CN116834325A - Preparation method of large-thickness carbon fiber composite material joint - Google Patents
Preparation method of large-thickness carbon fiber composite material joint Download PDFInfo
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- CN116834325A CN116834325A CN202210296347.XA CN202210296347A CN116834325A CN 116834325 A CN116834325 A CN 116834325A CN 202210296347 A CN202210296347 A CN 202210296347A CN 116834325 A CN116834325 A CN 116834325A
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- 239000002131 composite material Substances 0.000 title claims abstract description 82
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 50
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 50
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 50
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 31
- 238000004519 manufacturing process Methods 0.000 claims abstract description 17
- 238000000465 moulding Methods 0.000 claims abstract 2
- 229910052751 metal Inorganic materials 0.000 claims description 34
- 239000002184 metal Substances 0.000 claims description 34
- 238000003754 machining Methods 0.000 claims description 14
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 8
- 238000003825 pressing Methods 0.000 claims description 7
- XEKOWRVHYACXOJ-UHFFFAOYSA-N Ethyl acetate Chemical compound CCOC(C)=O XEKOWRVHYACXOJ-UHFFFAOYSA-N 0.000 claims description 6
- 238000005520 cutting process Methods 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 5
- 238000004140 cleaning Methods 0.000 claims description 5
- 239000003960 organic solvent Substances 0.000 claims description 5
- 238000005488 sandblasting Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 238000005086 pumping Methods 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- 238000007723 die pressing method Methods 0.000 claims description 3
- 239000000428 dust Substances 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000012535 impurity Substances 0.000 claims description 3
- 238000009966 trimming Methods 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 2
- 238000003672 processing method Methods 0.000 claims 1
- 229920005989 resin Polymers 0.000 abstract description 9
- 239000011347 resin Substances 0.000 abstract description 9
- 230000007547 defect Effects 0.000 abstract description 8
- 239000007787 solid Substances 0.000 abstract description 3
- 230000006866 deterioration Effects 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 28
- 238000005253 cladding Methods 0.000 description 3
- 239000003822 epoxy resin Substances 0.000 description 3
- 229920000647 polyepoxide Polymers 0.000 description 3
- 239000002344 surface layer Substances 0.000 description 3
- 229910000851 Alloy steel Inorganic materials 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000009940 knitting Methods 0.000 description 2
- 239000006082 mold release agent Substances 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 Teflon® Polymers 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 230000000630 rising effect Effects 0.000 description 1
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- 230000008023 solidification Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 239000002759 woven fabric Substances 0.000 description 1
Classifications
-
- 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
- B29C70/30—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
-
- 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
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention belongs to the technical field of aerospace, and relates to a preparation method of a large-thickness carbon fiber composite material joint, aiming at the situation that the carbon fiber composite material joint with the thickness larger than 50mm is used for a large solid rocket engine shell, thermal runaway, resin deterioration and the like are easy to occur in the large solid rocket engine shell due to a large amount of curing heat and higher temperature gradient during molding, so that the problems of uneven internal and external curing, incomplete curing, curing deformation, stress defects and the like are generated; meanwhile, the process method simplifies the production flow of the composite material joint, and the composite material layer is only required to be cured and molded once, so that the overall production efficiency of the product is improved, and the mass production of the product is easier to realize.
Description
Technical Field
The invention belongs to the technical field of aerospace, and particularly relates to a preparation method of a large-thickness carbon fiber composite joint.
Background
The joint is used as a key stress part and an external connecting part of the rocket engine shell and plays an important role in the whole system, the traditional rocket engine shell joint is usually made of metal aluminum and the like, the total mass of the front joint and the rear joint accounts for about 10-15% of the specific gravity of the shell, the carbon fiber composite material can reduce the weight of the similar metal joint by 30% under the condition of ensuring the same stress,
however, as rocket motor casings tend to become larger, the dimensions and thicknesses of the various parts thereof become larger. When the composite material component with large thickness (more than 50 mm) is molded, the internal part is easy to generate conditions of thermal runaway, resin deterioration and the like due to a large amount of resin curing heat and higher temperature gradient, so that the problems of uneven internal and external curing, incomplete curing, curing deformation, stress defect and the like are generated, and the appearance and mechanical properties of the composite material component are seriously influenced. The patent and literature disclose a production method of a composite material pressure vessel joint, and although a weight reduction effect is obtained by adopting carbon fiber to replace a metal material, the preparation process of the composite material joint with a large size and a large thickness, which is over 50mm thick, is not optimized and verified, and meanwhile, the structure design is complex, and the problems that the structural manufacturability of the product is poor, the production flow is complex (multiple mould pressing and solidification are needed), the mass production is difficult and the like are existed.
