Composite cabin wall board and preparation method thereof

Abstract

The invention discloses a composite cabin wall board and a preparation method thereof, and belongs to the technical field of cabin wall boards, and the preparation method comprises the following steps: performing blanking pretreatment on an inner skin, an outer skin and a framework for later use; the frameworks are filled with aerogel, and then the multiple frameworks are spliced and fixed through the inserting pieces to form a framework enclosure frame; the bonding surface of the inner skin and the bonding surface of the outer skin are coated with a toughening type epoxy resin adhesive in a brushing mode, then the inner skin and the outer skin are laid on the bonding surface of the framework enclosure frame, an inner cavity of the framework enclosure frame is filled with aerogel, and then the framework enclosure frame is fed into a hot press to be subjected to hot press forming; and spraying a polyurea elastomer coating on the outer surface of the outer skin subjected to hot press molding to obtain a finished product of the composite cabin wall board. According to the invention, the thermal insulation, water resistance, corrosion resistance and stone impact resistance of the cabin can be improved, good elasticity can be maintained under extreme weather conditions, and the cabin does not pulverize, crack and fall off after long-term use.

Description

Technical Field

[0001] The invention relates to the technical field of cabin wall panels, and in particular to a composite cabin wall panel and a preparation method thereof. Background Art

[0002] With the development of electronic technology, more and more advanced and complex electronic equipment such as communication systems, command and control systems, etc. are installed in square cabins. As an important part of the square cabin, the cabin wall panels provide a loading platform and a suitable working environment for the equipment in the cabin. However, the cabin wall panels of traditional square cabins are metal-skinned polyurethane foam sandwich structures with poor thermal insulation, which increases the load on the air conditioning in the cabin. Moreover, the environment at the bottom of the square cabin is harsh and vulnerable to stone impacts. The paint layer of the metal wall panels is easily damaged, and the skin is corroded and perforated, causing the cabin wall panels to fail. Summary of the invention

[0003] The main purpose of the present invention is to solve the above-mentioned technical problems to a certain extent, and to propose a composite cabin wall panel and a preparation method thereof, which can improve the cabin's thermal insulation, waterproof, corrosion resistance, and stone impact resistance performance, maintain good elasticity under extreme climatic conditions, and will not powder, crack, or fall off after long-term use.

[0004] On the one hand, a composite cabin wall panel is proposed, comprising a frame, an inner skin layer, an outer skin layer and an anti-stone impact layer, wherein a plurality of the frame members are fixedly connected by means of plug-ins, the inner skin layer and the outer skin layer are glued to the inner and outer surfaces of the frame frame by means of an adhesive layer, and an aerogel layer is filled in the inner cavity between two adjacent frame members to form a frame frame, and the anti-stone impact layer is arranged on the outer surface of the outer skin layer.

[0005] In some embodiments, the skeleton is a carbon fiber rectangular tube with a wall thickness of 1.5 mm.

[0006] In some embodiments, the inner skin layer is made of 0.8 mm high-strength carbon fiber plate.

[0007] In some embodiments, the outer skin layer is made of 1.2 mm high-strength carbon fiber plate.

[0008] On the one hand, a method for preparing a composite cabin wall panel is proposed, comprising the following steps: a) Cut the inner skin and outer skin according to the outer dimensions of the cabin wall panel, and then grind the bonding surfaces of the cut inner skin and outer skin for later use; b) Cutting the frame according to the dimensions of the cabin wall panel, and then grinding the bonding surface of the frame for bonding with the inner skin and the outer skin for later use; c) filling the inside of the skeleton with aerogel, and then splicing and fixing multiple skeletons through plug-ins to form a skeleton frame; d) Apply toughened epoxy resin adhesive on the bonding surface of the inner skin and the outer skin, and the amount of adhesive is controlled at 260-300 g / m2, and then the inner skin and the outer skin are laid on the bonding surface of the skeleton frame, and the aerogel is filled in the inner cavity of the skeleton frame, and then sent to a hot press for hot pressing; e) spraying a polyurea elastomer coating on the outer surface of the hot-pressed outer skin to obtain a finished composite cabin wall panel.

[0009] In some embodiments, the aerogel uses a flame retardant aerogel felt with a density of 0.22±0.03g / cm³.

