CN114211787B - Preparation method of carbon fiber laminated plate with multilayer space structure - Google Patents

Preparation method of carbon fiber laminated plate with multilayer space structure Download PDF

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Publication number
CN114211787B
CN114211787B CN202111529774.XA CN202111529774A CN114211787B CN 114211787 B CN114211787 B CN 114211787B CN 202111529774 A CN202111529774 A CN 202111529774A CN 114211787 B CN114211787 B CN 114211787B
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carbon fiber
plate
layer
corrugated
boss
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CN114211787A (en
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孙福臻
蔡克乾
王剑锋
杨娜
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Harbin Institute of Technology Weihai
Beijing National Innovation Institute of Lightweight Ltd
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Harbin Institute of Technology Weihai
Beijing National Innovation Institute of Lightweight Ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D7/00—Producing flat articles, e.g. films or sheets
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/52—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive
    • B29C65/54—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive between pre-assembled parts
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B29C66/1122—Single lap to lap joints, i.e. overlap joints
    • 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
    • B29C70/224—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 a net
    • 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
    • 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
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/30—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer formed with recesses or projections, e.g. hollows, grooves, protuberances, ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • 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

Abstract

A preparation method of a carbon fiber laminated plate with a multi-layer space structure relates to a preparation method of a carbon fiber laminated plate. The invention aims to solve the problems that the existing carbon fiber composite material lattice structure is complex in preparation process, difficult in mass production, unstable in surface core connection and easy to break and fall off. The method comprises the following steps: 1. pre-treating a mould; 2. pretreating fiber prepreg; 3. molding; 4. solidifying and demoulding to obtain a carbon fiber corrugated plate; 5. cutting to obtain a single-layer lattice core substrate; 6. overlapping to obtain a lattice core corrugated plate; seventh,: and assembling to obtain the carbon fiber laminated board with the multi-layer space structure. The advantages are that: the preparation process is simple, and the popularization is utilized to increase the bonding contact surface and improve the mechanical property of the dot matrix core corrugated plate. The method is mainly used for preparing the carbon fiber laminated plate with the multilayer space structure.

Description

Preparation method of carbon fiber laminated plate with multilayer space structure
Technical Field
The invention relates to a preparation method of a carbon fiber laminated plate.
Background
The lattice plate is a hollow structural plate with low mass density and high mechanical performance. At present, research on the metal lattice structure forms at home and abroad is mature, and lattice structures of various topological configurations such as pyramids, tetrahedrons, octahedrons and the like are proposed; however, the existing carbon fiber composite lattice structure has the problems of complex preparation process, difficult mass production, unstable connection of the surface core and easy occurrence of fracture and falling.
Disclosure of Invention
The invention aims to solve the problems that the existing carbon fiber composite material lattice structure is complex in preparation process and difficult in mass production, and the surface cores are not firmly connected and are easy to break and fall off, and provides a preparation method of a carbon fiber laminated plate with a multi-layer space structure.
