A bonding process for aircraft canopy transparencies

Abstract

The present application relates to the technical field of aviation manufacturing, in particular to a kind of gluing process of aircraft cabin transparent part edge. It includes the following steps: film is balanced at preset temperature, film is preheated before cutting;With the film after preheating, transparent part and polyester tape are bonded, and transparent part edge connecting bonding piece is obtained;Transparent part edge connecting bonding piece is cured under preset pressure, and transparent part edge connecting piece is obtained.The purpose of the gluing process of aircraft cabin transparent part edge is to solve the problems of long curing cycle and poor edge connecting bonding stability of traditional edge connecting gluing process.

Description

Technical Field

[0001] This invention relates to the field of aerospace manufacturing technology, specifically to an adhesive bonding process for the edges of transparent parts in an aircraft cockpit. Background Technology

[0002] The design and material selection of edge bonding structures have a significant impact on the strength and fatigue performance of aircraft cockpit transparent components. A reasonable edge bonding method will improve the strength and service life of aircraft cockpit transparent components.

[0003] Currently, the edge bonding adhesives for transparent aircraft cockpit components in China are mainly liquid adhesives. For example, SY-50s is used for edge bonding of transparent aircraft components, and its mechanical properties basically meet design requirements. However, SY-50s is difficult to apply evenly, and it is prone to dripping during curing, which is difficult to clean after curing on the transparent component surface. Another example is a method of using an edge bonding adhesive disclosed in Chinese patent CN104387602A. The adhesive needs to be applied and cured twice on polyester ribbon and once on acrylic glass. Existing edge bonding structures generally use similar processes, namely, brushing liquid or paste adhesive onto the bonding area, repeatedly applying and curing, and then bonding by mechanical pressure using a pressure clamp. The bonding process is complex, time-consuming, and significantly reduces manufacturing efficiency. Furthermore, the preparation of such adhesives requires the addition of a fixed amount of water, regular manual stirring, and the introduction of water vapor from the environment to participate in the reaction, resulting in a long cycle, complex process, and adhesive performance significantly affected by the construction environment and the experience of the construction personnel. Adhesive films, as solid or semi-solid adhesives, offer technical advantages such as simple application processes and uniform adhesive layer thickness. However, these advantages can only be maximized when used with appropriate application methods. Therefore, the application method plays a crucial role in the adhesion effect, bonding stability, and performance of the adhesive film.

[0004] Therefore, the inventors have provided an adhesive bonding process for the edges of transparent parts in aircraft cockpits. Summary of the Invention

[0005] (1) Technical problems to be solved

[0006] This invention provides an adhesive bonding process for the edges of transparent parts in aircraft cockpits, which solves the technical problems of long curing cycles and poor bonding stability of traditional edge bonding adhesive processes.

[0007] (2) Technical solution

[0008] This invention provides an adhesive bonding process for the edges of transparent parts in an aircraft cockpit, comprising the following steps:

[0009] The adhesive film is balanced at a preset temperature, and preheated before cutting.

[0010] The transparent part and the polyester ribbon are bonded together using the preheated adhesive film to obtain an edge-connected adhesive part for the transparent part.

[0011] The transparent edge connector is cured under a preset pressure to obtain the transparent edge connector.

[0012] Furthermore, the preset temperature is 20℃±5℃.

[0013] Furthermore, the step of bonding the transparent part and the polyester ribbon with the preheated adhesive film to obtain the edge-connecting adhesive for the transparent part specifically includes the following steps:

[0014] The adhesive film is applied to the surface of the edge connection area of ​​the transparent part;

[0015] Then, the polyester ribbon is adhered to the adhesive film in the same direction and rolled back and forth;

[0016] Adhesive film is bonded to the surface of the polyester ribbon, and hot air is blown and the adhesive film is rolled in the same direction. After repeating the operation multiple times, the bonded part is obtained.

[0017] The adhesive component is subjected to vacuum treatment to obtain the edge-connected adhesive component of the transparent component.

[0018] Furthermore, the material of the edge connection area of ​​the transparent component is plexiglass or polycarbonate.

[0019] Furthermore, the edge connection area of ​​the transparent component is sanded until opaque with sandpaper, and the bonding area is wiped with gasoline.

[0020] Furthermore, the sandpaper has a mesh size of 120 to 2000.

