Method for bonding aircraft glazing composite frames

Abstract

The application relates to a method for bonding a composite material frame of an aircraft glass, which comprises the following steps: laminating each layer structure of the aircraft glass to form a laminated glass; arranging at least one solid epoxy structural adhesive film on the edge of the laminated glass; placing at least one composite material frame on the solid epoxy structural adhesive film to assemble the laminated glass together to form a composite structure; and vacuum hot-pressing the composite structure to obtain the aircraft glass with the bonded composite material frame. The application combines the two processes of laminating and hot-pressing the aircraft glass and bonding the composite material frame into one hot-pressing laminating process, so that the composite material frame is bonded to the glass body in the laminating and hot-pressing process of the aircraft glass. Thus, the construction time can be saved, the manual intervention action can be saved, the production cost can be reduced, the appearance of the aircraft glass and the thickness of the bonding layer can be controlled, and the process control steps can be simplified.

Description

Technical Field

[0001] This application relates to aircraft glass, and more particularly to a method for bonding aircraft glass composite material frames. Background Technology

[0002] Currently, aircraft glass structures often employ a method of edge-bonding composite material frames to enhance the strength of the edge connections and reduce the weight of the aircraft glass. The typical manufacturing process involves bonding the composite material frame to the semi-finished structural glass obtained after laminating and hot-pressing the aircraft glass. This method is usually effective and simple, but it adds a special process to verify the bonding quality, thus requiring more labor, inspection, and management costs. Summary of the Invention

[0003] To address the problems existing in the prior art, this application provides a method for bonding aircraft glass composite material frames. The specific technical solution is as follows:

[0004] In a first aspect, a method for bonding a composite material frame to an aircraft glass is provided, comprising the following steps: laminating the various structural layers of the aircraft glass to form a laminated glass; providing at least one layer of solid epoxy structural adhesive film on the edge of the laminated glass; placing at least one composite material frame on the solid epoxy structural adhesive film, assembling it together with the laminated glass to form a composite structure; and vacuum hot-pressing the composite structure to obtain an aircraft glass with a bonded composite material frame.

[0005] In a first possible implementation of the first aspect, the laminated glass includes multiple layers of inorganic glass and interlayer film, wherein the multiple layers of inorganic glass are stacked and at least one interlayer film is disposed between adjacent layers of inorganic glass.

[0006] In conjunction with the first possible implementation of the first aspect, in the second possible implementation of the first aspect, the inorganic glass includes silicate glass or quartz glass.

[0007] In conjunction with the first possible implementation of the first aspect, in the third possible implementation of the first aspect, the number of solid epoxy structural films is two, the number of composite material frames is two, the two solid epoxy structural films are symmetrically arranged on the upper and lower sides of the laminated glass, and the two composite material frames are arranged on the two solid epoxy structural films.

[0008] In conjunction with the third possible implementation of the first aspect, in the fourth possible implementation of the first aspect, an edge filler is also provided between the two layers of solid epoxy structural adhesive film, and part of the solid epoxy structural adhesive film is located on the edge filler.

[0009] In a fifth possible implementation manner of the first aspect, in the vacuum heat pressing of the composite structure, the composite structure is first placed in a vacuum bag to be vacuumized, and then is sent to a heat pressing device to be heat pressed under the environment of a temperature of 100-130 DEG C and a pressure of 700-1200 kPa.

[0010] In a sixth possible implementation manner of the first aspect, the laminated glass comprises a plurality of organic glass layers and interlayer adhesive films, and the plurality of organic glass layers are arranged in a stack, and at least one interlayer adhesive film is arranged between two adjacent organic glass layers.

[0011] In a seventh possible implementation manner of the first aspect, in the sixth possible implementation manner of the first aspect, the organic glass comprises acrylic glass or PC glass.

[0012] In an eighth possible implementation manner of the first aspect, in the sixth possible implementation manner of the first aspect, the number of the solid epoxy structural adhesive films is one, the number of the composite material frames is one, the solid epoxy structural adhesive films are symmetrically arranged on one side of the laminated glass, and the composite material frame is arranged on the solid epoxy structural adhesive film.

