Airplane sealing plate and preparation method thereof

Abstract

The invention provides an aircraft sealing plate and a preparation method thereof. The preparation method of the aircraft sealing plate comprises the following steps: S1, preparing a carbon fiber skeleton and a modified low-temperature-resistant raw rubber layer; wherein the preparation raw materials of the modified low-temperature-resistant raw rubber layer comprise a rubber master batch and a low-temperature-resistant modified material; s2, epoxy resin glue is arranged on the surface of at least one side of the carbon fiber skeleton, the modified low-temperature-resistant raw rubber layer and the surface, provided with the epoxy resin glue, of the carbon fiber skeleton are overlapped, and an intermediate is obtained; and S3, the intermediate is subjected to vulcanization treatment, the airplane sealing plate is obtained, and the modified low-temperature-resistant rubber raw rubber layer in the intermediate is subjected to vulcanization treatment to form the modified low-temperature-resistant rubber layer. The airplane sealing plate prepared through the method has the advantages of being high in structural strength, large in deformation, high in rebound resilience, good in fatigue resistance, good in low temperature resistance and the like.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft sealing plate preparation, in particular to an aircraft sealing plate and a preparation method thereof. Background Art

[0002] The gap between the main wing and the movable wing of an aircraft will have a certain impact on its flight performance, and external water vapor will also enter the interior of the wing through the gap, corroding the connection structure and transmission structure in the wing, affecting the reliability and life of the wing. Therefore, at present, a sealing plate is generally set at the gap between the main wing and the movable wing of an aircraft. The sealing plate can eliminate the gap, improve the smoothness of the wing surface, and prevent external water vapor from entering the interior of the wing through the gap (the structure of the sealing plate can refer to patents such as CN207725605U). Since the wing surface of the aircraft will deflect and bend during flight, the sealing plate is required to have aerodynamic sealing characteristics such as high strength and high rigidity to resist aerodynamic suction, and at the same time, the sealing plate is required to have characteristics such as large deformation and high resilience to adapt to deflection / bending conditions.

[0003] Existing sealing plates generally adopt metal structures or composite materials. Since metal structures and composite materials are too rigid, it is difficult to meet the use requirements of sealing plates under large deformation conditions. During the deflection process, excessive stress may cause excessive steering torque, affecting aerodynamic operability and aircraft safety.

[0004] In order to solve the above problems, some existing sealing plates adopt a composite structure of rubber and composite materials, but this structure currently has the following problems: 1. The bonding strength between rubber and composite materials is insufficient, which affects the overall structural strength of the sealing plate; 2. The low-temperature resistance of the sealing plate is poor, and it is easy to be damaged / broken after repeated bending in a low-temperature environment, and the low-temperature service life is short. Summary of the invention

[0005] The purpose of the present invention is to provide a method for preparing an aircraft sealing plate. The aircraft sealing plate prepared by the method has the advantages of high structural strength, large deformation, high resilience, good fatigue resistance, good low temperature resistance and the like.

[0006] The present invention provides a method for preparing an aircraft sealing plate, comprising the following steps:

[0007] S1: preparing a carbon fiber skeleton and a modified low-temperature resistant rubber raw rubber layer; wherein the raw materials for preparing the modified low-temperature resistant rubber raw rubber layer include a rubber masterbatch and a low-temperature resistant modified material;

[0008] S2: arranging epoxy resin glue on the surface of at least one side of the carbon fiber skeleton, and superimposing the modified low-temperature resistant rubber raw rubber layer on the surface of the carbon fiber skeleton on which the epoxy resin glue is arranged, to obtain an intermediate;

[0009] S3: vulcanizing the intermediate to obtain an aircraft sealing plate, wherein the modified low-temperature resistant rubber raw rubber layer in the intermediate forms a modified low-temperature resistant rubber layer after vulcanization; wherein the vulcanization temperature of the intermediate is 150°C to 190°C, the vulcanization time is 10 minutes to 60 minutes, and the vulcanization pressure is 15MPa to 20MPa.

[0010] In one achievable manner, in the above step S1, the rubber masterbatch is methyl vinyl silicone rubber, and the low-temperature resistant modified material includes low-phenyl silicone rubber; wherein the mass of the low-phenyl silicone rubber is 18% to 22% of the mass of the methyl vinyl silicone rubber.

[0011] In one achievable manner, in the above-mentioned step S1, the raw materials for preparing the modified low-temperature resistant rubber raw rubber layer also include fillers, and the fillers include gas silica and a compatibilizer; wherein the mass of the gas silica is 4.5% to 5.5% of the mass of the methyl vinyl silicone rubber, and the mass of the compatibilizer is 0.9% to 1.1% of the mass of the methyl vinyl silicone rubber.

[0012] In one achievable manner, in the above-mentioned step S1, the rubber masterbatch is hydrogenated nitrile rubber, and the low-temperature resistant modified material includes dioctyl adipate and hydrogenated nitrile liquid; wherein the mass of the dioctyl adipate is 1.8% to 2.2% of the mass of the hydrogenated nitrile rubber, and the mass of the hydrogenated nitrile liquid is 0.9% to 1.1% of the mass of the hydrogenated nitrile rubber.