The preparation method of the carbon fiber laminated plate with the multilayer space structure comprises the following steps:
1. and (3) die pretreatment: the die comprises an upper extrusion die plate and a lower extrusion die plate, wherein an upper corrugated boss is arranged on one side of the upper extrusion die plate, which faces the direction of the lower extrusion die plate, and a lower corrugated boss is arranged on one side of the lower extrusion die plate, which faces the direction of the upper extrusion die plate, and is meshed with the lower corrugated boss; cleaning an upper corrugated boss and a lower corrugated boss by adopting acetone, and then coating a release agent on the surfaces of the upper corrugated boss and the lower corrugated boss to obtain a pretreated die;
2. pretreatment of fiber prepreg: according to the thickness of the carbon fiber corrugated plate which is actually required, calculating the specific number n of the single-layer unidirectional carbon fiber prepregs according to the thickness of the single-layer unidirectional carbon fiber prepreg, then alternately paving the n single-layer unidirectional carbon fiber prepregs according to three directions of 0/45 degrees/90 degrees to obtain a plurality of layers of carbon fiber prepregs, and preheating the plurality of layers of carbon fiber prepregs at the temperature of 20-30 ℃ to obtain a preheated plurality of layers of carbon fiber prepregs;
3. and (3) compression molding: paving the preheated multi-layer carbon fiber prepreg on the surface of a lower corrugated boss of a lower extrusion die plate, enabling the preheated multi-layer carbon fiber prepreg to be in contact and fit with the surface of the lower corrugated boss, closing the upper extrusion die plate and the lower extrusion die plate by using bolts, and controlling the forming pressure to be 3-8 MPa by using the bolts to obtain a die for loading the carbon fiber pretreatment piece;
4. curing and demolding: placing the die loaded with the carbon fiber pretreatment piece in a curing furnace for curing, and then demolding to obtain a carbon fiber corrugated plate;
5. cutting: cutting the corrugated boss of the carbon fiber corrugated plate along the direction perpendicular to the corrugated boss of the carbon fiber corrugated plate according to the size of the inverted corrugated boss to obtain a single-layer lattice core substrate;
6. overlapping: the two single-layer lattice core substrates are aligned and overlapped in a mode of forming a regular quadrangular frustum pyramid boss by mutually perpendicular corrugated bosses, and the surface contact parts of the two single-layer lattice core substrates are glued by brushing, so that a lattice core corrugated plate is obtained;
seventh,: and (3) assembling: and (3) aligning and superposing one side of the regular quadrangular frustum pyramid boss of the upper fixing plate and one side of the dot matrix core corrugated plate, which is far away from the regular quadrangular frustum pyramid boss, and then brushing and gluing the side of the lower fixing plate and one side of the dot matrix core corrugated plate, which is aligned and superposed, so as to obtain the carbon fiber laminated plate with the multilayer space structure.
The invention has the advantages that:
1. the invention only cuts the carbon fiber corrugated plate once to prepare the single-layer lattice core substrate, and then stacks the two single-layer lattice core substrates to obtain the lattice core corrugated plate, so that the preparation process is simple, the preparation of the large-area carbon fiber laminated plate is convenient, the popularization is facilitated, and the batch production is carried out.
2. The lug boss of the lattice core corrugated plate is in a regular quadrangular frustum pyramid shape, the lattice core corrugated plate is adhered to the upper fixing plate and the lower fixing plate through the brush adhesive, compared with a common regular quadrangular pyramid lattice structure sandwich plate, the point contact of the regular quadrangular frustum pyramid lug boss and the bonding side of the upper fixing plate is changed into the surface contact, the bonding contact surface is increased, the problem that the core plate is not firmly connected with the fixing plate and is easy to break and fall off is avoided, and the dispersion effect of the regular quadrangular frustum pyramid lug boss on concentrated loads is better.
3. The two single-layer lattice core substrates are mutually perpendicular and complementary to form a complete regular quadrangular frustum pyramid boss, and the formation of the regular quadrangular frustum pyramid boss enables the two single-layer lattice core substrates to have an interactive supporting force, so that the mechanical property of the lattice core corrugated plate is improved.
4. According to the thickness of the carbon fiber corrugated plate which is actually required, the specific layer number of the single-layer unidirectional carbon fiber prepreg is calculated according to the thickness of the single-layer unidirectional carbon fiber prepreg, and the first limiting plate and the second limiting plate with proper thicknesses can be selected according to the thickness of the carbon fiber corrugated plate which is actually required; the carbon fiber laminate of the multi-layer space structure of the actually required thickness can be precisely manufactured.
Drawings
FIG. 1 is a schematic diagram of a mold structure according to the present invention.
Fig. 2 is a schematic structural view of a carbon fiber laminated board of a multi-layered space structure according to the present invention.
Fig. 3 is a schematic structural view of a carbon fiber laminated central matrix core corrugated plate with a multi-layer space structure according to the present invention.
