CN112454938A - Forming method of carbon fiber honeycomb sandwich composite material member - Google Patents
Forming method of carbon fiber honeycomb sandwich composite material member Download PDFInfo
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- CN112454938A CN112454938A CN202011065170.XA CN202011065170A CN112454938A CN 112454938 A CN112454938 A CN 112454938A CN 202011065170 A CN202011065170 A CN 202011065170A CN 112454938 A CN112454938 A CN 112454938A
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- honeycomb core
- carbon fiber
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- composite material
- lower skin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
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Abstract
The invention provides a forming method suitable for a carbon fiber honeycomb sandwich composite material component, which comprises the following steps of firstly, processing a honeycomb core material blank to a required shape profile; then paving an adhesive film on the outer surface of the honeycomb core, and precuring to obtain a honeycomb core prefabricated member; then, laying and pasting prepreg of the lower skin, compacting the packaged vacuum bag after laying and pasting, and placing the honeycomb core prefabricated member in a corresponding area after compacting to enable the honeycomb core prefabricated member to be pasted with the lower skin; and then paving and pasting the upper skin prepreg, packaging the vacuum bag after paving and pasting for integral co-curing molding, and demolding to obtain the corresponding carbon fiber sandwich composite material component. The invention solves the problems of high manufacturing cost and long period caused by the fact that the traditional forming method finishes the curing of the lower skin and the integral component step by step after entering the autoclave for multiple times, reduces the quality risks of the defects of surface depression, fiber buckling and skin looseness of the product in the forming process, and effectively improves the surface flatness and performance of the product.
Description
Technical Field
The invention belongs to the technical field of composite material member forming, and particularly relates to a forming method of a carbon fiber honeycomb sandwich composite material member.
Background
At present, carbon fiber composite materials have been widely used in various fields such as aviation, aerospace, automobiles and the like due to excellent properties such as high specific strength, high specific modulus, designability, fatigue resistance and the like. The carbon fiber honeycomb sandwich composite material is a typical structure applied to various fields as a composite material, has good impact resistance and weight reduction effect, and is generally formed into a structural whole by combining a lower skin, a honeycomb core and an upper skin (as shown in figure 1).
For carbon fiber honeycomb sandwich composite material members, particularly honeycomb sandwich composite material members with complex molded surfaces, the traditional forming process mainly comprises two types: one is to complete the laying and curing molding of the lower skin step by step, assemble and position the honeycomb core, then lay the upper skin on the honeycomb core, and perform integral curing; and the other method is to complete the whole solidification and molding after the lower skin, the honeycomb core and the upper skin are sequentially laid.
Under the first molding method, the product needs to be cured in an autoclave for many times, and the manufacturing cost is high and the period is long. And due to the structural characteristics of the honeycomb core (as shown in fig. 2), the fiber buckling is very easy to occur when the skin on the product is heated and pressed in the curing process (as shown in fig. 3), and the surface is sunken to different degrees.
Under the second forming method, due to the structural characteristics of the honeycomb core, the lower skin can only be pressed at the cell walls of the core in the curing process, so that the defect of large-area loosening of the lower skin of the honeycomb core is easily caused, and the honeycomb core is easy to collapse.
Therefore, in order to solve the above problems, it is very necessary to provide a new method for forming a carbon fiber honeycomb sandwich composite material member, so as to reduce the manufacturing cost of the composite material member, shorten the manufacturing period of the product, and improve the product quality.
Disclosure of Invention
Aiming at the problems of high cost, long period and high possibility of quality defects of products in the prior art, the invention provides a forming method of a carbon fiber honeycomb sandwich composite material member.
The specific implementation content of the invention is as follows:
a forming method of a carbon fiber honeycomb sandwich composite material component comprises an upper skin, a honeycomb core and a lower skin, and comprises the following steps:
the method comprises the following steps: processing the honeycomb core blank to a required shape profile in a cutting and polishing mode;
step two: after the honeycomb core blank is processed into a required shape profile, uniformly paving a layer of adhesive film on the outer surface of the honeycomb core blank, then packaging a vacuum bag, vacuumizing and pre-curing to obtain a prefabricated member of the honeycomb core;
thirdly, laying and pasting prepreg on the lower skin according to the structural requirements, packaging a vacuum bag after laying and pasting are finished, compacting in a hot-pressing tank, and marking a prefabricated part placing area of the honeycomb core on the lower skin after compacting;
placing the prefabricated member of the honeycomb core in a prefabricated member placing area on the lower skin to ensure that the prefabricated member of the honeycomb core is attached to the lower skin;
and fifthly, paving and pasting prepreg on the upper skin according to the structural requirements, integrally co-curing and forming the upper skin, the honeycomb core and the lower skin by integrally packaging a vacuum bag after paving and pasting, and demoulding to obtain the corresponding carbon fiber sandwich composite material component.