[0013] In a ninth possible implementation manner of the first aspect, in the eighth possible implementation manner of the first aspect, in the vacuum heat pressing of the composite structure, the composite structure is first placed in a vacuum bag to be vacuumized, and then is sent to a heat pressing device to be heat pressed under the environment of a temperature of 80-105 DEG C and a pressure of 700-1200 kPa.

[0014] Compared with the prior art, the application has the following advantages:

[0015] The low-voltage suspended particle electrochromic film preparation method of the application combines the two processes of laminated heat pressing of the aircraft glass and bonding of the composite material frame into one laminated heat pressing process, so that the composite material frame is bonded to the glass body in the laminated heat pressing process of the aircraft glass, thereby saving construction time, saving manual intervention actions, reducing production cost, ensuring the controllability of the appearance of the aircraft glass and the thickness of the bonding layer, and simplifying the process control steps. BRIEF DESCRIPTION OF DRAWINGS

[0016] The accompanying drawings, which are included to provide a further understanding of the application and constitute a part of this application, illustrate certain illustrative embodiments of the application and together with the description serve to explain the application. In the drawings:

[0017] Figure 1 FIG. 1 is a step flow chart of an aircraft glass composite material frame bonding method according to an embodiment of the application.

[0018] Figure 2 FIG. 2 is a schematic view of an inorganic aircraft glass according to Embodiment 1.

[0019] Figure 3 is a schematic view of the organic aircraft glass in Example 2. DETAILED DESCRIPTION

[0020] For aircraft glass, it is usually necessary to bond a composite material frame on the edge of the glass body. The current bonding method is to bond the composite material frame on the semi-finished glass by adhesion. However, after the bonding is completed by this method, a special process is needed to verify the bonding quality, which requires more labor, inspection and management costs.

[0021] The aircraft glass composite material frame bonding method of the present application combines the two processes of aircraft glass lamination hot pressing and composite material frame bonding into one hot pressing lamination process, so that the composite material frame is bonded on the glass body in the lamination hot pressing process of the aircraft glass. This not only saves construction time, saves manual intervention actions and reduces production costs, but also ensures that the appearance of the aircraft glass and the thickness of the bonding layer are controllable, and simplifies the process control steps.

[0022] To make the purpose, technical solutions and advantages of the present application clearer, the embodiments of the present application will be further described in detail below with reference to the drawings.

[0023] Please refer to Figure 1 which is a step flow chart of the aircraft glass composite material frame bonding method of an embodiment of the present application. As shown in the figure, the aircraft glass composite material frame bonding method S includes the following steps S1 to S4. First, in step S1, a laminated glass is prepared. The layers of the aircraft glass are laminated to form a laminated glass. In an embodiment, the laminated glass includes multiple layers of inorganic glass and interlayer adhesive sheets, and the multiple layers of inorganic glass are arranged in a stack, and at least one interlayer adhesive sheet is arranged between adjacent two layers of inorganic glass. The inorganic glass includes silicate glass or quartz glass.

[0024] In another embodiment, the laminated glass includes multiple layers of organic glass and interlayer adhesive sheets, and the multiple layers of organic glass are arranged in a stack, and at least one interlayer adhesive sheet is arranged between adjacent two layers of organic glass. The organic glass includes acrylic glass or PC glass.

[0025] Then, in step S2, a solid epoxy structural adhesive film is arranged. At least one solid epoxy structural adhesive film is arranged on the edge of the laminated glass. The number of solid epoxy structural adhesive films can be selected according to the number of composite material frames. The solid epoxy structural adhesive film has the characteristics of water resistance, chemical corrosion resistance, crystal clearness and strong adhesion.

[0026] Next, in step S3, a composite material frame is placed. At least one composite material frame is placed on the solid epoxy structural adhesive film corresponding to the laminated glass, so that they are assembled together, and the relative position is fixed by adhesive tape to form a composite structure.

[0027] Finally, in step S4, the hot pressing lamination is performed. The composite structure is first vacuumed, and then is placed in a hot pressing device for hot pressing lamination. After the hot pressing lamination is completed, the aircraft glass is taken out, and thus the aircraft glass with the bonded composite material frame is obtained.

