CN111823614B - Forming method of composite material multi-cavity structure - Google Patents
Forming method of composite material multi-cavity structure Download PDFInfo
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- CN111823614B CN111823614B CN202010674242.4A CN202010674242A CN111823614B CN 111823614 B CN111823614 B CN 111823614B CN 202010674242 A CN202010674242 A CN 202010674242A CN 111823614 B CN111823614 B CN 111823614B
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- core mold
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/06—Making preforms by moulding the material
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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
Abstract
The invention relates to a method for forming a composite material multi-cavity structure, which comprises the following steps: s1: paving prepreg at two side ends of the core mold to obtain a prefabricated body, wherein the prepreg forms a prefabricated part at the two side ends of the core mold respectively; s2: arranging the prefabricated bodies in parallel, placing a vertical rib plate between every two adjacent prefabricated bodies, and then attaching and fixing the prefabricated bodies and the vertical rib plate through a fixing device to obtain a core mold assembly; s3: respectively paving an outer skin and an inner skin on two sides of the core mold component to form a blank; s4: placing the blank on the molding surface of the lower die, and closing the upper die and the lower die; s5: drawing out each core mold to form a cavity; s6: communicating vacuum bags arranged outside the upper die and the lower die and a vacuum bag pipe arranged on the inner wall of the cavity, vacuumizing, and curing; s7: and after the solidification is finished, opening the upper die and taking out the workpiece. Can reduce the cost, easily realize the demoulding, ensure the product quality and improve the production efficiency.
Description
Technical Field
The invention relates to the technical field of composite material multi-cavity structures, in particular to a forming method of a composite material multi-cavity structure.
Background
The composite material multi-cavity structure generally refers to a structure supported by an outer skin, an inner skin and a middle reinforcing rib, and the forming method of the structure mainly comprises a secondary assembling method, a metal core molding method, an air bag forming method and a rubber core molding method at present; these methods have good results, but have certain limitations.
The secondary assembly method increases a curing link and an assembly link, and has lower production efficiency; the metal core mold method is difficult to demold, and a workpiece is easy to damage in the demolding process; the manufacturing cost of the air bag in the air bag forming method is too high, and the repeated utilization rate is low; the expansion of rubber in the rubber core mold method is not easy to control, the stress is not uniform in the curing process of the finished piece, and the product quality of the finished piece cannot be ensured.
Therefore, how to provide a method for forming a multi-cavity structure of a composite material, which can reduce the cost, easily realize demoulding, ensure the product quality and improve the production efficiency, is a technical problem to be solved by the technical personnel in the field.
Disclosure of Invention
The invention aims to provide a method for forming a composite material multi-cavity structure, which can reduce the cost, is easy to realize demoulding, ensures the product quality and can improve the production efficiency.
In order to solve the technical problems, the invention provides a method for forming a composite material multi-cavity structure, which comprises the following steps:
s1: paving and pasting prepreg on two side ends of a core mold to obtain a prefabricated body, wherein the prepreg forms a prefabricated member on the two side ends of the core mold respectively;
s2: arranging the prefabricated bodies in parallel, placing a vertical rib plate between every two adjacent prefabricated bodies, and then attaching and fixing the prefabricated bodies and the vertical rib plate through a fixing device to obtain a core mould assembly;
s3: respectively paving an outer skin and an inner skin on two sides of the core mold component to form a blank;
s4: placing the blank on a forming surface of a lower die, and closing an upper die and the lower die;
s5: drawing out each core mold to form a cavity;
s6: communicating vacuum bags arranged outside the upper die and the lower die and a vacuum bag pipe arranged on the inner wall of the cavity, vacuumizing, and curing;
s7: and after the solidification is finished, opening the upper die and taking out the workpiece.