In order to better implement the method, further, in the fourth step, a layer of adhesive film is laid on the prefabricated part placing area on the lower skin, then the adhesive film on the prefabricated part placing area on the lower skin is softened by heat, then the prefabricated part of the honeycomb core is placed on the honeycomb core, and the honeycomb core is compacted by compaction;
and after the fourth step, flatly paving a layer of adhesive film on the upper surface of the prefabricated member of the honeycomb core, and then performing the operation in the fifth step.
In order to better realize the invention, the prepreg further comprises resin, and the adhesive film is an adhesive film with the same curing temperature as the resin contained in the prepreg.
In order to better realize the invention, further, when vacuumizing is carried out in the pre-curing process in the second step, the vacuum degree of vacuumizing is-0.1 MPa to-0.3 MPa.
In order to better realize the method, the pre-curing in the second step adopts an oven with a vacuum pumping system, the pre-curing time is 60-70 min, and the pre-curing temperature is 175-185 degrees.
In order to better realize the invention, further, when vacuumizing is carried out in the pre-curing process in the second step, the vacuum degree of vacuumizing is-0.18 MPa to-0.22 MPa.
In order to better realize the invention, in the third step, the compaction temperature is room temperature, and the compaction pressure is 0.4-0.7 MPa.
In order to better implement the present invention, further, in the third step, a laser projector is used to mark the preform placement area of the honeycomb core on the lower skin.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the curing frequency of the product entering the tank is effectively reduced, the manufacturing cost is reduced, the manufacturing period is shortened, and the risks of surface depression, fiber buckling and skin looseness defects of the product in the forming process can be effectively reduced.
Drawings
FIG. 1 is a schematic structural view of a carbon fiber honeycomb sandwich composite material member;
FIG. 2 is a schematic view of a cell wall structure of a honeycomb core;
FIG. 3 is a schematic illustration of fiber buckling;
FIG. 4 is a schematic view of a preform structure for a honeycomb core;
FIG. 5 is a schematic view of a carbon fiber honeycomb sandwich composite member produced in example 1;
FIG. 6 is a schematic view of a carbon fiber honeycomb sandwich composite member produced in example 2.
Wherein: 1. the method comprises the following steps of upper skin, 2, honeycomb core, 3, lower skin, 4, glue film, 5, honeycomb core cell wall and 6, and fiber buckling.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1:
a method for forming a carbon fiber honeycomb sandwich composite material member, as shown in fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5, wherein the carbon fiber honeycomb sandwich composite material comprises an upper skin 1, a honeycomb core 2 and a lower skin 3, and the method comprises the following steps:
the method comprises the following steps: processing the blank of the honeycomb core 2 to a required shape profile in a cutting and polishing mode;
step two: after the blank of the honeycomb core 2 is processed into a required shape profile, uniformly paving a layer of adhesive film 4 on the outer surface of the blank of the honeycomb core 2, then packaging a vacuum bag, vacuumizing and pre-curing to obtain a prefabricated member of the honeycomb core 2;
thirdly, laying and pasting prepreg on the lower skin 3 according to the structural requirements, packaging a vacuum bag after laying and pasting, compacting in a hot-pressing tank, and marking a prefabricated part placing area of the honeycomb core 2 on the lower skin 3 after compacting;
placing the prefabricated member of the honeycomb core 2 in a prefabricated member placing area on the lower skin 3 to ensure that the prefabricated member of the honeycomb core 2 is attached to the lower skin 3;
and fifthly, paving and pasting the prepreg on the upper skin 1 according to the structural requirements, integrally packaging the upper skin 1, the honeycomb core 2 and the lower skin 3 into a vacuum bag after paving and pasting are finished, carrying out integral co-curing molding, and demoulding to obtain the corresponding carbon fiber sandwich composite material component.