[0028] The aircraft glass composite material frame bonding method S of the embodiment is to place the composite material frame on the laminated glass through the solid epoxy structural adhesive film before the conventional aircraft glass hot pressing lamination process, and then enter the hot pressing lamination process, so that the composite material frame is bonded to the glass body in the laminated hot pressing process of the aircraft glass. In this way, two processes can be combined into one hot pressing lamination process, saving construction time, saving manual intervention actions, reducing production costs, and ensuring that the appearance of the aircraft glass and the thickness of the bonding layer are controllable, and simplifying the process control steps.

[0029] The beneficial effects of the aircraft glass composite material frame bonding method of the present application will be described below with specific examples 1 and 2.

[0030] Example 1:

[0031] The inorganic aircraft glass composite material frame bonding method includes the following steps:

[0032] 1. Inorganic aircraft glass lamination: according to the process requirements, the inorganic glass 1, the interlayer adhesive film 2 and the edge filler 3 are laminated as shown in Figure 2 , and after completion, they are ready for use.

[0033] 2. Laying solid epoxy structural adhesive film: after the solid epoxy structural adhesive film 4 is cut to be consistent with the composite material frame bonding area, two layers of solid epoxy structural adhesive film 4 are symmetrically arranged on the upper and lower sides of the laminated inorganic aircraft glass.

[0034] 3. Setting the composite material frame: two composite material frames are set on the two layers of solid epoxy structural adhesive film, and the corresponding positions are fixed with adhesive tape.

[0035] 4. Vacuum fixation: the composite structure prepared above is put into a vacuum bag, and after vacuumizing, the entire composite structure is sealed and fixed by the vacuum bag.

[0036] 5. Hot pressing lamination: the composite structure is sent into a hot pressing device, and the hot pressing work is completed under the temperature of 100-130℃ and the pressure of 700-1200kPa.

[0037] 6. Finished product: the product is taken out, and the inorganic aircraft glass with the bonded composite material frame is obtained.

[0038] Example 2:

[0039] The organic aircraft glass composite material frame bonding method includes the following steps:

[0040] 1. Organic aircraft glass lamination: according to the process requirements, the lamination of the organic glass 6 and the interlayer film 2 is completed as shown in the figure, and then the product is ready for use. Figure 3

[0041] 2. Laying of solid epoxy structural adhesive film: after the solid epoxy structural adhesive film 4 is cut to be consistent with the bonding area of the composite frame, a layer of solid epoxy structural adhesive film 4 is arranged on the edge of the laminated organic aircraft glass.

[0042] 3. Setting of the composite frame: a composite frame is arranged on the corresponding solid epoxy structural adhesive film, and the corresponding position is fixed with adhesive tape.

[0043] 4. Vacuum fixation: the composite structure prepared above is put into a vacuum bag, and after vacuumizing, the entire composite structure is sealed and fixed by the vacuum bag.

[0044] 5. Hot pressing lamination: the composite structure is sent into a hot pressing equipment, and the hot pressing work is completed under the temperature of 80-105℃ and the pressure of 700-1200kPa.

[0045] 6. Finished product: the product is taken out, and the organic aircraft glass with the bonded composite frame is obtained.

[0046] In summary, the present application provides a method for bonding the composite frame of the aircraft glass. The present application combines the two processes of aircraft glass lamination and hot pressing and composite frame bonding into one hot pressing lamination process, so that the composite frame is bonded to the glass body in the lamination and hot pressing process of the aircraft glass. This not only saves construction time, saves manual intervention actions, and reduces production cost, but also ensures the controllability of the appearance and bonding layer thickness of the aircraft glass, and simplifies the process control steps.

[0047] It should be noted that in this text, the term "includes", "contains" or any other variant thereof is intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or includes elements inherent to such process, method, article or device. Without more limitations, the element defined by the statement "includes a" does not exclude the presence of another identical element in the process, method, article or device including the element.

[0048] ​The embodiments of the present application are described above with reference to the accompanying drawings, but the present application is not limited to the specific embodiments described above, and the specific embodiments described above are merely illustrative, but not restrictive, and a person of ordinary skill in the art can make many forms under the inspiration of the present application without departing from the purpose of the present application and the scope protected by the claims.