FIG. 4 is a schematic structural view of a single-layer lattice core substrate according to the present invention.
In the accompanying drawings: the device comprises a 1-upper extrusion die plate, a 2-lower extrusion die plate, a 3-lattice core corrugated plate, a 31-single-layer lattice core substrate, a 32-regular quadrangular frustum pyramid boss, a 4-upper fixing plate, a 5-lower fixing plate, a 6-first limiting plate and a 7-second limiting plate.
Detailed Description
The first embodiment is as follows: the embodiment is a preparation method of a carbon fiber laminated plate with a multi-layer space structure, which is specifically completed by the following steps:
1. and (3) die pretreatment: the die comprises an upper extrusion die plate 1 and a lower extrusion die plate 2, wherein an upper corrugated boss is arranged on one side of the upper extrusion die plate 1, which faces the direction of the lower extrusion die plate 2, a lower corrugated boss is arranged on one side of the lower extrusion die plate 2, which faces the direction of the upper extrusion die plate 1, and the upper corrugated boss is meshed with the lower corrugated boss; cleaning an upper corrugated boss and a lower corrugated boss by adopting acetone, and then coating a release agent on the surfaces of the upper corrugated boss and the lower corrugated boss to obtain a pretreated die;
2. pretreatment of fiber prepreg: according to the thickness of the carbon fiber corrugated plate which is actually required, calculating the specific number n of the single-layer unidirectional carbon fiber prepregs according to the thickness of the single-layer unidirectional carbon fiber prepreg, then alternately paving the n single-layer unidirectional carbon fiber prepregs according to three directions of 0/45 degrees/90 degrees to obtain a plurality of layers of carbon fiber prepregs, and preheating the plurality of layers of carbon fiber prepregs at the temperature of 20-30 ℃ to obtain a preheated plurality of layers of carbon fiber prepregs;
3. and (3) compression molding: laying the preheated multi-layer carbon fiber prepreg on the surface of a lower corrugated boss of a lower extrusion die plate 2, enabling the preheated multi-layer carbon fiber prepreg to be in contact and fit with the surface of the lower corrugated boss, closing the die of the upper extrusion die plate 1 and the lower extrusion die plate 2 by using bolts, and controlling the forming pressure to be 3-8 MPa by using the bolts to obtain a die for loading the carbon fiber pretreatment piece;
4. curing and demolding: placing the die loaded with the carbon fiber pretreatment piece in a curing furnace for curing, and then demolding to obtain a carbon fiber corrugated plate;
5. cutting: cutting the corrugated bosses of the carbon fiber corrugated plate along the direction perpendicular to the corrugated bosses of the carbon fiber corrugated plate according to the size of the inverted corrugated bosses to obtain a single-layer lattice core substrate 31;
6. overlapping: the two single-layer lattice core substrates 31 are aligned and overlapped in a mode of forming a regular quadrangular frustum pyramid boss 32 by mutually perpendicular corrugated bosses, and the surface contact parts of the two single-layer lattice core substrates 31 are bonded by glue brushing to obtain a lattice core corrugated plate 3;
seventh,: and (3) assembling: and (3) aligning and superposing one side of the regular quadrangular frustum pyramid boss 32 of the upper fixing plate 4 and one side of the dot matrix core corrugated plate 3, brushing and gluing, and aligning and superposing one side of the lower fixing plate 5, which is away from the regular quadrangular frustum pyramid boss 32, of the dot matrix core corrugated plate 3, and gluing, so as to obtain the carbon fiber laminated plate with the multilayer space structure.
The second embodiment is as follows: the present embodiment differs from the first embodiment in that: in the first step, the die comprises a first limiting plate 6 and a second limiting plate 7, and the first limiting plate 6 and the second limiting plate 7 are arranged on two opposite sides between the upper extrusion die plate 1 and the lower extrusion die plate 2. The other is the same as in the first embodiment.