[0021] Furthermore, the hot air temperature is 30–40°C.

[0022] Furthermore, the step of curing the edge-connecting adhesive of the transparent component under a preset pressure specifically involves:

[0023] Curing time is 2–24 hours under a pressure not exceeding 0.10 MPa and a curing temperature of 50–100°C. After natural cooling to room temperature, the pressure is released.

[0024] Furthermore, the preheating treatment of the adhesive film before cutting is specifically as follows:

[0025] The preheating treatment time is 30-50 minutes, and the preheating treatment temperature is 30-40℃.

[0026] Furthermore, the adhesive film is an epoxy system structure adhesive film.

[0027] (3) Beneficial effects

[0028] In summary, this invention achieves the manufacturing of edge connection structures for transparent aircraft cockpit components by using an adhesive film to bond transparent parts to polyester ribbon. Compared to liquid edge bonding adhesives, this bonding process is convenient to operate, simple in process, has a short curing cycle, and provides stable edge bonding performance. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a schematic flowchart of an adhesive bonding process for the edge of a transparent component in an aircraft cockpit, provided by an embodiment of the present invention. Detailed Implementation

[0031] The embodiments of the present invention will be further described in detail below with reference to the accompanying drawings and examples. The following detailed description of the embodiments and the accompanying drawings are used to illustrate the principles of the present invention by way of example, but should not be used to limit the scope of the present invention, that is, the present invention is not limited to the described embodiments.

[0032] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0033] In the description of this invention, it should be understood that the terms "upper," "lower," "front," "rear," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used to facilitate the description of this invention and to simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0034] Figure 1 This is a schematic flowchart of an adhesive bonding process for the edge of a transparent component in an aircraft cockpit, provided by an embodiment of the present invention. The process may include the following steps:

[0035] S100. The adhesive film is balanced at a preset temperature and preheated before cutting. Specifically, the adhesive film is an epoxy system structure adhesive film. Before use, the adhesive film is balanced at 20℃±5℃ for at least 6 hours, and the adhesive film is placed on a heating table for preheating before cutting. The balance temperature is determined by the actual constant temperature construction site temperature conditions. All operations in this invention have no specific temperature requirements and are carried out under this temperature condition. The time is obtained from actual experimental data. The adhesive film used is generally sealed in a whole bag, about 20 square meters. When using, it is not possible to take out one sheet directly at low temperature for room temperature balance, which can easily cause the adhesive film to break. Therefore, the whole bag is balanced at constant temperature in actual use. Considering the large quantity, at least 6 hours are required to achieve sufficient balance. If the time is short, the risk of the adhesive film breaking increases. There are two reasons for needing to balance under this temperature and time conditions: (1) The adhesive film here is stored at -18℃ and needs to be fully balanced at room temperature before use. Because an appropriate amount of adhesive film needs to be taken out before the pretreatment operation. If the adhesive film is not properly equilibrated at room temperature, it may break during the removal process; (2) If it is not equilibrated at room temperature, and a whole roll of adhesive film is placed on a hot table to be heated and softened, a large amount of water vapor will be generated on the surface of the adhesive film, which will affect the subsequent bonding.

[0036] The preheating treatment time is 30–50 minutes, and the preheating temperature is 30–40℃. Compared with using preheated adhesive film for edge bonding, using unpreheated adhesive film for edge bonding is prone to bonding defects, resulting in unstable bonding quality. Analysis revealed that unpreheated adhesive film has poor initial tack, making it prone to polyester ribbon misalignment during film preparation and bonding operations, leading to unstable shear and peel strength after curing. Preheating effectively improves the initial tack of the adhesive film and reduces the role of polyester ribbon positioning in subsequent processes. If the temperature exceeds 40℃, some of the adhesive film will undergo gelation, affecting the final bonding effect. If the preheating temperature is too low or the time is too short, it cannot increase the fluidity and initial tack of the adhesive film, making it impossible to fix the polyester ribbon position. If the preheating time is too long, it increases the cost of the process.

[0037] S200. Use the preheated adhesive film to bond the transparent part and the polyester ribbon to obtain the transparent part edge connection adhesive.

[0038] Specifically, step S200 includes the following steps:

[0039] S201. Apply the adhesive film to the surface of the edge connection area of ​​the transparent part.

