CN112848381B - Composite component and preparation method thereof - Google Patents
Composite component and preparation method thereof Download PDFInfo
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- CN112848381B CN112848381B CN202011629780.8A CN202011629780A CN112848381B CN 112848381 B CN112848381 B CN 112848381B CN 202011629780 A CN202011629780 A CN 202011629780A CN 112848381 B CN112848381 B CN 112848381B
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- 239000002131 composite material Substances 0.000 title claims abstract description 54
- 238000002360 preparation method Methods 0.000 title claims abstract description 17
- 239000004744 fabric Substances 0.000 claims abstract description 119
- 230000007704 transition Effects 0.000 claims abstract description 29
- 238000000034 method Methods 0.000 claims abstract description 26
- 229920005989 resin Polymers 0.000 claims abstract description 25
- 239000011347 resin Substances 0.000 claims abstract description 25
- 238000009755 vacuum infusion Methods 0.000 claims abstract description 21
- 238000000465 moulding Methods 0.000 claims abstract description 14
- 239000010410 layer Substances 0.000 claims description 77
- 239000003292 glue Substances 0.000 claims description 20
- 239000003795 chemical substances by application Substances 0.000 claims description 10
- 238000005520 cutting process Methods 0.000 claims description 10
- 238000002156 mixing Methods 0.000 claims description 8
- 239000000203 mixture Substances 0.000 claims description 8
- 238000001802 infusion Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 5
- 239000003822 epoxy resin Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 4
- 229920000647 polyepoxide Polymers 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims description 3
- 238000011049 filling Methods 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 230000037303 wrinkles Effects 0.000 claims description 3
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 2
- 229920001568 phenolic resin Polymers 0.000 claims description 2
- 238000007711 solidification Methods 0.000 claims description 2
- 230000008023 solidification Effects 0.000 claims description 2
- 239000005007 epoxy-phenolic resin Substances 0.000 claims 1
- 239000002344 surface layer Substances 0.000 claims 1
- 239000003365 glass fiber Substances 0.000 description 11
- 239000000835 fiber Substances 0.000 description 5
- 238000004804 winding Methods 0.000 description 5
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 4
- 239000004593 Epoxy Substances 0.000 description 3
- 238000004140 cleaning Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
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- 238000005516 engineering process Methods 0.000 description 2
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- 238000012545 processing Methods 0.000 description 2
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- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 229920006253 high performance fiber Polymers 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
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- 239000002356 single layer Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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Classifications
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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
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/228—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a composite component and a preparation method thereof. The prepared composite member is of a cylindrical structure with a flange, and a transitional connecting structure is arranged from the outer surface of the main body of the cylindrical structure to the edge of the flange; different strip-shaped profile fabrics are respectively arranged for the cylindrical structure main body and the transition connection structure, and the two strip-shaped profile fabrics are alternately laid outside a female die of the composite member to form a multilayer laying layer; each layer is formed by vertically lapping and laying a plurality of strip-shaped profile fabrics, and lap joints of adjacent layers are arranged in a staggered manner to obtain a fabric laying layer; and (3) carrying out vacuum infusion and integral molding on the fabric layer in a mold to obtain the composite member. The flange structure of the tubular composite material is prepared by adopting a multilayer gradient staggered cloth laying method, so that flange flanging and a barrel body can be integrally formed, and smooth transition of the flanging and the barrel body can be realized; on the other hand, the reasonable process is adopted to ensure the uniformity of the resin content of the cylinder body, and the one-time integral pouring forming of the large-size and high-thickness cylindrical flange composite component is realized.
Description
Technical Field
The invention belongs to the field of composite component preparation, and particularly relates to a composite component and a preparation method thereof.
Background
The glass fiber reinforced composite member (GFRP) has the comprehensive excellent performances of high specific modulus, high specific strength, small specific gravity, high temperature resistance, fatigue resistance, electric insulation and the like, is gradually changed from miniaturization to maximization, is transited from a secondary structure to a primary structure, and is developed into a large-scale main load-bearing member, the thickness and the size of the GFRP structural member for engineering are continuously increased due to the trend, and the forming process and the performance guarantee of the GFRP structural member are key technologies in preparation and production. On the other hand, with the rapid development of industrial technology, the demand for cylindrical glass fiber reinforced plastic products (such as straight cylinder, variable cross section, variable thickness and multi-curve cylindrical structure) with end flange structures in special fields is increasing, and the overall thickness and size requirements are also increasing.
