CN114889161A - Integrated forming manufacturing method of carbon fiber reinforced resin matrix composite material - Google Patents
Integrated forming manufacturing method of carbon fiber reinforced resin matrix composite material Download PDFInfo
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- CN114889161A CN114889161A CN202210537132.2A CN202210537132A CN114889161A CN 114889161 A CN114889161 A CN 114889161A CN 202210537132 A CN202210537132 A CN 202210537132A CN 114889161 A CN114889161 A CN 114889161A
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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
- B29C70/345—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 matched moulds
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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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- 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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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a carbon fiber reinforced resin matrix composite material integrated forming manufacturing method, and belongs to the technical field of carbon fiber composite material forming. According to the invention, a multipoint mold is used for performing carbon fiber, a graphene electrothermal film is used for curing the preformed piece, the preformed piece is heated in a mold closing state, and the forming and curing of the carbon fiber skin part are realized. The invention does not need a special autoclave device, adopts a multi-point mould to replace a fixed mould, solves the problems of large equipment floor area, high cost, long mould manufacturing period, difficult storage and the like in the production of the autoclave method, and realizes the integration of the forming and curing of carbon fiber skin parts. The method can reduce equipment cost and shorten production period, and is suitable for production of carbon fiber skin parts in the aerospace field.
Description
Technical Field
The invention belongs to the technical field of carbon fiber composite material forming, and particularly relates to an integrated forming manufacturing method of a carbon fiber reinforced resin matrix composite material.
Background
The light weight is a constant pursuit target in the field of aerospace, and the weight reduction of materials is an important means for realizing the light weight. Compared with the traditional metal material, the carbon fiber reinforced resin matrix composite material has a series of advantages of small density, high strength and the like, is an ideal weight-reducing material, and is increasingly applied in the field of aerospace. Especially, the skin parts have the characteristics of complex shape and uneven stress, and are very suitable for being made of carbon fiber reinforced resin matrix composite materials.
The carbon fiber skin part is mainly prepared by an autoclave method, and three key factors of shape, pressure and temperature need to be considered in production. Wherein, the control of the shape is realized by a fixed die, and the control of the pressure and the temperature is realized by an autoclave. The specific process comprises two steps: firstly, preforming, namely laying carbon fiber prepreg cloth on a fixed mould in layers to enable the carbon fiber prepreg cloth to be attached to the molded surface of the mould, and obtaining a preformed piece with the same target shape; and secondly, curing, namely placing the preformed piece into an autoclave, and controlling the pressure and the temperature to shape the preformed piece and ensure the estimated product performance.
The products in the aerospace field have the characteristics of multiple models and small batch, the skin parts have the characteristics of large size and small curvature, and two outstanding problems exist when the skin parts are prepared by adopting a hot-pressing tank method: firstly, the required autoclave occupies a large area and is expensive, and common enterprises are difficult to bear. And secondly, when the fixed die is formed, a special die needs to be manufactured for each skin with different shapes, so that the die is long in production period and difficult to store.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention aims to provide the integrated forming manufacturing method of the carbon fiber reinforced resin matrix composite material, which is short in production period and low in production cost.
In order to realize the functions, the invention adopts the following technical scheme:
the integrated forming manufacturing method of the carbon fiber reinforced resin matrix composite is characterized by comprising carbon fiber prepreg cloth, an upper graphene base plate, a lower graphene base plate, a multi-point upper die and a multi-point lower die, wherein an upper protective layer, a graphene electrothermal film and a lower protective layer are sequentially arranged on the upper graphene base plate and the lower graphene base plate from top to bottom, and the manufacturing method comprises the following steps:
firstly, laying a prepreg cloth:
laying the carbon fiber prepreg layer by layer on the lower graphene base plate, and then placing the upper graphene base plate on the carbon fiber prepreg;
step two, model adjustment: adjusting the shape of the multi-point upper die and the multi-point lower die to enable the molded surface to be in a target shape;
step three, moving: moving the combined lower graphene base plate, the carbon fiber prepreg cloth and the upper graphene base plate to be placed on a multi-point lower die;
step four, obtaining a preformed piece: the multipoint upper die moves downwards, and is matched with the multipoint lower die for pressure maintaining, so that the shape of the carbon fiber prepreg cloth is the same as the shapes of the molded surfaces of the multipoint upper die and the multipoint lower die, and a preformed piece is obtained;
step five, curing: the multipoint upper die and the multipoint lower die are kept in a die closing state to ensure the shape of the part and finally obtain the qualified part with the designed shape and performance, the graphene electrothermal film is communicated with a power supply through a lead, and the graphene electrothermal film generates heat to solidify the preformed piece.
