CN114939938B - Preparation method of low-stress composite material embedded metal part product - Google Patents
Preparation method of low-stress composite material embedded metal part product Download PDFInfo
- Publication number
- CN114939938B CN114939938B CN202210402480.9A CN202210402480A CN114939938B CN 114939938 B CN114939938 B CN 114939938B CN 202210402480 A CN202210402480 A CN 202210402480A CN 114939938 B CN114939938 B CN 114939938B
- Authority
- CN
- China
- Prior art keywords
- composite material
- embedded part
- metal
- metal embedded
- adhesive film
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B11/00—Making preforms
- B29B11/14—Making preforms characterised by structure or composition
-
- 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
- B29C49/00—Blow-moulding, i.e. blowing a preform or parison to a desired shape within a mould; Apparatus therefor
- B29C49/071—Preforms or parisons characterised by their configuration, e.g. geometry, dimensions or physical properties
-
- 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
-
- 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
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/682—Preformed parts characterised by their structure, e.g. form
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/683—Pretreatment of the preformed part, e.g. insert
-
- 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
- B29C2949/00—Indexing scheme relating to blow-moulding
- B29C2949/07—Preforms or parisons characterised by their configuration
- B29C2949/0715—Preforms or parisons characterised by their configuration the preform having one end closed
-
- 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
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Manufacturing & Machinery (AREA)
- Laminated Bodies (AREA)
Abstract
The invention relates to a preparation method of a low-stress composite material embedded metal part product, which comprises the following steps of S1, carrying out primary processing on a metal embedded part, wherein the metal embedded part comprises a hexahedral main body with a hollow structure, six connecting surfaces of the hexahedral main body are selectively provided with interface bosses or lightening holes according to actual needs, grooves are processed on the six connecting surfaces of the metal embedded part, which are in contact with a composite material, the inside of the grooves is of a communicated structure, a circle of outer flanges are arranged at the positions, close to the edges of the connecting surfaces, of the grooves, and a circle of inner flanges are arranged at the positions, close to the interface bosses or the lightening holes, of the connecting surfaces; s2, carrying out sand blasting treatment on the metal embedded part; step S3, paving a transition layer; s4, laying prepreg; s5, die assembly; and S6, curing, wherein the curing system is 110 ℃/2-130 ℃/4 hours. The method solves the problems of deformation and interface clearance caused by overlarge internal stress of the composite material product with the embedded metal piece, and improves the dimensional stability of the composite material product.
Description
Technical Field
The invention belongs to the field of composite material product processing, relates to preparation of a composite material product with a pre-buried metal piece, and in particular relates to a preparation method of a low-stress composite material pre-buried metal piece product.
Background
Most composite products utilize metal parts as the processing and assembly interfaces. In the design process of the composite material product, in order to ensure the compact structure of the product, improve the bearing capacity and reduce the assembly connecting pieces, the metal piece is always designed to be embedded in the internal structure of the composite material, and the metal piece with the structure is completely wrapped by the composite material. However, because the composite material is molded and cured at a higher temperature, the thermal expansion coefficient of the metal piece is higher than that of the composite material, the deformation amount of the metal piece is larger than that of the composite material after the curing is completed and the temperature is reduced to room temperature, stress exists at the interface between the composite material and the metal piece, and if the ultimate stress is reached, microscopic gaps can be generated between the metal piece and the composite material or the deformation of the metal piece is caused, so that the secondary processing precision and the stability of long-term use size and form tolerance of the product are affected.
In order to solve the problem of stress between a metal piece and a composite material, an adhesive film is paved on the surface of the metal piece in the processing process of a composite material product, but the adhesive film is used as a process layer, the adhesive film is stressed greatly in the composite material forming process, more loss occurs after solidification, the thickness is not easy to control, and the problem of unstable effect is solved.