The working principle is as follows: the honeycomb core 2 has a plurality of honeycomb core cell walls 5 as shown in fig. 2, which tend to cause fiber buckling 6 in conventional processing methods; the method changes the traditional processing mode, firstly, the blank of the honeycomb core 2 is processed to the required shape profile; uniformly paving a layer of adhesive film 4 on the outer surface of the processed honeycomb core 2, and precuring to obtain a prefabricated member of the honeycomb core 2;
then laying and pasting prepreg of the lower skin 3 of the carbon fiber sandwich composite material component according to the structural requirements, compacting the lower skin in a hot-pressing tank by packaging a vacuum bag after laying and pasting are finished, and placing the prefabricated part of the honeycomb core 2 in a corresponding area after compacting to ensure that the prefabricated part of the honeycomb core 2 is pasted with the lower skin 3;
and then, paving and pasting prepreg of the skin 1 on the carbon fiber sandwich composite material component according to the structural requirements, packaging a vacuum bag after paving and pasting for integral co-curing molding, and demolding to obtain the corresponding carbon fiber sandwich composite material component.
The invention solves the problems of high manufacturing cost and long period caused by the fact that the lower skin 3 and the integral component are solidified step by step after entering the autoclave for many times in the traditional carbon fiber honeycomb sandwich composite material component forming method, can effectively reduce the quality risks of the defects of surface depression, fiber buckling 6 and skin looseness of the product in the forming process, and effectively improves the surface flatness and performance of the product.
Through the steps, the surface roughness of the final honeycomb core component can be improved to be more than Ra1.6, the quality risk of skin loosening defects of the honeycomb core component in the honeycomb core 2 area in the forming process is avoided, and meanwhile, the manufacturing cost of a workpiece is reduced by 30% -40%.
Example 2:
this embodiment is further improved on the basis of the above embodiment 1, as shown in fig. 6, the improvement is that: in the assembling process of the prefabricated member of the honeycomb core 2, firstly, a glue film 4 which is in the same system with resin contained in the prepreg is paved on a honeycomb core placing area of the lower skin 3, the glue film 4 is softened by an electric iron or a hair drier, then the prefabricated member of the honeycomb core 2 is placed in place and compacted, and a glue film 4 is paved on the upper surface of the prefabricated member of the honeycomb core 2 in a smooth mode, so that the prefabricated member of the honeycomb core is prevented from moving when the upper skin is paved on the prefabricated member of the honeycomb core 2.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
Example 3:
in this embodiment, on the basis of any one of the above embodiments 1-2, the adhesive film in the second step is an adhesive film J-299 which has the same curing temperature as the prepreg.
Other parts of this embodiment are the same as any of embodiments 1-2 described above, and thus are not described again.
Example 4:
in this embodiment, on the basis of any one of the embodiments 1 to 3, the pre-curing device in the second step adopts an oven with a vacuum pumping system, the pre-curing time is 60min to 70min, and the pre-curing temperature is 175 ℃ to 185 ℃.
Other parts of this embodiment are the same as any of embodiments 1 to 3, and thus are not described again.
Example 5:
in this embodiment, the vacuum pumping in the second step is performed in a vacuum degree of-0.18 MPa to-0.22 MPa based on any one of the embodiments 1 to 4.
Other parts of this embodiment are the same as any of embodiments 1 to 4, and thus are not described again.
Example 6:
in this embodiment, on the basis of any one of the above embodiments 1 to 5, further, the compacting in the third step is performed at room temperature and under a compacting pressure of 0.4MPa to 0.7 MPa.
Other parts of this embodiment are the same as any of embodiments 1 to 5, and thus are not described again.
Example 7:
this embodiment is based on any of embodiments 1 to 6 above, and further, in the third step, the preform placement region of the honeycomb core 2 is marked on the lower skin 3 by using a laser projector.