The composite material multi-cavity structure prepared by the molding method only needs one-time curing in the molding process, does not need secondary assembly operation, and can effectively improve the production efficiency. In the preparation process, the layering is finished on the core mold, the upper mold and the lower mold can guarantee the overall dimension and the surface quality of a workpiece, the quality is guaranteed through the metal core mold in the cavity, and the core mold is not occupied in the vacuumizing curing process, so that the core mold can be paved and the next workpiece can be prepared when the previous workpiece is vacuumized and cured, the production efficiency can be further improved, and compared with a secondary assembly method, the forming method can improve the efficiency by about 30%; compared with the airbag molding method, the method has the advantages that the cost of the adopted mold is only one tenth of that of the mold (airbag molding method), and the economy is good.
Optionally, before the step S1, a step S0 is further included: and wrapping an auxiliary material on the surface of the core mold, wherein the auxiliary material comprises the vacuum bag pipe.
Optionally, the auxiliary material comprises a breathable felt, an isolation film, the vacuum bag pipe and a polytetrafluoroethylene adhesive tape which are sequentially arranged from inside to outside.
Optionally, the prefabricated member is a C-shaped structure wrapped at one side end of the core mold, and the openings of two adjacent C-shaped structures in the core mold assembly are arranged in opposite directions.
Optionally, a step S21 is further included between step S2 and step S3: and filling a gap between two adjacent prefabricated members with carbon fiber prepreg.
Optionally, in step S3, after the fixing device drives the core mold assembly to move to be separated from the upper mold and the lower mold, respectively laying an outer skin and an inner skin on two sides of the core mold assembly to form the blank; in step S4, the fixing device drives the blank to move until the blank is attached to the molding surface of the lower mold.
Optionally, the vertical rib plate is a carbon fiber plate.
Optionally, the thickness of the stud plate is 0.8mm to 1.5 mm.
Optionally, in step S6, the curing step is to heat the substrate from room temperature to 120 ℃ at a heating rate of 2 ℃/min in a curing oven, and then cool the substrate to room temperature after holding the temperature for 2 hours.
Drawings
FIG. 1 is a block flow diagram of a method for forming a composite multi-cavity structure according to an embodiment of the present invention;
FIG. 2 is a detailed flow diagram of a method of forming a composite multi-cavity structure;
FIG. 3 is a schematic structural view of a composite multi-lumen structure;
fig. 4 is a schematic structural view of the core preform.
In the accompanying fig. 1-4, the reference numerals are illustrated as follows:
1-core mould; 2-auxiliary material, 21-air felt, 22-isolation film, 23-vacuum bag pipe, 24-polytetrafluoroethylene adhesive tape; 3-performing; 4-vertical rib plates; 5-outer skin; 6-inner skin; 7-twisting the strips.
Detailed Description
In order to make the technical solutions of the present invention better understood by those skilled in the art, the present invention will be further described in detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1-4, fig. 1 is a flow chart illustrating a method for forming a multi-cavity structure of a composite material according to an embodiment of the present invention; FIG. 2 is a detailed flow diagram of a method of forming a composite multi-cavity structure; FIG. 3 is a schematic structural view of a composite multi-lumen structure; fig. 4 is a schematic structural view of the core preform.
The embodiment of the invention provides a method for forming a composite material multi-cavity structure, which specifically comprises the following steps of:
s1: paving prepreg at two side ends of the core mold 1 to obtain a prefabricated body, wherein the prepreg forms a prefabricated part 3 at the two side ends of the core mold 1 respectively;
s2: arranging the prefabricated bodies in parallel, placing a vertical rib plate 4 between every two adjacent prefabricated bodies, and then tightly attaching and fixing the prefabricated bodies and the vertical rib plate 4 through a fixing device to obtain a core mould 1 assembly;
s3: respectively paving an outer skin 5 and an inner skin 6 on two sides of the core mould 1 assembly to form a blank;
s4: placing the blank on the molding surface of the lower die, and closing the upper die and the lower die;
s5: drawing out each core mold 1 and forming a cavity;
s6: communicating vacuum bags arranged outside the upper die and the lower die with a vacuum bag pipe 23 arranged on the inner wall of the cavity, vacuumizing, and curing;
s7: and after the solidification is finished, opening the upper die and taking out the workpiece.