Claims

1. A method of bonding an aircraft glazing composite frame, characterised in that, The method comprises the following steps: laminating each layer of the aircraft glass to form a laminated glass, wherein the laminated glass comprises multiple layers of inorganic glass and interlayer adhesive film, the multiple layers of inorganic glass are arranged in a stack, and at least one interlayer adhesive film is arranged between two adjacent layers of the inorganic glass; arranging at least one solid epoxy structural adhesive film on the edge of the laminated glass, wherein the number of the solid epoxy structural adhesive film is two, the number of the composite material frame is two, the two solid epoxy structural adhesive films are symmetrically arranged on the upper and lower sides of the laminated glass, the two composite material frames are arranged on the two solid epoxy structural adhesive films, and the edge filler is arranged between the two solid epoxy structural adhesive films, and part of the solid epoxy structural adhesive film is located on the edge filler; placing at least one composite material frame on the solid epoxy structural adhesive film to assemble the laminated glass together to form a composite structure; vacuum hot-pressing the composite structure to obtain the aircraft glass with the bonded composite material frame, wherein when the composite structure is vacuum hot-pressed, the composite structure is first placed in a vacuum bag to be vacuumized, and then is sent to a hot-pressing device to be hot-pressed under the condition of a temperature of 100-130 DEG C and a pressure of 700-1200 kPa.

2. The method of claim 1, wherein The inorganic glass comprises silicate glass or quartz glass.

3. An aircraft glazing composite frame bonding method, characterized in that, The method comprises the following steps: laminating each layer of the aircraft glass to form a laminated glass, wherein the laminated glass comprises multiple layers of inorganic glass and interlayer adhesive film, the multiple layers of inorganic glass are arranged in a stack, and at least one interlayer adhesive film is arranged between two adjacent layers of the inorganic glass; arranging at least one solid epoxy structural adhesive film on the edge of the laminated glass, wherein the number of the solid epoxy structural adhesive film is two, the number of the composite material frame is two, the two solid epoxy structural adhesive films are symmetrically arranged on the upper and lower sides of the laminated glass, the two composite material frames are arranged on the two solid epoxy structural adhesive films, and the edge filler is arranged between the two solid epoxy structural adhesive films, and part of the solid epoxy structural adhesive film is located on the edge filler; placing at least one composite material frame on the solid epoxy structural adhesive film to assemble the laminated glass together to form a composite structure; vacuum hot-pressing the composite structure to obtain the aircraft glass with the bonded composite material frame, wherein when the composite structure is vacuum hot-pressed, the composite structure is first placed in a vacuum bag to be vacuumized, and then is sent to a hot-pressing device to be hot-pressed under the condition of a temperature of 100-130 DEG C and a pressure of 700-1200 kPa.

4. The method of claim 3, wherein The inorganic glass comprises silicate glass or quartz glass. The method comprises the following steps: laminating each layer of the aircraft glass to form a laminated glass, wherein the laminated glass comprises multiple layers of inorganic glass and interlayer adhesive film, the multiple layers of inorganic glass are arranged in a stack, and at least one interlayer adhesive film is arranged between two adjacent layers of the inorganic glass; arranging at least one solid epoxy structural adhesive film on the edge of the laminated glass, wherein the number of the solid epoxy structural adhesive film is two, the number of the composite material frame is two, the two solid epoxy structural adhesive films are symmetrically arranged on the upper and lower sides of the laminated glass, the two composite material frames are arranged on the two solid epoxy structural adhesive films, and the edge filler is arranged between the two solid epoxy structural adhesive films, and part of the solid epoxy structural adhesive film is located on the edge filler; placing at least one composite material frame on the solid epoxy structural adhesive film to assemble the laminated glass together to form a composite structure; vacuum hot-pressing the composite structure to obtain the aircraft glass with the bonded composite material frame, wherein when the composite structure is vacuum hot-pressed, the composite structure is first placed in a vacuum bag to be vacuumized, and then is sent to a hot-pressing device to be hot-pressed under the condition of a temperature of 100-130 DEG C and a pressure of 700-1200 kPa. The inorganic glass comprises silicate glass or quartz glass.

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