Disclosure of Invention
In view of the above problems, the present invention aims to provide a method for preparing a low-stress composite material embedded metal part product, which comprises the steps of paving a transition layer between an interface of a metal part and a composite material, processing a groove on the surface of the metal part to control the thickness of the transition layer by adopting an adhesive film and chopped fibers, and utilizing plastic deformation of the transition layer in a cooling process after the composite material is molded and solidified to eliminate the problems of unmatched thermal expansion coefficients of the metal part and the composite material and internal stress generated after solidification, thereby solving the problems of deformation and interface clearance generated by overlarge internal stress of a composite material product with the embedded metal part and improving the dimensional stability of the composite material part.
In order to achieve the above purpose, the invention adopts the following technical scheme:
a preparation method of a low-stress composite material embedded metal part product comprises the following steps:
step S1, performing primary processing on the metal embedded part
Step S11, preparing a metal embedded part, wherein the metal embedded part comprises a hexahedral main body with a hollow structure, and six connecting surfaces of the hexahedral main body are selectively provided with an interface boss or a lightening hole according to actual needs;
step S12, grooves are processed on six connecting surfaces of the metal embedded part, which are in contact with the composite material, wherein the grooves are of a communicated structure, a circle of outer flanges are arranged at the positions, close to the edges of the connecting surfaces, of the grooves, and a circle of inner flanges are arranged at the positions, close to the interface bosses or the lightening holes, of the connecting surfaces;
s2, carrying out sand blasting treatment on the metal embedded part
Step S3, paving a transition layer
Paving transition layers in grooves of six connecting surfaces of the metal embedded part, wherein the transition layers are a first adhesive film layer, a chopped fiber layer and a second adhesive film layer in sequence from bottom to top; during laying, firstly, 1 layer of first adhesive film layer is laid in a groove of a metal embedded part, then glass fibers are cut into pieces, the surface of the first adhesive film layer is laid to serve as a chopped fiber layer, and then 1 layer of second adhesive film layer is laid;
s4, laying prepreg
The metal embedded part and the mould are laid with prepreg;
step S5, die assembly
Placing the laid die and metal embedded part on an inner die flat plate, combining an outer die, placing the outer die into a curing furnace, heating, further pressurizing the outer die when the temperature of the die reaches 70 ℃, controlling a die closing gap in the pre-pressing process, and avoiding excessive stress of the metal embedded part in the cold-bonding process;
step S6, solidifying
After the die assembly is completed, the whole die is put into a curing furnace, the curing system is 110 ℃/2h to 130 ℃/4h, and the product molding is completed.
Preferably, the depth of the groove processed in step S12 is 0.3mm.
As the preferable choice of the invention, when the step S2 is used for sand blasting the surface of the metal embedded part, 30 meshes of carborundum is selected, the sand blasting pressure is 0.6-0.8 Mpa, and the metal embedded part is cleaned by acetone after sand blasting.
As the preferable mode of the invention, the thickness of the first adhesive film layer and the second adhesive film layer in the step S3 is 0.35 mm-0.4 mm; the chopped fiber layer is made of glass fibers, the length of the glass fibers is 3-5 mm, the glass fibers are uniformly paved on the first adhesive film layer, and the coverage area is 50%.
As the preferential selection of the invention, the prepreg in the step S4 adopts a carbon fiber reinforced resin matrix composite material, and the resin adopts a cyanate resin cured at medium temperature; the metal embedded part is made of titanium alloy.
As a further preferable mode of the invention, the first adhesive film layer and the second adhesive film layer are LWF brand adhesive films, and the brand of the glass fiber is HT469LB-1200R.
The beneficial effects of the invention are as follows:
(1) According to the invention, the groove is formed in the metal embedded part, the transition layer is arranged in the groove, the deformation of the transition layer in the cooling process after the composite material is molded and cured is utilized, the internal stress generated after the thermal expansion coefficient of the metal embedded part and the thermal expansion coefficient of the composite material are not matched and cured is eliminated, the problem that the deformation and the interface clearance are generated due to the overlarge internal stress of the composite material product with the embedded metal part is solved, and the dimensional stability of the composite material product is improved.