The upper protective layer and the lower protective layer are both metal plates with the thickness of 1-3 mm.
The metal plate is a pure aluminum plate, and the characteristic of good aluminum formability is utilized, so that the molded surface of the die is continuous, and the surface of the formed part has no indentation.
When the carbon fiber prepreg cloth is laid, the included angle between adjacent carbon fiber carbon filament lines is alpha degrees.
The alpha of the invention is between 30 and 60 degrees, so as to enhance the strength and toughness of the part.
The graphene electrothermal film has the characteristics of high thermal conversion efficiency, balanced temperature surface and the like, and can provide a temperature environment equivalent to that of an autoclave. The multipoint forming technology can realize flexible forming by constructing different die molded surfaces by adjusting the height of the basic body. The method combines the graphene heating technology with the multipoint forming technology, controls the shape and pressure through the multipoint upper die and the multipoint lower die, controls the temperature through the graphene heating film, can obtain three key factors of the shape, the pressure and the temperature in the production of the autoclave method, further can realize the forming and curing of carbon fiber skin parts, and solves the problems of large occupied area of equipment, high cost, long manufacturing period of the die, difficult storage and the like in the autoclave forming. By adopting the technical scheme, the graphene heating technology and the multipoint forming technology are combined, the forming and curing of the carbon fiber skin parts are realized, the carbon fiber skin part forming and curing device is perfectly suitable for the characteristics of multiple skin parts in the aerospace field, such as small batch, large size, small curvature and the like, and has the characteristics of short production period, low production cost and the like.
Drawings
FIG. 1 is a schematic diagram showing the positional relationship of the components during the process of obtaining the preform and curing.
Fig. 2 is a schematic structural view of the upper graphene pad.
Detailed Description
The invention will be further explained with reference to the drawings,
example 1
The integrated forming manufacturing method of the carbon fiber reinforced resin matrix composite is characterized by comprising a carbon fiber prepreg 5, an upper graphene backing plate 3, a lower graphene backing plate 4, a multi-point upper die 1 and a multi-point lower die 2, wherein an upper protective layer 3-1, a graphene electrothermal film 3-2 and a lower protective layer 3-3 are sequentially arranged on the upper graphene backing plate 3 and the lower graphene backing plate 4 from top to bottom, and a copper wire is connected to the outer part of the graphene electrothermal film 3-2 to facilitate electrical connection; the basic body of the die is made of aluminum plates, and the cross section of the basic body is circular.
Firstly, laying a prepreg cloth:
laying the carbon fiber prepreg layer by layer on the lower graphene base plate, and then placing the upper graphene base plate on the carbon fiber prepreg;
step two, model adjustment: adjusting the shape of the multi-point upper die and the multi-point lower die to enable the molded surface to be in a target shape;
and thirdly, moving: moving the combined lower graphene base plate, the carbon fiber prepreg cloth and the upper graphene base plate to be placed on a multi-point lower die;
step four, obtaining a preformed piece: the multipoint upper die moves downwards, and is matched with the multipoint lower die for pressure maintaining, so that the shape of the carbon fiber prepreg cloth is the same as the shapes of the molded surfaces of the multipoint upper die and the multipoint lower die, and a preformed piece is obtained;
step five, curing: the multipoint upper die and the multipoint lower die are kept in a die closing state to ensure the shape of the part and finally obtain the qualified part with the designed shape and performance, the graphene electrothermal film is communicated with a power supply through a lead, and the graphene electrothermal film generates heat to solidify the preformed piece.
The upper protective layer and the lower protective layer are both metal plates with the thickness of 1 mm.
The metal plate is a pure aluminum plate, and the characteristic of good aluminum formability is utilized, so that the molded surface of the die is continuous, and the surface of the formed part has no indentation.
When the carbon fiber prepreg cloth is laid, the included angle between adjacent carbon fiber carbon wire grains is 45 degrees, so that the strength and the toughness of parts are enhanced.
