of the methods, apparatus, and / or systems described herein will be apparent after understanding the disclosure of this application. For example, the order of operations described herein is merely illustrative and is not limited to the order set forth herein; rather, changes that will be apparent after understanding the disclosure of this application may be made, except for operations that must occur in a specific order. Furthermore, for clarity and brevity, descriptions of features known in the art may be omitted.

[0024] The features described herein may be implemented in different forms and should not be construed as being limited to the examples described herein. Rather, the examples described herein have been provided merely to illustrate some of the many feasible ways of implementing the methods, apparatus, and / or systems described herein that will be apparent upon understanding the disclosure of this application.

[0025] Throughout the specification, when an element (such as a layer, region, or substrate) is described as being "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, it may be directly "on" another element, "connected to" another element, "bonded to" another element, "on" another element, or "covering" another element, or there may be one or more other elements in between. In contrast, when an element is described as being "directly on" another element, "directly connected to" another element, "directly bonded to" another element, "directly on" another element, or "directly covering" another element, there may be no other elements in between.

[0026] As used herein, the term “and / or” includes any one of the relevant items listed and any combination of any two or more items.

[0027] Although terms such as “first,” “second,” and “third” may be used herein to describe individual components, assemblies, regions, layers, or parts, these components, assemblies, regions, layers, or parts are not limited by these terms. Rather, these terms are used only to distinguish one component, assembly, region, layer, or part from another. Therefore, without departing from the teachings of the examples described herein, the first component, assembly, region, layer, or part referred to as the second component, assembly, region, layer, or part may also be referred to as the second component, assembly, region, layer, or part.

[0028] For ease of description, spatial relation terms such as “above,” “upper,” “below,” and “lower” are used herein to describe the relationship between one element and another, as shown in the accompanying drawings. Such spatial relation terms are intended to include not only the orientation depicted in the drawings but also different orientations of the device during use or operation. For example, if the device in the drawings is flipped, an element described as being “above” or “upper” relative to another element will subsequently be “below” or “lower” relative to that other element. Therefore, the term “above” includes both “above” and “below” orientations depending on the spatial orientation of the device. The device may also be positioned in other ways (e.g., rotated 90 degrees or in other orientations), and the spatial relation terms used herein will be interpreted accordingly.

[0029] The terminology used herein is for the purpose of describing various examples only and is not intended to limit this disclosure. Unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. The terms “comprising,” “including,” and “having” enumerate the stated features, quantities, operations, components, elements, and / or combinations thereof, but do not exclude the presence or addition of one or more other features, quantities, operations, components, elements, and / or combinations thereof.

[0030] Variations in the shapes shown in the accompanying drawings may occur due to manufacturing techniques and / or tolerances. Therefore, the examples described herein are not limited to the specific shapes shown in the accompanying drawings, but include changes in shape that may occur during manufacturing.

[0031] The features of the examples described herein can be combined in various ways that will be apparent upon understanding the disclosure of this application. Furthermore, although the examples described herein have a wide variety of constructions, other constructions are possible, as will be apparent upon understanding the disclosure of this application.

[0032] See Figure 1As shown, the cavity 100 includes an upper cavity 101 and a lower cavity 102. Both the upper cavity 101 and the lower cavity 102 have honeycomb regions 103, and the honeycomb regions 103 are covered with wire mesh 104. The cavity 100 is also provided with mounting edges 105 for connecting with adjacent components.

[0033] The honeycomb region 103 refers to the honeycomb sandwich structure region set inside the cavity 100. The honeycomb region 103 contains a honeycomb core material, which is composed of multiple honeycomb cells 110 arranged in a grid. The honeycomb core material can be a metal honeycomb core material (such as aluminum honeycomb core material or stainless steel honeycomb core material) or a non-metallic honeycomb core material (such as aramid paper honeycomb core material or glass cloth honeycomb core material), featuring lightweight and high strength. The outer surface of the honeycomb region 103 is covered with a wire mesh 104, and mounting edges 106 can be provided at the edges of the honeycomb region 103.