(2) The groove on the metal embedded part is provided with the outer flange at a position close to the edge of the connecting surface, and the inner flange at a position close to the interface boss or the lightening hole on the connecting surface, so that the outer flange and the inner flange can effectively prevent the glue film from losing when being converted into a liquid state in the high-temperature curing process, the glue film size is controlled more accurately, and enough plastic deformation in the thickness direction is realized so as to adapt to the deformation of the metal part.
(3) According to the transition layer, the chopped fiber layer is arranged between two adhesive films, and along with pressurization, temperature rise and solidification in the molding process, chopped fibers can be fully soaked by the adhesive films, so that the transition layer has toughness higher than the adhesive films and modulus lower than composite materials and metal parts; meanwhile, the chopped fiber can further prevent the liquid adhesive film from losing, and most of stress between the metal piece and the composite material can be eliminated under the condition of ensuring the bonding strength.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of a low stress composite pre-buried metal part prepared in example 1;
FIG. 2 is a cross-sectional view of a low stress composite pre-buried metal part prepared in example 1;
fig. 3 is a schematic structural diagram of a first angle of the embedded metal part adopted in embodiment 1;
fig. 4 is a schematic structural diagram of a second angle of the embedded metal part used in embodiment 1;
fig. 5 is a schematic structural diagram of a third angle of the embedded metal part adopted in embodiment 1;
FIG. 6 is a cross-sectional view of a transition layer of the present invention;
fig. 7 is a schematic structural diagram of the embedded metal part adopted in embodiment 2;
FIG. 8 is a schematic view of a molded product prepared in example 2;
FIG. 9 is a schematic structural view of the pre-buried metal piece used in comparative example 1;
FIG. 10 is a schematic view of the molded product prepared in comparative example 1.
Wherein the reference numerals are as follows: the metal embedded part 1, the composite material layer 2, the transition layer 3, the groove 4, the hexahedral main body 11, the interface boss 12, the lightening hole 13, the upper connecting surface 111, the lower connecting surface 112, the left connecting surface 113, the right connecting surface 114, the front connecting surface 115, the rear connecting surface 116, the first adhesive film layer 31, the chopped fiber layer 32, the second adhesive film layer 33, the outer flange 41 and the inner flange 42.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, based on the examples herein, which are within the scope of the invention as defined by the claims, will be within the scope of the invention as defined by the claims.
In the description of the present application, it should be noted that the terms "inner," "lower," and the like indicate the azimuth or positional relationship as follows: the use of the orientation or positional relationship shown in the drawings, or the orientation or positional relationship conventionally placed when the subject application is used, is merely for convenience of description and to simplify the description, and is not intended to indicate or imply that the apparatus or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the application. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; the two components can be mechanically connected, can be directly connected or can be indirectly connected through an intermediate medium, and can be communicated with each other. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
Example 1
A preparation method of a low-stress composite material embedded metal part product comprises the following steps:
step S1, performing primary processing on the metal embedded part
Step S11, preparing a metal embedded part, wherein the metal embedded part 1 comprises a hollow structureSix connecting surfaces of the hexahedral body are selectively provided with an interface boss 12 or a lightening hole 13 according to actual needs; the upper connecting surface 111 of the metal embedded part 1 provided in this embodiment is provided with an interface boss 12 and a lightening hole 13, the lower connecting surface 112 of the metal embedded part 1 is provided with two lightening holes 13, the left connecting surface 113 is provided with an interface boss 12, the right connecting surface 114 is provided with a lightening hole 13, and the front connecting surface 115 and the rear connecting surface 116 are not provided with the interface boss 12 and the lightening hole 13 (see fig. 3 to 5); the metal embedded part 1 is made of a titanium alloy material commonly used in aerospace, and is of the brand TC4, the wall thickness is 15mm, and the density is 4.5g/cm 3 Coefficient of thermal expansion 7.89×10 -6 /℃；