Compared with the traditional preparation method, the preparation cost of the horizontal stabilizer skin can be reduced by 30 percent, and the preparation period is reduced from the traditional 40 days to 30 days; the manufacturing cost of the lower skin of the central wing box can be reduced by 20%, and the manufacturing period is reduced from the original 14 days to 7 days; the manufacturing cost of the vertical tail skin can be reduced by 43 percent, and the manufacturing period is reduced from the previous 48 days to 24 days; the manufacturing cost of the skin on the rear fuselage can be reduced by 50%, and the manufacturing period is shortened from 50 days to 35 days. Because the adjacent carbon fiber carbon filament lines form an included angle of 45 degrees when the recarburized fiber prepreg cloth is laid, the strength and the toughness of the recarburized fiber prepreg cloth can be generally increased by 20-30 percent.
Example 2
The integrated forming manufacturing method of the carbon fiber reinforced resin matrix composite is characterized by comprising a carbon fiber prepreg 5, an upper graphene backing plate 3, a lower graphene backing plate 4, a multi-point upper die 1 and a multi-point lower die 2, wherein an upper protective layer 3-1, a graphene electrothermal film 3-2 and a lower protective layer 3-3 are sequentially arranged on the upper graphene backing plate 3 and the lower graphene backing plate 4 from top to bottom, and a copper wire is connected to the outer part of the graphene electrothermal film 3-2 to facilitate electrical connection; the basic body of the die is made of high-strength plastic, and the cross section of the basic body is square.
Firstly, laying a prepreg cloth:
laying the carbon fiber prepreg layer by layer on the lower graphene base plate, and then placing the upper graphene base plate on the carbon fiber prepreg;
step two, model adjustment: adjusting the shape of the multi-point upper die and the multi-point lower die to enable the molded surface to be in a target shape;
step three, moving: moving the combined lower graphene base plate, the carbon fiber prepreg cloth and the upper graphene base plate to be placed on a multi-point lower die;
step four, obtaining a preformed piece: the multipoint upper die moves downwards, and is matched with the multipoint lower die for pressure maintaining, so that the shape of the carbon fiber prepreg cloth is the same as the shapes of the molded surfaces of the multipoint upper die and the multipoint lower die, and a preformed piece is obtained;
step five, curing: the multipoint upper die and the multipoint lower die are kept in a die closing state to ensure the shape of the part and finally obtain the qualified part with the designed shape and performance, the graphene electrothermal film is communicated with a power supply through a lead, and the graphene electrothermal film generates heat to solidify the preformed piece.
The upper protective layer and the lower protective layer are both metal plates with the thickness of 2 mm.
The metal plate is a copper plate, and when the carbon fiber prepreg is laid, the included angle between adjacent carbon fiber carbon wire grains is 30 degrees. To enhance the strength and toughness of the part.
Compared with the traditional preparation method, the preparation cost of the horizontal stabilizer skin can be reduced by 30 percent, and the preparation period is reduced from the traditional 40 days to 28 days; the manufacturing cost of the lower skin of the central wing box can be reduced by 20%, and the manufacturing period is reduced from the original 14 days to 6 days; the manufacturing cost of the vertical tail wing skin can be reduced by 43 percent, and the manufacturing period is reduced from the previous 48 days to 26 days; the manufacturing cost of the skin on the rear fuselage can be reduced by 50%, and the manufacturing period is shortened from 50 days to 37 days. In addition, when the recarburized fiber prepreg is laid, the included angle of 30 degrees is formed between the adjacent carbon fiber carbon filament grains, so that the strength and the toughness of the carbon fiber carbon filament are generally increased by 15-20%.
Example 3
The integrated forming manufacturing method of the carbon fiber reinforced resin matrix composite is characterized by comprising a carbon fiber prepreg 5, an upper graphene backing plate 3, a lower graphene backing plate 4, a multi-point upper die 1 and a multi-point lower die 2, wherein an upper protective layer 3-1, a graphene electrothermal film 3-2 and a lower protective layer 3-3 are sequentially arranged on the upper graphene backing plate 3 and the lower graphene backing plate 4 from top to bottom, and a copper wire is connected to the outer part of the graphene electrothermal film 3-2 to facilitate electrical connection; the basic body of the die is made of aluminum plates or high-strength plastics, and the cross section of the basic body is in a regular hexagon shape.
Firstly, laying a prepreg cloth:
laying the carbon fiber prepreg layer by layer on the lower graphene base plate, and then placing the upper graphene base plate on the carbon fiber prepreg;
step two, model adjustment: adjusting the shape of the multi-point upper die and the multi-point lower die to enable the molded surface to be in a target shape;
step three, moving: moving the combined lower graphene base plate, the carbon fiber prepreg cloth and the upper graphene base plate to be placed on a multi-point lower die;
step four, obtaining a preformed piece: the multipoint upper die moves downwards, and is matched with the multipoint lower die for pressure maintaining, so that the shape of the carbon fiber prepreg cloth is the same as the shapes of the molded surfaces of the multipoint upper die and the multipoint lower die, and a preformed piece is obtained;
step five, curing: the multipoint upper die and the multipoint lower die are kept in a die closing state to ensure the shape of the part and finally obtain the qualified part with the designed shape and performance, the graphene electrothermal film is communicated with a power supply through a lead, and the graphene electrothermal film generates heat to solidify the preformed piece.