The tubular composite member prepared by the traditional winding process cannot meet the requirements of large-size high-pressure-resistant tubular composite members on thickness, size precision and strength, and the difference of resin proportion in the winding process causes the defects of internal quality and the instability of product quality. Patent CN111546615A discloses a method for forming a cylindrical epoxy glass fiber composite component product, in which epoxy glass cloth is wound on a winding machine to form, after the epoxy glass cloth is wound to a specified thickness, a vacuum film is used to seal a mould and the product, after vacuum pumping, the product is placed in an autoclave, and heated and cured under a vacuum pressurization state, so as to obtain products with various specifications and dimensions. However, the scheme is simply adopted, so that a large-size product with high thickness and size precision cannot be obtained, the machining difficulty is high, and the scheme is not suitable for integral forming of a barrel with a flange structure. On the other hand, the scheme adopts winding and autoclave molding, the defect of internal quality is easily caused in the winding process, and the autoclave process cost is high. Therefore, how to rapidly and inexpensively prepare an integrally formed large-size and high-thickness cylinder product with a flange structure becomes a main technical problem to be solved urgently at present.
Disclosure of Invention
The invention aims to provide a composite component and a preparation method thereof.
The technical solution for realizing the purpose of the invention is as follows: a composite member is prepared into a cylindrical structure with a flange, and a transitional connection structure is arranged from the outer surface of a main body of the cylindrical structure to the edge of the flange;
different strip-shaped profile fabrics are respectively arranged for the cylindrical structure main body and the transition connection structure, and the two strip-shaped profile fabrics are alternately laid outside a female die of the composite member to form a multilayer laying layer; each layer is formed by vertically lapping and laying a plurality of strip-shaped profile fabrics, and lap joints of adjacent layers are arranged in a staggered manner to obtain a fabric laying layer; and (3) carrying out vacuum infusion and integral molding on the fabric layer in a mold to obtain the composite member.
Further, the method specifically comprises the following steps:
step (1): preparing a fabric, and cutting the fabric in blocks according to the shape and the size of the tubular structure main body to obtain a first profile strip fabric; according to the shape and the size of the transition connection structure, cutting the fabric into blocks to obtain a second profile strip-shaped fabric;
step (2): vertically and axially and alternately laying a layer of the first-profile strip-shaped fabric obtained in the step (1) on the surface of a female die of the cylinder body in a staggered manner to form a layer of first-profile laying, wherein the whole laying range of the laying is all ranges related to the surface of the composite member;
and (3): vertically and axially and wholly laying a layer of the second-profile strip-shaped fabric obtained in the step (1) in a staggered manner in the area where the transition connection structure is located to form a layer of second-profile laying, wherein the whole laying range of the laying is the area where the transition connection structure is located;
and (4): repeating the steps (2) - (3), laying multiple layers of fabrics at equal proportion and interval in the sequence of firstly laying a layer along the cylinder body and then laying a layer in the transition region, wherein the length sizes of the first profile strip-shaped fabric and the second profile strip-shaped fabric in the axial direction of the cylinder body are respectively decreased progressively according to the thickness of the product and the arc size gradient of the transition region until the thickness size of the laid fabric meets the thickness size requirement of each part of the product, and obtaining a fabric laying layer;
and (5): and (4) carrying out vacuum infusion molding on the fabric laying layer obtained in the step (4) in a mold, after curing, sequentially removing the vacuum bag and the infusion auxiliary material to complete the preparation of the blank of the flange-containing cylindrical composite component, and then carrying out mechanical processing to obtain the cylindrical flange-containing composite component.
Further, the fabric prepared in the step (1) is a glass fiber fabric.