The laid prepreg can form a prefabricated member 3 at two opposite side ends of a core mold 1 respectively, then arrange the prefabricated members in parallel, place a vertical rib plate 4 between two adjacent prefabricated members, namely, a vertical rib plate 4 is clamped between the prefabricated member 3 of one prefabricated member and the prefabricated member 3 of the other prefabricated member, then tightly fix the prefabricated members and the vertical rib plate 4 through a fixing device to obtain a core mold assembly, and lay an outer skin 5 and an inner skin 6 on two sides of the core mold assembly respectively to form blanks.
After the outer skin 5 and the inner skin 6 are paved and adhered, the blank is placed on the molding surface of the lower die, the upper die is closed and fastened, wherein the molding surfaces of the upper die and the lower die are coated with a release agent, the core die 1 is drawn out after the upper die and the lower die are closed, and the position of the core die 1 forms a die cavity, and the cavity wall (comprising the prefabricated part 3, the outer skin 5 and the inner skin 6) of the die cavity is formed by paving and adhering prepreg, so the cavity wall has certain flexibility, the core die 1 is easy to operate in the drawing process, the situation of difficult demoulding can not be generated, then a vacuum bag is sleeved outside the upper die and the lower die and is communicated with a vacuum bag pipe 23 positioned on the inner wall of the die cavity, the vacuum bag is vacuumized and cured, and the upper die is opened after the curing is completed to take out the finished product.
Two prefab 3 and the stud plate 4 between the two have formed a strengthening rib that is located between outer skin 5 and the interior skin 6, and the position that can be between two adjacent strengthening ribs after mandrel 1 takes out forms the die cavity, and setting up of stud plate 4 can be when promoting overall structure intensity, can also provide the support for prefab 3 in the compound die in later stage, operation such as evacuation solidification, guarantee its structural strength, avoid prefab 3 to take place the condition such as fold deformation in the evacuation solidification process.
The composite material multi-cavity structure prepared by the molding method only needs one-time curing in the molding process, does not need secondary assembly operation, and can effectively improve the production efficiency. In the preparation process, the paving is finished on the core mold 1, the upper mold and the lower mold can ensure the overall dimension and the surface quality of a workpiece, the quality is ensured through the metal core mold 1 in the cavity, and the core mold 1 is not occupied in the vacuumizing curing process, so that the core mold 1 can be paved and the next workpiece can be prepared when the previous workpiece is vacuumized and cured, and the production efficiency can be further improved; compared with the airbag molding method, the method has the advantages that the cost of the adopted mold is only one tenth of that of the mold (airbag molding method), and the economy is good.
In the above embodiment, before the step S1, the method further includes the step S0: the surface of the core mold 1 is wrapped with the auxiliary material 2, the auxiliary material 2 includes the vacuum bag pipe 23, that is, the vacuum bag pipe 23 located in the cavity is wrapped on the outer wall of the core mold 1 in advance, however, in this embodiment, after the core mold 1 is drawn out, the vacuum bag pipe 23 is arranged on the inner wall of the cavity, then the vacuum bag is communicated with the vacuum bag pipe 23 and vacuumized, the vacuum bag pipe 23 is wrapped on the outer wall of the core mold 1 in advance, and the prepreg is laid on the outer wall of the core mold 1 wrapped with the auxiliary material 2, in step S5, when the core mold 1 is drawn out, the vacuum bag pipe 23 remains in the cavity and is attached to the inner wall of the cavity, and when the core mold 1 is vacuumized and cured in the later stage, the vacuum bag pipe 23 can be attached to the inner wall of the cavity better, thereby ensuring the quality of the inner wall of the cavity. Specifically, in step S7, the upper mold is opened and the product is taken out, and then the vacuum bag tubes 23 in the respective cavities are taken out.