[0040] S202. Then, the polyester ribbon is adhered to the adhesive film in the same direction and rolled back and forth. Specifically, it can be done manually by using a pressure roller to roll back and forth twice at a speed not exceeding 10mm / s. The bonding direction in this step is a critical process, and the rolling step cannot be omitted. The speed parameters are based on GB2792.

[0041] S203. Apply the adhesive film to the surface of the polyester ribbon, and simultaneously blow hot air and roll the film in the same direction. Repeat this process multiple times to obtain the bonded part. Specifically, use a hot air gun to blow hot air in one direction while rolling the film with a pressure roller, repeating this process at least 3 times. Due to the large bonding area, in actual use, at least 3 repetitions are necessary to ensure sufficient adhesion of the adhesive film. Furthermore, the temperature of the hot air gun should be 30-40℃. The hot air gun temperature must be consistent with the pretreatment temperature; this is also to increase the initial tack of the adhesive film.

[0042] S204. Vacuum treatment is applied to the bonded parts to obtain the transparent edge-connected bonded parts. Specifically, a vacuum bag can be made and a vacuum nozzle can be used. After ensuring that the vacuum bag is well sealed, the transparent edge-connected bonded parts can be obtained.

[0043] The material of the edge connection area of ​​the transparent component is plexiglass or polycarbonate. This area is sanded until opaque and then wiped with gasoline. Furthermore, the sandpaper grit should be between 120 and 2000 grit. Only within this range can high-quality bonding be achieved. If the sandpaper grit is too low, the surface will be too rough, easily damaging the plexiglass surface; if the sandpaper grit is too high, the surface will be too smooth, making surface treatment impossible and resulting in poor bonding.

[0044] Compared to blowing the adhesive film back and forth with a hot air gun or not using a hot air gun at all, using a hot air gun to blow the adhesive film in one direction can effectively prevent the adhesive film from sticking together, reduce the formation of adhesive nodules, and reduce the probability of the polyester tape shifting when vacuum-packing. Furthermore, compared to using a hot air gun to blow the adhesive film in one direction alone, using a hot air gun to blow the adhesive film in conjunction with a pressure roller can further improve the edge bonding strength. Analysis revealed that using a method of heating while rolling helps to remove air, increases the initial tack of the adhesive film, and firmly bonds the adhesive film to the polyester tape.

[0045] S300. The edge-connecting adhesive of the transparent component is cured under a preset pressure to obtain the edge-connecting component of the transparent component. Specifically, it is cured for 2 to 24 hours under a pressure not exceeding 0.10 MPa and a curing temperature of 50–100°C, and then the pressure is released after natural cooling to room temperature. The heat distortion temperature limit of the transparent component restricts the curing temperature here to not exceed 100°C. This invention is only applicable to cockpit transparent components that are used for a long period of time within the range of 50–100°C. Transparent components outside this range are not applicable to this invention. The innovation of this invention lies in the use of a heat-curing adhesive for edge connection. Furthermore, a high-strength edge connection structure can be prepared according to the bonding process of this invention. Other curing conditions are not within the protection scope of this invention.

[0046] It should be noted that the order of the three steps—film preparation, bonding, and curing—and the adjustment of the relevant process parameter ranges in this invention will significantly affect the achievement of the technical effect. To achieve the best results, the order of steps S100, S200, and S300 in this invention is fixed and cannot be arbitrarily adjusted.

[0047] Example 1

[0048] (1) Preparation of adhesive film: First, equilibrate the adhesive film at 20℃±5℃ for 6 hours, and then place the adhesive film on a 40℃ hot table for 30 minutes to preheat.

[0049] The purpose is to ensure that the adhesive film is in a soft and elastic state, making it easy to cut. It also increases the initial tack of the adhesive film, making it easier to bond.

[0050] (2) Adhesion:

[0051] (a) Apply the cut adhesive film to the surface of the acrylic glass, where the acrylic glass surface is sanded with 180-grit sandpaper, and the bonding area is wiped with a lint-free cloth dampened with gasoline. The components to be installed in the furnace are treated in the same way.

[0052] (b) Remove the release paper from the adhesive film and attach the polyester ribbon to the adhesive film in one direction. During this process, you can repeatedly peel and attach the polyester ribbon. Repeat the operation until the polyester ribbon is aligned with the adhesive film. Then manually use a pressure roller to roll the polyester ribbon back and forth twice at a speed of 10mm / s.