And a third specific embodiment: this embodiment differs from the first or second embodiment in that: in the second step, the multi-layer carbon fiber prepreg is sequentially divided into a first layer, a second layer, a third layer, a fourth layer and a fifth layer from top to bottom, wherein the first layer is formed by alternately paving four layers of unidirectional carbon fiber prepregs from top to bottom according to 45 degrees/0/45 degrees/0, the second layer is formed by alternately paving a plurality of layers of unidirectional carbon fiber prepregs from top to bottom according to 90 degrees/0, the third layer is formed by alternately paving two layers of unidirectional carbon fiber prepregs from top to bottom according to 45 degrees/0, the fourth layer is formed by alternately paving a plurality of layers of unidirectional carbon fiber prepregs from top to bottom according to 90 degrees/0, and the fifth layer is formed by alternately paving two layers of unidirectional carbon fiber prepregs from top to bottom according to 45 degrees/90 degrees. The other embodiments are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: one difference between this embodiment and the first to third embodiments is that: the concrete process of curing in the fourth step is as follows: the temperature in the curing furnace is firstly heated to 110-130 ℃ from the room temperature at the heating rate of 1-4 ℃/min, then the temperature is kept for 60-120 min under the condition of 110-130 ℃, and then the curing is completed after the furnace is cooled to 50-60 ℃. The other embodiments are the same as those of the first to third embodiments.
Fifth embodiment: one to four differences between the present embodiment and the specific embodiment are: in the fifth step, the thickness of the single-layer lattice core substrate 31 is 1.5 mm-3 mm. The other embodiments are the same as those of the first to fourth embodiments.
Specific embodiment six: the present embodiment differs from the first to fifth embodiments in that: in the fifth step, the width of the top of the corrugated boss of the single-layer lattice core substrate 31 is 12mm, the width of the bottom of the corrugated boss is 27mm, and the height of the corrugated boss is 20mm. The other embodiments are the same as those of the first to fifth embodiments.
Seventh embodiment: one difference between the present embodiment and the first to sixth embodiments is that: in the sixth step, the top of the regular quadrangular frustum pyramid boss 32 of the lattice core corrugated plate 3 is square, the side length is 12mm, the bottom of the regular quadrangular frustum pyramid boss 32 is square, and the side length is 27mm. The other embodiments are the same as those of the first to sixth embodiments.
Eighth embodiment: one difference between the present embodiment and the first to seventh embodiments is that: in the seventh step, the upper fixing plate 4 and the lower fixing plate 5 are both carbon fiber plates. The other embodiments are the same as those of the first to seventh embodiments.
Detailed description nine: the eighth difference between this embodiment and the specific embodiment is that: the thickness of the carbon fiber plate is 2mm. The other is the same as in the eighth embodiment.
Detailed description ten: the present embodiment differs from the first to ninth embodiments in that: and step six and step seven, wherein the glue is DP460 epoxy resin glue. The other embodiments are the same as those of the first to ninth embodiments.
The present invention is not limited to the above embodiments, and the object of the invention can be achieved by one or a combination of several embodiments.
