Composite material pre-impregnated plate and composite material part
By introducing a pulling layer into the composite prepreg plate, covering the wrinkle area during the forming of the thermal insulation film and contacting the diaphragm, the problem of wrinkles caused by insufficient interlayer slip during the forming of the thermal insulation film is solved, and the molding quality and mechanical properties of the parts are improved.
Patent Information
- Application Number
- CN202422234051.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-12
- Publication Date
- 2025-06-20
- Estimated Expiration
- 2034-09-12
AI Technical Summary
During the thermal insulation molding process, composite parts with larger thickness or more complex structures may wrinkle due to insufficient slipping capacity of the interlayer prepreg, which affects the mechanical properties of the parts and may lead to the scrapping of the parts.
A composite prepreg plate is employed, which includes a pulling layer and several prepreg layers, the pulling layer is connected to at least one prepreg layer and covers the wrinkle area when the thermal diaphragm is formed, and the other end is in contact with the diaphragm member to enhance the traction force and interlayer slip capability of the prepreg layer.
Effectively control the wrinkles of the prepreg layer during the forming of the thermal insulation film, improve the molding quality of the parts, enhance the stress and slip capacity of the prepreg layer, and avoid the scrapping of the parts due to wrinkles.
Smart Images
Figure CN223001212U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of composite material forming, in particular to a composite material prepreg board and a composite material part. Background Art
[0002] With the extensive use of composite materials in the aviation field, the hot diaphragm forming process method has gradually been widely applied in composite material manufacturing. The hot diaphragm forming process is to place the laid prepreg laminate on the tooling, heat the laminate to a preset temperature, and apply pressure to the diaphragm and the laminate by means of vacuum pumping, so that the diaphragm drives the material layer to gradually bend and close to the tooling during the deformation process until the sheet completely fits the tooling surface.
[0003] During the hot diaphragm forming process, the diaphragm only directly contacts the surface prepreg. For example, in the case of a single diaphragm, the diaphragm only contacts the prepreg on the side away from the tooling, and in the case of a double diaphragm, the diaphragm only contacts the prepreg on the side away from the tooling and the side in contact with the tooling. Therefore, in addition to the surface prepreg being directly affected by the traction force of the diaphragm, the bending of the remaining material layers mainly depends on the gradual transmission of the traction force and the interlayer slip between the prepregs. For parts with a larger thickness or a more complex structure, wrinkles may occur due to insufficient interlayer slip ability of the prepregs, which will affect the mechanical properties of the parts and may even lead to the scrapping of the parts in severe cases. At present, the methods for controlling wrinkles in hot diaphragm forming mainly focus on adjusting process parameters such as temperature, pressure, and time of hot diaphragm forming. For parts with complex configurations, the existing methods sometimes have limited effects and at the same time cause waste of costs in terms of materials, cycle, and labor.
[0004] Therefore, there is an urgent need to provide a new type of composite material prepreg board and a composite material part to solve the above technical problems in the prior art. Summary of the Utility Model
[0005] The purpose of the utility model is to provide a composite material prepreg board, which can effectively control the wrinkles of the prepreg layer during hot diaphragm forming, can increase the stress area of the composite material prepreg board, improve the stress of the prepreg layer during the hot diaphragm forming process, enhance the interlayer slip ability of the prepreg layer, and improve the forming quality of the final part.
[0006] To achieve the above object, the utility model adopts the following technical solutions:
[0007] The prepreg plate of the composite material comprises a traction layer and a plurality of prepreg layers. The plurality of prepreg layers are stacked along a first direction. When the prepreg plate of the composite material is formed by hot diaphragm, at least one of the prepreg layers will wrinkle to form a wrinkled area. The traction layer is connected to at least one of the prepreg layers. One end of the traction layer along a second direction can at least cover the wrinkled area, and the other end extends out of the prepreg layer and can contact the diaphragm during hot diaphragm forming. The second direction is perpendicular to the first direction.
[0008] Optionally, the Nth prepreg layer counted from top to bottom along the first direction will wrinkle during hot diaphragm forming, and the traction layer is connected to the Nth prepreg layer.
[0009] Optionally, the traction layer is sandwiched between the Nth prepreg layer and the (N - 1)th prepreg layer, or the traction layer is sandwiched between the Nth prepreg layer and the (N + 1)th prepreg layer.
[0010] Optionally, the traction layer is integrally formed with the Nth prepreg layer.
[0011] Optionally, there are two traction layers, and the two traction layers are respectively arranged at both ends of the Nth prepreg layer along the second direction.
[0012] Optionally, the fiber direction of the traction layer is parallel or perpendicular to the fiber direction of the Nth prepreg layer.