Other parts of this embodiment are the same as any of embodiments 1 to 6, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (8)
1. A forming method of a carbon fiber honeycomb sandwich composite material component is characterized in that the carbon fiber honeycomb sandwich composite material comprises an upper skin (1), a honeycomb core (2) and a lower skin (3), and the forming method comprises the following steps:
the method comprises the following steps: machining a blank of the honeycomb core (2) to a required shape profile in a cutting and polishing mode;
step two: after a blank of the honeycomb core (2) is processed into a required shape profile, uniformly paving a layer of glue film (4) on the outer surface of the blank of the honeycomb core (2), then packaging a vacuum bag, vacuumizing and precuring to obtain a prefabricated member of the honeycomb core (2);
thirdly, laying and pasting prepreg on the lower skin (3) according to the structural requirements, packaging a vacuum bag after laying and pasting, compacting in a hot-pressing tank, and marking a prefabricated part placing area of the honeycomb core (2) on the lower skin (3) after compacting;
fourthly, placing the prefabricated member of the honeycomb core (2) in a prefabricated member placing area on the lower skin (3) to ensure that the prefabricated member of the honeycomb core (2) is attached to the lower skin (3);
and fifthly, paving and pasting the prepreg on the upper skin (1) according to the structural requirements, integrally packaging the upper skin (1), the honeycomb core (2) and the lower skin (3) into a vacuum bag for integral co-curing molding after paving and pasting are finished, and demolding to obtain the corresponding carbon fiber sandwich composite material component.
2. The forming method of the carbon fiber honeycomb sandwich composite material member as claimed in claim 1, wherein in the fourth step, a layer of glue film (4) is laid on the preform placing area on the lower skin (3), then the glue film (4) on the preform placing area on the lower skin (3) is softened by heat, then the preform of the honeycomb core (2) is placed on the glue film, and the preform is compacted by compaction;
and after the fourth step, flatly paving a layer of adhesive film (4) on the upper surface of the prefabricated member of the honeycomb core (2), and then performing the operation in the fifth step.
3. The method for molding the carbon fiber honeycomb sandwich composite member according to any one of claims 1 or 2, wherein the prepreg comprises a resin, and the adhesive film (4) is an adhesive film (4) which has the same curing temperature system as the resin contained in the prepreg.
4. The method for forming the carbon fiber honeycomb sandwich composite material member as claimed in claim 3, wherein the degree of vacuum of the vacuum is-0.1 MPa to-0.3 MPa when the vacuum is pumped in the pre-curing process in the second step.
5. The method for forming the carbon fiber honeycomb sandwich composite material member according to claim 3, wherein the pre-curing in the second step is performed by using an oven with a vacuum pumping system, the pre-curing time is 60-70 min, and the pre-curing temperature is 175-185 °.
6. The method for forming the carbon fiber honeycomb sandwich composite material member as claimed in claim 3, wherein the degree of vacuum of the vacuum is-0.18 MPa to-0.22 MPa when the vacuum is pumped in the pre-curing process in the second step.
7. The method for forming the carbon fiber honeycomb sandwich composite member according to claim 3, wherein in the third step, the compaction temperature is room temperature, and the compaction pressure is 0.4MPa to 0.7 MPa.
8. A method for forming a carbon fiber honeycomb sandwich composite member as claimed in claim 3, wherein in the third step, a laser projector is used to mark the preform placement area of the honeycomb core (2) on the lower skin (3).
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113601878A (en) * | 2021-06-30 | 2021-11-05 | 航天材料及工艺研究所 | Large-curvature special-shaped surface and large-height honeycomb co-curing sandwich structure composite material and forming method thereof |
| CN113619150A (en) * | 2021-07-30 | 2021-11-09 | 中国航空工业集团公司济南特种结构研究所 | Composite material sandwich structure with honeycomb as molding tool and molding process method |
| CN113772076A (en) * | 2021-08-24 | 2021-12-10 | 成都飞机工业（集团）有限责任公司 | Foam sandwich hat-shaped reinforced wall plate structure and integrated forming method |
| CN114055807A (en) * | 2021-11-12 | 2022-02-18 | 广东汇天航空航天科技有限公司 | Method for forming part made of composite material, formed part and aircraft |
| CN114166938A (en) * | 2021-10-22 | 2022-03-11 | 安徽佳力奇先进复合材料科技股份公司 | Aramid paper honeycomb internal quality detection method |
| CN114379121A (en) * | 2021-11-24 | 2022-04-22 | 中国南方航空股份有限公司 | Engine reverse thrust sliding door inner cylinder front honeycomb sandwich structure repair process |
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| CN113601878B (en) * | 2021-06-30 | 2023-03-24 | 航天材料及工艺研究所 | Large-curvature special-shaped surface and large-height honeycomb co-curing sandwich structure composite material and forming method thereof |
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| CN113772076A (en) * | 2021-08-24 | 2021-12-10 | 成都飞机工业（集团）有限责任公司 | Foam sandwich hat-shaped reinforced wall plate structure and integrated forming method |
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Application publication date: 20210309 |