[0013] In one achievable manner, in the above step S1, the step of preparing the carbon fiber skeleton comprises:

[0014] (1) pressing epoxy resin or bismaleimide resin to form a film, and placing the film on both sides of the carbon fiber fabric to obtain a carbon fiber prepreg;

[0015] (2) stacking multiple layers of the carbon fiber prepreg and performing a vacuum treatment on the multiple layers of the carbon fiber prepreg to obtain a carbon fiber composite;

[0016] (3) placing the carbon fiber composite in an autoclave for curing to obtain the carbon fiber skeleton; wherein the curing temperature of the carbon fiber composite is 150°C to 185°C, the curing time is 3 hours to 7 hours, and the curing pressure is 0.3 MPa to 0.6 MPa.

[0017] In one achievable manner, in the above step S1, the step of preparing the modified low-temperature resistant rubber raw rubber layer comprises:

[0018] The raw materials for preparing the modified low-temperature resistant rubber raw rubber layer are mixed uniformly to obtain a mixture; the mixture is rolled to form a sheet structure, thereby obtaining the modified low-temperature resistant rubber raw rubber layer.

[0019] In one achievable manner, in the above step S2, the epoxy resin glue is disposed on the surface of one side of the carbon fiber skeleton, and the surface of the carbon fiber skeleton on the side where the epoxy resin glue is disposed is superimposed with the modified low-temperature resistant rubber raw rubber layer;

[0020] Alternatively, the epoxy resin glue is disposed on surfaces on two opposite sides of the carbon fiber skeleton, and the surfaces on two opposite sides of the carbon fiber skeleton are both superimposed with the modified low-temperature resistant rubber raw rubber layer.

[0021] In one achievable manner, in the above step S2, two modified low-temperature resistant rubber raw rubber layers are superimposed on the surface of at least one side of the carbon fiber skeleton, and a reinforcing layer is sandwiched between the two modified low-temperature resistant rubber raw rubber layers; the reinforcing layer is obtained by immersing the reinforcing cloth in an adhesive.

[0022] In one achievable manner, in the above step S3, after the intermediate is vulcanized, a wear-resistant coating is provided on the surface of at least one side of the intermediate.

[0023] The present invention also provides an aircraft sealing plate, which is manufactured by the above-mentioned preparation method of the aircraft sealing plate; the aircraft sealing plate comprises a carbon fiber skeleton and a modified low-temperature resistant rubber layer arranged on at least one side surface of the carbon fiber skeleton.

[0024] The preparation method of the aircraft sealing plate provided by the present invention adopts the method of integrally vulcanizing and molding a carbon fiber skeleton and a modified low-temperature resistant rubber raw rubber layer to obtain the aircraft sealing plate. Since the aircraft sealing plate has a carbon fiber skeleton structure and a modified low-temperature resistant rubber layer structure, the aircraft sealing plate has the advantages of high structural strength, large deformation, high resilience, good fatigue resistance, etc., and meets the use conditions of not being damaged under long-term large-angle bending conditions; at the same time, since epoxy resin glue is provided on the surface of the carbon fiber skeleton, the epoxy resin glue can play a role in bonding the carbon fiber skeleton and the modified low-temperature resistant rubber raw rubber layer, thereby improving the bonding force and bonding strength between the carbon fiber skeleton and the modified low-temperature resistant rubber layer, avoiding the peeling of the two, and then improving the overall structural strength of the aircraft sealing plate. Moreover, since the modified low-temperature resistant rubber raw rubber layer has a low-temperature resistant modified material added to the rubber masterbatch, the low-temperature resistance of the modified low-temperature resistant rubber layer is improved, so that the aircraft sealing plate is not easily damaged / broken even after repeated bending in a low-temperature environment, meeting the use conditions of not being damaged in a high-altitude low-temperature flight environment, and improving the low-temperature service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0026] Figure 1 Schematic diagram of the cross section of an aircraft sealing plate in an embodiment of the present invention.

[0027] Figure 2 It is a cross-sectional schematic diagram of an aircraft sealing plate in another embodiment of the present invention.

[0028] Figure 3 It is a cross-sectional schematic diagram of an aircraft sealing plate in another embodiment of the present invention. DETAILED DESCRIPTION

[0029] The specific embodiments of the present invention are described in further detail below. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention. The terms "first", "second", "third", "fourth", etc. (if any) in the specification and claims of the present invention are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequential order.

[0030] like Figure 1 As shown, an embodiment of the present invention provides a method for preparing an aircraft sealing plate, comprising the following steps:

[0031] S1: preparing a carbon fiber skeleton 1 and a modified low-temperature resistant rubber raw rubber layer; wherein the raw materials for preparing the modified low-temperature resistant rubber raw rubber layer include a rubber masterbatch and a low-temperature resistant modified material, and the modified low-temperature resistant rubber raw rubber layer is a sheet structure (i.e., a layered structure);

[0032] S2: Epoxy resin glue is provided on the surface of at least one side of the carbon fiber skeleton 1, and the modified low-temperature resistant rubber raw rubber layer is superimposed on the surface of the carbon fiber skeleton 1 provided with epoxy resin glue (that is, the modified low-temperature resistant rubber raw rubber layer is bonded to the carbon fiber skeleton 1 along the thickness direction) to obtain an intermediate; at this time, the modified low-temperature resistant rubber raw rubber layer and the carbon fiber skeleton 1 can be pre-bonded together by epoxy resin glue;

[0033] S3: The intermediate is vulcanized to obtain an aircraft sealing plate 100; after the vulcanization, the modified low-temperature resistant rubber raw rubber layer in the intermediate is vulcanized to form a modified low-temperature resistant rubber layer 2, and the epoxy resin glue is cured to firmly bond the modified low-temperature resistant rubber layer 2 to the carbon fiber skeleton 1, that is, the aircraft sealing plate 100 includes a carbon fiber skeleton 1 and a modified low-temperature resistant rubber layer 2 arranged on at least one side surface of the carbon fiber skeleton 1; wherein the vulcanization temperature of the intermediate is 150°C to 190°C, the vulcanization time is 10 minutes to 60 minutes, and the vulcanization pressure is 15MPa to 20MPa.

