CN114939938A - 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
- CN114939938A CN114939938A CN202210402480.9A CN202210402480A CN114939938A CN 114939938 A CN114939938 A CN 114939938A CN 202210402480 A CN202210402480 A CN 202210402480A CN 114939938 A CN114939938 A CN 114939938A
- Authority
- CN
- China
- Prior art keywords
- composite material
- metal
- embedded part
- film layer
- 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.)
- Granted
Links
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 110
- 239000002184 metal Substances 0.000 title claims abstract description 110
- 239000002131 composite material Substances 0.000 title claims abstract description 69
- 238000002360 preparation method Methods 0.000 title claims abstract description 8
- 238000000034 method Methods 0.000 claims abstract description 26
- 230000007704 transition Effects 0.000 claims abstract description 24
- 238000005488 sandblasting Methods 0.000 claims abstract description 13
- 239000002313 adhesive film Substances 0.000 claims description 37
- 239000000835 fiber Substances 0.000 claims description 21
- 239000003365 glass fiber Substances 0.000 claims description 20
- 239000003292 glue Substances 0.000 claims description 14
- 239000011347 resin Substances 0.000 claims description 10
- 229920005989 resin Polymers 0.000 claims description 10
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000004643 cyanate ester Substances 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000011159 matrix material Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- 239000004698 Polyethylene Substances 0.000 claims 1
- -1 polyethylene Polymers 0.000 claims 1
- 229920000573 polyethylene Polymers 0.000 claims 1
- 238000003825 pressing Methods 0.000 claims 1
- 230000035882 stress Effects 0.000 description 11
- 230000000052 comparative effect Effects 0.000 description 4
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 239000004033 plastic Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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 piece product, which comprises the step S1 of carrying out primary processing on a metal embedded part, wherein the metal embedded part comprises a hexahedral main body with a hollow structure inside, six connecting surfaces of the hexahedral main body are provided with an interface boss or a lightening hole according to actual needs, six connecting surfaces of the metal embedded part, which are contacted with a composite material, are all provided with a groove, the inside of the groove is of a communicated structure, the groove is provided with a circle of outer flanges at positions close to the edges of the connecting surfaces, and the groove is provided with a circle of inner flanges at positions close to the interface boss or the lightening hole on the connecting surfaces; step S2, performing sand blasting treatment on the metal embedded part; step S3, paving a transition layer; step S4, laying a prepreg; step S5, mold closing; and step S6, curing, wherein the curing system is 110 ℃/2 h-130 ℃/4 h. 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 an embedded metal part, and particularly relates to a preparation method of a low-stress composite material embedded metal part product.
Background
Most of composite material products utilize metal parts as processing and assembling interfaces. In the design process of the composite material product, in order to ensure that the product has a compact structure, improve the bearing capacity and reduce the number of assembly connecting pieces, the metal piece is often designed to be embedded in the inner structure of the composite material, and the metal piece with the structure is completely wrapped by the composite material. However, since the composite material is molded and cured at a relatively high temperature, the thermal expansion coefficient of the metal part is higher than that of the composite material, the deformation amount of the metal part is larger than that of the composite material after the curing is finished and the temperature is reduced to room temperature, stress exists at the interface of the composite material and the metal part, and if the ultimate stress is reached, microscopic gaps are generated between the metal part and the composite material or the metal part is deformed, so that the secondary processing precision and the stability of the long-term use size and form and position tolerance of the product are influenced.
In order to solve the problem of stress between the metal part and the composite material, an adhesive film is usually laid on the surface of the metal part in the processing process of the composite material product, but the adhesive film is used as a process layer, so that the pressure is high in the composite material forming process, the loss is high after curing, the thickness is not easy to control, and the solution effect is unstable.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a method for preparing a low-stress composite material embedded metal product, in which a transition layer is laid between a metal part and a composite material interface, the transition layer is made of a glue film and chopped fibers, a groove is formed in the surface of the metal part to control the thickness of the transition layer, and the plastic deformation of the transition layer in the cooling process after the composite material is formed and cured is utilized to eliminate the problems of thermal expansion coefficient mismatch between the metal part and the composite material and internal stress generated after curing, thereby solving the problems of deformation and interface gap generated by excessive internal stress of the composite material product with the embedded metal part, and improving the dimensional stability of the composite material product.
