CN113290884B - Composite material plate shell with thickness gradient region and forming device and method thereof - Google Patents

Composite material plate shell with thickness gradient region and forming device and method thereof Download PDF

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Publication number
CN113290884B
CN113290884B CN202110438048.0A CN202110438048A CN113290884B CN 113290884 B CN113290884 B CN 113290884B CN 202110438048 A CN202110438048 A CN 202110438048A CN 113290884 B CN113290884 B CN 113290884B
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composite material
film
material layer
air
felt
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CN113290884A (en
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徐云研
沈辉
鲁东东
赵丁丁
魏耀林
史文锋
邱保强
夏海祥
张国凯
张志斌
侯小龙
余娜
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Shanghai Composite Material Science and Technology Co Ltd
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Shanghai Composite Material Science and Technology Co Ltd
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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
    • B29C70/28—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • 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)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

The invention relates to a composite material plate shell with a thickness gradient region and a forming device and a forming method thereof in the technical field of composite material forming, wherein the forming device comprises a forming die, a ventilation demolding cloth, a porous isolating film, a surrounding strip, a ventilation felt and a vacuum film; the method comprises the steps that prepreg is paved between air-permeable release cloth and the inner surface of a forming die, the air-permeable release cloth, a porous isolation film, an air-permeable felt and a vacuum film are sequentially laminated on the prepreg, the side surfaces of surrounding strips are contacted with the end surface of a composite material layer, and the surrounding strips are used for preventing the composite material layer from flowing outwards; the air-permeable demolding cloth, the porous isolating film and the surrounding strips are covered in the air-permeable felt, the vacuum film is covered outside the air-permeable felt, and the vacuum film is connected with the surface of the forming die in a sealing way. The invention ensures that the pressure area applied to the composite material layer in the manufacturing process of the plate shell is uniform by the design of the pressure stabilizing structural member and the adsorption structural member, ensures that the loss amount of the composite material layer is in a control range, and improves the manufacturing quality of the plate shell.

Description

Composite material plate shell with thickness gradient region and forming device and method thereof
Technical Field
The invention relates to the technical field of composite material forming, in particular to a composite material plate shell with a thickness gradient region, and a forming device and a forming method thereof.
Background
The existing carrier rocket, satellite and spacecraft load-carrying structures for spaceflight use a large amount of high-strength composite materials, and the main advantage of the composite materials is that the composite materials have good weight-reducing effect and can increase the effective load of single-shot. In order to improve the structural strength and the bearing efficiency, a large-wall-thickness thickening area is generally arranged at a position with larger internal stress of the composite material plate shell bearing piece, and continuous and smooth transition from thick wall thickness to thin wall thickness is realized through the wall-thickness gradual change area. When the prepreg is used for layering and forming the plate shell, air is inevitably clamped between the prepreg layers, and the prepreg also contains a large amount of micromolecular volatile matters, so that the volatile matters are volatilized into gas during curing. In the prepreg compression process, the forming pressure of the thicker side of the gradual change region of the wall thickness of the plate shell is higher than that of the thinner side, so that gas in the gradual change region migrates from the thicker side to the thinner side and is converged into bubbles with larger size. In the curing process of the thick-wall plate shell, the gas is difficult to be completely discharged before the resin gel, so that part of the gas is retained between layers to form layering defects. The process flow is optimized, so that the sufficient discharge of the gas in the prepreg is realized, and the internal quality of the plate shell is improved.
According to the search of the prior patent literature, the invention patent of CN112123810A discloses a process method for improving the internal molding quality of a large-thickness composite rudder, which mainly solves the layering defect caused by migration of a release agent into a product and the wrinkling defect caused by hot press molding of a large-wall-thickness product press, but is not suitable for large-scale plate-shell products molded by an autoclave.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a composite material plate shell with a thickness gradient region, and a forming device and a forming method thereof.