In the above embodiment, the auxiliary material 2 includes the airfelt 21, the separation film 22, the above vacuum bag tube 23 and the teflon tape 24 which are sequentially arranged from the inside to the outside. Specifically, the wrapping sequence of the auxiliary material 2 on the surface of the core mold 1 is as follows: firstly, the surface of the core mould 1 is wrapped with a ventilated felt 21 and a separation film 22, wherein the separation film 22 is fixed by a pressure sensitive adhesive tape, then a vacuum bag pipe 23 is sleeved on the separation film, and the outer surface of the vacuum bag pipe 23 is wrapped with a polytetrafluoroethylene adhesive tape 24. The airfelt 21 can prevent the core mold 1 from scratching the vacuum bag tube 23, and in the present embodiment, the mode of extraction of the core mold 1 is not limited, and it is sufficient to provide bolt holes in the end surface of the core mold 1, and to pull out the core mold 1 by fitting bolts into the bolt holes at the time of extraction, or to push out the core mold 1 from one end to the other end.
In the above embodiment, the preform 3 has a C-shaped structure, that is, the core mold 1 is located between the open grooves of two C-shaped structures, the openings of two adjacent C-shaped structures in the core mold assembly are oppositely arranged, and the stud plate 4 is sandwiched between the two C-shaped structures. That is to say, this multi-chamber structure's strengthening rib is I shape structure, and structural stability is better. And, when setting up prefab 3 into C type structure, when spreading outer skin 5 and interior skin 6, can increase the bonding area between each layer preimpregnation material of prefab 3 and outer skin 5 and interior skin 6 to further guarantee structural stability.
In the above embodiment, step S21 is further included between step S2 and step S3: and filling a gap between two adjacent prefabricated members 3 by using the carbon fiber prepreg, for example, filling the gap by using twisted strips 7 of the carbon fiber prepreg until the gap between the two prefabricated members 3 is filled, so that the influence of the existence of a gap on the overall mechanical property of the multi-cavity structure is avoided.
In the above embodiment, the stud plate 4 is a carbon fiber plate, and the thickness of the stud plate 4 is 0.8mm to 1.5mm, so that sufficient strength can be ensured and the material consumption of the carbon fiber plate can be reduced. In this embodiment, the specific thickness of the stud plate 4 can be set according to practical situations, and is not limited herein,
in the above embodiments, the fixing device is not only used to fix each core mold to form the core mold assembly, but also used to drive the core mold assembly to move to be separated from the upper mold and the lower mold or to be attached to the molding surface of the lower mold. In detail, in step S3, the fixing device drives the core mold assembly to move to be separated from the upper mold and the lower mold, and then the outer skin 5 and the inner skin 6 are respectively laid on two sides of the core mold assembly to form a blank. Then, in step S4, the blank is moved again by the fixing device until the blank is attached to the molding surface of the lower mold.
Specifically, in this embodiment, the specific structure of the fixing device is not limited, for example, the fixing device may be configured as two parallel support arms, wherein one side of the two support arms opposite to each other is correspondingly provided with a fixing structure for fixing the end portion of the core mold 1, and one end of the support arm is hinged to the lower mold and can drive the core mold assembly to rotate relative to the lower mold. Alternatively, it may be provided as a separate member as long as it is possible to secure the respective preforms and the stud plates and to move the core mold assembly and the blank member.
In the step S6, the curing refers to curing in a curing oven, specifically, the temperature is increased from room temperature to 120 ℃ at a rate of 2 ℃/min, and after heat preservation for 2 hours, the temperature is naturally cooled to room temperature, or the curing may be performed in an autoclave, which is not limited in particular.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that it is obvious to those skilled in the art that various modifications and improvements can be made without departing from the principle of the present invention, and these modifications and improvements should also be considered as the protection scope of the present invention.