[0013] Optionally, the thickness of the traction layer is not less than the thickness of the prepreg layer.
[0014] Optionally, the traction layer and the prepreg layer are made of the same material.
[0015] Optionally, the size of the wrinkled area along a third direction is L, and the size of the traction layer along the third direction is L', where L' > L. The first direction, the second direction, and the third direction are perpendicular to each other pairwise.
[0016] Another object of the present utility model is to provide a composite material part, which is obtained by hot diaphragm forming from the prepreg plate of the composite material according to any one of the above solutions.
[0017] Beneficial effects:
[0018] In the composite material prepreg board of the present utility model, by providing a traction layer in at least one of several prepreg layers, the traction layer covers the wrinkled area on the prepreg layer, and the other end of the traction layer extends out of the prepreg layer and can contact the diaphragm during thermo-diaphragm forming. During thermo-diaphragm forming, the diaphragm can not only provide traction force to the topmost prepreg layer, but also apply traction force to the traction layer, so that the traction layer applies traction force to the prepreg layer connected to it, thereby increasing the traction force between the prepreg layers and avoiding wrinkles in the prepreg layer. This composite material prepreg board can increase the force-bearing area of the composite material prepreg board, improve the force on the prepreg layer during the thermo-diaphragm forming process, enhance the interlayer slip ability of the prepreg layer, effectively control the wrinkles of the prepreg layer during thermo-diaphragm forming, and improve the forming quality of the final part. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 is a schematic diagram of a composite material part provided by a specific embodiment of the present utility model;
[0020] Figure 2 is a longitudinal sectional view of the wrinkled area after thermo-diaphragm forming of a composite material prepreg board provided by the prior art;
[0021] Figure 3 is a top view of a composite material prepreg board provided by a specific embodiment of the present utility model;
[0022] Figure 4 is a longitudinal sectional view of a composite material prepreg board provided by a specific embodiment of the present utility model.
[0023] In the figure:
[0024] 10. Prepreg layer; 11. Wrinkled area; 20. Traction layer; 30. Diaphragm. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0025] The present utility model will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the present utility model, rather than limiting the present utility model. In addition, it should be noted that for the sake of description, only parts related to the present utility model are shown in the drawings, not all structures.
[0026] In the description of the present utility model, unless otherwise clearly defined and limited, the terms "connected", "connected to", and "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.
[0027] In the present utility model, unless otherwise clearly specified and defined, the first feature being "above" or "below" the second feature may include the direct contact between the first and second features, or may also include the situation where the first and second features are not in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over" and "on the top of" the second feature includes that the first feature is directly above and obliquely above the second feature, or merely indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "below", "under" and "beneath" the second feature includes that the first feature is directly below and obliquely below the second feature, or merely indicates that the horizontal height of the first feature is lower than that of the second feature.
[0028] In the description of this embodiment, the orientation or positional relationships such as "above", "below", "right", etc. are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of description and simplifying the operation, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.
[0029] The first direction described in this embodiment is Figure 4 the X direction shown in Figure 3 and Figure 4 also the thickness direction of the composite material prepreg; the second direction is Figure 1 and Figure 3 the Y direction shown in
[0030] Please refer to Figure 1 and Figure 2 When the composite material prepreg in the prior art is formed by hot diaphragm, one or more of the prepreg layers 10 may have wrinkles in the prepreg layer 10 and a wrinkle area 11 due to insufficient slip force between layers, reducing the quality of the subsequent formed composite parts. To solve the above technical problems, please refer to Figure 3 and Figure 4 This embodiment provides a novel composite material prepreg.
[0031] In this embodiment, the composite material prepreg plate includes a traction layer 20 and several prepreg layers 10. The several prepreg layers 10 are stacked along a first direction. When the composite material prepreg plate is formed by hot diaphragm, at least one of the prepreg layers 10 will have wrinkles and form a wrinkled area 11; the traction layer 20 is connected to at least one of the prepreg layers 10. One end of the traction layer 20 along a second direction can at least cover the wrinkled area 11, and the other end extends out of the prepreg layer 10 and can contact a diaphragm member 30 during hot diaphragm forming. The second direction is perpendicular to the first direction.
[0032] By arranging the traction layer 20 on at least one of the several prepreg layers 10 of the composite material prepreg plate, the traction layer 20 covers the wrinkled area 11 on the prepreg layer 10, and the other end of the traction layer 20 extends out of the prepreg layer 10 and can contact the diaphragm member 30 during hot diaphragm forming. During hot diaphragm forming, the diaphragm member 30 can not only provide a traction force to the uppermost prepreg layer 10, but also apply a traction force to the traction layer 20, so that the traction layer 20 applies a traction force to the prepreg layer 10 connected thereto, thereby increasing the traction force between the prepreg layers 10 and avoiding wrinkles in the prepreg layers 10. The composite material prepreg plate can increase the force-bearing area of the composite material prepreg plate, improve the force on the prepreg layer 10 during the hot diaphragm forming process, enhance the interlayer slip ability of the prepreg layer 10, effectively control the wrinkles of the prepreg layer 10 during hot diaphragm forming, and improve the forming quality of the final part.