Step S12, grooves 4 are processed on six connecting surfaces of the metal embedded part 1, which are in contact with the composite material, the inside of each groove 4 is of a communicated structure, a circle of outer flanges 41 are arranged at the positions, close to the edges of the connecting surfaces, of each groove 4, a circle of inner flanges 42 are arranged at the positions, close to the interface bosses or the lightening holes on the connecting surfaces, of each groove, the outer flanges 41 and the inner flanges 42 of each groove are used for preventing the high-temperature curing process, and the adhesive film runs off when being converted into a liquid state (see figures 3 to 5); the depth of the groove 4 is 0.3mm, the thickness of the transition layer after solidification can be controlled to be 0.3mm, compared with a metal embedded part without the groove, the size of the adhesive film is controlled more accurately, the adhesive film is extruded by the prepreg and runs off less, and enough plastic deformation in the thickness direction is realized so as to adapt to the deformation of the metal embedded part;
step S2, carrying out sand blasting treatment on the metal embedded part, wherein when the surface of the metal embedded part is subjected to sand blasting treatment, 30-mesh silicon carbide is selected, the sand blasting pressure is 0.6-0.8 Mpa, and the metal embedded part is cleaned by acetone after sand blasting;
step S3, paving a transition layer
The method comprises the steps that transition layers 3 are paved in grooves of six connecting surfaces of a metal embedded part 1, the transition layers 3 are sequentially a first adhesive film layer 31, a chopped fiber layer 32 and a second adhesive film layer 33 (see figure 6) from bottom to top, the first adhesive film layer 31 and the second adhesive film layer 33 in the transition layers 3 are LWF brand adhesive films produced by Heilongjiang petrochemical institute, the thickness is 0.35-0.4 mm, the curing temperature is 120-125 ℃, and the curing time is 2-3 h; the chopped fiber layer 32 in the transition layer 3 is made of glass fibers, the brand of the glass fibers is HT469LB-1200R, when the transition layer is paved, firstly, 1 layer of first adhesive film layer is paved in a groove of a metal embedded part, then the glass fibers are sheared to be 3-5 mm in length, the chopped fibers are paved on the surface of the first adhesive film layer to serve as chopped fiber layers (the glass fibers uniformly cover 50% of the area), and then 1 layer of second adhesive film layer is paved;
s4, laying prepreg
The metal embedded part and the mould are laid together to form a prepreg, the prepreg is made of carbon fiber reinforced resin matrix composite material, the resin is made of cyanate resin with a medium temperature curing formula at 130 ℃, compared with the traditional high temperature resin formula (curing at 180-190 ℃), the temperature is reduced to room temperature after curing, the thermal stress generated between the metal part and the composite material is smaller, the reinforcing material is made of M40JB brand fibers, the isotropic layering design is aligned, and the thermal expansion coefficient of the composite material part is 1.23 multiplied by 10 -6 /℃；
Step S5, die assembly
Placing the laid die and metal embedded part on an inner die flat plate, combining an outer die, placing the outer die into a curing furnace, heating, further pressurizing the outer die when the temperature of the die reaches 70 ℃, controlling a die closing gap in the pre-pressing process, and avoiding excessive stress of the metal embedded part in the cold-bonding process;
step S6, solidifying
After the die assembly is completed, the whole die is placed into a curing furnace, the curing system is 110 ℃/2h to 130 ℃/4h, the product molding is completed, the molded product is shown in figure 1, and the sectional view is shown in figure 2. In the single embedded metal part composite material structure shown in fig. 1, TC4 is selected as a metal part material, the wall thickness is 15mm, the groove is 0.3mm, M40 JB/cyanate ester is selected as a composite material, LWF is selected as a glue film, the thickness is 0.35mm, glass fibers are chopped fibers, and the glass fibers are named HT469LB-1200R.
Example 2
The difference from example 1 is the structure of the metal embedment, and the structure of the final produced composite material is slightly different.