[0034] Wherein, in the above step S3, the intermediate can be placed in a vulcanizer (e.g., a flat vulcanizer) for vulcanization. The vulcanization temperature of the intermediate can be 150°C, 160°C, 170°C, 180°C, 190°C, etc., or any combination range of the above temperatures; the vulcanization time can be 10 minutes, 20 minutes, 30 minutes, 40 minutes, 50 minutes, 60 minutes, etc., or any combination range of the above times; the vulcanization pressure can be 15MPa, 16MPa, 17MPa, 18MPa, 19MPa, 20MPa, etc., or any combination range of the above pressures.

[0035] The preparation method of the aircraft sealing plate provided in the embodiment of the present invention adopts the method of integrally vulcanizing and molding a carbon fiber skeleton 1 and a modified low-temperature resistant rubber raw rubber layer to obtain the aircraft sealing plate 100. Since the aircraft sealing plate 100 has the structure of the carbon fiber skeleton 1 and the structure of the modified low-temperature resistant rubber layer 2, the aircraft sealing plate 100 has the advantages of high structural strength, large deformation, high resilience, good fatigue resistance, etc., and meets the conditions of use without being damaged under long-term large-angle bending conditions; at the same time, since epoxy resin glue is provided on the surface of the carbon fiber skeleton 1, the epoxy resin glue can play a role in bonding the carbon fiber skeleton 1 and the modified low-temperature resistant rubber raw rubber layer, thereby improving the bonding force and bonding strength between the carbon fiber skeleton 1 and the modified low-temperature resistant rubber layer 2, avoiding peeling between the two, and further improving the overall structural strength of the aircraft sealing plate 100. Moreover, since the modified low-temperature resistant rubber raw rubber layer has low-temperature resistant modified materials added to the rubber masterbatch, the low-temperature resistance of the modified low-temperature resistant rubber layer 2 is improved, so that the aircraft sealing plate 100 is not easily damaged / broken even after repeated bending in a low-temperature environment, meeting the use conditions of not being damaged in a high-altitude and low-temperature flight environment, and improving the low-temperature service life of the aircraft sealing plate 100.

[0036] like Figure 1 As shown, as an embodiment, in the above-mentioned step S2, epoxy resin glue is arranged on the surfaces on the opposite sides of the carbon fiber skeleton 1, and the surfaces on the opposite sides of the carbon fiber skeleton 1 are superimposed with modified low-temperature resistant rubber raw rubber layers; in this way, modified low-temperature resistant rubber layers 2 are formed on the surfaces on the opposite sides of the carbon fiber skeleton 1.

[0037] like Figure 2 As shown, as another embodiment, in the above-mentioned step S2, the epoxy resin glue is arranged on the surface of one side of the carbon fiber skeleton 1, and the surface of the carbon fiber skeleton 1 on the side where the epoxy resin glue is arranged is superimposed with a modified low-temperature resistant rubber raw rubber layer; in this way, a modified low-temperature resistant rubber layer 2 is formed on the surface of one side of the carbon fiber skeleton 1.

[0038] As an embodiment, in the above-mentioned step S2, epoxy resin glue is set on the surface of the carbon fiber skeleton 1. Specifically, the carbon fiber skeleton 1 can be immersed in the epoxy resin glue for a period of time (for example, 1 minute), or the epoxy resin glue can be sprayed on the surface of the carbon fiber skeleton 1 so that the epoxy resin glue adheres to the surface of the carbon fiber skeleton 1.

[0039] As an embodiment, in the above step S2, the thickness of the carbon fiber skeleton 1 can be 0.5 mm to 3 mm, and the thickness of the modified low-temperature resistant rubber raw rubber layer on each side can be 0.5 mm to 3 mm. The ratio of the thickness of the carbon fiber skeleton 1 to the modified low-temperature resistant rubber raw rubber layer on each side can be (1:1) to (7:3).

[0040] As an embodiment, in the above step S1, the step of preparing the carbon fiber skeleton 1 includes:

[0041] (1) pressing epoxy resin or bismaleimide resin to form a film, and placing the film on both sides of the carbon fiber fabric to obtain a carbon fiber prepreg;

[0042] (2) stacking multiple layers of carbon fiber prepreg and performing vacuum treatment on the multiple layers of carbon fiber prepreg to densify the carbon fiber prepregs to obtain a carbon fiber composite;

[0043] (3) The carbon fiber composite is placed in an autoclave for curing to obtain a carbon fiber skeleton 1; wherein the curing temperature of the carbon fiber composite is 150°C to 185°C, the curing time is 3 hours to 7 hours, and the curing pressure is 0.3 MPa to 0.6 MPa.