[0034] Wire mesh 104 refers to the metal mesh structure covering the outer surface of the honeycomb area 103, used to protect the honeycomb core material and provide surface support. Wire mesh 104 can be made of metal materials such as stainless steel wire mesh, nickel-based alloy wire mesh, and titanium alloy wire mesh. The mesh size and wire diameter of wire mesh 104 can be selected according to the usage requirements of the cavity 100.

[0035] Cellular cells 110 refer to hexagonal (or other shaped) cavity units formed by honeycomb walls in a honeycomb core material. The dimensions of cellular cells 110 can be determined according to the specifications of the honeycomb core material; common cellular cell sizes include 3.2mm, 4.8mm, and 6.4mm. During the repair process of cellular cells 110, it is necessary to ensure that the adhesive film can fully adhere to its inner wall.

[0036] The repair method provided in this application achieves high-precision and high-reliability repair of damaged honeycomb mesh in complex cavities through steps such as removing the damaged mesh 104, cleaning the honeycomb area 103, laying and preheating the adhesive film, laying the replacement mesh 105, setting the edge overlapping structure 109, and pressurizing and heating for curing. The specific embodiments of this application are described in detail below with reference to the accompanying drawings.

[0037] This application provides a method for repairing a cavity with a honeycomb mesh. The cavity 100 has a honeycomb region 103, and the honeycomb region 103 is covered with a mesh. The repair method includes: (1) Remove the damaged portion of the damaged wire mesh 104 to expose the honeycomb area 103; (2) Clean the exposed honeycomb area 103; (3) Lay an adhesive film on the honeycomb area 103 and heat it to bond the adhesive film to the honeycomb area 103; (4) Lay a replacement wire mesh 105 on the honeycomb area 103 where the adhesive film is bonded; (5) An edge overlap structure 109 is provided in the edge area of ​​the replacement wire mesh 105; (6) Apply pressure to the area where the replacement wire mesh 105 and edge overlap structure 109 are laid, and heat to cure.

[0038] See Figure 2 and Figure 3 The diagram shows the upper cavity 101 and lower cavity 102 before the damaged wire mesh is removed. The damaged portion of the wire mesh 104 is removed using a suitable tool to expose the honeycomb area 103. Damage to the honeycomb core material should be avoided during removal. The cavity 100 is divided into an upper cavity 101 and a lower cavity 102 along its central plane of symmetry. Both the upper cavity 101 and lower cavity 102 have complex curved shapes, and can be repaired independently. The upper cavity 101 and lower cavity 102 are connected by a mounting edge 106.

[0039] The exposed honeycomb area 103 is cleaned. Specifically, a stainless steel wire brush can be used to clean the honeycomb area 103 to remove solid particles such as sanding debris, dust, and soot. Further, isopropyl alcohol and a lint-free cloth can be used to wipe the outer surface of the honeycomb area 103 to remove lubricant and grease. Additionally, the exposed edges of the honeycomb area 103 are lightly cleaned with emery paper and wiped again with isopropyl alcohol and a lint-free cloth, allowing it to air dry.

[0040] See Figure 4 and Figure 5 As shown, an adhesive film is laid on the honeycomb area 103, and the film is bonded to the honeycomb area 103 by heating. The adhesive film can be preheated and bonded using a hot air gun on a low setting or an air heater. The adhesive film refers to a thin film adhesive used to bond the replacement wire mesh 105 to the surface of the honeycomb area 103. The adhesive film can be a thermosetting adhesive film, such as epoxy film, phenolphthalein film, bismaleimide film, etc. The adhesive film has a uniform thickness to ensure uniform adhesion to the honeycomb area 103. The thickness of the adhesive film can be selected according to the repair requirements, typically 0.1mm to 0.5mm.

[0041] A replacement wire mesh 105 is laid on the honeycomb area 103 where the adhesive film is bonded. The size of the replacement wire mesh 105 should be the same as the damaged portion of the removed wire mesh 104, and its outline should match the outline of the honeycomb area 103. The replacement wire mesh 105 refers to a new wire mesh used to replace the damaged wire mesh 104. The material, mesh size, and wire diameter of the replacement wire mesh 105 can be the same as the damaged wire mesh 104, or it can be selected according to the repair requirements. The replacement wire mesh 105 can be made of stainless steel wire mesh, nickel-plated steel wire mesh, titanium alloy wire mesh, etc. The laying of the replacement wire mesh 105 should ensure that it is in full contact with the surface of the honeycomb area 103 to ensure the bonding strength after the adhesive film cures.