The metal embedded part 1 comprises a hexahedral main body, only one of six connecting surfaces (top surface) of the hexahedral main body is provided with two interface bosses 12, the other connecting surfaces are not provided with interface bosses and lightening holes, each connecting surface is provided with a groove 4, the inside of each groove 4 is of a communicated structure, each groove 4 is provided with a circle of outer flanges 41 at a position close to the edge of the connecting surface, and each groove is provided with a circle of inner flanges 42 at a position close to the interface boss 12 on the connecting surface (see fig. 7).
The single embedded metal part composite material structure shown in fig. 8 is prepared by adopting the method of the metal embedded part 1 and the embodiment 1, the single embedded metal part composite material structure shown in fig. 8 is prepared by adopting TC4 as a metal embedded part material, adopting 5mm of wall thickness and 0.3mm of groove, adopting M40 JB/cyanate as a composite material, adopting LWF as a glue film with 5mm of wall thickness and 0.35mm of thickness, adopting glass fiber as chopped fiber, and adopting HT469LB-1200R as a glass fiber mark.
Comparative example 1
The difference from embodiment 1 is that the metal embedded part has a structure that only one connecting surface without the interface boss and the lightening hole is provided with grooves, and the other connecting surfaces are not provided with grooves, as shown in fig. 9.
The single embedded metal part composite material structure shown in fig. 10 is prepared by adopting a metal embedded part 1 without grooves and referring to the method of the embodiment 1, the single embedded metal part composite material structure shown in fig. 10 is prepared by adopting TC4 as a metal embedded part material, 15mm of wall thickness, no grooves are processed, M40 JB/cyanate as a composite material, LWF as a glue film with 10mm of wall thickness and 0.35mm of thickness, glass fiber as a chopped fiber and HT469LB-1200R as a glass fiber mark.
And (3) detection:
(1) The nondestructive inspection is carried out on the product in the embodiment 1, the bonding area of the metal piece and the composite material is detected, the result shows that the bonding area of the metal piece and the composite material occupies 95 percent of the total area, and the method solves the problems that the internal stress of the composite material product is overlarge to generate deformation and the interface gap is generated between the metal piece and the composite material.
(2) And (3) processing the boss surface of the product of the example 2 until the flatness is less than or equal to 0.03mm, then performing a thermal cycle test, wherein the test temperature is 5-55 ℃, and measuring the flatness after processing, wherein the flatness is 0.03mm. The composite material product adopting the design structure and the process has higher dimensional stability.
(3) The product of comparative example 1 is subjected to nondestructive inspection, the bonding area of the metal piece and the composite material is detected, the result shows that the bonding area of the metal piece and the composite material occupies 48 percent of the total area, and the design of the groove structure in the metal embedded part plays a role in avoiding the loss of the adhesive film.
The foregoing is merely illustrative embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about variations or substitutions within the technical scope of the present invention, and the invention should be covered. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (2)
1. The preparation method of the low-stress composite material embedded metal part product is characterized by comprising the following steps of:
step S1, performing primary processing on the metal embedded part
Step S11, preparing a metal embedded part, wherein the metal embedded part comprises a hexahedral main body with a hollow structure, and six connecting surfaces of the hexahedral main body are selectively provided with an interface boss or a lightening hole according to actual needs;
step S12, grooves are processed on six connecting surfaces of the metal embedded part and the composite material, the depth of each processed groove is 0.3mm, the inside of each groove is of a communicated structure, a circle of outer flanges are arranged at the positions, close to the edges of the connecting surfaces, of each groove, and a circle of inner flanges are arranged at the positions, close to the interface bosses or the lightening holes, of the connecting surfaces;
step S2, performing sand blasting treatment on the metal embedded part, selecting 30-mesh silicon carbide, performing sand blasting under the pressure of 0.6-0.8 mpa, and cleaning with acetone after sand blasting;
step S3, paving a transition layer
Paving transition layers in grooves of six connecting surfaces of the metal embedded part, wherein the transition layers are a first adhesive film layer, a chopped fiber layer and a second adhesive film layer in sequence from bottom to top; during laying, firstly, 1 layer of first adhesive film layer is laid in a groove of a metal embedded part, then glass fibers are cut into pieces, the surface of the first adhesive film layer is laid to serve as a chopped fiber layer, and then 1 layer of second adhesive film layer is laid;
the thickness of the first adhesive film layer and the second adhesive film layer is 0.35 mm-0.4 mm; the chopped fiber layer is made of glass fibers, the length of the glass fibers is 3-5 mm, the glass fibers are uniformly paved on the first adhesive film layer, and the coverage area is 50%;
s4, laying prepreg
The metal embedded part and the mould are laid with prepreg;
step S5, die assembly
Placing the laid die and metal embedded part on an inner die flat plate, combining an outer die, placing the outer die into a curing furnace, heating, pressurizing the outer die when the temperature of the die reaches 70 ℃, controlling a die closing gap in the pre-pressing process, and avoiding the excessive stress of the metal embedded part in the cold-bonding process;
step S6, solidifying
And after the die assembly is completed, the whole die is placed into a curing furnace, the curing system is 110 ℃/2h to 130 ℃/4h, and the product molding is completed.