Further, in the step (2), two adjacent strip fabrics in the first profile laying layer are in staggered lap joint, and the lap joint range is 30-100mm; and (4) in the step (3), two adjacent strip fabrics in the second profile layer are in staggered lap joint, and the lap joint range is 30-100mm.
Further, the first profile strip-shaped fabric and the second profile strip-shaped fabric in the steps (2) and (3) are smoothly attached to the cloth layer without folds in the laying process.
Further, when the step (4) is repeated in the steps (2) - (3), the adjacent first profile laying layers and the lap seams between the adjacent second profile laying layers are arranged in a staggered mode, and the distance of the lap seams of the adjacent layers is larger than 50mm.
Further, double-layer vacuum bag films are paved during vacuum infusion molding infusion in the step (5), and a breathable felt and an air exhaust port are arranged between the vacuum bag films; arranging a plurality of glue inlets and glue outlets during vacuum infusion, wherein the glue inlets and the glue outlets are staggered and uniformly distributed; the resin viscosity adopted by the vacuum infusion molding in the step (5) is not higher than 500mpa & s.
Furthermore, the resin is suitable for a vacuum infusion process such as epoxy resin, phenolic resin, unsaturated resin and the like, and the curing agent used for vacuum infusion is a curing agent matched with the epoxy resin; the single glue mixing amount of vacuum infusion molding is less than the theoretical total glue injection amount, and subsequent glue mixing is configured according to the infusion progress and the principle of small amount and multiple times.
Further, the specific process parameters of vacuum infusion molding are as follows:
and (3) after the fabric is laid, keeping the temperature of the mold at 20-40 ℃ for 30 +/-5 min, preheating and keeping the temperature of the resin and the curing agent at the optimal pouring temperature of a resin system, pouring the mixture into the fabric layer obtained in the step (4), heating and curing under corresponding curing conditions, naturally cooling to room temperature after complete curing, and demolding to obtain the composite member.
A composite member is prepared by the method.
Compared with the prior art, the invention has the remarkable advantages that:
according to the preparation method of the large-size and high-thickness cylindrical flange structure composite component, the flange structure of the insulating cylinder is prepared by a multilayer gradient cloth laying method, the flange flanging and the cylinder body can be integrally formed, smooth transition of the flanging and the cylinder body can be realized, the external surface precision is high, the machining difficulty is small, and the structural strength is high; furthermore, the consistency of the layer of the cylinder structure and the uniformity of the resin content of the cylinder are ensured by adopting a multi-time pouring mode, and the quick and low-cost preparation of the large-size and high-thickness cylindrical flange structure composite component is realized.
Drawings
FIG. 1 is a three-dimensional schematic view of a composite member of the present invention.
Fig. 2 is a front view of a composite member of the present invention.
FIG. 3 is a schematic view of a lay-up of a composite component of the present invention.
Description of reference numerals:
1-composite member female die, 2-second profile layer and 3-first profile layer.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
A method for preparing a large-size and high-thickness cylindrical flange-structure-containing composite component comprises an end flange and a barrel body, wherein the flange and the barrel body are prepared from glass fiber fabrics or other high-performance fiber fabric reinforced composite components.
As shown in fig. 1-2, the overall composite member is a curved structure, and in order to avoid the wrinkle phenomenon during the forming process, the fabric reinforcement is firstly cut, that is, cut at the position where the wrinkle occurs to ensure smooth transition of the fabric, and then the fabric reinforcement is laid on the peripheral wall of the cylindrical mold layer by layer to form an overall structure, so as to achieve the overall forming effect.
In order to further improve the dimensional accuracy of the composite component, the fabric needs to be laid in different areas (molded surfaces) and blocks to ensure the dimensional accuracy of different parts.
In order to further improve the mechanical property of the composite component, when the composite component is laid in different areas, the fabrics in all the areas (molded surfaces) are laid at intervals in equal proportion.
In order to further improve the uniformity of the resin content of the composite component and avoid dry spots, reasonable process design needs to be carried out according to the thickness of the component to realize uniform infiltration of the resin.