The following experiments are adopted to verify the effect of the invention:
example 1: the preparation method of the carbon fiber laminated plate with the multilayer space structure comprises the following steps:
1. and (3) die pretreatment: the die comprises an upper extrusion die plate 1 and a lower extrusion die plate 2, wherein an upper corrugated boss is arranged on one side of the upper extrusion die plate 1, which faces the direction of the lower extrusion die plate 2, a lower corrugated boss is arranged on one side of the lower extrusion die plate 2, which faces the direction of the upper extrusion die plate 1, and the upper corrugated boss is meshed with the lower corrugated boss; cleaning an upper corrugated boss and a lower corrugated boss by adopting acetone, and then coating a release agent on the surfaces of the upper corrugated boss and the lower corrugated boss to obtain a pretreated die;
2. pretreatment of fiber prepreg: according to the thickness of a carbon fiber corrugated plate of 2mm actually required, calculating the specific number of 16 layers of single-layer unidirectional carbon fiber prepregs according to the thickness of 0.125mm of the single-layer unidirectional carbon fiber prepreg, and then alternately paving 16 layers of single-layer unidirectional carbon fiber prepregs according to three directions of 0/45 degrees/90 degrees to obtain a plurality of layers of carbon fiber prepregs, wherein the plurality of layers of carbon fiber prepregs are sequentially divided into a first layer, a second layer, a third layer, a fourth layer and a fifth layer from top to bottom, the first layer is alternately paved according to 45 degrees/0/45 degrees/0 from top to bottom, the second layer is alternately paved according to 90 degrees/0 from top to bottom, the third layer is alternately paved according to 45 degrees/0 degrees from top to bottom, the fourth layer is alternately paved according to 90 degrees/0 degrees from top to bottom, and the fifth layer is alternately paved according to 45 degrees/90 degrees from top to bottom; preheating the multi-layer carbon fiber prepreg at the temperature of 25 ℃ to obtain the preheated multi-layer carbon fiber prepreg;
3. and (3) compression molding: laying the preheated multi-layer carbon fiber prepreg on the surface of a lower corrugated boss of a lower extrusion die plate 2, enabling the preheated multi-layer carbon fiber prepreg to be in contact with the surface of the lower corrugated boss, closing the dies of the upper extrusion die plate 1 and the lower extrusion die plate 2 by using bolts, and controlling the forming pressure to be 5MPa by using the bolts to obtain a die for loading the carbon fiber pretreatment piece;
4. curing and demolding: placing the die loaded with the carbon fiber pretreatment piece in a curing furnace for curing, and then demolding to obtain a carbon fiber corrugated plate;
5. cutting: cutting the corrugated bosses of the carbon fiber corrugated plate along the direction perpendicular to the corrugated bosses of the carbon fiber corrugated plate according to the size of the inverted corrugated bosses to obtain a single-layer lattice core substrate 31;
6. overlapping: the two single-layer lattice core substrates 31 are aligned and overlapped in a mode of forming a regular quadrangular frustum pyramid boss 32 by mutually perpendicular corrugated bosses, and the surface contact parts of the two single-layer lattice core substrates 31 are bonded by glue brushing to obtain a lattice core corrugated plate 3;
seventh,: and (3) assembling: and (3) aligning and superposing one side of the regular quadrangular frustum pyramid boss 32 of the upper fixing plate 4 and one side of the dot matrix core corrugated plate 3, brushing and gluing, and aligning and superposing one side of the lower fixing plate 5, which is away from the regular quadrangular frustum pyramid boss 32, of the dot matrix core corrugated plate 3, and gluing, so as to obtain the carbon fiber laminated plate with the multilayer space structure.
The die in step one of embodiment 1 includes a first limiting plate 6 and a second limiting plate 7, and the first limiting plate 6 and the second limiting plate 7 are disposed on opposite sides between the upper extrusion die plate 1 and the lower extrusion die plate 2.
In the second step of example 1, 12 single-layer unidirectional carbon fiber prepregs were alternately laid in a direction of 0/90 ° to obtain a multilayer carbon fiber prepreg.
The specific procedure for curing described in step four of example 1 is as follows: the temperature in the curing furnace is firstly increased from room temperature to 120 ℃ at the heating rate of 2 ℃/min, then the temperature is kept for 90min under the condition that the temperature is 120 ℃, and then the curing is completed after the furnace is cooled to 60 ℃.
The thickness of the single-layer lattice core substrate 31 in the fifth step of example 1 is 2mm; the width of the top of the corrugated boss of the single-layer lattice core substrate 31 is 12mm, the width of the bottom of the corrugated boss is 27mm, and the height of the corrugated boss is 20mm.
In the sixth step of example 1, the top of the regular quadrangular frustum pyramid shaped boss 32 of the lattice core corrugated plate 3 is square, the side length is 12mm, the bottom of the regular quadrangular frustum pyramid shaped boss 32 is square, and the side length is 27mm.