2. The method for preparing a low-stress composite material embedded metal part product according to claim 1, wherein the prepreg in the step S4 is a carbon fiber reinforced resin matrix composite material, and the resin is a cyanate resin cured at medium temperature; the metal embedded part is made of titanium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210402480.9A CN114939938B (en) | 2022-04-18 | 2022-04-18 | Preparation method of low-stress composite material embedded metal part product |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210402480.9A CN114939938B (en) | 2022-04-18 | 2022-04-18 | Preparation method of low-stress composite material embedded metal part product |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114939938A CN114939938A (en) | 2022-08-26 |
| CN114939938B true CN114939938B (en) | 2023-06-23 |
Family
ID=82906459
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210402480.9A Active CN114939938B (en) | 2022-04-18 | 2022-04-18 | Preparation method of low-stress composite material embedded metal part product |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114939938B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4937032A (en) * | 1988-05-31 | 1990-06-26 | Phillips Petroleum Company | Method for molding a composite with an integrally molded rib |
| CN109591335A (en) * | 2018-11-30 | 2019-04-09 | 长春长光宇航复合材料有限公司 | The built-in process of metalwork in a kind of composite products forming process |
| CN109664515A (en) * | 2017-10-13 | 2019-04-23 | 标致雪铁龙汽车股份有限公司 | Composite material component with metal insert |
| CN110549643A (en) * | 2019-09-06 | 2019-12-10 | 长沙晶优新材料科技有限公司 | antenna cover plate profiling prefabricated part puncturing method and antenna cover plate forming method |
| CN110696220A (en) * | 2019-09-20 | 2020-01-17 | 艾达索高新材料芜湖有限公司 | Manufacturing process of degradable carbon felt prepreg and cover inner plate |
| CN111707145A (en) * | 2020-06-10 | 2020-09-25 | 宁波曙翔新材料股份有限公司 | Loading, ablation and heat-proof integrated composite material missile wing and rudder for hypersonic missile and preparation method thereof |
| CN112571825A (en) * | 2020-11-06 | 2021-03-30 | 湖北航天技术研究院总体设计所 | Composite material joint and preparation method thereof |
| CN113997967A (en) * | 2021-11-24 | 2022-02-01 | 长三角先进材料研究院 | Integral forming structure and manufacturing method of composite material window frame of cab |
| CN114013072A (en) * | 2021-10-25 | 2022-02-08 | 中航复合材料有限责任公司 | Integral forming method for embedded part in SMC compression molding composite part |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8834782B2 (en) * | 2007-08-07 | 2014-09-16 | William L. Rodman | Composite structures and methods of making same |
| CA2740892A1 (en) * | 2008-10-16 | 2010-04-22 | Composite Transport Technologies, Inc. | Lightweight unit load device |
| JP7295376B2 (en) * | 2017-12-28 | 2023-06-21 | 日本製鉄株式会社 | METAL-FIBER REINFORCED RESIN MATERIAL COMPOSITE AND PRODUCTION METHOD THEREOF |
-
2022
- 2022-04-18 CN CN202210402480.9A patent/CN114939938B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4937032A (en) * | 1988-05-31 | 1990-06-26 | Phillips Petroleum Company | Method for molding a composite with an integrally molded rib |
| CN109664515A (en) * | 2017-10-13 | 2019-04-23 | 标致雪铁龙汽车股份有限公司 | Composite material component with metal insert |
| CN109591335A (en) * | 2018-11-30 | 2019-04-09 | 长春长光宇航复合材料有限公司 | The built-in process of metalwork in a kind of composite products forming process |