The invention provides a forming device of a composite material plate shell with a thickness gradient region, which comprises a forming die, a breathable release cloth, a porous isolation film, a surrounding strip, a ventilated felt and a vacuum film, wherein the forming die is arranged on the surrounding strip;
the air-permeable demolding cloth, the porous isolating film, the air-permeable felt and the vacuum film are sequentially laminated on the prepreg, the side surfaces of the surrounding strips are contacted with the end surface of the composite material layer, and the surrounding strips are used for preventing the composite material layer from flowing outwards;
the air-permeable release cloth, the porous isolation film and the surrounding strips are covered in the air-permeable felt, the vacuum film is covered outside the air-permeable felt, and the vacuum film is in sealing connection with the surface of the forming die.
In some embodiments, a platen is also included and is disposed between the apertured separator film and the airfelt.
In some embodiments, the porous release film further comprises a suction felt disposed between the air-permeable release cloth and the porous release film.
In some embodiments, the forming die further comprises an isostatic pressing block, wherein the isostatic pressing block is attached to the side face of the surrounding strip and is located in the airfelt, an isostatic groove is arranged between the isostatic pressing block and the surface of the forming die, and the isostatic groove is communicated with the forming die along the circumferential direction of the forming die.
The invention also provides a forming method of the composite material plate shell with the thickness gradient region, which adopts the composite material plate shell forming device and comprises the following steps:
s1, cleaning: cleaning the inner surface of the forming die and coating a release agent;
s2, paving: paving part of prepreg on the inner surface of the forming die, sequentially surrounding the surrounding strips and the isobaric blocks on the side surface of the composite material layer from inside to outside, sequentially laminating the breathable release cloth, the porous isolating film, the ventilated felt and the vacuum film on the composite material layer, and carrying out normal-temperature vacuum compaction operation;
s3, hot pressing: the molding device operated in the step S2 is sent into an autoclave, and hot compacting operation is carried out through vacuumizing, heating and pressurizing, and after the hot compacting operation is finished, the breathable release cloth, the porous isolating film, the surrounding strips, the ventilated felt and the vacuum film are removed;
s4, the residual material paving step: laying the rest prepreg on the composite material layer formed in the step S3, sequentially stacking the breathable release cloth, the porous isolation film, the airfelt and the vacuum film on the composite material layer, enclosing the enclosing strip on the end surface of the composite material layer, and performing normal-temperature vacuum compaction operation;
s5, curing: sending the molding device operated in the step S4 into an autoclave, and forming a plate shell through vacuumizing, heating, pressurizing and solidifying and cooling;
s6, demolding: and removing the ventilation demolding cloth, the porous isolating film, the surrounding strips, the ventilation felt, the vacuum film and the isobaric blocks, and demolding to form the composite material plate shell with the thickness gradient region.
In some embodiments, in the step S2, a pressing plate is further disposed between the porous isolating film and the airfelt.
In some embodiments, in the step S3, a suction felt is disposed between the breathable release cloth and the porous release film.
In some embodiments, when the layer thickness of the composite material layer formed in the step S2 reaches 3-6mm, the hot pressing operation in the step S3 is performed once.
In some embodiments, in the step S5, the pressure application manner in the press curing is intermittent, and when the temperature rises to the preset temperature point, a corresponding pressure is applied, and the application of the pressure is stepwise.
The invention also provides a composite material plate shell with a thickness gradient region, the composite material plate shell with the thickness gradient region is manufactured by the forming method.
Compared with the prior art, the invention has the following beneficial effects:
1. the forming device for the composite material plate shell with the thickness gradient region provided by the invention has the advantages that the structure similar to the shell is formed by the airfelt, so that the gas exhausted by the composite material layer is concentrated in the shell of the airfelt and exhausted by the vacuum suction nozzle through the airfelt, and the removal rate of the gas is improved.
2. The forming device of the composite material plate shell with the thickness gradient region provided by the invention ensures that the pressure region applied to the composite material layer in the plate shell manufacturing process is uniform through the design of the voltage stabilizing structural part and the adsorption structural part, ensures that the loss amount of the composite material layer is in a control range, and improves the manufacturing quality of the plate shell
3. According to the forming method of the composite material plate shell with the thickness gradient region, provided by the invention, the glue absorbing felt with rated adsorption capacity is arranged in the composite material plate shell forming device in the hot pressing step, so that the loss capacity in the process of forming the plate shell by the composite material is controlled, and the manufacturing quality of the plate shell is improved.