[0042] See Figure 6 and Figure 7 As shown, an edge overlap structure 109 is provided in the edge area of ​​the replacement wire mesh 105. The edge overlap structure 109 includes a supporting adhesive film layer 107 and a fiber prepreg layer 108. The edge overlap structure 109 is a reinforcing structure provided in the edge area of ​​the replacement wire mesh 105 to improve the connection strength between the replacement wire mesh 105 and the surrounding substrate structure. The edge overlap structure 109 achieves reliable multi-layer bonding through a laminated structure design. The width of the edge overlap structure 109 can be determined according to the size of the repair area, typically 25mm to 50mm. The supporting adhesive film layer 107 is an adhesive film layer provided between the replacement wire mesh 105 and the fiber prepreg layer 108. The main function of the supporting adhesive film layer 107 is to bond the fiber prepreg layer 108 to the edge area of ​​the replacement wire mesh 105, while also providing a certain structural support. The supporting adhesive film layer 107 can be made of the same material as the adhesive film, or it can be made of an adhesive film material with different properties. The fiber prepreg layer 108 refers to a fiber-reinforced material layer pre-impregnated with resin. The fiber prepreg layer 108 can be made of glass fiber, carbon fiber, or aramid fiber, etc. The fiber prepreg layer 108 possesses good strength and durability, effectively enhancing the connection strength in edge areas. The fiber prepreg layer 108 can be made of different forms, such as unidirectional prepreg or woven prepreg.

[0043] Pressure is applied to the area where the replacement wire mesh 105 and edge overlap structure 109 are laid, and then cured by heat. The pressure can be applied mechanically by clamping the area with a release agent-coated clamp, or by using vacuum bag technology to evacuate to a predetermined vacuum level. The release agent is a coating material applied to the clamp surface to prevent the adhesive film and fiber prepreg layer 108 from adhering to the clamp surface. The release agent can be an epoxy release agent, liquid release agent, film release agent, etc. Epoxy release agents effectively prevent adhesives from adhering to the aluminum clamp surface, ensuring easy demolding of the cured parts. Vacuum bag technology involves covering the area with the replacement wire mesh 105 and edge overlap structure 109 with a vacuum bag and evacuating to a predetermined vacuum level from inside the vacuum bag, thereby generating uniform external pressure to fully cure the adhesive film and fiber prepreg layer 108. Vacuum bag technology can provide uniform pressure distribution and is suitable for curing complex curved surfaces.

[0044] According to an exemplary embodiment, step (3) of bonding the adhesive film to the honeycomb region 103 includes: The honeycomb area 103 covered with adhesive film is heated to the first temperature range so that the adhesive film initially adheres to the honeycomb area 103; Make perforations on the adhesive film at positions corresponding to honeycomb 110; Reheat to the first temperature range to cause the adhesive film to sink into and adhere to the inner wall of the honeycomb pores 110.

[0045] Specifically, the honeycomb area 103 covered with the adhesive film is heated to a first temperature range, so that the adhesive film initially adheres to the honeycomb area 103. An air heater can be used for heating. After preheating the air heater to the first temperature range, the upper half cavity 101 and / or the lower half cavity 102 are placed in the air heater for 1 min to 2 min, allowing the adhesive film to gently adhere to the honeycomb cells 110.

[0046] Make perforations in the adhesive film corresponding to the honeycomb cells 110. A razor, scraper, or suitable tool can be used to penetrate the adhesive film of each honeycomb cell 110, ensuring that the adhesive film is completely retracted and adhered to the inner wall of the honeycomb cell 110.

[0047] Reheat to the first temperature range to allow the adhesive film to sink into and adhere to the inner wall of the honeycomb cell 110. Then, use a hot air gun on a low setting or an air heater to retract the adhesive film and adhere it to the honeycomb.

[0048] According to an exemplary embodiment, the first temperature range is 110°C to 130°C.

[0049] Specifically, the first temperature range is 110℃~130℃. This temperature range allows the adhesive film to reach a preliminary adhesion state without over-curing, which facilitates subsequent perforation and precise positioning operations.

