CN114083843B - Composite material with layer structure design and application thereof - Google Patents

Composite material with layer structure design and application thereof Download PDF

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Publication number
CN114083843B
CN114083843B CN202111401683.8A CN202111401683A CN114083843B CN 114083843 B CN114083843 B CN 114083843B CN 202111401683 A CN202111401683 A CN 202111401683A CN 114083843 B CN114083843 B CN 114083843B
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Prior art keywords
composite material
area
shaped anti
shaped
cracking area
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CN114083843A (en
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井文奇
杜逸飞
张涛
田智立
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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
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/04—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by at least one layer folded at the edge, e.g. over another layer ; characterised by at least one layer enveloping or enclosing a material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B32B2260/023—Two or more layers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/558—Impact strength, toughness
    • 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

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  • Laminated Bodies (AREA)

Abstract

The invention relates to the technical field of aerospace materials, in particular to a composite material with a layer structure design and an application thereof, wherein the structure of the composite material comprises a main bearing area, a U-shaped anti-cracking area and a clip-shaped anti-cracking area, the U-shaped anti-cracking area is used as a secondary outer layer of the composite material and wrapped in a U-shaped structure to be used as the main bearing area in the middle of the composite material, the clip-shaped anti-cracking area is used as an outer layer of the composite material and wrapped in a clip-shaped structure to be used as the U-shaped anti-cracking area, and the main bearing area, the U-shaped anti-cracking area and the clip-cracking area are all prepared from fiber reinforced materials; compared with the traditional design structure with 0 degree between each layer, the composite material with the ply structure design provided by the invention has the advantages that the ultrahigh-speed-fixed impact resistance is improved by 1.5 times, can bear 15000g acceleration overload for 10ms without damage, and has extremely high strength.