The preparation method of the large-size and high-thickness cylindrical flange structure composite component comprises the following steps:
preparing a fabric, and cutting the fabric into a first profile strip fabric in blocks according to the shape and the size of the whole cylinder;
the first-profile strip-shaped fiber fabric obtained in the step 1) is axially staggered and integrally laid on the surface of a barrel female die by one layer, wherein the integral laying range is all barrel ranges related to the surface of a member;
preparing a fabric, and cutting the fabric into second profile strip-shaped fabrics in blocks according to the shape and the size of the transitional connection area between the cylinder body and the flange flanging;
the second type surface strip-shaped fiber fabric obtained in the step 3) is integrally paved on the transition area of the cylinder body and the flange flanging in a staggered way along the axial direction, and the whole paving range comprises the starting point of the transition area to the outer edge of the flange flanging;
repeating the steps 1) to 4), and paving a plurality of layers of the cylinder body and the cloth layer of the transition region (the connection region of the flange and the cylinder body) in an equal proportion and gradient manner according to the shape of the product, as shown in figure 3, as follows: sequentially laying a plurality of layers of fabrics at equal proportion and intervals according to the sequence of firstly laying a layer along the cylinder body and then laying a layer in the transition region, wherein the length sizes of the first profile strip-shaped fabric and the second profile strip-shaped fabric in the cylinder axial line direction are decreased progressively according to the product thickness and the arc size gradient of the transition region respectively until the thickness size of the laid fabric meets the thickness size requirement of each part of the product;
and (3) carrying out vacuum infusion integral forming on the fabric laying layer obtained in the step 5) in a mould, after solidification, sequentially removing the vacuum bag and the infusion auxiliary material to complete the preparation of a blank piece of the flange-containing cylindrical composite component, and then carrying out simple machining to obtain the large-size and high-thickness cylindrical flange-containing structural composite component.
The large-size and high-thickness tubular flange structure composite member prepared by the method can be particularly applied to large-size product members and other special members with higher mechanical property requirements, and by adopting the composite member, the size precision and the quality uniformity of the product can be further improved on the premise of meeting the mechanical requirements of the members, and the development cost is reduced.
According to the invention, firstly, fiber fabrics with different specifications are prepared according to the shape of the product and the thickness requirements of each part, and then the fiber fabrics are integrally laid and molded. Wherein, the fiber fabric can be produced and cut in advance in batch.
In order to improve the preparation accuracy, in the steps 1) and 3), the first profile strip-shaped fabric and the second profile strip-shaped fabric are respectively cut into the shape of the cylinder body and the shape of the spread transition area.
In the steps 2), 4) and 5), the cloth layers are overlapped by 30-100mm, the distance of overlapping seams of adjacent layers is more than 50mm, and the overlapping seams between the adjacent layers are staggered and uniformly distributed in the circumferential direction.
In order to improve the consistency and accuracy of the laying, in the steps 2), 4) and 5), the fabric laying process must ensure that the fabric layer is smoothly attached to the clothing without folds.
In order to further improve the quality uniformity and mechanical properties of the obtained product, in the step 6), the viscosity of the resin used for vacuum infusion is not higher than 500 mpa-s. The resin used for vacuum infusion in the present application may be any of various resins, preferably epoxy resin.
And 6) mixing the pouring resin and the curing agent according to the proportion, wherein the single glue mixing amount is less than the theoretical total glue injection amount, and the subsequent glue mixing is configured according to the pouring progress and according to the principle of 'small amount and multiple times'.
In order to improve the seepage uniformity of the resin, in the step 6), a plurality of glue inlets and glue outlets are arranged and are distributed uniformly in a staggered manner.
In order to improve the forming quality, in the step 6), a double-layer vacuum bag film is paved during pouring.
Furthermore, a breathable felt and an air extraction opening are arranged between the vacuum bag films.