[0053] (c) Then attach the same size adhesive film to the surface of the polyester ribbon, and then use a 40°C hot air gun to blow on the adhesive film surface (keeping the release paper on one side) in one direction while pressing the adhesive film with a pressure roller. Repeat the operation 6 times.

[0054] The purpose is to expel air, solidify the adhesive layer, and ensure that the adhesive film adheres tightly to the surface of the polyester ribbon.

[0055] (d) Vacuum-bag the part from step (c) to ensure the vacuum bag is airtight, thus obtaining the acrylic edge bonding part. Bond the parts to the furnace using the same method.

[0056] (3) Curing:

[0057] The aforementioned acrylic edge bonding components were vacuum-pressurized to 0.09 MPa and cured in an 80°C oven for 10 hours. After natural cooling to room temperature, the pressure was released. The components in the same oven were cured using the same method.

[0058] The required bonding strength of the edge connection of the transparent parts of the aircraft cockpit is shown in Table 1 below. The test results of the parts in the furnace are shown in Table 2 below. The appearance quality and bonding performance stability of the edge connection are shown in Table 5 below.

[0059] Experimental results show that, in this embodiment, the average, single, and minimum values ​​of the shear strength and peel strength of the cured acrylic edge-joint adhesive are all greater than the design index values ​​of the edge-joint structure, meeting the design requirements. Neither the acrylic edge-joint components nor the furnace-mounted components exhibited excess or flow of adhesive, demonstrating good bonding appearance quality.

[0060] Example 2

[0061] (1) Preparation of adhesive film: First, equilibrate the adhesive film at 20℃±5℃ for 12 hours, and then place the adhesive film on a 30℃ hot table for 45 minutes to preheat.

[0062] (2) Adhesion:

[0063] (a) Apply the cut adhesive film to the polycarbonate surface, where the polycarbonate surface is sanded with 500-grit sandpaper and the bonding area is wiped with a lint-free cloth dampened with gasoline. Treat the furnace components in the same way.

[0064] (b) Remove the release paper from the adhesive film and attach the polyester ribbon to the film in one direction. During this process, you can repeatedly peel and attach the polyester ribbon. Repeat the operation until the polyester ribbon is aligned with the adhesive film. Then manually use a pressure roller to roll the polyester ribbon back and forth twice at a speed of 8mm / s.

[0065] (c) Then attach the same size adhesive film to the surface of the polyester ribbon, and then use a 35°C hot air gun to blow on the adhesive film surface (keeping the release paper on one side) in one direction while pressing the adhesive film with a pressure roller. Repeat the operation 8 times.

[0066] (d) Vacuum-bag the part from step (c) to ensure the vacuum bag is airtight, thus obtaining the polycarbonate edge-bonded part. Bond the parts to the furnace using the same method.

[0067] (3) Curing:

[0068] The above-mentioned polycarbonate edge-joint adhesives were vacuum-pressurized to 0.07 MPa and cured in an oven at 70℃ / 1h + 90℃ / 6h. After natural cooling to room temperature, the pressure was released. The parts in the oven were cured using the same method. The results are detailed in Table 3 below. The appearance quality and bonding performance stability of the edge-joint adhesives are detailed in Table 5 below.

[0069] Experimental results show that, in this embodiment, the average, single, and minimum values ​​of the shear strength and peel strength of the cured polycarbonate edge-joint adhesive are all greater than the design specifications for the edge-joint structure, meeting the design requirements. Neither the polycarbonate edge-joint components nor the furnace-mounted components exhibited excess or flow of adhesive, demonstrating good bonding appearance quality.

[0070] Comparative Example 1

[0071] The bonding and curing steps were exactly the same as in Example 1, except that preheating was not performed during adhesive film preparation. Results for the oven-baked parts are detailed in Table 4 below.

[0072] Comparative Example 2

[0073] The adhesive film preparation and curing steps were exactly the same as in Example 1, except that during the bonding operation step (c), the adhesive film was only blown in one direction with a hot air gun, and no pressure roller was used to press the adhesive film. Results for the oven-baked parts are detailed in Table 4 below.