Description

Composite material with layering structure design and application thereof
Technical Field
The invention relates to the technical aerospace material field, in particular to a composite material with a layer structure design and application thereof.
Background
The carbon fiber composite material has the characteristics of high specific strength, high specific stiffness, excellent corrosion resistance, good designability and the like, is an important way for realizing the light weight of the equipment structure, and is widely applied to a novel aerospace weapon equipment structure system. But the external shock resistance of the carbon fiber composite material is weak, so that the application of the material in the field of super-high-speed shock resistant materials is limited. At present, few theoretical and experimental researches for improving the ultrahigh-speed impact resistance of the composite material from the aspect of layer design exist.
CN110962364B discloses a bionic composite material spiral laying design method. The method is based on the structures and the function revelation of the anti-impact fiber of the mantis shrimps, and stacking the symmetrical spiral laminated plates according to the stacking through the linearly increasing stacking angle theta i. The layering design method can effectively weaken the inherent anisotropy of the fiber reinforced layered composite material on one hand, and on the other hand, improves the interlayer performance of the layered composite material through the mutual coupling and synergistic effect of different fiber orientations. The theoretical analysis result shows that: the bionic spiral layering design method provided by the method can effectively improve the interlaminar shear strength of the layered composite material. However, the planes of each layer of fibers in the method are parallel to each other, and the interlayer performance cannot be greatly improved.
CN112699584A discloses a laying arrangement method for a composite material thick laminated board. The method comprises the following steps: estimating the number of layers required for the composite material thick laminated board adopting the new material to reach the total thickness according to the total thickness of the composite material thick laminated board adopting the old material; according to a preset laying design principle and the estimated laying number, adopting a new material to carry out laying to obtain a laying scheme of the new composite material thick laminated board; and (3) reducing the number of layers in the layering scheme and/or finely adjusting parameters of layering according to a preset layering design principle, so that the main direction elastic modulus and the in-plane shear modulus of the layering scheme subjected to layer reduction and/or fine adjustment are close to those of a composite thick-layer laminated plate made of an old material. The layering structure of the method is a traditional layering structure, and layers are parallel.
Therefore, in response to the above deficiencies, it would be desirable to provide a carbon fiber composite material with a ply design.
Disclosure of Invention
The invention aims to solve the technical problems that the out-of-plane impact resistance of the currently designed carbon fiber composite material is weak, and the structural performance cannot meet the requirement of higher strength, and provides a composite material designed by a layer structure and application thereof aiming at the defects in the prior art.
In order to solve the technical problems, in a first aspect, the invention provides a composite material with a layer structure design, wherein the structure of the composite material comprises a main bearing area, a U-shaped anti-cracking area and a clip-shaped anti-cracking area, the U-shaped anti-cracking area is used as a secondary outer layer of the composite material and wraps the main bearing area as the middle part of the composite material in a U-shaped structure, the clip-shaped anti-cracking area is used as an outer layer of the composite material and wraps the U-shaped anti-cracking area in a clip-shaped structure, and the main bearing area, the U-shaped anti-cracking area and the clip-cracking area are all prepared from fiber reinforced materials.
The composite material designed by the ply structure forms an inner layer structure, a middle layer structure and an outer layer structure through 3 structures, the main bearing area is wrapped by the secondary outer layer unidirectional tape to form an end part capable of bearing ultra-high speed impact, and the impact resistance strength is further improved through the square-shaped laying of the unidirectional tape. The main reasons are: by utilizing the high strength and high modulus of the fiber, two layers of protection of circumferential constraint (U-shaped region) and impact end constraint (U-shaped region) are provided for the main bearing region, and the occurrence of tip cracks (U-shaped region action) and crack propagation (U-shaped region action) of the main bearing region under the impact action (the main damage form of the tip splitting composite material under the impact) are prevented. The U-shaped area and the clip-shaped area complement each other.
In the invention, the fibers in the three regions are orthogonally arranged in three dimensions, and the interlaminar performance of the part can be greatly and integrally improved by utilizing the high strength and high modulus of the fibers.
Compared with the traditional design structure with 0 degree between each layer, the traditional paving layer can bear 10000g of acceleration overload for 10ms at most without damage, and the ultrahigh-speed-resistant solid impact resistance of the invention is improved by 1.5 times, can bear 15000g of acceleration overload for 10ms without damage, and has extremely high strength.
Preferably, the main bearing area is formed by laying and stacking 9 layers of fiber reinforced materials.
Preferably, the U-shaped anti-cracking zone is composed of 2 to 4 (for example, 2, 3 or 4) layers of fiber reinforced material with a U-shaped structure stacked on top of each other.
Preferably, the clip-shaped anti-cracking zone consists of 2 to 4 (for example, 2, 3 or 4 layers) stacked fiber reinforced materials having a clip-shaped structure.
Preferably, the fiber reinforced material is prepared from a prepreg consisting of a matrix and fibers; the matrix is thermosetting resin or thermoplastic resin, and the fiber is glass fiber or carbon fiber.
In the present invention, the fiber reinforced material, specifically the preparation process, can be prepared by a material synthesis method which is conventional in the art.
Preferably, the thermosetting resin comprises any one of epoxy resin, bismaleimide or vinyl ester. In the present invention, the thermosetting resin is not limited to the above-mentioned examples, and may be any other thermosetting resin capable of producing a fiber-reinforced material.
Preferably, the thermoplastic resin comprises polyethylene and/or polyetheretherketone.
Preferably, the prepreg has a fiber volume fraction of 60% to 65%, for example, 60%, 61%, 62%, 63%, 64%, 65%, or the like.
The composite material with the ply structure design provided by the invention can be prepared by the traditional mould pressing process and the autoclave process, and the two processes are known to those skilled in the art.
In a second aspect, the present invention provides the use of a composite material designed according to the lay-up structure of the first aspect in an aerospace material.
The implementation of the invention has the following beneficial effects:
the composite material designed by the ply structure forms 3 layers of structures including an inner layer, a middle layer and an outer layer through 3 structures, the main bearing area is wrapped by the unidirectional belt of the secondary outer layer, the end part capable of bearing ultra-high speed impact is formed, the unidirectional belt is further laid in a zigzag mode, the impact resistance strength is further improved, compared with the traditional design structure with 0 degree between the layers, the ultra-high speed impact resistance is improved by 1.5 times, the composite material can bear 15000g acceleration overload for 10ms without damage, and the composite material has extremely high strength.
Drawings
FIG. 1 is a schematic structural diagram of a composite material for a ply structure design provided in example 1 of the present invention;
fig. 2 is a schematic view of a split structure of a composite material designed by a ply structure provided in embodiment 1 of the present invention, which includes a 1-main bearing area, a 2-U-shaped anti-cracking area, and a 3-return type anti-cracking area.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
Example 1
The embodiment provides a composite material designed by a ply structure, and the concrete structure is as follows, and is shown in reference to fig. 1 and fig. 2:
the composite material structurally comprises a main bearing area 1, a U-shaped anti-cracking area 2 and a reverse-shaped anti-cracking area 3, wherein the U-shaped anti-cracking area 2 is used as a secondary outer layer of the composite material and wrapped in a U-shaped structure to be used as the main bearing area 1 in the middle of the composite material, the reverse-shaped anti-cracking area 3 is used as an outer layer of the composite material and wrapped in the U-shaped anti-cracking area 2 in a reverse-shaped structure, the main bearing area 1, the U-shaped anti-cracking area 2 and the reverse-shaped anti-cracking area 3 are all made of fiber reinforced materials, the main bearing area 1 is formed by laying and stacking 9 layers of fiber reinforced materials, the U-shaped anti-cracking area 2 is formed by stacking 3 layers of fiber reinforced materials with U-shaped structures, and the reverse-shaped anti-cracking area 3 is formed by stacking 2 layers of fiber reinforced materials with reverse-shaped structures.
Example 2
The embodiment provides a composite material of a layer structure design, and the concrete structure is as follows:
the composite material structurally comprises a main bearing area, a U-shaped anti-cracking area and a U-shaped anti-cracking area, wherein the U-shaped anti-cracking area is used as a secondary outer layer of the composite material and wrapped by a U-shaped structure to be used as a main bearing area in the middle of the composite material, the U-shaped anti-cracking area is used as an outer layer of the composite material and wrapped by a U-shaped structure to be used as a U-shaped anti-cracking area, the main bearing area, the U-shaped anti-cracking area and the U-shaped anti-cracking area are all made of fiber reinforced materials, the main bearing area is formed by laying and stacking 9 layers of fiber reinforced materials, the U-shaped anti-cracking area is formed by stacking 2 layers of fiber reinforced materials with U-shaped structures, and the U-shaped anti-cracking area is formed by stacking 3 layers of fiber reinforced materials with U-shaped structures.
Example 3
The embodiment provides a composite material of a layer structure design, and the concrete structure is as follows:
the composite material structurally comprises a main bearing area, a U-shaped anti-cracking area and a U-shaped anti-cracking area, wherein the U-shaped anti-cracking area is used as a secondary outer layer of the composite material and wrapped in a U-shaped structure to be used as a main bearing area in the middle of the composite material, the U-shaped anti-cracking area is used as an outer layer of the composite material and wrapped in a U-shaped structure to be used as a U-shaped anti-cracking area, the main bearing area, the U-shaped anti-cracking area and the U-shaped anti-cracking area are all made of fiber reinforced materials, the main bearing area is formed by laying and stacking 9 layers of fiber reinforced materials, the U-shaped anti-cracking area is formed by stacking 4 layers of fiber reinforced materials with U-shaped structures, and the U-shaped anti-cracking area is formed by stacking 4 layers of fiber reinforced materials with U-shaped structures.
Example 4
The embodiment provides a composite material of a layer structure design, and the concrete structure is as follows:
the composite material structurally comprises a main bearing area, a U-shaped anti-cracking area and a U-shaped anti-cracking area, wherein the U-shaped anti-cracking area is used as a secondary outer layer of the composite material and wrapped in a U-shaped structure to be used as a main bearing area in the middle of the composite material, the U-shaped anti-cracking area is used as an outer layer of the composite material and wrapped in a U-shaped structure to be used as a U-shaped anti-cracking area, the main bearing area, the U-shaped anti-cracking area and the U-shaped anti-cracking area are all made of fiber reinforced materials, the main bearing area is formed by laying and stacking 9 layers of fiber reinforced materials, the U-shaped anti-cracking area is formed by stacking 3 layers of fiber reinforced materials with U-shaped structures, and the U-shaped anti-cracking area is formed by stacking 3 layers of fiber reinforced materials with U-shaped structures.
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 (6)