In order to realize good fitting effect of the fabric and the mold surface and further improve the mechanical property of the product and the uniformity of the resin content, in the step 6), after the fabric is paved, the mold is kept at the temperature of 20-40 ℃ for 30 +/-5 min, then a mixture of resin and a curing agent at the optimal pouring temperature of a resin system is poured into the fabric paving layer obtained in the step 5), the fabric paving layer is heated and cured under the corresponding curing condition, the fabric paving layer is naturally cooled to the room temperature after the fabric and the mold are completely cured, and the structural composite member is obtained after demolding. The method is simple to operate, and the mechanical property and the forming precision of the product can be guaranteed.
In the examples, the flange and the barrel portion were made of triaxial glass fiber fabric (0 °/± 45 °) manufactured by taishan glass fiber limited, and the mold was a metal female mold.
Example 1:
as shown in the figure, the large-size and high-thickness cylindrical flange-structure-containing composite component comprises two end flanges and a straight cylinder body for connecting flanges of the two flanges.
The preparation method of the large-size and high-thickness tubular flange structure composite component comprises the following steps:
step 1) cleaning a die: cleaning foreign matters and rubber residues on the surface of the mold, and scrubbing the surface of the mold by using acetone to ensure that the surface is clean;
step 2) after acetone is volatilized, coating a release agent on the surface of the cavity of the whole mold (the mold produced for the first time needs to be fully punched for 5 times;
and 3) preparing the glass fiber fabric, cutting the glass fiber fabric into first profile strip fabrics in blocks according to the shape and the size of the cylinder, and cutting the glass fiber fabric into second profile strip fabrics in blocks according to the shape and the size of the cylinder body and the flange flanging transition area. The cutting size is as follows:
| name of Material | Cloth cutting size/mm | Single layer number/piece | Number of layers | Remarks to note |
| First profile fabric | 317.5×1450 | 10 | 10 layers of | Barrel body |
| Second type surface fabric | 140×787.5 | 8 | 10 layers of | Transition zone |
| First profile fabric | 317.5×1425 | 10 | 10 layers of | Barrel body |
| Second type surface fabric | 110×790 | 8 | 10 layers of | Transition zone |
| First profile fabric | 317.5×1400 | 11 | 10 layers of | Barrel body |
| Second type surface fabric | 95×794 | 8 | 10 layers of | Transition zone |
| First profile fabric | 317.5×1370 | 11 | 10 layers of | Barrel body |
| Second type surface fabric | 80×800 | 8 | 10 layers of | Transition zone |
| First profile fabric | 317.5×1350 | 11 | 5 layers of | Barrel body |
Step 4) splicing and laying a plurality of pieces according to the shape of the product, wherein the first profile strip-shaped glass fiber fabric is staggered and laid for 45 layers along the axial direction of the surface of the cylinder mould, and the whole laying range is the range of the cylinder covered by the outer edge of the lower flange flanging and the outer edge of the upper flange flanging; and the second profile strip-shaped glass fiber fabric is axially staggered along the cylinder body and the flange flanging transition region for 40 layers, and the whole laying range comprises the initial point of the transition region to the outer edge of the flange flanging. The first molded fabric and the second molded fabric are alternately laid in equal proportion, wherein the cloth layers are lapped for 30-100mm, the lap seam distance of adjacent layers is larger than 50mm, the cloth layers are smooth and have no folds in the laying process, and a small amount of 3M glue is used for fixing the cloth layers.
And 5) preserving the temperature of the mold at 30-35 ℃ for 30 +/-5 min, preheating and preserving the temperature of the resin and the curing agent at 35 ℃, pouring the mixture into the fabric layer obtained in the step (4), and heating for 4 hours at 85 +/-5 ℃ or heating for 3 hours at 100 +/-5 ℃ until the mixture is completely cured.
And 6) naturally cooling to room temperature after curing, and sequentially removing the vacuum bag and filling the auxiliary materials to complete the preparation of the double-outer-flange tubular composite component blank.
Finally, the outer surface of the product can meet the outer surface precision requirement of the product through simple mechanical processing.