[0010] In some embodiments, both the inner skin and the outer skin are formed by heat-pressing and curing multiple layers of carbon fiber prepreg, wherein the thickness of each layer of carbon fiber prepreg is 0.16 mm.

[0011] In some embodiments, the skeleton is made into a rectangular tube structure by a weaving molding process, and the inner surface of the skeleton is coated with an interface agent before filling the aerogel.

[0012] In some embodiments, when grinding the inner skin, outer skin and frame, use 240-grit sandpaper to evenly grind until they are evenly matte, then use compressed air to blow away the remaining dust, and then use a 1:1 mixture of isopropyl alcohol and anhydrous ethanolamine to clean them, and dry them at room temperature for more than 15 minutes for use.

[0013] In some embodiments, the gap between the outer diameter of the plug and the inner diameter of the frame is 0.1 mm, and the plug and the frame are bonded by double-sided gluing using a toughened epoxy resin adhesive, wherein the total amount of adhesive is 100 to 150 g / m².

[0014] In some embodiments, the toughening agent content in the toughened epoxy resin adhesive is 5%.

[0015] In some embodiments, during the hot pressing process, the molding pressure is 0.2-0.3 MPa, the molding temperature is 125±5°C, the molding time is 1.5-2h, the heating rate is 1-2°C / min, and the cooling rate is 2-3°C / min.

[0016] In some embodiments, when spraying the polyurea elastomer coating, the temperature in the spraying room is ≥15°C at room temperature; the relative humidity in the spraying room is less than 75%; the pressure of the spraying compressed air source is 0.70~0.80MPa; and the polyurea elastomer coating is heated to 70~75°C for spraying.

[0017] In some embodiments, the polyurea elastomer coating comprises component A and component B, the mass ratio of component A to component B is 1:1, component A is a mixture of polyether polyol and amino-terminated polyether, and component B is polyisocyanate.

[0018] The above technical solution provided by this application has the following advantages compared with the prior art: The present invention combines an inner skin and an outer skin made of high-strength carbon fiber composite materials with a frame, so that the overall wall panel has the characteristics of lightness and high strength, improves the load-bearing capacity and stability of the wall panel, is suitable for the special requirements of military vehicle cabins, and at the same time provides good mechanical strength support and protection of the internal sandwich layer.

[0019] The filling of the aerogel of the present invention provides excellent thermal insulation performance for the entire wall panel, reduces the load of the air conditioner in the cabin, improves the thermal insulation efficiency of the cabin, and contributes to energy conservation and emission reduction.

[0020] The use of the toughened epoxy resin adhesive layer of the present invention ensures a firm bond between the inner skin and the outer skin, improves the overall performance and reliability of the wall panel, and at the same time, the skeleton frame formed by the skeleton connected by plug-ins and bonded with the toughened epoxy resin adhesive further enhances the structural strength and stability of the wall panel.

[0021] The invention sprays a polyurea elastomer coating on the outer surface of the outer skin so that the wallboard has high impact resistance and high wear resistance, effectively resists stone impact, protects the cabin from damage, and prolongs the service life of the cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0023] Figure 1 The process flow chart of the composite cabin wall panel preparation method of the present invention is as follows; Figure 2 It is a structural diagram of the composite cabin wall panel of the present invention.

[0024] Reference numerals: 1-skeleton; 2-inner skin layer; 3-outer skin layer; 4-anti-stone impact layer; 5-adhesive layer; 6-aerogel layer. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0027] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features limited to "first" and "second" may explicitly or implicitly include at least one of the features. In addition, if "and / or" or "and / or" appears in the full text, its meaning includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, solution B, or solutions that satisfy both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0028] like Figure 1 As shown, the present invention proposes a method for preparing a composite cabin wall panel, comprising the following steps: a) Cut the inner skin and outer skin according to the outer dimensions of the cabin hull panel. Both the inner skin and outer skin are made of multiple layers of carbon fiber prepreg cured by hot pressing, wherein the thickness of each layer of carbon fiber prepreg is 0.16 mm, the inner skin layer is a 0.8 mm high-strength carbon fiber plate, and the outer skin layer is a 1.2 mm high-strength carbon fiber plate. Then, the bonding surfaces of the cut inner skin and outer skin are polished for standby use.