[0033] In this embodiment, as Figure 2 and Figure 4 shown, the Nth prepreg layer 10 counted from top to bottom along the first direction will have wrinkles during hot diaphragm forming, and the traction layer 20 is connected to the Nth prepreg layer 10. During specific operation, according to the product structure of the composite material prepreg plate without the traction layer 20 after hot diaphragm forming, it is analyzed that the Nth prepreg layer 10 is prone to wrinkles. In subsequent production processes, the traction layer 20 can be arranged on the Nth prepreg layer 10 to avoid wrinkles in the Nth prepreg layer 10. The Nth prepreg layer 10 mentioned here does not specifically refer to a certain layer, and can be the 2nd layer, 3rd layer, 4th layer, etc. As long as there are wrinkles, the traction layer 20 can be arranged.
[0034] As Figure 3 shown, the dimension of the wrinkled area 11 along a third direction is L, and the dimension of the traction layer 20 along the third direction is L', and L' > L. The first direction, the second direction, and the third direction are perpendicular to each other pairwise. Since the dimension of the traction layer 20 along the third direction is greater than the dimension of the wrinkled area 11 along the third direction, the traction layer 20 can completely cover the wrinkled area 11, ensuring that the wrinkled area 11 will not have wrinkles after hot diaphragm forming and improving the forming quality.
[0035] Furthermore, the dimension of the pulling layer 20 in the second direction is W, and the value of W is not specifically limited as long as the pulling layer 20 can contact the diaphragm member 30 after extending out of the prepreg layer 10, which will not be elaborated here.
[0036] It should be noted that the above-mentioned pulling layer 20 is integrally formed with the Nth layer of the above-mentioned prepreg layer 10. That is, the pulling layer 20 is a convex area formed after the size of the prepreg layer 10 is enlarged in the wrinkled area 11, and it can also apply a pulling force to the prepreg layer 10 after contacting the diaphragm member 30. Compared with the method of arranging the pulling layer 20 on the upper and lower surfaces of the Nth layer of the above-mentioned prepreg layer 10, its manufacturing process is simpler and can provide a greater pulling force, but the amount of composite material used and the cost will increase. Those skilled in the art can select according to specific requirements, which will not be elaborated here.
[0037] Please continue to refer to Figure 3 and Figure 4 As shown above, two pulling layers 20 are provided, and the two pulling layers 20 are respectively arranged at both ends of the Nth layer of the above-mentioned prepreg layer 10 along the second direction. The two pulling layers 20 can perform traction from both ends of the prepreg layer 10 along the second direction, flatten the prepreg layer 10 from both ends to form a shape, further avoid the generation of wrinkles and improve the forming quality.
[0038] Optionally, the fiber direction of the above-mentioned pulling layer 20 is parallel or perpendicular to the fiber direction of the Nth layer of the above-mentioned prepreg layer 10. In this embodiment, the prepreg layer 10 has three fiber directions of 0°, 45°, and 90°. Specifically, the prepreg layer 10 with a fiber direction of 0° will have wrinkles. The fiber direction of the pulling layer 20 can be selected as 0° or 90°, and both can apply the required pulling force to the prepreg layer 10. The pulling force is more balanced and stable, and the direction of the pulling force can be along the second direction, further avoiding the generation of wrinkles.
[0039] Furthermore, as Figure 4 shown, the above-mentioned pulling layer 20 is sandwiched between the Nth layer of the above-mentioned prepreg layer 10 and the (N - 1)th layer of the above-mentioned prepreg layer 10, or the above-mentioned pulling layer 20 is sandwiched between the Nth layer of the above-mentioned prepreg layer 10 and the (N + 1)th layer of the above-mentioned prepreg layer 10. That is, the pulling layer 20 can be arranged on the upper surface or the lower surface of the Nth layer of the above-mentioned prepreg layer 10, and both can apply a pulling force to the prepreg layer 10 to improve the quality of the thermal diaphragm forming and reduce the generation of wrinkles.
[0040] In this embodiment, the thickness of the above-mentioned pulling layer 20 is not less than the thickness of the prepreg layer 10. Such a setting enables the pulling layer 20 to avoid being torn during the traction process when pulling the prepreg layer 10, ensuring that the pulling layer 20 can provide sufficient pulling force.