In order to achieve the 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 metal embedded part
S11, preparing a metal embedded part, wherein the metal embedded part comprises a hexahedron main body with a hollow structure inside, and six connecting surfaces of the hexahedron main body are provided with interface bosses or lightening holes selectively 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, the inner parts of 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 interface bosses or lightening holes on the connecting surfaces, of the grooves;
step 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 sequentially comprise a first glue film layer, a chopped fiber layer and a second glue film layer from bottom to top; when in paving, 1 layer of first adhesive film layer is paved in the groove of the metal embedded part, then the glass fiber is cut into pieces and paved on the surface of the first adhesive film layer as a chopped fiber layer, and then 1 layer of second adhesive film layer is paved;
step S4 of laying prepreg
Laying a prepreg by the metal embedded part and the mould;
step S5, mold clamping
Placing the laid die and the metal embedded part on an inner die flat plate, combining an outer die, placing the outer die in a curing furnace, heating, further pressurizing the outer die when the temperature of the die reaches 70 ℃, and carefully controlling a die closing gap in a prepressing process so as to avoid overlarge stress of the metal embedded part in a cold closing process;
step S6, solidifying
After the die assembly is finished, the die is integrally placed into a curing furnace, and the curing system is 110 ℃/2 h-130 ℃/4h, so that the product molding is finished.
Preferably, the depth of the groove processed in step S12 is 0.3 mm.
Preferably, when the surface of the metal embedded part is subjected to sand blasting treatment in the step S2, 30-mesh 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.
Preferably, the thickness of the first adhesive film layer and the second adhesive film layer in step S3 is 0.35mm to 0.4 mm; the chopped fiber layer adopts glass fiber, the length of the glass fiber is 3-5 mm, the glass fiber is uniformly paved on the first adhesive film layer, and the coverage area is 50%.
Preferably, the prepreg in the step S4 is made of a carbon fiber reinforced resin matrix composite material, and the resin is cyanate ester resin cured at a medium temperature; the metal embedded part is made of titanium alloy.
As a further optimization of the invention, the first adhesive film layer and the second adhesive film layer are LWF (light weight fiber) adhesive films, and the grade of the glass fiber is HT469 LB-1200R.
The invention has the following beneficial effects:
(1) according to the invention, the groove is formed in the metal embedded part, the transition layer is arranged in the groove, and the internal stress generated after the thermal expansion coefficients of the metal embedded part and the composite material are mismatched and cured is eliminated by utilizing the deformation of the transition layer in the cooling process after the composite material is molded and cured, so that the problems of deformation and interface clearance generated by overlarge internal stress of a composite material product with the embedded metal part are solved, and the dimensional stability of the composite material product is improved.
(2) The groove on the metal embedded part is provided with a circle of outer flanges at the position close to the edge of the connecting surface, and a circle of inner flanges at the position close to the interface boss or the lightening hole on the connecting surface, so that the outer flanges and the inner flanges can effectively prevent the loss of a glue film when the glue film is converted into a liquid state in the high-temperature curing process, the size of the glue film is more accurately controlled, and the sufficient plastic deformation in the thickness direction is realized to adapt to the deformation of a metal piece.
(3) According to the invention, the chopped fiber layer is arranged between the two glue films of the transition layer, and the chopped fibers can be fully soaked by the glue films along with pressurization, temperature rise and solidification in the forming process, so that the transition layer has higher toughness than the glue films and lower modulus than the composite material and the metal piece; meanwhile, the chopped fibers can further prevent the liquid glue film from losing, and can eliminate most of stress between the metal piece and the composite material under the condition of ensuring the bonding strength.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view of an overall structure of a low-stress composite material embedded metal part prepared in embodiment 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 view of a first angle of the embedded metal part adopted in embodiment 1;
fig. 4 is a schematic structural view of a second angle of the embedded metal part adopted in embodiment 1;
fig. 5 is a schematic structural view 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 view of a pre-buried metal piece adopted in embodiment 2;
FIG. 8 is a schematic view of a molded product produced in example 2;
fig. 9 is a schematic structural view of a buried metal member used in comparative example 1;
fig. 10 is a schematic view of a molded product prepared in comparative example 1.
Wherein the reference numerals are: the composite material layer comprises a metal embedded part 1, a composite material layer 2, a transition layer 3, a groove 4, a hexahedral main body 11, an interface boss 12, a lightening hole 13, an upper connecting surface 111, a lower connecting surface 112, a left connecting surface 113, a right connecting surface 114, a front connecting surface 115, a rear connecting surface 116, a first glue film layer 31, a chopped fiber layer 32, a second glue film layer 33, an outer flange 41 and an 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 is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.