The upper protective layer and the lower protective layer are both aluminum plates with the thickness of 3 mm.
The metal plate is a pure aluminum plate, and the characteristic of good aluminum formability is utilized, so that the molded surface of the die is continuous, and the surface of the formed part has no indentation.
When the carbon fiber prepreg cloth is laid, the included angle between adjacent carbon fiber carbon filament lines is 60 degrees.
Compared with the traditional preparation method, the manufacturing cost of the horizontal stabilizer skin can be reduced by 30 percent, and the manufacturing period is reduced from the traditional 40 days to 31 days; the manufacturing cost of the lower skin of the central wing box can be reduced by 20%, and the manufacturing period is reduced from the original 14 days to 8 days; the manufacturing cost of the vertical tail skin can be reduced by 43 percent, and the manufacturing period is reduced from previous 48 days to 25 days; the manufacturing cost of the skin on the rear fuselage can be reduced by 50%, and the manufacturing period is shortened from 50 days to 34 days. In addition, when the recarburized fiber prepreg is laid, the included angle of 30 degrees is formed between the adjacent carbon fiber carbon filament grains, so that the strength and the toughness of the carbon fiber carbon filament are generally increased by 15-20%.
Claims (5)
1. The integrated forming manufacturing method of the carbon fiber reinforced resin matrix composite is characterized by comprising carbon fiber prepreg cloth, an upper graphene base plate, a lower graphene base plate, a multi-point upper die and a multi-point lower die, wherein an upper protective layer, a graphene electrothermal film and a lower protective layer are sequentially arranged on the upper graphene base plate and the lower graphene base plate from top to bottom, and the manufacturing method comprises the following steps:
firstly, laying a prepreg cloth:
laying the carbon fiber prepreg layer by layer on the lower graphene base plate, and then placing the upper graphene base plate on the carbon fiber prepreg;
step two, model adjustment: adjusting the shape of the multi-point upper die and the multi-point lower die to enable the molded surface to be in a target shape;
step three, moving: moving the combined lower graphene base plate, the carbon fiber prepreg cloth and the upper graphene base plate to be placed on a multi-point lower die;
step four, obtaining a preformed piece: the multipoint upper die moves downwards, and is matched with the multipoint lower die for pressure maintaining, so that the shape of the carbon fiber prepreg cloth is the same as the shapes of the molded surfaces of the multipoint upper die and the multipoint lower die, and a preformed piece is obtained;
step five, curing: the multipoint upper die and the multipoint lower die are kept in a die closing state, the graphene electrothermal film is communicated with a power supply through a lead, and the graphene electrothermal film generates heat to solidify the preformed piece.
2. The integrated forming method for carbon fiber reinforced resin matrix composite material as claimed in claim 1, wherein the upper protective layer and the lower protective layer are both metal plates with a thickness of 1-3 mm.
3. The integrated forming method for manufacturing the carbon fiber reinforced resin-based composite material as claimed in claim 1, wherein the metal plate is a pure aluminum plate.
4. The integrated forming and manufacturing method of the carbon fiber reinforced resin matrix composite material as claimed in claim 1, wherein an included angle between adjacent carbon fiber carbon filament lines is α degrees when the carbon fiber prepreg is laid.
5. The method for integrally forming the carbon fiber reinforced resin-based composite material as claimed in claim 4, wherein α is between 30 and 60 degrees.
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| CN202210537132.2A CN114889161A (en) | 2022-05-18 | 2022-05-18 | Integrated forming manufacturing method of carbon fiber reinforced resin matrix composite material |
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| CN101224480A (en) * | 2008-01-23 | 2008-07-23 | 哈尔滨工业大学 | Flexible multipoint forming lower die for sheet metal |
| EP2189269A1 (en) * | 2008-11-19 | 2010-05-26 | Createx S.A. | Method of producing sails using reinforced, formed fabrics |
| CN102458788A (en) * | 2009-06-08 | 2012-05-16 | 光纤芯Ip有限公司 | Mould system and method for operating said system |
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