[0074] Comparative Example 3

[0075] The adhesive film preparation and curing steps were exactly the same as in Example 2, except that during the bonding operation step (c), the hot air gun was used to blow the adhesive film back and forth. Results for the parts in the oven are detailed in Table 4 below.

[0076] Comparative Example 4

[0077] The adhesive film preparation and curing steps were exactly the same as in Example 2, except that a hot air gun was not used during the bonding operation step (c); only a pressure roller was used. Results for the parts in the oven are detailed in Table 4 below.

[0078] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the scope of protection of the present invention. Any simple substitutions or changes made within the scope of the technical ideas disclosed in the present invention and in accordance with the technical solutions of the present invention should be within the scope of protection of the present invention.

[0079] Table 1 Indicator Requirements

[0080]

[0081]

[0082] Table 2 Mechanical test results of Example 1

[0083]

[0084] Table 3 Mechanical test results of Example 2

[0085] sample Shear strength kN / m Forms of destruction Peel strength kN / m Forms of destruction B-01 232.05 Polyester ribbon debonding 3.604 Polyester ribbon debonding B-02 229.98 Polyester ribbon debonding 3.732 Polyester ribbon debonding B-03 238.12 Polyester ribbon debonding 3.400 Polyester ribbon debonding B-04 230.52 Polyester ribbon debonding 3.513 Polyester ribbon debonding B-05 231.14 Polyester ribbon debonding 3.609 Polyester ribbon debonding average value 232.36 / 3.572 /

[0086] Table 4 shows the mechanical test results of Comparative Example 1.

[0087]

[0088]

[0089] Table 5 Performance Summary

[0090]

[0091] It should be noted that the various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the figures. Furthermore, for the sake of brevity, detailed descriptions of known methods and techniques are omitted here.

[0092] The above are merely embodiments of this application and are not intended to limit the scope of this application. Various modifications and variations can be made to this application by those skilled in the art without departing from the scope of the invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this application should be included within the scope of the claims of this application.

Claims

1. A bonding process for the edge of a transparent component in an aircraft cockpit, characterized in that, The adhesive bonding process includes the following steps: The adhesive film is balanced at a preset temperature, and preheated before cutting. The transparent part and the polyester ribbon are bonded together using the preheated adhesive film to obtain an edge-connected adhesive part for the transparent part. The transparent edge connection adhesive is cured under a preset pressure to obtain the transparent edge connection. The process of bonding the transparent part and the polyester ribbon together with the preheated adhesive film to obtain the edge-connected adhesive part of the transparent part includes the following steps: The adhesive film is applied to the surface of the edge connection area of ​​the transparent part; Then, the polyester ribbon is adhered to the adhesive film in the same direction and rolled back and forth; Adhesive film is bonded to the surface of the polyester ribbon, and hot air is blown and the adhesive film is rolled in the same direction. After repeating the operation multiple times, the bonded part is obtained. The adhesive component is subjected to vacuum treatment to obtain the edge-connected adhesive component of the transparent component; The step of curing the edge-connecting adhesive of the transparent component under a preset pressure is specifically as follows: Curing time is 2-24 hours under a pressure not exceeding 0.10 MPa and a curing temperature of 50-100℃. After natural cooling to room temperature, the pressure is released. The process of preheating the adhesive film before cutting is specifically as follows: The preheating treatment time is 30-50 minutes, and the preheating treatment temperature is 30-40℃.

2. The bonding process for the edge of the transparent part of the aircraft cockpit according to claim 1, characterized in that, The preset temperature is 20℃±5℃.

3. The bonding process for the edge of the transparent part of the aircraft cockpit according to claim 1, characterized in that, The material of the edge connection area of ​​the transparent component is plexiglass or polycarbonate.

4. The bonding process for the edge of the transparent part of the aircraft cockpit according to claim 3, characterized in that, The edge connection area of ​​the transparent part is sanded until opaque, and the bonding area is wiped with gasoline.

5. The bonding process for the edge of the transparent part of the aircraft cockpit according to claim 4, characterized in that, The sandpaper has a mesh size of 120 to 2000.

6. The bonding process for the edge of the transparent part of the aircraft cockpit according to claim 1, characterized in that, The hot air temperature is 30-40℃.

7. The bonding process for the edge of the transparent part of the aircraft cockpit according to any one of claims 1-6, characterized in that, The adhesive film is an epoxy system adhesive film.

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