1. A composite material with a layered structure design is characterized in that: the structure of the composite material comprises a main bearing area, a U-shaped anti-cracking area and a U-shaped anti-cracking area, wherein the U-shaped anti-cracking area is used as a secondary outer layer of the composite material and wrapped in a U-shaped structure to be used as a main bearing area in the middle of the composite material, the U-shaped anti-cracking area is used as an outer layer of the composite material and wrapped in a U-shaped structure to be used as a U-shaped anti-cracking area, and the main bearing area, the U-shaped anti-cracking area and the U-shaped anti-cracking area are all prepared from fiber reinforced materials; the main bearing area is formed by laying and stacking 9 layers of fiber reinforced materials; the U-shaped anti-cracking area is formed by stacking 2-4 layers of fiber reinforced materials with U-shaped structures; the clip-shaped anti-cracking area is formed by stacking 2-4 layers of fiber reinforced materials with clip-shaped structures; the fibers of the three regions are arranged orthogonally in three dimensions.
2. The composite material of claim 1, wherein: the fiber reinforced material is prepared from a prepreg consisting of a matrix and fibers; the matrix is thermosetting resin or thermoplastic resin, and the fiber is glass fiber or carbon fiber.
3. The composite material of claim 2, wherein: the thermosetting resin comprises any one of epoxy resin, bismaleimide or vinyl ester.
4. The composite material of claim 2, wherein: the thermoplastic resin comprises polyethylene and/or polyetheretherketone.
5. The composite material of claim 2, wherein: the fiber volume fraction of the prepreg is 60-65%.
6. Use of a composite material designed according to the ply structure of any one of claims 1 to 5 in an aerospace material.
CN202111401683.8A 2021-11-19 2021-11-19 Composite material with layer structure design and application thereof Active CN114083843B (en)

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CN106218146A (en) * 2016-07-26 2016-12-14 东华大学 Composite that a kind of case and bag flexible material is toughness reinforcing and preparation thereof and application
CN109228547B (en) * 2018-10-24 2021-04-16 株洲时代新材料科技股份有限公司 Fiber layering structure of reinforced material and pultrusion profile
CN109648943B (en) * 2018-12-28 2020-06-19 吉林大学 Bionic composite material and preparation method thereof
CN109849368B (en) * 2019-03-20 2021-09-21 成都联科航空技术有限公司 Method for processing composite material belt taper section variable-thickness revolving body connecting structure
CN110524960B (en) * 2019-08-07 2021-10-01 东华大学 Asymmetric high-buffering flexible functional auxetic composite material and preparation method thereof
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CN111893812A (en) * 2020-08-28 2020-11-06 南京工业大学 Multi-axial fiber-reinforced pultruded profile sandwich composite spandrel girder and preparation method thereof
CN212375639U (en) * 2020-08-28 2021-01-19 南京工业大学 Multi-axial fiber-reinforced pultruded profile sandwich composite spandrel girder
CN113334793B (en) * 2021-05-18 2022-06-17 山东非金属材料研究所 Method for improving interlayer strength of fiber reinforced thermosetting resin-based unidirectional composite material

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