4. According to the forming method of the composite material plate shell with the thickness gradient region, provided by the invention, through optimizing the hot pressing step and optimizing the position of the pressing plate, the gas discharge effect in the composite material layer compaction forming process is improved, and the manufacturing quality of the plate shell is improved
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a cross-sectional view of a composite plate and shell structure with a thickness transition zone of the present invention;
FIG. 2 is a schematic view of the overall structure of a composite plate shell with a thickness gradient region according to the present invention; the method comprises the steps of carrying out a first treatment on the surface of the
FIG. 3 is a process flow diagram of a method of forming a composite panel shell having a thickness transition region according to the present invention;
wherein, the marks in the drawings are as follows:
1-forming die, 2-ventilation release cloth, 3-porous isolating film, 4-surrounding strips, 5-ventilation felt, 6-vacuum film, 7-pressing plate, 8-adhesive absorbing felt, 9-equal pressing block, 10-isopipe, 100-composite material plate shell, 101-thickening area, 102-thickness gradual change area and 103-plain thickness area.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
The invention provides a forming device of a composite material plate shell with a thickness gradient region, which is particularly suitable for a forming device of a plate shell structure with a single curved surface or a double curved surface of a flange edge, as shown in figures 1-2, and comprises a forming die 1, an air-permeable demolding cloth 2, an apertured isolating film 3, a surrounding strip 4, an air-permeable felt 5 and a vacuum film 6. The forming die 1 is used as a basic bearing piece, and the composite material prepreg for forming the plate shell is paved on the inner surface of the forming die 1 to form a composite material layer. The shape of the forming die 1 is designed according to the shape of the plate shell to be manufactured, such as a typical structure comprising a hemispherical shape of an outer edge platform, a frustum shape, and the like. The surrounding strip 4 is movably arranged on the outer edge platform of the inner surface of the forming die 1, and one side surface of the surrounding strip 4 is used for being in fit contact with the side surface of the composite material layer and preventing the composite material layer from flowing outwards under the condition of pressurization and/or heating, and at the moment, the height of the surrounding strip 4 is higher than the thickness of the composite material layer at the contact part of the surrounding strip 4, so that the prepreg does not flow outwards. The air-permeable release cloth 2, the porous isolating film 3, the air-permeable felt 5 and the vacuum film 6 are sequentially arranged on the composite material layer in a lamination mode, and the air-permeable release cloth 2 is contacted with the composite material layer. Meanwhile, the airfelt 5 covers the airfelt release cloth 2, the porous isolating film 3 and the surrounding strips 4 inside, and the implementation mode can be realized by pressing the edges of the airfelt 5 on the inner surface of the forming die 1. The vacuum film 6 is covered on the outer layer of the airfelt 5 and is in sealing connection with the forming die 1, and the sealing connection can seal and press the edge of the vacuum film 6 on the inner surface of the forming die 1 through the sealing strip 11.
The working principle of the composite material plate and shell forming device provided by the invention is as follows: through the pressurizing and heating operation, the prepreg arranged between the inner surface of the forming die 1 and the ventilation release cloth 2 flows, the flow of the prepreg provides driving force for bubbles between the prepreg layers, the prepreg in the thickness gradient region carries the bubbles to move to a thinner equal thickness region, the bubbles in the prepreg interlayer escape through the porous isolation film 3 and are concentrated in the shell of the ventilation felt, and then the gas is discharged through the vacuum suction nozzle, so that the removal rate of the bubbles is improved.
Preferably, the laminated board 7 is arranged between the porous isolating film 3 and the airfelt 5, the laminated board 7 has the function of improving the flatness of the composite material layer, and mainly comprises a planar board, a curved board, a hyperboloid board and the like, when the laminated board is a planar board, the laminated board can be made of steel, when the laminated board is a curved board, the laminated board is mainly made of single-curved board and has certain flexibility, such as an aluminum laminated board with the thickness of 0.3mm and a glass fiber reinforced plastic laminated board with the thickness of 0.5mm, when the laminated board is a hyperboloid board, the laminated board formed by pressurizing a rubber soft film is preferable, so that the adaptability to molded surfaces is improved.
Example 2
The embodiment 2 is formed on the basis of the embodiment 1, and the pressure area applied to the composite material layer in the manufacturing process of the plate shell is uniform through the design of the pressure stabilizing structural member and the adsorption structural member, so that the loss amount of the composite material layer is ensured to be in a control range, and the manufacturing quality of the plate shell is improved.