[0044] The above step (1) may specifically be as follows: the epoxy resin or bismaleimide resin is stirred evenly, and then pressed by a roller press to form a film, the thickness of the film may be 0.05 mm to 0.1 mm; then the film is compounded with both sides of the carbon fiber fabric by double-sided lamination (that is, after the two sides of the film and the carbon fiber fabric are stacked, the film and the carbon fiber fabric are compounded together by roller pressing), so as to obtain a carbon fiber composite; the carbon fiber fabric may specifically be a carbon fiber cloth, a carbon fiber tape, etc., and the carbon fiber in the carbon fiber fabric may be a high-strength carbon fiber of the T300, T700, T800 series, etc.; the thickness of the carbon fiber fabric may be 0.05 mm to 0.2 mm.

[0045] Wherein, in the above step (2), the number of stacked layers of carbon fiber prepreg can be determined according to the required thickness of the carbon fiber skeleton 1, for example, 5-15 layers. When the multi-layer carbon fiber prepreg is subjected to vacuum treatment, vacuum can be drawn once after stacking 2-3 layers of carbon fiber prepreg each time (i.e., a total of multiple vacuuming is required), and the pressure of each vacuuming is, for example, 0.085-0.1MPa, and the time of each vacuuming is, for example, 15 minutes, so as to better extract the gas between the carbon fiber prepregs and make the carbon fiber prepregs compact.

[0046] Among them, in the above step (3), the curing temperature of the carbon fiber composite can be 150°C, 160°C, 170°C, 180°C, 185°C, etc., and can also be any combination range of the above temperatures; the curing time can be 3 hours, 4 hours, 5 hours, 6 hours, 7 hours, etc., and can also be any combination range of the above times; the curing pressure can be 0.3MPa, 0.4MPa, 0.5MPa, 0.6MPa, etc., and can also be any combination range of the above pressures.

[0047] Wherein, after the above step (3), according to actual needs, the preparation steps of the carbon fiber skeleton 1 may further include:

[0048] (4) The carbon fiber skeleton 1 is cut according to the required shape of the aircraft sealing plate 100 to obtain a carbon fiber skeleton 1 of a specific shape.

[0049] As an embodiment, in the above step S1, the step of preparing the modified low-temperature resistant rubber raw rubber layer includes:

[0050] The raw materials for preparing the modified low-temperature resistant rubber raw rubber layer (including rubber masterbatch, low-temperature resistant modified material, etc.) are mixed uniformly to obtain a mixture; the mixture is rolled (for example, by a roller press) to form the mixture into a sheet structure, thereby obtaining the modified low-temperature resistant rubber raw rubber layer.

[0051] As an embodiment, in the above step S1, the rubber masterbatch is methyl vinyl silicone rubber, and the low temperature resistant modified material includes low phenyl silicone rubber (when the phenyl content (phenyl to silicon atomic ratio) is at a low level (generally 5-10%), it is generally referred to as low phenyl silicone rubber); wherein the mass of the low phenyl silicone rubber is 18% to 22% of the mass of the methyl vinyl silicone rubber, that is, in terms of mass parts, when the methyl vinyl silicone rubber is 100 parts, the low phenyl silicone rubber is 18 to 22 parts. Among them, the low phenyl silicone rubber can significantly improve the low temperature resistance of the methyl vinyl silicone rubber.

[0052] As an embodiment, in the above step S1, the raw materials for preparing the modified low-temperature resistant rubber raw rubber layer also include fillers, and the fillers include gas silicon (i.e. silicon hydroxide, chemical formula SiO2·xH2O) and compatibilizers, and the compatibilizers can specifically be multifunctional vinyl silicone oils. Among them, gas silicon and compatibilizers can improve the mechanical strength of rubber materials; the mass of gas silicon is 4.5% to 5.5% of the mass of methyl vinyl silicone rubber, and the mass of compatibilizers is 0.9% to 1.1% of the mass of methyl vinyl silicone rubber.

[0053] As an embodiment, the mass of low phenyl silicone rubber can be 18%, 19%, 20%, 21%, 22%, etc. of the mass of methyl vinyl silicone rubber, or any combination range of the above percentages. The mass of gas silicone can be 4.5%, 4.7%, 4.9%, 5.0%, 5.2%, 5.5%, etc. of the mass of methyl vinyl silicone rubber, or any combination range of the above percentages. The mass of compatibilizer can be 0.9%, 1.0%, 1.1%, etc. of the mass of methyl vinyl silicone rubber, or any combination range of the above percentages.

[0054] In order to verify the performance of the modified low-temperature resistant rubber layer made by the above material combination, the following test was designed:

[0055] ① Add 20% low-phenyl silicone rubber, 5% gas silicon and 1% compatibilizer (multifunctional vinyl silicone oil) to methyl vinyl silicone rubber, mix well and roll it into a sheet, and then vulcanize it (vulcanization temperature is 160°C, vulcanization time is 30 minutes, vulcanization pressure is 15Mpa) to obtain a modified low-temperature resistant rubber layer.

[0056] ② The methyl vinyl silicone rubber is rolled into a sheet, and then subjected to vulcanization treatment (vulcanization temperature is 160° C., vulcanization time is 30 minutes, and vulcanization pressure is 15 MPa) to obtain a first rubber layer.

[0057] The thickness of the modified low-temperature resistant rubber layer and the first rubber layer are both 2 mm.

[0058] The glass transition temperature (the glass transition temperature of rubber refers to the temperature at which the rubber material changes from a highly elastic state to a glassy state; below this temperature, the rubber exhibits brittleness, while above this temperature, the rubber exhibits elasticity), tensile strength, tensile elongation, hardness, etc. of the modified low-temperature resistant rubber layer and the first rubber layer are tested respectively. The test standards for each index are as follows:

[0059] Glass transition temperature: Tested in accordance with GB / T19466.2-2004 Part 2, Determination of glass transition temperature.