Disclosure of Invention
Aiming at the composite material joint component for the large solid rocket engine shell, the invention provides a preparation method of a large-thickness (more than 50 mm) carbon fiber composite material joint, and the defects of cracks, layering and the like in the large-thickness composite material are reduced by optimizing the structural design, the production method and the technological parameters of a joint product, so that the bearing capacity of the product is improved. Meanwhile, the composite material layer in the process is formed by one-time compression molding and curing, so that the production flow of the joint is simplified, and the overall production efficiency of the product is improved.
The aim of the invention is realized by the following technical scheme:
a preparation method of a large-thickness carbon fiber composite material joint mainly comprises the following steps:
forming a composite material body and processing a metal insert;
the composite material body is basically provided with an annular flange with a boss, is formed by layering, die pressing and solidifying carbon fiber prepreg, and is provided with a mounting hole matched with the size of the metal insert by machining, wherein the thickness of the boss is more than 50mm;
the metal embedded part is formed by metal machining, the cylinder is connected with the composite material layer through bonding and wrapped inside the joint, two ends of the cylinder are exposed on the surface of the composite material layer, and the small end of the cylinder is provided with a threaded hole for being connected with an external mechanism.
The invention provides a preparation method of a large-thickness carbon fiber composite material joint, which specifically comprises the following steps:
1. and (3) forming a composite material body: the carbon fiber prepreg is formed by layering, die pressing and curing, wherein the carbon fiber prepreg is mainly made of T700-grade carbon fiber, the tensile strength is higher than 4900MPa, and the tensile modulus is higher than 230GPa.
Further, the composite material body forming process method specifically comprises the following steps:
(1) Cleaning and assembling a die: firstly, using a high-pressure air gun to primarily clean dust and resin residues on the surface of a die, then using an organic solvent to scrub the surfaces of the blocks of the die and the male die respectively, removing impurities such as greasy dirt and the like, spraying a release agent or omitting the release agent according to the condition of the die after the organic solvent volatilizes, and finally completing the assembly of the die according to a die drawing;
the organic solvent includes but is not limited to ethyl acetate, acetone, etc.;
the die conditions are as follows: if the mold surface has been previously sprayed with a release coating (including but not limited to teflon), then there is no need to spray a release agent; otherwise, the mold release agent is sprayed on each bonding surface of the mold, and the mold release agent is repeatedly sprayed for 3 times at intervals of 20-30 min each time to be dried into a film.
(2) And (3) blanking: cutting the carbon fiber prepreg according to the requirements of shape, angle, sequence and quantity in a process design file, and marking the serial numbers of the layering sequence;
the cutting tool is generally an automatic blanking machine;
(3) Paving and preforming: the assembled female die is paved in sections according to different areas, the outermost layer of the paved area is a surface layer, and the layer uses carbon fiber woven cloth prepreg to avoid damage to the unidirectional tape on the outer layer of the product caused by subsequent machining, so that the appearance and performance of the product are optimized; the inner area uses carbon fiber unidirectional tape prepreg with the grade of T700 or more, the layering mode is determined according to the strength requirement and the structural design file, the layers are sequentially butted and paved layer by layer, and the paving angles are [ (0 degree/45 degree/90 degree/45 degree/0 degree ] in sequence s ] n° And inserting a preforming step.
The preforming steps include, but are not limited to, vacuum bagging or multiple cold press preforming;
further, when vacuum-pumping preforming is adopted, a vacuum bag is arranged once for each 3-5 layers of material sheets, and the duration of each vacuum pumping is about 15-30 min;
further, when cold pressing preforming is adopted, 10-15 layers of tablets are paved each time, the cold pressing preforming is carried out once, and the cold pressing duration time of each time is about 60-90 min;
(4) Curing: arranging a thermocouple at the position of the female die glue overflow groove, then closing the die of the male die and the female die according to the drawing direction of the die, transferring the die to a hot press platform, and releasing pressure and demoulding after curing is finished; (one of the inventive aspects of the present invention is to modify and optimize the temperature/pressure-time curing curve according to the characteristics of the composite material with a large thickness, and slow down the temperature and pressure rising rate, so as to prevent the occurrence of uneven curing inside and outside due to a large difference in temperature inside and outside, thereby generating defects.)