Claims (9)
1. A method for forming a composite material multi-cavity structure is characterized by comprising the following steps:
s1: paving prepreg at two side ends of a core mould (1) to obtain a prefabricated body, wherein the prepreg forms a prefabricated part (3) at the two side ends of the core mould (1) respectively;
s2: arranging the prefabricated bodies in parallel, placing a vertical rib plate (4) between every two adjacent prefabricated bodies, and then closely fixing the prefabricated bodies and the vertical rib plate (4) through a fixing device to obtain a core mould assembly;
s3: respectively paving an outer skin (5) and an inner skin (6) on two sides of the core mold component to form a blank;
s4: placing the blank on a forming surface of a lower die, and closing an upper die and the lower die;
s5: drawing out each core mold (1) and forming a cavity;
s6: communicating vacuum bags arranged outside the upper die and the lower die with a vacuum bag pipe (23) arranged on the inner wall of the cavity, vacuumizing, and curing;
s7: and after the solidification is finished, opening the upper die and taking out the workpiece.
2. The method of forming a composite material multi-chamber structure according to claim 1, further comprising, before step S1, step S0: and (3) wrapping an auxiliary material (2) on the surface of the core mold (1), wherein the auxiliary material (2) comprises the vacuum bag pipe (23).
3. A method for forming a composite multi-chamber structure according to claim 2, wherein the auxiliary material (2) comprises an air-permeable felt (21), a separation film (22), the vacuum bag tube (23) and a teflon tape (24) which are arranged from inside to outside.
4. A method for forming a composite material multiple cavity structure according to any one of claims 1-3, wherein the preform (3) is a C-shaped structure wrapped around one side end of the core mold (1), and the openings of two adjacent C-shaped structures in the core mold assembly are oppositely arranged.
5. The method for forming a composite multi-chamber structure according to any one of claims 1-3, further comprising, between step S2 and step S3, step S21: and filling a gap between two adjacent prefabricated members (3) with carbon fiber prepreg.
6. A method for forming a composite multi-cavity structure according to any one of claims 1-3, wherein in step S3, after a fixing device drives a core mold assembly to move to be separated from the upper mold and the lower mold, an outer skin (5) and an inner skin (6) are respectively laid on two sides of the core mold assembly to form the blank;
in step S4, the fixing device drives the blank to move until the blank is attached to the molding surface of the lower mold.
7. A method for forming a composite material multi-cavity structure according to any one of claims 1-3, wherein the vertical rib plates (4) are carbon fiber plates.
8. The method for forming a composite material multi-cavity structure according to claim 7, wherein the thickness of the vertical rib plate (4) is 0.8 mm-1.5 mm.
9. The method for forming a multi-cavity structure in a composite material according to any one of claims 1-3, wherein in step S6, the curing is performed by heating the composite material from room temperature to 120 ℃ at a heating rate of 2 ℃/min in a curing oven, and naturally cooling the composite material to room temperature after keeping the temperature for 2 hours.
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| CN114274552B (en) * | 2021-11-24 | 2023-11-10 | 常州启赋安泰复合材料科技有限公司 | Forming die and processing method of composite material transmission shaft |
| CN114347509A (en) * | 2022-01-04 | 2022-04-15 | 广东汇天航空航天科技有限公司 | Composite material part forming method, composite material part and forming die |
| CN116021797A (en) * | 2023-01-28 | 2023-04-28 | 哈尔滨远驰航空装备有限公司 | Mold for air inlet channel pipe type part structure and molding process |
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| JP6184808B2 (en) * | 2013-09-05 | 2017-08-23 | 三菱重工業株式会社 | Manufacturing method of core type and hollow structure |
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| CN103978699A (en) * | 2014-05-14 | 2014-08-13 | 江西洪都航空工业集团有限责任公司 | Carbon fiber tube part forming method |
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