[0050] According to an exemplary embodiment, in step (5), the edge overlap structure 109 includes a support film layer 107 and a fiber prepreg layer 108. The support film layer 107 is disposed on the replacement wire mesh 105, and the fiber prepreg layer 108 is disposed on the support film layer 107. Adjacent fiber prepreg layers 108 are butted together, and the butt joint gap 111 is 0 to 0.03 inches.

[0051] Specifically, the edge overlap structure 109 includes a supporting adhesive film layer 107 and a fiber prepreg layer 108. The supporting adhesive film layer 107 is disposed on the replacement wire mesh 105, and the fiber prepreg layer 108 is disposed on the supporting adhesive film layer 107. Adjacent fiber prepreg layers 108 are butted together, and the butt joint gap 111 can be 0 to 0.03 inches. This butt joint gap 111 ensures the continuity and strength of the edge overlap structure 109, while avoiding stress concentration caused by overlapping or excessive gaps between the fiber prepreg layers 108.

[0052] According to an exemplary embodiment, the fiber prepreg layer 108 is a glass fiber prepreg layer. The glass fiber prepreg layer has good strength and durability, and can effectively enhance the connection strength in the edge region. The glass fiber prepreg layer can be made of different types of glass fibers such as E-glass fiber and S-glass fiber.

[0053] According to an exemplary embodiment, the heating and curing temperature in step (6) is 170°C to 182°C, and the curing time is 110 min to 130 min.

[0054] Specifically, the curing temperature can be 170℃, 175℃, or 182℃, and the curing time can be 110min, 120min, or 130min. The selection of these parameters can be adjusted according to the specific adhesive type and cavity structure. The curing time is preferably 120min, as this curing parameter allows the adhesive film and fiber prepreg layer 108 to fully cure, forming a high-strength bond.

[0055] According to an exemplary embodiment, applying pressure in step (6) includes: applying mechanical pressure under the clamping of a clamp coated with a separating agent; or, covering the area where the replacement wire mesh 105 and the edge overlap structure 109 are laid with a vacuum bag and evacuating the vacuum bag to a predetermined vacuum level.

[0056] Specifically, step (6) provides two methods for applying pressure. The first method is to apply mechanical pressure under the clamping of a clamp coated with a separating agent. The second method is to use vacuum bag technology to cover the area where the replacement wire mesh 105 and the edge overlap structure 109 are laid with a vacuum, and to evacuate the vacuum bag to a predetermined vacuum level.

[0057] According to an exemplary embodiment, the separating agent is an epoxy separating agent, and the clamping plate is an aluminum clamping plate; the predetermined vacuum degree is at least 22 inches of mercury.

[0058] Specifically, the release agent is an epoxy release agent, and the clamping plate is an aluminum clamping plate; the predetermined vacuum level is at least 22 inches of mercury. The epoxy release agent can effectively prevent adhesive from adhering to the surface of the aluminum clamping plate, ensuring that the cured parts are easy to demold.

[0059] According to an exemplary embodiment, step (3) further includes filling the cavities between the cells in the cellular region 103 and the mounting area for mounting fasteners with a filler.

[0060] Specifically, filler type A can be used to fill the cavities between honeycomb cells, and filler type B can be used to fill the areas where pins and / or bosses and inserts are installed. The use of filler effectively enhances the structural strength of the honeycomb area 103 and provides a stable substrate for subsequent fastener installation. The filling operation should be completed before laying the adhesive film to ensure sufficient bonding between the filler and the honeycomb core material. Filler refers to the material used to fill the cavities between honeycomb cells in the honeycomb area 103. Fillers can include epoxy resin fillers, lightweight fillers, microsphere fillers, etc., and their main function is to enhance the structural strength of the honeycomb area 103 and provide stable substrate support for fastener installation. The density and strength of the filler can be selected according to the application requirements.

[0061] According to an exemplary embodiment, the cavity 100 includes an upper cavity 101 and a lower cavity 102, and the steps of removing, cleaning, laying adhesive film, laying replacement mesh, setting edge overlap structure, applying pressure and heating curing are respectively performed on the upper cavity 101 and the lower cavity 102.