The thermocouple is connected with a temperature measuring instrument to control the temperature of the die, and the curing process is completed according to a temperature/pressure-time curing curve shown in fig. 5;
the temperature rise rate in the temperature/pressure-time curing curve is not higher than 0.5 ℃/min, and the pressure rise rate is not higher than 0.1MPa/min.
(5) And (3) machining: machining the composite material joint body after demolding;
the machining of the composite material joint body comprises trimming and machining, wherein the outer edge spines and burrs are trimmed and cut off firstly, then the metal insert mounting holes are machined according to product design files, and the specific number is determined according to the product strength and structural design requirements.
2. Machining a metal insert: the device is formed by adding a metal machine, the appearance is conical, a threaded hole for connecting with an external mechanism is formed in the small end, and a torsion stress surface which is symmetrical to the axial direction of the threaded hole is added on the side surface of the column body;
the depth of the threaded hole is about 80-90% of the height of the cone body so as to reduce the dead weight of the metal insert; the effective thread depth is about 30-40% of the cone height, so as to ensure the thread connection strength;
the torsion stress surface is used for blocking the axial rotation of the metal insert relative to the composite material layer when the bolt is disassembled and assembled;
3. bonding the metal inserts: and (3) mounting the metal insert into the composite material joint body by using an epoxy resin adhesive, and heating and curing to obtain a composite material joint finished product.
Before the metal inserts are installed, the surface of the cylinder is subjected to sand blasting. The sand blasting process is used for increasing the roughness of the metal surface and enhancing the bonding strength.
The invention also provides the large-thickness carbon fiber composite material joint prepared by the preparation method of the large-thickness carbon fiber composite material joint.
Compared with the prior art, the invention has the following positive effects:
the invention aims at the joint flange for the large rocket engine shell, and provides the preparation method of the large-thickness carbon fiber composite joint, which simplifies the production process flow of the composite joint under the condition of ensuring the bearing requirement of the product by optimizing the structure form and the layering mode of the composite joint, improves the overall production efficiency of the product (the composite layer only needs to be cured and molded once, and compared with the composite structure published by CN112571825A and the like, the production efficiency is higher) and ensures that the mass production is easier to realize; meanwhile, aiming at the problems of easy generation of cracks, layering and the like in the large-thickness composite material, the forming process is improved, the generation of internal defects is reduced, and the bearing capacity of the product is improved.
Drawings
FIG. 1 is a diagram of a joint structure of a large-thickness carbon fiber composite material according to embodiment 1 of the present invention;
FIG. 2 is a cross-sectional view of a large-thickness carbon fiber composite joint according to embodiment 1 of the present invention;
FIG. 3 is a schematic structural view of a metal insert for a large-thickness carbon fiber composite joint according to embodiment 1 of the present invention;
FIG. 4 is a schematic diagram of a layering manner of a large-thickness carbon fiber composite joint body according to embodiment 1 of the present invention;
FIG. 5 is a graph showing the curing process of the joint of the large-thickness carbon fiber composite material according to the embodiment 1 of the present invention;
FIG. 6 is a photograph showing the cross section of a large-thickness carbon fiber composite joint sample (left) provided in example 1 of the present invention compared with the cross section of a composite joint sample produced by a conventional process (right);
in the figure: (1) the carbon fiber composite material comprises a carbon fiber composite material body, (2) a metal insert, (3) defects such as internal cracks and resin gaps, and the like, and (4) edge deformation.
Detailed Description
The following provides a specific embodiment of a method for manufacturing a large-thickness carbon fiber composite joint according to the present invention.
Example 1
As shown in fig. 1 and 2, a large-thickness carbon fiber composite connector is basically provided with a flange with an annular boss, a carbon fiber composite body (1) is basically provided with a maximum thickness position of 145mm, 30 connecting holes are formed in the flange surface, and metal inserts (2) with corresponding sizes and numbers are installed.