In the seventh step of embodiment 1, the upper fixing plate 4 and the lower fixing plate 5 are both carbon fiber boards; the thickness of the carbon fiber plate is 2mm.
The glue described in example 1, step six and step seven, was DP460 epoxy glue.
Comparative example 1: pyramid lattice structure sandwich board:
firstly, dividing a carbon fiber laminated board with the thickness of 2mm into a plurality of regular triangle carbon fiber laminated boards, bonding and combining a pyramid lattice with the height of 20mm by brushing glue every four regular triangle carbon fiber laminated boards, sequentially uniformly bonding the plurality of pyramid lattices on a lower fixing plate, bonding one side of two adjacent pyramid lattices with one side being away from the direction of the lower fixing plate, and bonding an upper fixing plate on one side of the pyramid lattice with the direction away from the lower fixing plate to obtain a pyramid lattice structure sandwich board; the upper fixing plate is the same as the upper fixing plate 4 described in embodiment 1, and the lower fixing plate is the same as the lower fixing plate 5 described in embodiment 1.
The load test is carried out on the carbon fiber laminated plate with the multilayer space structure obtained in the example 1 and the pyramid lattice structure sandwich plate obtained in the comparison example 1, so that the maximum load value of the carbon fiber laminated plate with the multilayer space structure obtained in the example 1 is 14464.3N, while the maximum load value of the pyramid lattice structure sandwich plate obtained in the comparison example 1 is 13158.6N, and under the condition that the thicknesses are the same, the load of the carbon fiber laminated plate with the multilayer space structure prepared by the invention is improved under the condition that the problem that the connection between the sandwich plate and the fixed plate is not firm and is easy to break and fall off is solved.

Claims (10)

1. The preparation method of the carbon fiber laminated plate with the multilayer space structure is characterized by comprising the following steps of:
1. and (3) die pretreatment: the die comprises an upper extrusion die plate (1) and a lower extrusion die plate (2), wherein an upper corrugated boss is arranged on one side of the upper extrusion die plate (1) facing the direction of the lower extrusion die plate (2), a lower corrugated boss is arranged on one side of the lower extrusion die plate (2) facing the direction of the upper extrusion die plate (1), and the upper corrugated boss is meshed with the lower corrugated boss; cleaning an upper corrugated boss and a lower corrugated boss by adopting acetone, and then coating a release agent on the surfaces of the upper corrugated boss and the lower corrugated boss to obtain a pretreated die;
2. pretreatment of fiber prepreg: according to the thickness of the carbon fiber corrugated plate which is actually required, calculating the specific number n of the single-layer unidirectional carbon fiber prepregs according to the thickness of the single-layer unidirectional carbon fiber prepreg, then alternately paving the n single-layer unidirectional carbon fiber prepregs according to three directions of 0/45 degrees/90 degrees to obtain a plurality of layers of carbon fiber prepregs, and preheating the plurality of layers of carbon fiber prepregs at the temperature of 20-30 ℃ to obtain a preheated plurality of layers of carbon fiber prepregs;
3. and (3) compression molding: laying the preheated multi-layer carbon fiber prepreg on the surface of a lower corrugated boss of a lower extrusion die plate (2), enabling the preheated multi-layer carbon fiber prepreg to be in contact and fit with the surface of the lower corrugated boss, closing the upper extrusion die plate (1) and the lower extrusion die plate (2) by using bolts, and controlling the forming pressure to be 3-8 MPa by using the bolts to obtain a die for loading the carbon fiber pretreatment piece;
4. curing and demolding: placing the die loaded with the carbon fiber pretreatment piece in a curing furnace for curing, and then demolding to obtain a carbon fiber corrugated plate;
5. cutting: cutting the corrugated boss of the carbon fiber corrugated plate along the direction perpendicular to the corrugated boss of the carbon fiber corrugated plate according to the size of the inverted corrugated boss to obtain a single-layer lattice core substrate (31);
6. overlapping: the two single-layer lattice core substrates (31) are aligned and overlapped in a mode of forming a regular quadrangular frustum pyramid boss (32) according to the corrugated boss mutually perpendicular, and the surface contact positions of the two single-layer lattice core substrates (31) are bonded by brushing glue to obtain a lattice core corrugated plate (3);
seventh,: and (3) assembling: and (3) aligning and superposing one side of the regular quadrangular frustum pyramid boss (32) of the upper fixing plate (4) and one side of the dot matrix core corrugated plate (3) opposite to the direction of the regular quadrangular frustum pyramid boss (32) of the lower fixing plate (5) and one side of the dot matrix core corrugated plate (3) and brushing and gluing and bonding, and obtaining the carbon fiber laminated plate with the multi-layer space structure.