[0062] Specifically, cavity 100 includes an upper cavity 101 and a lower cavity 102. The upper cavity 101 and lower cavity 102 can be repaired independently or simultaneously to improve efficiency. The steps of removal, cleaning, applying adhesive film, applying replacement mesh, setting edge overlap structures, applying pressure, and heat curing are performed on the upper cavity 101 and lower cavity 102 respectively. This separate repair method ensures the repair quality of each cavity half and avoids the problem of incomplete repair in some areas due to the complex cavity structure.

[0063] After repair, a varnish can be applied to the edge overlap structure 109 and the original fiberglass area and cured according to the manufacturer's instructions. The application of the varnish can be tailored to the durability and aesthetics of the repaired area, while also providing some corrosion protection. Varnish refers to a transparent protective coating applied to the surface of the repaired area. Varnishes can be epoxy varnish, polyurethane varnish, acrylic varnish, etc. The application of the varnish protects the edge overlap structure 109 and the fiber prepreg layer 108 from environmental erosion while providing a smooth surface appearance. The varnish should be cured according to the manufacturer's instructions to ensure its protective performance.

[0064] The above description is only a partial embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A method for repairing a cavity with a honeycomb mesh, wherein the cavity has a honeycomb region, and the honeycomb region is covered with a mesh, characterized in that, The repair method includes: (1) Remove the damaged portions of the wire mesh to expose the honeycomb area; (2) Clean the exposed honeycomb area; (3) Lay an adhesive film on the honeycomb area and heat it to bond the adhesive film to the honeycomb area; (4) Lay a replacement wire mesh on the honeycomb area where the adhesive film is bonded; (5) An edge overlap structure is provided in the edge area of ​​the replacement wire mesh; (6) Apply pressure to the area where the replacement wire mesh and the edge overlap structure are laid, and heat to cure.

2. The method for repairing cavity honeycomb mesh according to claim 1, characterized in that, Step (3) of bonding the adhesive film to the honeycomb region includes: The honeycomb region on which the adhesive film is laid is heated to a first temperature range, so that the adhesive film is initially adhered to the honeycomb region; Perforation is made on the adhesive film at the corresponding honeycomb grid locations; The temperature is then reheated to the first temperature range, causing the adhesive film to sink into and adhere to the inner wall of the honeycomb pores.

3. The method for repairing cavity honeycomb mesh according to claim 2, characterized in that, The first temperature range is 110℃~130℃.

4. The method for repairing cavity honeycomb mesh according to claim 1, characterized in that, The edge overlap structure in step (5) includes a support film layer and a fiber prepreg layer. The support film layer is disposed on the replacement mesh, and the fiber prepreg layer is disposed on the support film layer. Adjacent fiber prepreg layers are butted together with a butt joint gap of 0 to 0.03 inches.

5. The method for repairing cavity honeycomb mesh according to claim 4, characterized in that, The fiber prepreg layer is a glass fiber prepreg layer.

6. The method for repairing cavity honeycomb mesh according to claim 1, characterized in that, The heating and curing temperature in step (6) is 170℃~182℃, and the curing time is 110min~130min.

7. The method for repairing cavity honeycomb mesh according to claim 1, characterized in that, The pressure applied in step (6) includes: applying mechanical pressure under the clamping of a clamp coated with a separating agent; or, covering the area where the replacement wire mesh and the edge overlapping structure are laid with a vacuum bag and evacuating the vacuum bag to a predetermined vacuum level.

8. The method for repairing cavity honeycomb mesh according to claim 7, characterized in that, The separating agent is an epoxy separating agent, and the clamping plate is an aluminum clamping plate; the predetermined vacuum degree is at least 22 inches of mercury.

9. The method for repairing cavity honeycomb mesh according to claim 1, characterized in that, Step (3) further includes filling the cavities between the cells in the cellular region and the mounting area for mounting fasteners with a filler.

10. The method for repairing cavity honeycomb mesh according to claim 1, characterized in that, The cavity includes an upper cavity and a lower cavity, and the steps of removal, cleaning, laying adhesive film, laying replacement wire mesh, setting edge overlapping structure, applying pressure and heating curing are respectively performed on the upper cavity and the lower cavity.

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