In the description of the present application, it should be noted that the terms "in", "under", and the like indicate the orientation or positional relationship: the particular arrangements or components shown in the drawings, or the orientations or positional relationships conventionally used in the manufacture of the applications, are for convenience only and to simplify the description, and are not intended to indicate or imply that the referenced devices or components must be in a particular orientation, constructed and operated in a particular orientation, and are not to be construed as limiting the application. Furthermore, the terms "first," "second," and the like are used solely to distinguish one from another, and are not to be construed as indicating or implying relative importance.
In the description of the present application, it should also be noted that, unless expressly stated or limited otherwise, the terms "disposed" and "connected" are to be construed broadly, and may for example be fixedly connected, detachably connected, or integrally connected; they may be mechanically coupled, directly coupled, indirectly coupled through intervening media, or may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
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 hexahedron main body 11 with a hollow structure inside, and six connecting surfaces of the hexahedron main body are provided with an interface boss 12 or a lightening hole 13 according to actual needs; an upper connecting surface 111 of a metal embedded part 1 provided in this embodiment is provided with an interface boss 12 and a lightening hole 13, a lower connecting surface 112 of the metal embedded part 1 is provided with two lightening holes 13, a left connecting surface 113 is provided with an interface boss 12, a right connecting surface 114 is provided with a lightening hole 13, and a front connecting surface 115 and a 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 characterized by the mark TC4, the wall thickness of 15mm and the density of 4.5g/cm 3 Coefficient of thermal expansion of 7.89X 10 -6 /℃；
Step S12, processing grooves 4 on six connecting surfaces of the metal embedded part 1, which are in contact with the composite material, wherein the insides of the grooves 4 are of communicated structures, a circle of outer flanges 41 are arranged at the positions, close to the edges of the connecting surfaces, of the grooves 4, a circle of inner flanges 42 are arranged at the positions, close to interface bosses or lightening holes on the connecting surfaces, of the grooves, and the outer flanges 41 and the inner flanges 42 of the grooves are used for preventing the high-temperature curing process and the adhesive film from losing when the adhesive film is turned into a liquid state (see the figures 3 to 5); the depth of the groove 4 is 0.3mm, the thickness of the cured transition layer can be controlled to be 0.3mm, compared with a metal embedded part without the groove, the size of an adhesive film is more accurately controlled, the adhesive film is less extruded and lost by prepreg, and sufficient plastic deformation in the thickness direction is realized to adapt to the deformation of the metal embedded part;
s2, performing sand blasting treatment on the metal embedded part, selecting 30-mesh carborundum when the surface of the metal embedded part is subjected to sand blasting treatment, wherein the sand blasting pressure is 0.6-0.8 Mpa, and cleaning the metal embedded part by using acetone after sand blasting;
step S3, paving a transition layer
The method comprises the steps that a transition layer 3 is laid in grooves of six connecting faces of a metal embedded part 1, the transition layer 3 sequentially comprises 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 layer 3 are LWF (light weight fiber) brand adhesive films produced by petrochemical houses in Heilongjiang province, 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 mark number of the glass fibers is HT469LB-1200R, when the transition layer is paved, 1 first adhesive film layer is paved in a groove of a metal embedded part, then the glass fibers are sheared into the length of 3-5 mm, the first adhesive film layer is paved on the surface of the first adhesive film layer to serve as a chopped fiber layer (the glass fibers uniformly cover 50% of the area), and then 1 second adhesive film layer is paved;
step S4 of laying prepreg
The prepreg is laid by the metal embedded part and the mould together, the prepreg is made of a carbon fiber reinforced resin matrix composite, the resin is cyanate ester resin with a 130 ℃ medium temperature curing formula, compared with a traditional high-temperature resin formula (cured 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 fiber, the fiber is designed according to quasi-isotropic layering, and the thermal expansion coefficient of the composite material part is 1.23 multiplied by 10 -6 /℃；
Step S5, mold clamping
Placing the laid die and the metal embedded part on an inner die flat plate, combining an outer die, placing the outer die in a curing furnace, heating, further pressurizing the outer die when the temperature of the die reaches 70 ℃, and carefully controlling a die closing gap in a prepressing process so as to avoid overlarge stress of the metal embedded part in a cold closing process;
step S6, solidifying
After the die assembly is finished, the die is integrally placed into a curing furnace, the curing system is 110 ℃/2 h-130 ℃/4h, the product molding is finished, the molded product is shown in figure 1, and the sectional view is shown in figure 2. In the composite material structure of the single embedded metal part shown in fig. 1, the metal part is made of TC4 with the wall thickness of 15mm and the groove of 0.3mm, the composite material is made of M40 JB/cyanate with the wall thickness of 10mm, the adhesive film is made of LWF with the thickness of 0.35mm, the chopped fiber is glass fiber, and the glass fiber is HT469 LB-1200R.