As shown in fig. 1-2, a suction felt 8 with an adsorption function is arranged in the composite material plate shell forming device, and the suction felt 8 is arranged between the ventilation release cloth 2 and the porous isolating film 3 and is used for adsorbing the composite material overflowed in the process of pressurizing and heating the composite material layer. Through the adsorption capacity of the design suction felt 8, namely through the rated adsorption capacity of the design suction felt 8, the loss of the composite material is ensured to be in a controllable range, so that the consumption of the composite material of the formed plate shell is ensured, namely the density of the plate shell can be ensured, and the quality of the plate shell is improved.
Further, in the composite material panel case molding apparatus, an isopipe 9 is provided, the isopipe 9 is attached to the side surface of the surrounding strip 4, and after the isopipe 9 is connected to the surface of the molding die 1, an isopipe 10 is formed between the isopipe 9 and the molding die 1. The isopipe 10 is arranged to penetrate along the circumferential direction of the forming die 1, and when the isopipe 10 is vacuumized and pressurized, the isopipe 10 has the same pressure due to the penetration design, so that the pressure applied to the composite material layer can be ensured to have better uniformity, and the quality of the molded plate shell can be improved. The communication between the isopipe 10 and the external air can be achieved by providing micro gaps on the isopipe 9 or between the plurality of isopipes 9. The isopipe 10 is preferably provided on the ground of the isopipe 9, and is formed by forming a groove. Naturally, the isopipe 10 may be provided on the surface of the molding die 1, and may be formed by covering the square isopipe 9.
Example 3
In this embodiment 3, a method for forming a composite plate shell having a thickness gradient region is formed by using the forming apparatus for a composite plate shell having a thickness gradient region in embodiment 1 or embodiment 2, as shown in fig. 1 to 3, taking a composite plate shell having a large wall thickness and including a hyperboloid and a thickness gradient as an example, a main body portion of the composite plate shell 100 to be formed is in a spherical crown shape (double curvature profile), a planar flange is disposed on an outer edge of the main body, the flange and an adjacent partial spherical surface are in a thickening region 101, a main body portion thereof is referred to as a flat thickness region 103, and a distance from the thickening region 101 to the thickness gradient region 103 is referred to as a thickness gradient region 102. The thickness of the thickened region 101 is 12mm, the thickness of the flat region is 6mm, and a thickness gradual change region 102 with the length of 60mm is arranged between the thickened region 101 and the flat region 103. The prepreg used in the plate shell 2 is a carbon fiber/epoxy resin system, wherein the resin is high-temperature cured epoxy resin, the gel temperature is 120 ℃, the curing temperature is 200 ℃, and the required molding pressure is 0.8MPa. The method specifically comprises the following steps:
s1, cleaning and coating: the surface of the molding die 1 is cleaned and coated with a release agent.
S2, paving: part of the prepreg is paved on the inner surface of the forming die 1 to form a composite material layer, the surrounding strip 4 and the isobaric blocks 9 are sequentially surrounded on the outer side surface of the composite material layer from inside to outside, the isobaric blocks 9 are positioned on the outer side of the surrounding strip 4, the air-permeable release cloth 2, the porous isolating film 3, the pressing plate 7, the air-permeable felt 5 and the vacuum film 6 are sequentially laminated on the composite material layer, and vacuum compaction operation is carried out at normal temperature. The method comprises the following specific steps:
the surface of the molding die 1 was laid up with half of the total prepreg so that the thickness of the flat region 103 became 3mm and the thickness of the thickened region 101 became 6mm. In the laying process, the vacuum compaction operation is carried out once when the thickness of the composite material layer formed by laying the prepreg is increased by 0.6-1 mm. Before the vacuum compaction operation, the surrounding strip 4 and the isobaric block 9 are sequentially surrounded on the side surface of the composite material layer from inside to outside, the ventilation release cloth 2, the porous isolating film 3, the pressing plate 7, the ventilation felt 5 and the vacuum film 6 are sequentially stacked on the composite material layer, the ventilation felt 5 serves as a first layer of housing, the ventilation release cloth 2, the porous isolating film 3, the surrounding strip 4 and the isobaric block 9 are covered in, and the edges are sealed and pressed with the surface of the forming die 1 through sealing rubber strips. Meanwhile, the vacuum film 6 is used as a second layer of housing positioned on the outer layer of the airfelt 5, and the periphery of the vacuum film is sealed and pressed with the forming die 1 through sealing rubber strips. The vacuum pressure in the vacuum compaction operation is-0.10 to-0.090 MPa, and the pressure maintaining time is 1-48 hours.