2. The method for manufacturing a carbon fiber laminated plate with a multi-layer space structure according to claim 1, wherein in the first step, the mold comprises a first limiting plate (6) and a second limiting plate (7), and the first limiting plate (6) and the second limiting plate (7) are arranged on two opposite sides between the upper extrusion die plate (1) and the lower extrusion die plate (2).
3. The method for preparing the carbon fiber laminated plate with the multilayer space structure according to claim 2, wherein in the second step, the multilayer carbon fiber prepreg is sequentially divided into a first layer, a second layer, a third layer, a fourth layer and a fifth layer from top to bottom, wherein the first layer is formed by alternately paving four layers of unidirectional carbon fiber prepregs from top to bottom according to 45 degrees/0/45 degrees/0, the second layer is formed by alternately paving a plurality of layers of unidirectional carbon fiber prepregs from top to bottom according to 90 degrees/0, the third layer is formed by alternately paving two layers of unidirectional carbon fiber prepregs from top to bottom according to 45 degrees/0, the fourth layer is formed by alternately paving a plurality of layers of unidirectional carbon fiber prepregs from top to bottom according to 90 degrees/0, and the fifth layer is formed by alternately paving two layers of unidirectional carbon fiber prepregs from top to bottom according to 45 degrees/90 degrees.
4. A method for producing a carbon fiber laminate having a multi-layered space structure according to claim 3, wherein the curing in the fourth step is performed as follows: the temperature in the curing furnace is firstly heated to 110-130 ℃ from the room temperature at the heating rate of 1-4 ℃/min, then the temperature is kept for 60-120 min under the condition of 110-130 ℃, and then the curing is completed after the furnace is cooled to 50-60 ℃.
5. The method for producing a carbon fiber laminate having a multi-layered spatial structure according to claim 4, wherein the thickness of the single-layered lattice core substrate (31) in the fifth step is 1.5mm to 3mm.
6. The method for manufacturing a carbon fiber laminated plate with a multi-layer space structure according to claim 5, wherein in the fifth step, the width of the top of the corrugated boss of the single-layer lattice core substrate (31) is 12mm, the width of the bottom of the corrugated boss is 27mm, and the height of the corrugated boss is 20mm.
7. The method for manufacturing a carbon fiber laminated plate with a multi-layer space structure according to claim 6, wherein in the sixth step, the top of the regular quadrangular frustum pyramid shaped boss (32) of the lattice core corrugated plate (3) is square, the side length is 12mm, the bottom of the regular quadrangular frustum pyramid shaped boss (32) is square, and the side length is 27mm.
8. The method for producing a carbon fiber laminated plate of a multi-layered space structure according to claim 7, wherein in the seventh step, the upper fixing plate (4) and the lower fixing plate (5) are both carbon fiber plates.
9. The method for producing a carbon fiber laminated plate of a multi-layered spatial structure according to claim 8, wherein the thickness of the carbon fiber sheet is 2mm.
10. The method for producing a carbon fiber laminated board having a multi-layered space structure according to claim 9, wherein the glue in the sixth neutralization step seven is DP460 epoxy resin glue.
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CN105479768A (en) * 2015-11-23 2016-04-13 西北工业大学 Self-resistance electric heating curing method for resin-based carbon fiber composite material
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