Claims (4)
1. The preparation method of the composite member is characterized in that the prepared composite member is a cylindrical structure containing a flange, and a transitional connection structure is arranged from the outer surface of a main body of the cylindrical structure to the edge of the flange;
different strip-shaped profile fabrics are respectively arranged for the cylindrical structure main body and the transition connection structure, and the two strip-shaped profile fabrics are alternately laid outside a female die of the composite member to form a multilayer laying layer; each layer is formed by vertically lapping and laying a plurality of strip-shaped profile fabrics, and lap joints of adjacent layers are arranged in a staggered manner to obtain a fabric laying layer; carrying out vacuum infusion and integral molding on the fabric layer in a mold to obtain a composite member;
the method specifically comprises the following steps:
step (1): preparing a fabric, and cutting the fabric in blocks according to the shape and the size of the tubular structure main body to obtain a first profile strip fabric; according to the shape and the size of the transition connection structure, cutting the fabric into blocks to obtain a second profile strip-shaped fabric;
step (2): vertically and axially and alternately laying a layer of the first-profile strip-shaped fabric obtained in the step (1) on the surface of a female die of the cylinder body in a staggered manner to form a layer of first-profile laying, wherein the whole laying range of the laying is all ranges related to the surface of the composite member;
and (3): vertically and axially and wholly laying a layer of the second-profile strip-shaped fabric obtained in the step (1) in a staggered manner in the area where the transition connection structure is located to form a layer of second-profile laying, wherein the whole laying range of the laying is the area where the transition connection structure is located;
and (4): repeating the steps (2) - (3), laying multiple layers of fabrics at equal proportion and interval in the sequence of firstly laying a layer along the cylinder body and then laying a layer in the transition region, wherein the length sizes of the first profile strip-shaped fabric and the second profile strip-shaped fabric in the axial direction of the cylinder body are respectively decreased progressively according to the thickness of the product and the arc size gradient of the transition region until the thickness size of the laid fabric meets the thickness size requirement of each part of the product, and obtaining a fabric laying layer;
and (5): vacuum infusion molding is carried out on the fabric laying layer obtained in the step (4) in a mold, after solidification, the vacuum bag and the infusion auxiliary material are removed in sequence, the preparation of a blank of the flange-containing cylindrical composite component is completed, and then the cylindrical flange-containing composite component is obtained through machining;
in the step (2), two adjacent strip fabrics in the first molded surface layer are overlapped in a staggered mode, and the overlapping range is 30-100mm; in the step (3), two adjacent strip fabrics in the second profile layer are overlapped in a staggered mode, and the overlapping range is 30-100mm;
when the step (4) is repeated, overlapping seams between the adjacent first profile laying layers and the adjacent second profile laying layers are arranged in a staggered mode, and the distance of the overlapping seams between the adjacent layers is larger than 50mm;
paving double-layer vacuum bag films during vacuum infusion molding and infusion in the step (5), wherein a breathable felt and an air exhaust port are arranged between the vacuum bag films; arranging a plurality of glue inlets and glue outlets during vacuum infusion, wherein the glue inlets and the glue outlets are staggered and uniformly distributed; the resin viscosity adopted by the vacuum infusion molding in the step (5) is not higher than 500mpa · s;
the resin system is epoxy resin, phenolic resin and unsaturated resin suitable for vacuum infusion process and matched curing agent; the single glue mixing amount of vacuum infusion molding is less than the theoretical total glue injection amount, and subsequent glue mixing is configured according to the infusion progress and following the principle of small quantity and multiple times;
the specific technological parameters of vacuum infusion molding are as follows:
and (3) after the fabric is laid, keeping the temperature of the mold at 20-40 ℃ for 30 +/-5 min, preheating and keeping the temperature of the resin and the curing agent at the optimal filling temperature of a resin system, mixing and filling the resin and the curing agent into the fabric layer obtained in the step (4), heating and curing the mixture under corresponding curing conditions, naturally cooling the mixture to room temperature after the mixture is completely cured, and demolding the mixture to obtain the composite member.
2. The method of claim 1, wherein the fabric produced in step (1) is a fibrous fabric.
3. The method according to claim 2, wherein the first and second profile strips of steps (2) and (3) are laid down smoothly and without wrinkles.
4. A composite component, characterized in that it is produced by a method according to any one of claims 1 to 3.
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