As shown in FIG. 3, the metal insert is machined from high-strength alloy steel 30CrMnSi, the shape is conical, the diameter of the small end is 50mm, the diameter of the large end is 70mm, the small end is provided with an M33 threaded hole for connecting with an external mechanism, the hole depth is 120mm, the effective thread depth is 45mm, the cylinder height is 140mm, and a side machine is provided with a torsion stress surface symmetrical to the axial direction of the threaded hole and used for blocking the axial rotation of the metal insert relative to the composite material layer when the bolt is disassembled.
The raw materials and the preparation method of the large-thickness carbon fiber composite material joint are as follows:
raw materials: the prepreg used for the composite material joint body is self-made (also can be purchased externally) by our company, wherein the surface density of the woven cloth prepreg is 320g/m 2 The carbon-containing fiber is 3K T300 grade, the knitting direction is vertical knitting, the resin is MT3 type epoxy resin, and the curing temperature is 130-135 ℃; the surface density of the unidirectional tape prepreg is 600g/m 2 The carbon fiber is 12K T700 grade, the resin is HT2 type epoxy resin, and the curing temperature is 180-185 ℃; the metal insert is formed by machining high-strength alloy steel 30 CrMnSi.
The preparation method comprises the following steps:
(1) Cleaning and assembling a die: firstly, using a high-pressure air gun to primarily clean dust and resin residues on the surface of a die, then using acetone to scrub the surfaces of the blocks of the female die and the male die respectively, removing impurities, coating a release agent on each contact surface of the die after the acetone volatilizes, and finally completing the assembly of the female die according to a die drawing;
(2) And (3) blanking: cutting the carbon fiber prepreg according to the shape, angle, sequence and quantity requirements in the process design file by using an automatic blanking machine, and marking the serial numbers of the layering sequence, wherein the total number of the product is 243 layers of tablets;
(3) Paving and preforming: and (4) paving the assembled female die in sections according to different areas, wherein the specific paving mode is shown in fig. 4. The outermost layer of the paving area is a surface layer, and the surface layer is made of carbon fiber woven fabric prepreg; the inside is respectively an outer cladding layer, an inclined paving layer and a flat paving layer, the area is all made of carbon fiber unidirectional tape prepreg with the T700 grade or more, and each prepreg sheet is according to the technological documentThe design sequence of the (C) is that the layers are butted and paved layer by layer, and the paving angles are [ (0 degree/45 degree/90 degree/45 degree/0 degree) in sequence s ] n° Simultaneously, 3 layers of material sheets are paved, a vacuum bag is made once, vacuum is pumped for preforming, the pressure is less than-0.094 MPa, and the duration is 15min;
(4) Curing: arranging a thermocouple at the position of the female die glue overflow groove, then closing the die of the male die and the female die according to the direction of a die drawing, transferring to a hot press platform, connecting the thermocouple with a thermometer to control the temperature of the die, completing the curing process according to a curing process curve shown in fig. 5, and finally releasing pressure and demoulding;
(5) And (3) machining: firstly, roughly trimming and cutting the demolding composite material joint body, removing sharp burrs and burrs on the outer edge, and then machining a metal insert mounting hole according to a product design file;
(6) Bonding the metal inserts: and installing the metal embedded part into the composite material joint body by using an adhesive, and heating and curing to obtain a finished product of the composite material joint.
Before the metal insert is installed, the surface of the cylinder needs to be subjected to sand blasting treatment to improve the bonding strength with the composite material layer, and the sand blasting treatment needs to be carried out within 4 hours before bonding.
Fig. 6 shows a comparison of the cross section (left) of the large-thickness carbon fiber composite joint sample prepared in this example with the cross section (right) of the large-thickness composite joint sample of the same size produced by the conventional process, and it can be clearly observed from the figure that the interior of the composite joint sample produced by the conventional process has a large number of cracks and defects, including severe penetrable interlayer cracks, scattered local delamination, resin voids (3) at the interface between the flat layer and the outer cladding layer, and edge deformation (4) of the prepreg caused by stress concentration, which seriously affect the mechanical properties and structural stability of the composite joint member. After the process is improved, the penetrability cracks in the product disappear, the local layering phenomenon is obviously reduced, the junction of the tiled layer and the outer cladding layer becomes compact, the prepreg at the edge of the sample also presents a relatively flat and compact state, and the defects are greatly reduced.
The foregoing is merely exemplary embodiments of the present invention, and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the spirit of the present invention and are intended to be within the scope of the present invention.