Example 2
The difference from example 1 is that the structure of the metallic embedment and the final composite structure are slightly different.
The metal embedded part 1 comprises a hexahedron body, wherein two interface bosses 12 are arranged on only one of the connection surfaces (top surface) of the six connection surfaces of the hexahedron body, the other connection surfaces are not provided with the interface bosses and lightening holes, each connection surface is provided with a groove 4, the inside of each groove 4 is a communicated structure, the groove 4 is provided with a circle of outer flanges 41 at the position close to the edge of the connection surface, and the groove is provided with a circle of inner flanges 42 at the position close to the interface bosses 12 on the connection surface (see fig. 7).
The single embedded metal part composite material structure shown in fig. 8 and the single embedded metal part composite material structure shown in fig. 8 are prepared by the method of the embodiment 1 and the metal embedded part 1, wherein the metal embedded part material is TC4, the wall thickness is 5mm, the groove is 0.3mm, the composite material is M40 JB/cyanate, the wall thickness is 5mm, the adhesive film is LWF, the thickness is 0.35mm, the chopped fibers are glass fibers, and the glass fiber brand is HT469 LB-1200R.
Comparative example 1
The difference from the embodiment 1 lies in the structure of the metal embedded part, that is, only one connecting surface of the metal embedded part, which is not provided with the interface boss and the lightening hole, is provided with the groove, and the rest connecting surfaces are not provided with the grooves, as shown in fig. 9.
The single embedded metal part composite material structure shown in fig. 10 and the single embedded metal part composite material structure shown in fig. 10 were prepared by using a metal embedded part 1 without a groove and referring to the method of example 1, wherein the metal embedded part material was TC4 with a wall thickness of 15mm, no groove was machined, the composite material was M40 JB/cyanate with a wall thickness of 10mm, the adhesive film was LWF with a thickness of 0.35mm, the chopped fibers were glass fibers, and the glass fiber brand number was HT469 LB-1200R.
And (3) detection:
(1) the product obtained in example 1 was subjected to nondestructive inspection, and the bonding area between the metal member and the composite material was measured, and the result showed that the bonding area between the metal member and the composite material occupied 95% of the total area, which indicates that the method solves the problems of deformation due to excessive internal stress of the composite material product and interfacial gaps between the metal member and the composite material.
(2) The surface of the boss of the product in the example 2 is processed until the planeness is less than or equal to 0.03mm, then a thermal cycle test is carried out, the test temperature range is 5-55 ℃, and the planeness is measured after processing, wherein the planeness is 0.03 mm. The composite material product adopting the design structure and the process has higher dimensional stability.
(3) And (3) carrying out nondestructive inspection on the product of the comparative example 1, and detecting the bonding area of the metal part and the composite material, wherein the result shows that the bonding area of the metal part and the composite material accounts for 48% of the total area, which shows that the design of the groove structure in the metal embedded part plays a role in avoiding the loss of the adhesive film.
The above description is only for the specific 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 conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. A preparation method of a low-stress composite material embedded metal part product is characterized by comprising the following steps:
step S1, performing primary processing on the metal embedded part
S11, preparing a metal embedded part, wherein the metal embedded part comprises a hexahedron main body with a hollow structure inside, and six connecting surfaces of the hexahedron main body are provided with interface bosses or lightening holes selectively 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, the inner parts of 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 interface bosses or lightening holes on the connecting surfaces, of the grooves;
step S2, performing 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 sequentially comprise a first glue film layer, a chopped fiber layer and a second glue film layer from bottom to top; when in paving, 1 layer of first adhesive film layer is paved in the groove of the metal embedded part, then the glass fiber is cut into pieces and paved on the surface of the first adhesive film layer as a chopped fiber layer, and then 1 layer of second adhesive film layer is paved;
step S4 of laying prepreg
Laying a prepreg on the metal embedded part and the mould together;
step S5, mold clamping
Placing the laid die and the metal embedded part on an inner die flat plate, combining an outer die, placing the combined outer die in a curing furnace, then heating, further pressurizing the outer die when the temperature of the die reaches 70 ℃, and controlling a die closing gap in a pre-pressing process so as to avoid overlarge stress of the metal embedded part in a cold-closing process;
step S6, curing
After the die assembly is finished, the die is integrally placed into a curing furnace, the curing system is 110 ℃/2 h-130 ℃/4h, and the product molding is finished.
2. The method for preparing a low-stress composite material embedded metal piece product according to claim 1, wherein the depth of the groove processed in the step S12 is 0.3 mm.