[0041] Furthermore, the above-mentioned tension layer 20 and the above-mentioned prepreg layer 10 are made of the same material. Such an arrangement enables the tension layer 20 to directly select materials and be cut and formed from the prepreg layer 10 during production, or be integrally formed from the prepreg layer 10, reducing production costs and production process steps.
[0042] Another object of the present utility model is to provide a composite material part, which is obtained by thermo-diaphragm forming from the composite material prepreg board described in any of the above solutions. Specifically, as Figure 1 shown, the composite material part is a C-shaped beam, and its forming process includes:
[0043] 1) First, select the prepreg layer 10 that will have wrinkles: The C-shaped beam will generate a wrinkle area 11 in the area shown as Figure 1 shown. Among them, the prepreg layers 10 of the 17th layer and the 48th layer have the most serious wrinkling. Therefore, the above-mentioned tension layer 20 needs to be provided between the 17th layer and the 18th layer, and between the 47th layer and the 48th layer;
[0044] 2) Stack along the first direction and complete the laying of all prepreg layers 10;
[0045] 3) Prepare the tension layer 20, and place the prepared tension layer 20 between the 17th layer and the 18th layer, and between the 47th layer and the 48th layer to obtain the required composite material prepreg board;
[0046] 4) Place the laid composite material prepreg board between the thermo-diaphragm forming tooling and the diaphragm member 30, and carry out preforming by using the thermo-diaphragm forming process. Among them, the uppermost prepreg layer 10 and the tension layer 20 are in direct contact with the diaphragm member 30 during the forming process. The diaphragm member 30 will extend and generate a traction tension under the vacuum pressure, and the tension is directly applied to the prepreg layer 10 connected to the tension layer 20, improving the slip ability of the prepreg layer 10 and reducing the generation of wrinkles.
[0047] Obviously, the above-mentioned embodiments of the present utility model are merely examples for clearly explaining the present utility model, rather than limitations on the implementation manners of the present utility model. For those of ordinary skill in the art, various obvious changes, re-adjustments and substitutions can be made without departing from the protection scope of the present utility model. It is not necessary and impossible to enumerate all the implementation manners here. Any modifications, equivalent substitutions and improvements made within the spirit and principle of the present utility model shall be included within the protection scope of the claims of the present utility model.
Claims
1. Composite material prepreg board, characterized in that: include: A plurality of prepreg layers (10), wherein the plurality of prepreg layers (10) are stacked along a first direction, wherein when the composite material prepreg plate is formed by a thermal diaphragm, at least one of the prepreg layers (10) will be wrinkled and produce a wrinkle area (11); A pulling layer (20), wherein the pulling layer (20) is connected to at least one layer of the prepreg layer (10), one end of the pulling layer (20) along a second direction can at least cover the wrinkle area (11), and the other end extends out of the prepreg layer (10) and can contact the diaphragm member (30) during thermal diaphragm molding, and the second direction is perpendicular to the first direction.
2. The composite material prepreg board according to claim 1, characterized in that: The Nth prepreg layer (10) counted from top to bottom along the first direction will have wrinkles during thermal insulation molding, and the pulling layer (20) is connected to the Nth prepreg layer (10).
3. The composite material prepreg board according to claim 2, characterized in that: The pulling layer (20) is sandwiched between the Nth prepreg layer (10) and the N-1th prepreg layer (10), or the pulling layer (20) is sandwiched between the Nth prepreg layer (10) and the N+1th prepreg layer (10).
4. The composite material prepreg board according to claim 2, characterized in that: The pulling layer (20) and the Nth prepreg layer (10) are integrally formed.
5. The composite material prepreg board according to claim 2, characterized in that: Two pulling layers (20) are provided, and the two pulling layers (20) are respectively arranged at two ends of the Nth prepreg layer (10) along the second direction.
6. The composite material prepreg board according to claim 2, characterized in that: The fiber direction of the pulling layer (20) is parallel or perpendicular to the fiber direction of the Nth prepreg layer (10).
7. The composite material prepreg board according to claim 6, characterized in that: The thickness of the pulling layer (20) is not less than the thickness of the prepreg layer (10).
8. The composite material prepreg board according to claim 6, characterized in that: The pulling layer (20) and the prepreg layer (10) are made of the same material.
9. The composite material prepreg board according to any one of claims 1 to 8, characterized in that: The dimension of the folded area (11) along the third direction is L, the dimension of the pulling layer (20) along the third direction is L', L'>L, and the first direction, the second direction and the third direction are perpendicular to each other.
10. A composite material part, characterized in that: The composite material prepreg plate according to any one of claims 1 to 9 is produced by hot diaphragm molding.