Claims (10)
1. A preparation method of a large-thickness carbon fiber composite material joint is characterized by comprising the following steps: mainly comprises the following steps: forming a composite material body and processing a metal insert;
the composite material body is basically provided with an annular flange with a boss, is formed by layering, die pressing and solidifying carbon fiber prepreg, and is provided with a mounting hole matched with the size of the metal insert by machining, wherein the thickness of the boss is more than 50mm;
the metal embedded part is formed by metal machining, the cylinder is connected with the composite material layer through bonding and wrapped inside the joint, two ends of the cylinder are exposed on the surface of the composite material layer, and the small end of the cylinder is provided with a threaded hole for being connected with an external mechanism.
2. The method for preparing the large-thickness carbon fiber composite material joint as claimed in claim 1, wherein the method comprises the following steps: the composite material body is only required to be cured and molded once, then the metal insert is installed into the composite material body through bonding by using an adhesive, and a finished product of the composite material joint is obtained after heating and curing.
3. The method for manufacturing a large-thickness carbon fiber composite joint according to claim 1, wherein the method for molding the composite joint body mainly comprises the following steps:
(1) Cleaning and assembling a die: cleaning the surfaces of the mold blocks by using a high-pressure air gun and an organic solvent respectively, removing impurities such as dust, greasy dirt and the like, spraying a release agent, and completing mold assembly;
(2) And (3) blanking: cutting the carbon fiber prepreg according to the requirement, and marking the layering sequence;
(3) Paving and preforming: paving the assembled female die according to the requirements of the process command file, and inserting a preforming step at the same time;
(4) Curing: arranging a thermocouple and closing the die, completing the curing process according to a temperature/pressure-time curing curve of a process command file, and then releasing pressure and demolding;
(5) And (3) machining: and trimming and cutting the edge of the composite material joint body of the demolding and processing a metal insert mounting hole.
4. A method of making a high thickness carbon fiber composite joint as defined in claim 3, wherein: in step (1) of the composite joint body forming process, the organic solvents used for cleaning the mold include, but are not limited to, acetone, ethyl acetate and the like.
5. A method of making a high thickness carbon fiber composite joint as defined in claim 3, wherein: in step (3), the preforming step includes, but is not limited to, bagging with a vacuum or multiple cold press preforming.
6. The method for preparing the large-thickness carbon fiber composite material joint as claimed in claim 5, wherein: when the vacuum-pumping preforming is adopted in the preforming step, 3-5 layers of material sheets are paved and stuck, a vacuum bag is made once, and the duration of each vacuum pumping is 15-30 min.
7. The method for preparing the large-thickness carbon fiber composite material joint as claimed in claim 5, wherein: when the preforming step adopts cold pressing preforming, 10-15 layers of material sheets are paved and pasted each time, the cold pressing preforming is carried out once, and the cold pressing duration time of each time is 60-90 min.
8. The method for preparing the large-thickness carbon fiber composite material joint as claimed in claim 1, wherein: the processing method of the metal insert comprises the following steps: the metal insert is conical, the threaded hole is formed in the small end of the cone, and the side face of the cylinder is provided with a torsion stress surface symmetrical to the axial direction of the threaded hole.
9. The method for preparing the large-thickness carbon fiber composite material joint as claimed in claim 1, wherein: and in the final bonding step, the surface of the cylinder before the metal insert is installed is subjected to sand blasting treatment.
10. A high-thickness carbon fiber composite joint produced by the method of producing a high-thickness carbon fiber composite joint according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210296347.XA CN116834325A (en) | 2022-03-24 | 2022-03-24 | Preparation method of large-thickness carbon fiber composite material joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210296347.XA CN116834325A (en) | 2022-03-24 | 2022-03-24 | Preparation method of large-thickness carbon fiber composite material joint |
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| Publication Number | Publication Date |
|---|---|
| CN116834325A true CN116834325A (en) | 2023-10-03 |
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|---|---|---|---|
| CN202210296347.XA Pending CN116834325A (en) | 2022-03-24 | 2022-03-24 | Preparation method of large-thickness carbon fiber composite material joint |
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| Country | Link |
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| CN (1) | CN116834325A (en) |
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- 2022-03-24 CN CN202210296347.XA patent/CN116834325A/en active Pending
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