S3, hot pressing: and (2) sending the forming device carrying the composite material layer in the step (S2) into an autoclave, vacuumizing until the vacuum pressure in the bag is minus 0.10 to minus 0.090MPa, heating to 80 ℃, then externally pressurizing by air or nitrogen for 0.5MPa, and standing the plate shell (2) for 1 to 4 hours under the environment after the pressurization is finished. After the hot compaction is finished, the temperature in the tank is firstly reduced to 30-60 ℃, and then pressure relief and vacuum stopping are sequentially carried out. After the hot compacting operation is finished by vacuumizing, heating and pressurizing, the ventilation release cloth 2, the porous isolating film 3, the surrounding strips 4, the pressing plate 7, the ventilation felt 5 and the vacuum film 6 are removed. Wherein, in the step, the temperature in the autoclave is 40-80 ℃, the external pressure is 0.1-0.5 MPa, and the vacuum pressure in the vacuum bag is-0.10 to-0.090 MPa.
S4, the residual material paving step: and (3) continuously paving the rest prepreg on the composite material layer formed in the step (S3), sequentially stacking the breathable release cloth 2, the porous isolating film 3, the pressing plate 7, the airfelt 5 and the vacuum film 6 on the composite material layer, enclosing the enclosing strip 4 on the end surface of the composite material layer, and carrying out vacuum compaction operation at normal temperature. The method comprises the following specific steps:
the surface of the molding die 1 was laid up with half of the total prepreg so that the wall thickness of the flat region became 6mm and the wall thickness of the thickened region became 12mm. In the course of the laying process, and (3) performing vacuum compaction operation once when the thickness of the composite material layer formed by laying the prepreg is increased by 0.8-1 mm. Before the vacuum compaction operation, the surrounding strip 4 and the isobaric block 9 are sequentially surrounded on the side surface of the composite material layer from inside to outside, the ventilation release cloth 2, the porous isolating film 3, the pressing plate 7, the ventilation felt 5 and the vacuum film 6 are sequentially stacked on the composite material layer, the ventilation felt 5 serves as a first layer of housing, the ventilation release cloth 2, the porous isolating film 3, the surrounding strip 4 and the isobaric block 9 are covered in, and the edges are sealed and pressed with the surface of the forming die 1 through sealing rubber strips. Meanwhile, the vacuum film 6 is used as a second layer of housing positioned on the outer layer of the airfelt 5, and the periphery of the vacuum film is sealed and pressed with the forming die 1 through sealing rubber strips. The vacuum pressure in the vacuum compaction operation is-0.10 to-0.090 MPa, and the pressure maintaining time is 1-48 hours.
S5, curing: and (3) conveying the composite material plate shell forming device bearing the composite material layer in the step (S4) into an autoclave, and forming a plate shell through vacuumizing, heating, pressurizing and solidifying and cooling. Wherein, vacuumizing to the vacuum pressure in the bag of-0.10 to-0.090 MPa, and heating, pressurizing and solidifying, wherein the solidifying pressure applying mode is discontinuous graded pressurizing, namely, different pressures are applied when the temperature is raised to different temperatures, and the applied pressure changes stepwise along with the temperature rise, specifically, the method comprises the following steps: pressurizing to 0.2MPa when the temperature is raised to 80 ℃, pressurizing to 0.4MPa when the temperature is raised to 100 ℃, pressurizing to 0.8MPa when the temperature is raised to 120 ℃, continuously heating to 200 ℃ after the pressurization is finished, and standing for 2-5 hours at the temperature of 200 ℃ and the pressure of 0.8MPa to finish curing to form the plate shell.