| CN110549643A (en) * | 2019-09-06 | 2019-12-10 | 长沙晶优新材料科技有限公司 | antenna cover plate profiling prefabricated part puncturing method and antenna cover plate forming method |
| CN110696220A (en) * | 2019-09-20 | 2020-01-17 | 艾达索高新材料芜湖有限公司 | Manufacturing process of degradable carbon felt prepreg and cover inner plate |
| CN111707145A (en) * | 2020-06-10 | 2020-09-25 | 宁波曙翔新材料股份有限公司 | Loading, ablation and heat-proof integrated composite material missile wing and rudder for hypersonic missile and preparation method thereof |
| CN112571825A (en) * | 2020-11-06 | 2021-03-30 | 湖北航天技术研究院总体设计所 | Composite material joint and preparation method thereof |
| CN114013072A (en) * | 2021-10-25 | 2022-02-08 | 中航复合材料有限责任公司 | Integral forming method for embedded part in SMC compression molding composite part |
| CN113997967A (en) * | 2021-11-24 | 2022-02-01 | 长三角先进材料研究院 | Integral forming structure and manufacturing method of composite material window frame of cab |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114939938A (en) | 2022-08-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104162996B (en) | The manufacturing process of the U-shaped part of carbon fibre composite | |
| CN102320139B (en) | Forming process of curved composite tube | |
| CN105034403B (en) | Method for manufacturing composite shell | |
| CN107139503B (en) | The forming method of composite material cylinder component partial honeycomb sandwich construction | |
| CN102009501A (en) | Enhanced honeycomb sandwich structural slab and production method thereof | |
| US8784089B2 (en) | Foamed tools | |
| CN103273662A (en) | Preparation method of low heat expansion carbon fiber reinforced resin matrix composite material mold | |
| JP5686994B2 (en) | Manufacturing method of molded body | |
| CN109532058A (en) | A kind of Varying-thickness polymer matrix composites structure preparation method | |
| CN101462369B (en) | Method for preparing pipe sheet for heat-exchange facility and products produced thereby | |
| CN109822949A (en) | A kind of preparation method of the rocket long row's cover of light sandwich structure | |
| CN101497253A (en) | Metal and non-metal composite board | |
| CN114939938B (en) | Preparation method of low-stress composite material embedded metal part product | |
| WO2019188195A1 (en) | Method for producing fiber-reinforced resin | |
| CN101961893B (en) | Composite material mold and manufacturing method thereof | |
| CN109719880B (en) | Forming method of composite molded product of high silica fiber and carbon fiber | |
| CN110181905B (en) | Aircraft floor made of fiber/metal laminate composite material and manufacturing method | |
| EP0662380A2 (en) | Mould for fibre-reinforced plastics | |
| CN109435271B (en) | Forming method suitable for main bearing frame body of satellite laser radar frame | |
| CN115847863A (en) | Method for accurately manufacturing pores of composite laminated board | |
| JP5293945B2 (en) | Thermosetting resin molded product and manufacturing method thereof | |
| JP2019015227A (en) | Manufacturing method for cylinder block | |
| CN208529790U (en) | Fan blade | |
| CN217943908U (en) | Low-stress composite material embedded metal part structure | |
| CN113370550B (en) | Composite sandwich spherical crown structure and forming method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |