CN112373061B - Composite material member and manufacturing method thereof - Google Patents

Composite material member and manufacturing method thereof Download PDF

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Publication number
CN112373061B
CN112373061B CN202011088372.6A CN202011088372A CN112373061B CN 112373061 B CN112373061 B CN 112373061B CN 202011088372 A CN202011088372 A CN 202011088372A CN 112373061 B CN112373061 B CN 112373061B
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Prior art keywords
composite material
fiber
material member
scale
micron
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CN112373061A (en
Inventor
井文奇
杜逸飞
张涛
田智立
刘雷波
李卓达
夏雅男
魏洪峰
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Aerospace Research Institute of Materials and Processing Technology
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Aerospace Research Institute of Materials and Processing Technology
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • 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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/42—Moulds or cores; Details thereof or accessories therefor characterised by the shape of the moulding surface, e.g. ribs or grooves
    • 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

Abstract

The invention relates to a composite material component and a manufacturing method thereof. A plurality of micrometer-scale protrusions are distributed on the surface of the composite material component, which is required to be in contact fit with the assembly structure, and gaps exist among the micrometer-scale protrusions. The manufacturing method comprises the following steps: (1) obtaining a flexible mould by a 3D printing method, wherein a plurality of concave hole structures with micron scale are distributed on the flexible mould, and gaps exist among the concave hole structures; (2) and (2) placing the flexible mold prepared in the step (1) on the surface of the composite material preformed body, and removing the flexible mold after curing to obtain the composite material member. According to the invention, a micron-scale island-shaped interface is formed between the composite material member and the assembly structure by using the plurality of micron-scale protrusions, the micron-scale protrusions can improve the friction coefficient of the interface, and the existence of the gap provides a space for the deformation of the protrusion, so that the composite material can be tightly contacted with the assembly structure, and a contact fit gap is not caused by the problem of profile processing precision.

Description

Composite material member and manufacturing method thereof
Technical Field
The invention relates to the technical field of aerospace composite material components, in particular to a composite material component and a manufacturing method thereof.
Background
With the continuous expansion of the application field of composite materials, in some application scenarios, a composite material part needs to establish a contact fit relationship with other assembly structures. In such a contact fitting, in order to ensure technical effects, it is necessary that the surface of the composite material member has a high friction coefficient and a high deformability, so that the composite material member is in close contact with the assembly structure and a contact fitting gap is not generated due to a problem of profile processing accuracy.
However, in the conventional molding process, the surface of the composite material part is generally smooth, and the smoothness is determined by the processing precision of the mold. From the aspect of mold processing, the current manufacturing process is also generally used to prepare composite material members with smooth surfaces.
Disclosure of Invention
The first purpose of the invention is to provide a composite material member, the surface of which has high friction coefficient and higher deformability, so as to achieve the purpose that the composite material member is tightly contacted with an assembly structure and contact fit clearance is not generated due to the problem of profile processing precision;
a second object of the invention is to provide a method for manufacturing a composite material element as described above.
In order to solve the technical problems, the invention provides the following technical scheme:
a composite material member is provided, wherein a plurality of micrometer-scale protrusions are distributed on the surface of the composite material member to be in contact fit with an assembly structure, and gaps exist among the micrometer-scale protrusions.
Preferably, the composite material is a fibre reinforced resin based composite material.
Preferably, the resin is a thermosetting resin and/or a thermoplastic resin; and/or
The fiber is any one or more of inorganic fiber, organic fiber and metal fiber.
Preferably, the thermosetting resin is selected from any one or more of epoxy resin, unsaturated polyester, vinyl resin, polyurethane, polycyanate, bismaleimide and thermosetting polyimide;
the thermoplastic resin is selected from any one or more of polyethylene, polypropylene, polystyrene, polyurethane, polyarylketone and thermoplastic polyimide;
the inorganic fiber is selected from any one or more of glass fiber, carbon fiber, boron fiber, silicon carbide fiber, silicon nitride fiber and basalt fiber;
the organic fiber is selected from any one or more of cotton, hemp, aramid fiber, spandex, acrylic fiber, viscose and polyphenyl ether; and/or
The metal fiber is selected from any one or more of aluminum, stainless steel and brass.
Preferably, the sum S of the base areas of the micrometer-scale protrusions satisfies the following condition:
0.25S0≤S≤0.5S0in which S is0Refers to the area of the surface of the composite material member that is in contact engagement with the mounting structure.
Preferably, the protrusion is in the shape of any one or more of a cylinder, a cone, a cube.
Preferably a plurality of said protrusions form a regularly arranged array.
Preferably, the protrusions have a height of 50 μm or less and a maximum width of 150 μm;
preferably, the voids are 200 μm.
Preferably, the composite material member is a flat or curved member.
A method for manufacturing the composite material member is characterized by comprising the following steps:
(1) obtaining a flexible mould by a 3D printing method, wherein a plurality of concave hole structures with micron scale are distributed on the flexible mould, and gaps exist among the concave hole structures;
(2) and (2) placing the flexible mold prepared in the step (1) on the surface of the composite material preformed body, and removing the flexible mold after curing to obtain the composite material member.
Advantageous effects
The technical scheme of the invention has the following advantages:
according to the invention, a micron-scale island-shaped interface is formed between the composite material member and the assembly structure by using the plurality of micron-scale protrusions, the micron-scale protrusions can improve the friction coefficient of the interface, and the existence of the gap provides a space for the deformation of the protrusion, so that the composite material can be tightly contacted with the assembly structure, and a contact fit gap is not caused by the problem of profile processing precision.
Invention controlThe sum S of the base areas of the plurality of micrometer-scale protrusions satisfies the following condition: 0.25S0≤S≤0.5S0In which S is0The area of the surface of the composite material component in contact fit with the assembly structure enables the designed island-shaped interface to be capable of improving the friction coefficient of the interface well and not reducing the long-term service life of the composite material component combined with the assembly structure.
Drawings
FIG. 1 is a flow chart of the fabrication of a composite component provided by the present invention;
fig. 2 is a pictorial view of a composite material member provided by the present invention.
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 clearly and completely described below with reference to the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
< first aspect >
The present invention provides in a first aspect a composite material member for contact engagement with an assembly structure, as shown in figures 1 and 2, having a plurality of micron-scale protrusions distributed over the surface to be contact-engaged with the assembly structure, with spaces between the micron-scale protrusions.
The micron-scale protrusions form a micron-scale island-shaped interface between the composite material member and the assembly structure, the micron-scale protrusions can improve the friction coefficient of the interface, and the existence of the gaps provides a space for deformation of the protrusions, so that the composite material can be in close contact with the assembly structure, and contact fit gaps cannot occur due to the problem of profile machining precision.
The composite material is preferably a fibre reinforced resin based composite material.
The type of the resin is not particularly limited in the present invention, and a thermosetting resin and/or a thermoplastic resin can be used as the resin.
Examples of the thermosetting resin include epoxy resins, unsaturated polyesters, vinyl resins, polyurethanes, polycyanates, bismaleimides, thermosetting polyimides, and the like.
Examples of the thermoplastic resin include polyethylene, polypropylene, polystyrene, polyurethane, polyaryletherketone, and thermoplastic polyimide.
The type of the fiber is not particularly limited in the present invention, and the fiber may be any one or more of an organic fiber, an inorganic fiber, and a metal fiber.
Examples of the organic fiber include cotton, hemp, aramid, spandex, acrylic, viscose, polyphenylene oxide, and the like.
Examples of the inorganic fibers include glass fibers, carbon fibers, boron fibers, silicon carbide fibers, silicon nitride fibers, basalt fibers, and the like.
Examples of the metal fiber include aluminum, stainless steel, and brass.
Suitable resins and fibers can be selected according to the use requirements (or the use purpose or the use scene).
When designing the island-shaped interface on the surface of the resin-based fiber reinforced composite material, the inventor finds that the island-shaped interface is not the better as the coverage area is larger, and when the coverage area is too large, the island-shaped interface can influence the combination of the component and the assembly structure, so that the long-term service life is reduced. Of course, too small a coverage area does not provide a good effect of increasing the friction coefficient. In some preferred embodiments, the sum S of the base areas of the plurality of micrometer-scale protrusions preferably satisfies the following condition:
0.25S0≤S≤0.5S0in which S is0Refers to the area of the surface of the composite material member that is in contact engagement with the mounting structure.
The island-shaped interface designed by the method can improve the friction coefficient of the interface well, and can not reduce the long-term service life of the composite material member combined with the assembly structure.
The shape of the protrusions is not particularly limited in the present invention, but it is preferable that the shape of the protrusions is any one or more of a cylindrical shape, a conical shape, and a cubic shape (e.g., a rectangular shape and/or a square shape) from the viewpoint of the production process. More preferably, the array having the above-described shape features is formed in a regular arrangement.
In some preferred embodiments, the protrusions have a height of 50 μm or less and a maximum width of 150 μm. When the protrusion is in a regular shape such as a cylinder, a rectangle, a square, etc., the maximum width refers to the diameter of the cylinder, the length of the bottom side of the rectangle, and the side length of the square; when the protrusion is conical in shape, the maximum width refers to the diameter of the base. Preferably, the voids are 200 μm.
The composite material member provided by the invention can be a flat plate or a curved plate, namely, the island-shaped interface can be designed on the surface of the flat plate-shaped composite material member (which refers to the surface required to be in contact with and matched with the assembly structure), and the island-shaped interface can be designed on the curved surface-shaped composite material member (which refers to the surface required to be in contact with and matched with the assembly structure).
< second aspect >
The present invention provides in a second aspect a method of manufacturing a composite component provided in the first aspect, the method comprising the steps of:
step (1): step of providing a flexible mold
The flexibility is conformal, so that the micron-scale mold can be attached to the surface with a complex shape, and a micro-scale island-shaped interface can be smoothly prepared on the complex surface. The flexible mold has the following properties in structure: a plurality of pit structures with micrometer scale are distributed, and gaps exist among the pit structures. The shape of the dimple arrangement affects the shape of the protrusion. Therefore, the shape of the cavity structure can be designed according to the required shape of the protrusion, and if the required protrusion is cylindrical, the cavity structure is a cylindrical hollow structure; if the required protrusion is conical, the concave structure is a conical hollow structure; if the required protrusion is rectangular, the concave hole structure is a rectangular hollow structure; if the desired protrusion is square, the cavity structure is a square hollow structure.
In addition, the height, width, gap, arrangement, etc. of the cavity structures affect the corresponding parameters of the protrusions. Thus, the corresponding properties of the cavity structure can be designed in the design of the flexible mould according to the desired properties of the protrusions (e.g. height, width, spacing, arrangement).
The flexible mold is obtained by the 3D printing method, and the flexible mold has the advantage of flexible design.
(2) And (2) placing the flexible mold prepared in the step (1) on the surface of the composite material preformed body, removing the flexible mold after curing to obtain a composite material member, wherein a plurality of micrometer-scale protruding objects are distributed on the surface of the composite material member, which is required to be in contact fit with the assembly structure, and gaps exist among the micrometer-scale protruding objects.
The following are examples of the present invention.
Example 1
A carbon fiber reinforced polyurethane resin composite material flat component is provided, wherein a plurality of micrometer scale protruding objects are distributed on the surface of the composite material component which needs to be contacted and matched with an assembly structure, and gaps exist among the micrometer scale protruding objects; the protrusions were cylindrical in shape, 50 μm in height, 100 μm in diameter, and 200 μm in void; a plurality of protrusions forming a regularly arranged array; the sum S of the base areas of the plurality of micrometer-scale protrusions satisfies the following condition: s is 0.3S0In which S is0Refers to the area of the surface of the composite material member that is in contact engagement with the mounting structure.
The manufacturing method comprises the following steps:
s1, obtaining a flexible mold through a 3D printing method, wherein a plurality of micrometer-scale concave hole structures are distributed on the flexible mold, and gaps exist among the concave hole structures; the concave hole structure is a cylindrical hollow structure, the height of the concave hole structure is 50 micrometers, the diameter of the concave hole structure is 100 micrometers, the gap of the concave hole structure is 200 micrometers, and a plurality of concave hole structures form a regularly arranged array;
s2; stacking prepreg layers to obtain a composite material preformed body;
and S3, placing the flexible mold on the surface of the composite material preformed body, and removing the flexible mold after curing to obtain the composite material member. A plurality of micron-scale protrusions on the surface of the member form a micron-scale island-shaped interface between the composite material member and the assembly structure, the micron-scale protrusions can improve the friction coefficient of the interface, and the existence of gaps provides a space for deformation of the protrusions, so that the composite material can be in close contact with the assembly structure, and contact fit gaps cannot occur due to the problem of profile machining precision.
Example 2
A quartz fiber reinforced epoxy resin composite material flat component is characterized in that a plurality of micrometer-scale protrusions are distributed on the surface of the composite material component which needs to be in contact fit with an assembly structure, and gaps exist among the micrometer-scale protrusions; the shape of the protrusion is cone, the height is 50 μm, the diameter of the bottom surface is 150 μm, and the gap is 200 μm; a plurality of protrusions forming a regularly arranged array; the sum S of the base areas of the plurality of micrometer-scale protrusions satisfies the following condition: s is 0.3S0In which S is0Refers to the area of the surface of the composite material member that is in contact engagement with the mounting structure.
The manufacturing method comprises the following steps:
s1, obtaining a flexible mold through a 3D printing method, wherein a plurality of micrometer-scale concave hole structures are distributed on the flexible mold, and gaps exist among the concave hole structures; the concave hole structure is a conical hollow structure, the height of the concave hole structure is 50 micrometers, the diameter of the concave hole structure is 150 micrometers, the gap of the concave hole structure is 200 micrometers, and a plurality of concave hole structures form a regularly arranged array;
s2; stacking prepreg layers to obtain a composite material preformed body;
and S3, placing the flexible mold on the surface of the composite material preformed body, and removing the flexible mold after curing to obtain the composite material member. A plurality of micron-scale protrusions on the surface of the member form a micron-scale island-shaped interface between the composite material member and the assembly structure, the micron-scale protrusions can improve the friction coefficient of the interface, and the existence of gaps provides a space for deformation of the protrusions, so that the composite material can be in close contact with the assembly structure, and contact fit gaps cannot occur due to the problem of profile machining precision.
Example 3
A quartz fiber reinforced epoxy resin composite material flat component is characterized in that a plurality of micrometer-scale protrusions are distributed on the surface of the composite material component which needs to be in contact fit with an assembly structure, and gaps exist among the micrometer-scale protrusions; the shape of the protrusion is a cube, the side length is 50 μm, and the gap is 150 μm; a plurality of protrusions forming a regularly arranged array; the sum S of the base areas of the plurality of micrometer-scale protrusions satisfies the following condition: s is 0.3S0In which S is0Refers to the area of the surface of the composite material member that is in contact engagement with the mounting structure.
The manufacturing method comprises the following steps:
s1, obtaining a flexible mold through a 3D printing method, wherein a plurality of micrometer-scale concave hole structures are distributed on the flexible mold, and gaps exist among the concave hole structures; the concave hole structure is a cube hollow structure, the side length is 50 micrometers, and a plurality of concave hole structures form a regularly arranged array;
s2; stacking prepreg layers to obtain a composite material preformed body;
and S3, placing the flexible mold on the surface of the composite material preformed body, and removing the flexible mold after curing to obtain the composite material member. A plurality of micron-scale protrusions on the surface of the member form a micron-scale island-shaped interface between the composite material member and the assembly structure, the micron-scale protrusions can improve the friction coefficient of the interface, and the existence of gaps provides a space for deformation of the protrusions, so that the composite material can be in close contact with the assembly structure, and contact fit gaps cannot occur due to the problem of profile machining precision.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims (10)

1. A composite material member is characterized in that a plurality of micron-scale protrusions are distributed on the surface of the composite material member, which is required to be in contact fit with an assembly structure, gaps exist among the micron-scale protrusions, and a micron-scale island-shaped interface is formed between the composite material member and the assembly structure by the micron-scale protrusions;
the sum S of the bottom areas of the micrometer-scale protrusions satisfies the following condition:
0.25S0≤S≤0.5S0in which S is0Refers to the area of the surface of the composite material member that is in contact engagement with the mounting structure.
2. The composite material member according to claim 1,
the composite material is a fiber reinforced resin matrix composite material.
3. The composite material member according to claim 2,
the resin is thermosetting resin and/or thermoplastic resin; and/or
The fiber is any one or more of inorganic fiber, organic fiber and metal fiber.
4. The composite material member according to claim 3,
the thermosetting resin is selected from any one or more of epoxy resin, unsaturated polyester, vinyl resin, polyurethane, polycyanate, bismaleimide and thermosetting polyimide;
the thermoplastic resin is selected from any one or more of polyethylene, polypropylene, polystyrene, polyurethane, polyarylketone and thermoplastic polyimide;
the inorganic fiber is selected from any one or more of glass fiber, carbon fiber, boron fiber, silicon carbide fiber, silicon nitride fiber and basalt fiber;
the organic fiber is selected from any one or more of cotton, hemp, aramid fiber, spandex, acrylic fiber, viscose and polyphenyl ether; and/or
The metal fiber is selected from any one or more of aluminum, stainless steel and brass.
5. The composite material member according to claim 1,
the protrusion may be in the shape of any one or more of a cylinder, a cone, a cube.
6. The composite material member according to claim 5,
a plurality of the protrusions form a regularly arranged array.
7. The composite material member according to claim 5 or 6,
the protrusions have a height of 50 μm or less and a maximum width of 150 μm.
8. The composite material member according to claim 1,
the voids are 200 μm.
9. The composite material member according to claim 1,
the composite material member is a flat plate or a curved plate.
10. A method of manufacturing a composite component according to any one of claims 1 to 9, comprising the steps of:
(1) obtaining a flexible mould by a 3D printing method, wherein a plurality of concave hole structures with micron scale are distributed on the flexible mould, and gaps exist among the concave hole structures;
(2) and (2) placing the flexible mold prepared in the step (1) on the surface of the composite material preformed body, and removing the flexible mold after curing to obtain the composite material member.
CN202011088372.6A 2020-10-13 2020-10-13 Composite material member and manufacturing method thereof Active CN112373061B (en)

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CN112373061B true CN112373061B (en) 2022-04-29

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6663820B2 (en) * 2001-03-14 2003-12-16 The Procter & Gamble Company Method of manufacturing microneedle structures using soft lithography and photolithography
CN106696309A (en) * 2016-12-15 2017-05-24 中国航空工业集团公司基础技术研究院 Method for preparing composite material with micro structures on surface through soft printing process and composite material prepared by method
CN108928016A (en) * 2017-09-22 2018-12-04 中国航空工业集团公司基础技术研究院 A kind of composite material and preparation method with high-precision surface micro-structure
CN108072389B (en) * 2017-11-30 2019-09-03 西安交通大学 A kind of wearable health monitoring sensor manufacturing process of bionical attaching type
CN111113742A (en) * 2019-12-27 2020-05-08 同济大学 Forming method of composite material part

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