S6, demolding: and (3) removing the ventilation release cloth 2, the porous isolating film 3, the surrounding strips 4, the ventilation felt 5, the vacuum film 6, the pressing plate 7 and the isobaric blocks 9 from the heating tank of the composite material plate shell forming device in the step (S5), and separating the plate shell from the forming die 1.
Example 4
In the embodiment 4, the production quality of the plate shell is improved by optimizing the position of the pressing plate and improving the gas discharge effect in the compaction forming process of the composite material layer on the basis of the embodiment 3. Specifically:
the pressure plate 7 disposed between the apertured release film 3 and the airfelt 5 as shown in fig. 1-3 is laid partially, with the pressure plate 7 laid only on the thickened region 101, or with the pressure plate 7 laid only on the thickened region 101 and the thickness gradient region 102, the pressure exerted on the thickening area 101 and/or the thickness-graded area 102 can be effectively increased by the gravity of the pressing plate 7 itself, and the pressure can be effectively increased by the pressure or the heating, in particular by the heating, the driving force of resin flowing from a thicker region to a thinner region can be further improved, interlayer gas and micromolecular volatile gas in the prepreg in the thickness gradual change region are driven to flow from the thickness gradual change region to a thinner equal thickness region through the driving force, and then the gas is discharged, so that the gas discharge effect of the composite material in the compaction process is improved, and the compaction degree of the prepreg is improved.
Example 5
In the embodiment 5, the absorbent felt with rated absorption capacity is arranged in the composite material plate shell forming device in the hot pressing step, so that the loss amount in the process of forming the plate shell by the composite material is controlled, and the manufacturing quality of the plate shell is improved.
As shown in S5 of fig. 1 to 3, before the hot pressing step is started, a suction felt 8 with rated adsorption capacity is arranged between the ventilation release cloth 2 and the porous isolation film 3 before the composite board shell forming device loaded with the composite material layer is sent into the autoclave, and is used for adsorbing the composite material overflowed in the process of heating the composite material layer under pressure. Each of the suction adhesive 8 has rated adsorption capacity, namely, the suction adhesive felt 8 with corresponding rated adsorption capacity is designed and used to be placed at the corresponding part of the composite material layer to be heated and compacted to adsorb the resin and other composite materials overflowed due to heating, so that the loss of the composite materials is ensured within a controllable range, the consumption of the composite materials of the formed plate shell is further ensured, the density of the formed plate shell is ensured, and the quality of the plate shell is improved. The working principle is as follows: when heating, the resin in the thickness gradual change region flows to the outer direction of the prepreg surface, and enters the suction felt 8 after passing through the ventilation release cloth 2, and as the porous isolation film 3 is arranged on the outer side of the suction felt 8, after the suction felt 8 reaches the rated adsorption capacity, the porous isolation film 3 limits the loss amount of the resin, so that the quantitative discharge of the resin is realized, namely: not only can bring out interlayer bubbles, but also can not cause excessive resin loss
The suction felt 6 can be formed by stacking a plurality of layers of alkali-free glass fiber fabrics, for example, the suction felt can be formed by stacking 3 layers of alkali-free glass fiber fabrics with the thickness of 0.6mm and the thickness of 0.2 mm.
Further preferably, the position of the suction felt 8 can be adjusted according to the thickness of the composite material layer, for example, when the wall thickness of a partial region of the finally manufactured plate shell is thinner, for example, less than or equal to 1.5mm, the suction felt 8 is not arranged at the partial region, the suction felt is arranged only at the region with thicker wall thickness, and the material loss transition such as resin is realized at the partial region with thinner wall thickness.
Example 6
Embodiment 6 is a composite panel housing formed on the basis of any one of embodiments 3 to 5, the composite panel housing having a thickness gradient region being formed by the method for forming a composite panel housing having a thickness gradient region described in any one of embodiments 3 to 5.
In the description of the present application, it is to be understood that, the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate an azimuth or a positional relationship based on that shown in the drawings, it is used solely for convenience in describing the present application and for simplicity of description, and does not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operate in a particular orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.