[0060] Tensile strength: Tested in accordance with GB / T 528-2009 - Determination of tensile stress-strain properties of vulcanized rubber or thermoplastic rubber.

[0061] Tensile elongation: Tested in accordance with GB / T 19466.2-2004 - Determination of tensile stress-strain properties of vulcanized rubber or thermoplastic rubber.

[0062] Hardness: Test according to GB / T 531.1-2008 Test method for indentation hardness of vulcanized rubber or thermoplastic rubber Part 1: Shore durometer method.

[0063] The test results are shown in the following table:

[0064] Test items Before modification (first rubber layer) After modification (modified low temperature resistant rubber layer) Glass transition temperature(℃) -60 -70 Tensile strength(Mpa) 8 6.5 Tensile elongation (%) 600 450 Hardness Shore A 55 48

[0065] It can be seen from the above table that after modification, although the tensile strength and tensile elongation of the rubber material are reduced (but within the applicable standard range), the glass transition temperature of the rubber material is significantly reduced, that is, the low temperature resistance of the rubber material is significantly enhanced; at the same time, the hardness of the rubber material is also reduced, indicating that the deformation performance of the rubber material is also improved.

[0066] As another embodiment, in the above-mentioned step S1, the rubber masterbatch is hydrogenated nitrile rubber (specifically, it can be low acrylonitrile hydrogenated nitrile rubber), and the low-temperature resistant modified material includes dioctyl adipate (DOA) and hydrogenated nitrile liquid (specifically, it can be macromolecular liquid hydrogenated nitrile); dioctyl adipate and hydrogenated nitrile liquid are both plasticizers, and both dioctyl adipate and hydrogenated nitrile liquid can improve the low-temperature resistance of hydrogenated nitrile rubber, and the hydrogenated nitrile liquid can also play a role in increasing the cross-linking density of the rubber, thereby improving the structural strength of the rubber material. Among them, the mass of dioctyl adipate is 1.8% to 2.2% of the mass of hydrogenated nitrile rubber, specifically 1.8%, 1.9%, 2.0%, 2.1%, 2.2%, etc., and can also be any combination range of the above percentages; the mass of hydrogenated nitrile liquid is 0.9% to 1.1% of the mass of hydrogenated nitrile rubber, specifically 0.9%, 1.0%, 1.1%, etc., and can also be any combination range of the above percentages.

[0067] In order to verify the performance of the modified low-temperature resistant rubber layer made by the above material combination, the following test was designed:

[0068] ① Add 2% of dioctyl adipate and 1% of hydrogenated nitrile liquid to hydrogenated nitrile rubber, mix well and roll into sheets, then vulcanize (vulcanization temperature is 160°C, vulcanization time is 30 minutes, vulcanization pressure is 15Mpa) to obtain a modified low-temperature resistant rubber layer.

[0069] ② The hydrogenated nitrile rubber is rolled into a sheet, and then subjected to vulcanization treatment (vulcanization temperature is 160° C., vulcanization time is 30 minutes, and vulcanization pressure is 15 MPa) to obtain a second rubber layer.

[0070] The thickness of the modified low-temperature resistant rubber layer and the second rubber layer are both 2 mm.

[0071] The glass transition temperature, tensile strength, tensile elongation, hardness, etc. of the modified low-temperature resistant rubber layer and the second rubber layer were tested respectively, and the test standards of each index were the same as above.

[0072] The test results are shown in the following table:

[0073] Test items Before modification (second rubber layer) After modification (modified low temperature resistant rubber layer) Glass transition temperature(℃) -40 -45 Tensile strength(Mpa) 23 26 Tensile elongation (%) 260 300 Hardness Shore A 80 75

[0074] It can be seen from the above table that after modification, the glass transition temperature of the rubber material is significantly reduced, that is, the low temperature resistance of the rubber material is significantly enhanced; at the same time, the tensile strength and tensile elongation of the rubber material are increased, indicating that the structural strength of the rubber material is improved; at the same time, the hardness of the rubber material is also reduced, indicating that the deformation performance of the rubber material is also improved.

[0075] like Figure 1 As shown, as an embodiment, in the above step S3, after the intermediate is vulcanized, a wear-resistant coating 4 is also provided on the surface of at least one side of the intermediate to improve the wear resistance of the aircraft sealing plate 100. Preferably, the wear-resistant coating 4 is provided on the surfaces of the opposite sides of the intermediate, so that both sides of the aircraft sealing plate 100 have a wear-resistant coating 4 (when the modified low-temperature resistant rubber layer 2 is formed on the surfaces of the opposite sides of the carbon fiber skeleton 1, the wear-resistant coating 4 is provided on the surfaces of the modified low-temperature resistant rubber layer 2 on the opposite sides. When the modified low-temperature resistant rubber layer 2 is formed on the surface of one side of the carbon fiber skeleton 1, the wear-resistant coating 4 is provided on the surface of the modified low-temperature resistant rubber layer 2 and on the surface of the carbon fiber skeleton 1). The wear-resistant coating 4 can be formed by spraying a wear-resistant material on the surface of the intermediate, and the wear-resistant material can be a fluorine-containing low-friction coefficient material (such as Teflon coating). The thickness of the wear-resistant coating 4 can be 5 to 15 microns.

[0076] like Figure 3 As shown, as another embodiment, in order to enhance the low-temperature tensile strength of the aircraft sealing plate 100 at a local position, a local reinforcement method can be used to solve / improve the problem of easy tearing and cracking caused by the reduced deformation ability of the rubber material in a low-temperature environment. The process steps of the local reinforcement are as follows:

[0077] In the above-mentioned step S2, two modified low-temperature resistant rubber raw rubber layers are superimposed on the surface of at least one side of the carbon fiber skeleton 1 (the two modified low-temperature resistant rubber raw rubber layers form two modified low-temperature resistant rubber layers 2 after vulcanization), and a reinforcing layer 3 is sandwiched between the two modified low-temperature resistant rubber raw rubber layers; the reinforcing layer 3 is obtained by immersing the reinforcing cloth in an adhesive.

[0078] Specifically, the reinforcing cloth can be polyester cloth, polyester cloth, cotton fiber cloth, etc., and the thickness of the reinforcing cloth can be 0.02mm~0.1mm; the adhesive can be an isocyanate adhesive; and the soaking time can be about 5 minutes. Specifically, during the production, the reinforcing cloth is soaked in the adhesive for a period of time to make the adhesive adhere to the reinforcing cloth to obtain the reinforcing layer 3, and then the reinforcing layer 3 is sandwiched between two modified low-temperature resistant rubber raw rubber layers, and then the two modified low-temperature resistant rubber raw rubber layers are superimposed on the carbon fiber skeleton 1; after the subsequent vulcanization treatment, the adhesive in the reinforcing layer 3 is cured, and the reinforcing cloth and the two modified low-temperature resistant rubber layers 2 are firmly bonded together. The reinforcing layer 3 can significantly improve the low-temperature tensile strength of the aircraft sealing panel 100. Among them, the reinforcing layer 3 (that is, as Figure 3 As shown in FIG. 1 ), the reinforcing layer 3 may be provided only in the modified low-temperature resistant rubber layer 2 on one side of the carbon fiber skeleton 1. According to actual use requirements, the reinforcing layer 3 may be provided only at a local position of the aircraft sealing plate 100 (i.e., as shown in FIG. 1 ). Figure 3 As shown), a reinforcement layer 3 (ie, the size of the reinforcement layer 3 is the same as the size of the carbon fiber skeleton 1) may also be provided at various positions of the aircraft sealing plate 100.

[0079] In order to verify the effect of the reinforcement layer 3 on the low temperature strength of the rubber material, the following test was designed:

[0080] ① Roll the hydrogenated nitrile rubber into sheets to obtain raw rubber sheets, each of which has a thickness of 1 mm; soak the 0.1 mm thick reinforcing cloth in an isocyanate adhesive for 5 minutes to obtain a reinforcing layer 3, and then sandwich the reinforcing layer 3 between two raw rubber sheets, and then vulcanize the reinforcing cloth (vulcanization temperature is 160°C, vulcanization time is 30 minutes, and vulcanization pressure is 15Mpa) to obtain a rubber material sample. Among them, the reinforcing cloths are respectively polyester cloth, polyester cloth and cotton fiber cloth, so three rubber material samples are obtained, and the three rubber material samples are respectively sample 1 (reinforcing cloth is polyester cloth), sample 2 (reinforcing cloth is polyester cloth) and sample 3 (reinforcing cloth is cotton fiber cloth).

[0081] ② Roll the hydrogenated nitrile rubber into a sheet, and then vulcanize it (vulcanization temperature is 160°C, vulcanization time is 30 minutes, and vulcanization pressure is 15 MPa) to obtain a third rubber layer. The thickness of the third rubber layer is 2 mm.

[0082] The low-temperature tensile strength (at -40°C), low-temperature tensile elongation (at -40°C) and other parameters of sample 1, sample 2, sample 3 and the third rubber layer were tested respectively. The test standards for each parameter are as follows:

[0083] Low temperature tensile strength: tested at -40℃ in accordance with GB / T 528-2009 - Determination of tensile stress-strain properties of vulcanized rubber or thermoplastic rubber.

[0084] Low temperature tensile elongation: tested at -40℃ in accordance with GB / T 19466.2-2004 - Determination of tensile stress-strain properties of vulcanized rubber or thermoplastic rubber.

[0085] The test results are shown in the following table:

[0086] Test items The third rubber layer Sample 1 Sample 2 Sample 3 Low temperature tensile strength(Mpa) 18 25 22 19 Low temperature tensile elongation (%) 30 60 100 50

[0087] It can be seen from the above table that after adding a reinforcement layer to the rubber material, the low-temperature tensile strength and low-temperature tensile elongation of the rubber material can be significantly improved, thereby improving the performance of the rubber material at low temperatures.

[0088] The embodiment of the present invention further provides an aircraft sealing plate 100, which is manufactured using the above-mentioned aircraft sealing plate preparation method; the aircraft sealing plate 100 includes a carbon fiber skeleton 1 and a modified low-temperature resistant rubber layer 2 arranged on at least one side surface of the carbon fiber skeleton 1.

[0089] Example 1

[0090] (1) Preparation of carbon fiber skeleton:

[0091] The epoxy resin was stirred evenly and then pressed by a roller press to form a film with a thickness of 0.1 mm. The film was then compounded with both sides of the carbon fiber fabric by double-sided lamination (the carbon fiber in the carbon fiber fabric was T700 series and the thickness of the carbon fiber fabric was 0.15 mm) to obtain a carbon fiber prepreg with a thickness of 0.2 mm.

[0092] Seven layers of carbon fiber prepreg are stacked and vacuumed to make the carbon fiber prepregs compacted to obtain a carbon fiber composite. During the vacuuming process, vacuum is applied after stacking 2 to 3 layers of carbon fiber prepreg each time, and the vacuuming pressure is 0.085 MPa for 15 minutes each time.

[0093] The carbon fiber composite is placed in an autoclave for curing to obtain a carbon fiber skeleton; wherein the curing temperature of the carbon fiber composite is 180°C, the curing time is 4 hours, and the curing pressure is 0.4 MPa.

[0094] (2) Preparation of modified low temperature resistant rubber raw rubber layer:

[0095] 20% of low-phenyl silicone rubber, 5% of gas silicone and 1% of compatibilizer (multifunctional vinyl silicone oil) are added to methyl vinyl silicone rubber, mixed evenly and rolled into a sheet-like modified low-temperature resistant rubber raw rubber layer.

[0096] (3) Soaking the carbon fiber skeleton in epoxy resin glue for a period of time, and then stacking modified low-temperature resistant rubber raw rubber layers on both sides of the carbon fiber skeleton to obtain an intermediate; then placing the intermediate in a vulcanizer for vulcanization treatment to obtain a sealing plate sample 1, and the overall thickness of the sealing plate sample 1 is 2 mm; wherein the vulcanization temperature is 160°C, the vulcanization time is 30 minutes, and the vulcanization pressure is 15 MPa.

[0097] Example 2

[0098] (1) Preparation of carbon fiber skeleton:

[0099] The epoxy resin was stirred evenly and then pressed by a roller press to form a film with a thickness of 0.1 mm. The film was then compounded with both sides of the carbon fiber fabric by double-sided lamination (the carbon fiber in the carbon fiber fabric was T700 series and the thickness of the carbon fiber fabric was 0.15 mm) to obtain a carbon fiber prepreg with a thickness of 0.2 mm.

[0100] Seven layers of carbon fiber prepreg are stacked and vacuumed to make the carbon fiber prepregs compacted to obtain a carbon fiber composite. During the vacuuming process, vacuum is applied after stacking 2 to 3 layers of carbon fiber prepreg each time, and the vacuuming pressure is 0.085 MPa for 15 minutes each time.

[0101] The carbon fiber composite is placed in an autoclave for curing to obtain a carbon fiber skeleton; wherein the curing temperature of the carbon fiber composite is 180°C, the curing time is 4 hours, and the curing pressure is 0.4 MPa.

[0102] (2) Preparation of modified low temperature resistant rubber raw rubber layer:

[0103] 2% of dioctyl adipate and 1% of hydrogenated nitrile liquid are added to hydrogenated nitrile rubber, mixed evenly and then rolled into a sheet-like modified low-temperature resistant rubber raw rubber layer.

[0104] (3) Soaking the carbon fiber skeleton in epoxy resin glue for a period of time, and then stacking modified low-temperature resistant rubber raw rubber layers on both sides of the carbon fiber skeleton to obtain an intermediate; then placing the intermediate in a vulcanizer for vulcanization treatment to obtain a sealing plate sample 2, and the overall thickness of the sealing plate sample 2 is 2 mm; wherein the vulcanization temperature is 160°C, the vulcanization time is 30 minutes, and the vulcanization pressure is 15 MPa.

[0105] Comparative Example

[0106] (1) Preparation of carbon fiber skeleton:

[0107] The epoxy resin was stirred evenly and then pressed by a roller press to form a film with a thickness of 0.1 mm. The film was then compounded with both sides of the carbon fiber fabric by double-sided lamination (the carbon fiber in the carbon fiber fabric was T700 series and the thickness of the carbon fiber fabric was 0.15 mm) to obtain a carbon fiber prepreg with a thickness of 0.2 mm.

[0108] Seven layers of carbon fiber prepreg are stacked and vacuumed to make the carbon fiber prepregs compacted to obtain a carbon fiber composite. During the vacuuming process, vacuum is applied after stacking 2 to 3 layers of carbon fiber prepreg each time, and the vacuuming pressure is 0.085 MPa for 15 minutes each time.

[0109] The carbon fiber composite is placed in an autoclave for curing to obtain a carbon fiber skeleton; wherein the curing temperature of the carbon fiber composite is 180°C, the curing time is 4 hours, and the curing pressure is 0.4 MPa.

[0110] (2) The hydrogenated nitrile rubber is rolled into a sheet to obtain a raw rubber sheet; the raw rubber sheets are stacked on both sides of the carbon fiber skeleton (the raw rubber sheet has not been modified, and the carbon fiber skeleton has not been impregnated) to obtain an intermediate; the intermediate is then placed in a vulcanizer for vulcanization to obtain a sealing plate sample 3, and the overall thickness of the sealing plate sample 3 is 2 mm; wherein the vulcanization temperature is 160°C, the vulcanization time is 30 minutes, and the vulcanization pressure is 15 MPa.

[0111] The sealing plate sample 1, sealing plate sample 2 and sealing plate sample 3 were subjected to repeated bending tests (bending angle was ±25°) at -30°C, -40°C and 25°C respectively until the sample was damaged / broken, and the number of bending times of each sample was recorded (the more bending times, the higher the structural strength and the better the fatigue resistance); the test results are shown in the following table:

[0112] Test items Sealing plate sample 1 Sealing plate sample 2 Sealing plate sample 3 Bending times at -30℃ 2000 1500 300 Bending times at -40℃ 650 500 120 Bending times at 25℃ 65000 60000 15000

[0113] It can be seen from the above table that under the temperature conditions of -30°C, -40°C and 25°C, the bending times of sealing plate sample 1 and sealing plate sample 2 are much greater than the bending times of sealing plate sample 3, indicating that the aircraft sealing plates prepared by the method of the present invention have obvious improvements in structural strength and fatigue resistance, whether in a low temperature environment or a normal temperature environment.

[0114] The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art who is familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A method for preparing an aircraft sealing plate, characterized in that: The following steps are involved: S1: preparing a carbon fiber skeleton and a modified low-temperature resistant rubber raw rubber layer; wherein the raw materials for preparing the modified low-temperature resistant rubber raw rubber layer include a rubber masterbatch and a low-temperature resistant modified material; S2: arranging epoxy resin glue on the surface of at least one side of the carbon fiber skeleton, and superimposing the modified low-temperature resistant rubber raw rubber layer on the surface of the carbon fiber skeleton on which the epoxy resin glue is arranged, to obtain an intermediate; S3: vulcanizing the intermediate to obtain an aircraft sealing plate, wherein the modified low-temperature resistant rubber raw rubber layer in the intermediate forms a modified low-temperature resistant rubber layer after vulcanization; wherein the vulcanization temperature of the intermediate is 150°C to 190°C, the vulcanization time is 10 minutes to 60 minutes, and the vulcanization pressure is 15MPa to 20MPa.

2. The method for preparing an aircraft sealing plate according to claim 1, characterized in that: In the above step S1, the rubber masterbatch is methyl vinyl silicone rubber, and the low-temperature resistant modified material includes low-phenyl silicone rubber; wherein the mass of the low-phenyl silicone rubber is 18% to 22% of the mass of the methyl vinyl silicone rubber.

3. The method for preparing an aircraft sealing plate according to claim 2, characterized in that: In the above step S1, the raw materials for preparing the modified low-temperature resistant rubber raw rubber layer also include fillers, and the fillers include gas silica and a compatibilizer; wherein the mass of the gas silica is 4.5% to 5.5% of the mass of the methyl vinyl silicone rubber, and the mass of the compatibilizer is 0.9% to 1.1% of the mass of the methyl vinyl silicone rubber.

4. The method for preparing an aircraft sealing plate according to claim 1, characterized in that: In the above step S1, the rubber masterbatch is hydrogenated nitrile rubber, and the low-temperature resistant modified material includes dioctyl adipate and hydrogenated nitrile liquid; wherein the mass of the dioctyl adipate is 1.8% to 2.2% of the mass of the hydrogenated nitrile rubber, and the mass of the hydrogenated nitrile liquid is 0.9% to 1.1% of the mass of the hydrogenated nitrile rubber.

5. The method for preparing an aircraft sealing plate according to claim 1, characterized in that: In the above step S1, the steps of preparing the carbon fiber skeleton include: (1) pressing epoxy resin or bismaleimide resin to form a film, and placing the film on both sides of the carbon fiber fabric to obtain a carbon fiber prepreg; (2) stacking multiple layers of the carbon fiber prepreg and performing a vacuum treatment on the multiple layers of the carbon fiber prepreg to obtain a carbon fiber composite; (3) placing the carbon fiber composite in an autoclave for curing to obtain the carbon fiber skeleton; wherein the curing temperature of the carbon fiber composite is 150°C to 185°C, the curing time is 3 hours to 7 hours, and the curing pressure is 0.3 MPa to 0.6 MPa.

6. The method for preparing an aircraft sealing plate according to claim 1, characterized in that: In the above step S1, the steps of preparing the modified low-temperature resistant rubber raw rubber layer include: The raw materials for preparing the modified low-temperature resistant rubber raw rubber layer are mixed uniformly to obtain a mixture; the mixture is rolled to form a sheet structure, thereby obtaining the modified low-temperature resistant rubber raw rubber layer.

7. The method for preparing an aircraft sealing plate according to claim 1, characterized in that: In the above step S2, the epoxy resin glue is disposed on the surface of one side of the carbon fiber skeleton, and the surface of the carbon fiber skeleton on the side where the epoxy resin glue is disposed is superimposed with the modified low-temperature resistant rubber raw rubber layer; Alternatively, the epoxy resin glue is disposed on surfaces on two opposite sides of the carbon fiber skeleton, and the surfaces on two opposite sides of the carbon fiber skeleton are both superimposed with the modified low-temperature resistant rubber raw rubber layer.

8. The method for preparing an aircraft sealing plate according to claim 1, characterized in that: In the above step S2, two modified low-temperature resistant rubber raw rubber layers are superimposed on the surface of at least one side of the carbon fiber skeleton, and a reinforcing layer is sandwiched between the two modified low-temperature resistant rubber raw rubber layers; the reinforcing layer is obtained by immersing the reinforcing cloth in an adhesive.

9. The method for preparing an aircraft sealing plate according to any one of claims 1 to 8, characterized in that: In the above step S3, after the intermediate is vulcanized, a wear-resistant coating is provided on the surface of at least one side of the intermediate.

10. An aircraft sealing plate, characterized in that: The aircraft sealing plate is manufactured by the preparation method of any one of claims 1 to 9; the aircraft sealing plate comprises a carbon fiber skeleton and a modified low-temperature resistant rubber layer arranged on at least one side surface of the carbon fiber skeleton.

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