3. The method for preparing the low-stress composite material embedded metal part product according to claim 1, wherein in the step S2, 30-mesh carborundum is selected when the surface of the metal embedded part is subjected to sand blasting, the sand blasting pressure is 0.6-0.8 Mpa, and the product is cleaned by acetone after sand blasting.
4. The method for preparing the low-stress composite material embedded metal piece product according to claim 1, wherein the thicknesses of the first adhesive film layer and the second adhesive film layer in the step S3 are 0.35-0.4 mm; the chopped fiber layer adopts glass fiber, the length of the glass fiber is 3-5 mm, the glass fiber is uniformly paved on the first adhesive film layer, and the coverage area is 50%.
5. The method for preparing the low-stress composite material embedded metal part product according to claim 1, wherein the prepreg obtained in the step S4 is made of a carbon fiber reinforced resin matrix composite material, and the resin is cyanate ester resin cured at medium temperature; the metal embedded part is made of titanium alloy.
6. The method for preparing a low-stress composite material embedded metal part product according to claim 1, wherein the first adhesive film layer and the second adhesive film layer are LWF (low-pressure polyethylene) adhesive films, and the glass fiber is HT469 LB-1200R.
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 true CN114939938A (en) | 2022-08-26 |
| CN114939938B 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 (12)
| 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 |
| US20090041972A1 (en) * | 2007-08-07 | 2009-02-12 | Rodman William L | Composite structures and methods of making same |
| US20110247958A1 (en) * | 2008-10-16 | 2011-10-13 | Composite Transport Technologies ,Inc. | Lightweight unit load device |
| 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 |
| US20210187908A1 (en) * | 2017-12-28 | 2021-06-24 | Nippon Steel Corporation | Metal-fiber-reinforced resin material composite and production 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 |
-
2022
- 2022-04-18 CN CN202210402480.9A patent/CN114939938B/en active Active
Patent Citations (12)
| 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 |
| US20090041972A1 (en) * | 2007-08-07 | 2009-02-12 | Rodman William L | Composite structures and methods of making same |
| US20110247958A1 (en) * | 2008-10-16 | 2011-10-13 | Composite Transport Technologies ,Inc. | Lightweight unit load device |
| 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 |
| US20210187908A1 (en) * | 2017-12-28 | 2021-06-24 | Nippon Steel Corporation | Metal-fiber-reinforced resin material composite and production method thereof |
| 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 |
|---|---|
| CN114939938B (en) | 2023-06-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103273662B (en) | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould | |
| CN104162996B (en) | The manufacturing process of the U-shaped part of carbon fibre composite | |
| CN102320139A (en) | Forming process of curved composite tube | |
| CN108481767B (en) | Mutually-embedded topological pipeline structure and integral forming method | |
| CN106113522A (en) | A kind of variable cross-section I-shaped beam mantle assistant formation method containing corrugated listrium | |
| CN101462369B (en) | Method for preparing pipe sheet for heat-exchange facility and products produced thereby | |
| CN115847868B (en) | Manufacturing method of carbon fiber composite low-temperature blade | |
| CN113601878A (en) | Large-curvature special-shaped surface and large-height honeycomb co-curing sandwich structure composite material and forming method thereof | |
| CN109532058A (en) | A kind of Varying-thickness polymer matrix composites structure preparation method | |
| CN113059824B (en) | Fiber-reinforced thermoplastic resin-based composite material and preparation method and application thereof | |
| WO2019188195A1 (en) | Method for producing fiber-reinforced resin | |
| CN114939938A (en) | Preparation method of low-stress composite material embedded metal part product | |
| CN101961893A (en) | Composite material mold and manufacturing method thereof | |
| EP0662380A2 (en) | Mould for fibre-reinforced plastics | |
| CN116901481A (en) | A modular cylindrical shell structure, combined mold and preparation method | |
| CN217943908U (en) | Low-stress composite material embedded metal part structure | |
| EP4137299B1 (en) | Mold for carbon fiber composite material | |
| CN113910637B (en) | Forming method of composite material complex special-shaped air inlet channel | |
| CN115847863A (en) | Method for accurately manufacturing pores of composite laminated board | |
| CN110712382B (en) | Rear cover device suitable for space-borne full-composite camera and integral forming method | |
| CN114211777A (en) | Manufacturing method of carbon fiber composite material reflecting surface | |
| CN209987489U (en) | a trough member | |
| JP5078865B2 (en) | Laminated composite material and method for producing laminated composite material | |
| CN208529790U (en) | Fan blade | |
| CN218430090U (en) | Fiber reinforced composite structure |
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 |