Claims (3)

1. The forming device of the composite material plate shell with the thickness gradual change area is characterized by comprising a forming die (1), an air-permeable demolding cloth (2), a porous isolating film (3), a surrounding strip (4), an air-permeable felt (5) and a vacuum film (6);
the air-permeable demolding cloth (2) and the inner surface of the forming mold (1) are used for paving prepreg, the air-permeable demolding cloth (2), the porous isolating film (3), the air-permeable felt (5) and the vacuum film (6) are sequentially laminated on the prepreg, the side surfaces of the surrounding strips (4) are in contact with the end surfaces of the composite material layer, and the surrounding strips (4) are used for preventing the composite material layer from flowing outwards;
the air-permeable demolding cloth (2), the porous isolating film (3) and the surrounding strips (4) are covered in the air-permeable felt (5), the vacuum film (6) is covered outside the air-permeable felt (5), and the vacuum film (6) is in sealing connection with the surface of the forming mold (1);
the molding machine further comprises an equal pressure block (9), wherein the equal pressure block (9) is attached to the side face of the surrounding strip (4) and is positioned in the airfelt (5), an equal pressure groove (10) is arranged between the equal pressure block (9) and the surface of the molding die (1), and the equal pressure groove (10) is communicated and arranged along the circumferential direction of the molding die (1);
the air-permeable felt also comprises a pressing plate (7), wherein the pressing plate (7) is arranged between the porous isolating film (3) and the air-permeable felt (5);
the porous isolation film is characterized by further comprising a glue absorbing felt (8), wherein the glue absorbing felt (8) is paved between the breathable release cloth (2) and the porous isolation film (3), and the loss of the composite material is ensured to be in a controllable range through the design of the rated adsorption quantity of the glue absorbing felt (8).
2. A method for forming a composite plate shell with a thickness gradient region, characterized in that the composite plate shell forming device as claimed in claim 1 is adopted, comprising the following steps:
s1, cleaning: cleaning the inner surface of the forming die (1) and coating a release agent;
s2, paving: paving part of prepreg on the inner surface of the forming die (1), sequentially surrounding the surrounding strips (4) and the isobaric blocks (9) on the side surface of the composite material layer from inside to outside, sequentially layering the breathable release cloth (2), the porous isolating film (3), the airfelt (5) and the vacuum film (6) on the composite material layer, and carrying out normal-temperature vacuum compaction operation;
s3, hot pressing: the molding device operated in the step S2 is sent into an autoclave, and hot compacting operation is carried out through vacuumizing, heating and pressurizing, and after the hot compacting operation is finished, the breathable release cloth (2), the porous isolating film (3), the surrounding strips (4), the airfelt (5) and the vacuum film (6) are removed;
s4 the process comprises, and (3) paving the residual materials: paving the rest prepreg on the composite material layer formed in the step S3, sequentially layering the breathable release cloth (2), the porous isolation film (3), the airfelt (5) and the vacuum film (6) on the composite material layer, enclosing the enclosing strip (4) on the end surface of the composite material layer, and performing normal-temperature vacuum compaction operation, wherein in the paving process, the vacuum compaction operation is performed once when the temperature of the composite material layer formed by paving the prepreg is increased by 0.8-1 mm;
s5, curing: sending the molding device operated in the step S4 into an autoclave, and forming a plate shell through vacuumizing, heating, pressurizing and solidifying and cooling;
s6, demolding: removing the ventilation demolding cloth (2), the porous isolating film (3), the surrounding strips (4), the ventilation felt (5), the vacuum film (6) and the isobaric blocks (9), and demolding to form a composite material plate shell with a thickness gradient region;
in the step S2, a pressing plate (7) is further arranged between the porous isolation film (3) and the airfelt (5);
in the step S3, a glue absorbing felt (8) is arranged between the breathable release cloth (2) and the porous isolation film (3);
when the layer thickness of the composite material layer formed in the step S2 reaches 3-6mm, performing hot pressing operation in the step S3 once;
in the step S5, the pressure application mode in the press curing is intermittent, and when the temperature rises to the preset temperature point, a corresponding pressure is applied, and the application of the pressure is stepwise.
3. A composite panel shell having a thickness gradient region, wherein the composite panel shell is manufactured by the method of forming a composite panel shell having a thickness gradient region as set forth in claim 2.
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CN115256998B (en) * 2022-08-05 2024-06-25 西安电子科技大学 Method for inhibiting fiber wrinkling during compaction of composite components
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