[0029] Furthermore, when grinding the inner and outer skins, use 240-grit sandpaper to evenly grind until the gloss is evenly lost, then use compressed air to blow away the remaining dust, and then use a solvent mixed with isopropyl alcohol and anhydrous ethanolamine in a ratio of 1:1 to clean, and dry at room temperature for more than 15 minutes for use.

[0030] b) Cut the frame according to the external dimensions of the cabin hull panel, the frame adopts a carbon fiber rectangular tube with a wall thickness of 1.5 mm, and then grind the bonding surface of the frame for bonding with the inner skin and the outer skin for use; when grinding the frame, use 240-grit sandpaper to evenly grind until it loses gloss evenly, then blow away the remaining dust with compressed air, and then clean it with a solvent mixed with isopropyl alcohol and anhydrous ethanolamine in a ratio of 1:1, and dry it at room temperature for more than 15 minutes for use.

[0031] c) filling the inside of the skeleton with aerogel, and then splicing and fixing multiple skeletons through plug-ins to form a skeleton frame. The skeleton is made into a rectangular tube structure through a weaving molding process, and before filling the aerogel, the inner surface of the skeleton is coated with an interface agent to facilitate the adhesion of the aerogel to the inner wall of the skeleton.

[0032] d) Apply toughened epoxy resin adhesive on the bonding surface of the inner skin and the outer skin, and control the amount of adhesive to be 260-300g / m2. Then lay the inner skin and the outer skin on the bonding surface of the skeleton frame, and fill the inner cavity of the skeleton frame with aerogel, wherein the aerogel adopts a flame-retardant aerogel felt with a density of 0.22±0.03g / cm³ and a thermal conductivity of less than 0.018W / (m·K). The filling of aerogel provides excellent thermal insulation performance for the whole wall panel, reduces the load of the air conditioner in the cabin, improves the thermal insulation efficiency of the cabin, and contributes to energy conservation and emission reduction. Subsequently, the wall panel is sent to a hot press for hot pressing. The application of hot pressing process ensures the molding quality and dimensional accuracy of the wall panel, and improves the production efficiency and consistency of the wall panel.

[0033] Exemplarily, during the hot pressing process, the molding pressure is 0.2-0.3 MPa, the molding temperature is 125±5° C., the molding time is 1.5-2 h, and the heating rate is 1-2° C. / min, and the cooling rate is 2-3° C. / min.

[0034] e) spraying a polyurea elastomer coating on the outer surface of the outer skin after hot pressing to obtain a finished composite cabin wall panel, the polyurea elastomer coating comprises component A and component B, the mass ratio of component A to component B is 1:1, the component A is a mixture of polyether polyol and terminal amino polyether, the component B is polyisocyanate, and the polyurea elastomer coating makes the wall panel have high impact resistance and high wear resistance, effectively resists stone impact, protects the cabin from damage, and extends the service life of the cabin.

[0035] Exemplarily, when spraying the polyurea elastomer coating, the temperature in the spraying room is ≥15°C at room temperature; the relative humidity in the spraying room is less than 75%; the pressure of the spraying compressed air source is 0.70~0.80MPa; the polyurea elastomer coating is heated to 70~75°C for spraying, and the use of high-pressure airless spraying equipment ensures the uniform spraying of the polyurea elastomer coating, improves the quality and adhesion of the coating, and enhances the stone impact resistance of the siding.

[0036] like Figure 2As shown, the cabin wall panel prepared by the preparation method includes a skeleton 1, an inner skin layer 2, an outer skin layer 3 and an anti-stone impact layer 4, and multiple skeletons 1 are fixedly connected by a set plug-in, and the inner skin layer 2 and the outer skin layer 3 are glued to the inner and outer surfaces of the skeleton 1 frame by a set adhesive layer 5, and the adhesive layer 5 adopts a toughened epoxy resin adhesive, and the inner cavity between two adjacent skeletons 1 is filled with an aerogel layer 6 to form a skeleton 1 frame, and the anti-stone impact layer 4 is arranged on the outer surface of the outer skin layer 3, wherein the anti-stone impact layer 4 is a sprayed polyurea elastomer coating; by combining the inner skin and outer skin made of high-strength carbon fiber composite materials with the skeleton 1, the wall panel as a whole has the characteristics of light weight and high strength, and the bearing capacity and stability of the wall panel are improved, which is suitable for the special requirements of military vehicle cabins, and at the same time provides good mechanical strength support and protection of the internal sandwich layer.

[0037] In another embodiment, during the preparation of the composite cabin wall panel, the gap between the outer diameter of the plug-in and the inner diameter of the frame is 0.1 mm, and the plug-in and the frame are bonded by a toughened epoxy resin adhesive using a double-sided gluing method on the bonding surface. The content of the toughening agent in the toughened epoxy resin adhesive is 5%, and the double-sided gluing method is used on the bonding surface to promptly clean up the adhesive overflowed during the plug-in, wherein the total amount of adhesive is 100 to 150 g / m².

[0038] Furthermore, the use of a toughened epoxy resin adhesive layer during bonding ensures a strong bond between the inner skin and the outer skin, thereby improving the overall performance and reliability of the wall panels. At the same time, the skeleton frame formed by the skeleton connected by plug-ins and bonded with the toughened epoxy resin adhesive further enhances the structural strength and stability of the wall panels.

[0039] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A composite cabin wall panel, characterized in that: It includes a skeleton, an inner skin layer, an outer skin layer and an anti-stone impact layer. The multiple skeletons are fixedly connected by a plug-in. The inner skin layer and the outer skin layer are glued to the inner and outer surfaces of the skeleton frame by an adhesive layer. An aerogel layer is filled in the inner cavity between two adjacent skeletons to form a skeleton frame. The anti-stone impact layer is arranged on the outer surface of the outer skin layer.

2. A method for preparing a composite cabin wall panel, characterized in that: The following steps are involved: a) Cut the inner skin and outer skin according to the outer dimensions of the cabin wall panel, and then grind the bonding surfaces of the cut inner skin and outer skin for later use; b) Cutting the frame according to the dimensions of the cabin wall panel, and then grinding the bonding surface of the frame for bonding with the inner skin and the outer skin for later use; c) filling the inside of the skeleton with aerogel, and then splicing and fixing multiple skeletons through plug-ins to form a skeleton frame; d) applying toughened epoxy resin adhesive on the bonding surface of the inner skin and the outer skin, laying the inner skin and the outer skin on the bonding surface of the skeleton frame, filling the inner cavity of the skeleton frame with aerogel, and then sending it into a hot press for hot pressing; e) spraying a polyurea elastomer coating on the outer surface of the hot-pressed outer skin to obtain a finished composite cabin wall panel.

3. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: Both the inner skin and the outer skin are made of multiple layers of carbon fiber prepreg that are cured by hot pressing, wherein the thickness of each layer of carbon fiber prepreg is 0.16 mm.

4. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: The skeleton is made into a rectangular tube structure through a weaving molding process, and the inner surface of the skeleton is coated with an interface agent before filling the aerogel.

5. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: When grinding the inner skin, outer skin and frame, use 240-grit sandpaper to evenly grind until they lose gloss evenly, then use compressed air to blow away the remaining dust, and then use a solvent mixed with isopropyl alcohol and anhydrous ethanolamine in a ratio of 1:1 to clean them, and dry them at room temperature for more than 15 minutes for use.

6. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: The gap between the outer diameter of the plug-in and the inner diameter of the frame is 0.1 mm, and the plug-in and the frame are bonded by double-sided gluing using a toughened epoxy resin adhesive, wherein the total amount of adhesive is 100-150 g / m².

7. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: The content of toughening agent in the toughened epoxy resin adhesive is 5%.

8. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: During the hot pressing process, the molding pressure is 0.2-0.3 MPa, the molding temperature is 125±5°C, the molding time is 1.5-2h, the heating rate is 1-2°C / min, and the cooling rate is 2-3°C / min.

9. The method for preparing a composite cabin wall panel according to claim 2, characterized in that: When spraying polyurea elastomer coating, the temperature of the spraying room is ≥15℃ at room temperature; the relative humidity of the spraying room is less than 75%; the pressure of the spraying compressed air source is 0.70~0.80MPa; the polyurea elastomer coating is heated to 70~75℃ for spraying.

10. The method for preparing a composite cabin wall panel according to claim 9, characterized in that: The polyurea elastomer coating comprises component A and component B, wherein the mass ratio of component A to component B is 1:1, the component A is a mixture of polyether polyol and amino-terminated polyether, and the component B is polyisocyanate.

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