CN112810258B - Fiber spiral laying bionic impact-resistant composite material and preparation method thereof - Google Patents
Fiber spiral laying bionic impact-resistant composite material and preparation method thereof Download PDFInfo
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- CN112810258B CN112810258B CN202110052983.3A CN202110052983A CN112810258B CN 112810258 B CN112810258 B CN 112810258B CN 202110052983 A CN202110052983 A CN 202110052983A CN 112810258 B CN112810258 B CN 112810258B
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- 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
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- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/08—Impregnating
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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
- B32B5/12—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 characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
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- 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
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- 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
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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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
- B32B2262/0261—Polyamide fibres
- B32B2262/0269—Aromatic polyamide fibres
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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
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
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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
- 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
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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
- 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
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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
- 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
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Abstract
The invention provides a bionic impact-resistant composite material with spirally laid fibers and a preparation method thereof, wherein the bionic impact-resistant composite material comprises the following steps: the fiber paving layer groups are arranged in a periodic spiral mode along the paving layer direction, periodically-changed spiral turning angles are formed between adjacent fiber paving layer groups, and the fiber layers in the same fiber paving layer group have preset angle differences. According to the composite material, due to the difference of the layering angles between the adjacent fiber layering sets and the fiber layers in the same fiber layering set, when the composite material is subjected to external impact load, the fiber layering sets rotate, and the fiber slippage, the fiber bridging and the fiber stretching in the same fiber layering set absorb impact energy, so that cracks are effectively prevented from expanding among the fiber layers, meanwhile, the periodically changed spiral turning angle of the fiber layering sets meets the symmetry criterion in the fiber layering design, and the problems of single layering angle and insufficient interlayer impact resistance toughness of the traditional fiber composite material are effectively solved.
Description
Technical Field
The invention belongs to the technical field of composite materials, and particularly relates to a fiber spiral laying bionic impact-resistant composite material and a preparation method thereof.
Background
The fiber reinforced composite material has the advantages of high specific strength, large specific modulus, strong designability of material performance, good corrosion resistance and durability and the like, can meet the requirements of modern structures on large span, high rise, heavy load, light weight, high strength and work development under severe conditions, and can also meet the requirements of industrial development of modern building construction, so the fiber reinforced composite material is more and more widely applied to the fields of aerospace, rail transit, bridges, highways, oceans, hydraulic structures, underground structures and the like.
The traditional fiber reinforced composite material has a single ply angle, crack damage is easy to transfer among layers, so that the interlayer impact toughness of the fiber reinforced composite material is obviously insufficient, and a series of impact damage such as interlayer stripping, fiber fracture, fiber resin debonding and the like easily occurs when the fiber reinforced composite material is subjected to impact load.
Therefore, the prior art is subject to further improvement.
Disclosure of Invention
In view of the defects in the prior art, the invention aims to provide a bionic impact-resistant composite material with spirally laid fibers and a preparation method thereof, and solves the problems that the traditional fiber reinforced composite material has a single laying angle and is easy to suffer impact damage such as interlayer peeling, fiber fracture, fiber resin debonding and the like when subjected to impact load.
The technical scheme adopted by the invention for solving the technical problem is as follows:
a bionic impact-resistant composite material with spirally laid fibers comprises: the fiber layer paving groups are arranged in a periodic spiral mode along the paving direction, periodically-changed spiral turning angles are formed between every two adjacent fiber layer paving groups, and preset angle differences exist among the fiber layers in the same fiber layer paving group.
The bionic impact-resistant composite material with the spirally laid fiber layers is characterized in that the fiber layers with the same sequence in each fiber layer laying set are periodically and spirally laid along the laying direction.
The bionic impact-resistant composite material with the spirally laid fibers is characterized in that the spiral period and the spiral rotation angle corresponding to the fiber layers with the same sequence in each fiber laying layer group are the same as those of the spiral periods and the spiral rotation angles corresponding to the fiber laying layer groups.
The bionic impact-resistant composite material with the spirally laid fibers is characterized in that the spiral period corresponding to a plurality of fiber laying groups is integral multiple of 180 degrees, and the period number corresponding to a plurality of fiber laying groups is greater than or equal to 1.
The bionic impact-resistant composite material with the spirally laid fiber layers is characterized in that the spiral rotation angle corresponding to a plurality of the fiber layer laying groups is 0-90 degrees.
The bionic impact-resistant composite material with the spirally laid fibers is characterized in that the difference of the preset angles is 0-90 degrees, and the number of the fiber layers in each fiber group is a non-zero natural number.
The bionic impact-resistant composite material with the spirally laid fibers is characterized in that the fibers in the fiber layer are one or more of carbon fibers, glass fibers, basalt fibers and aramid fibers.
The preparation method of the bionic impact-resistant composite material with the spirally laid fibers comprises the following steps:
cutting a plurality of single-layer fiber cloths with different fiber angles, and infiltrating the single-layer fiber cloths with resin;
sequentially paving a plurality of single-layer fiber cloths soaked by resin according to preset angle differences in a manual paving mode to obtain a plurality of fiber paving layer groups;
sequentially paving a plurality of fiber layer paving groups in a manual paving mode according to a preset spiral rotation angle and a preset spiral period, and putting the paved fiber layer paving groups into a mold cavity;
and carrying out hot press molding on a plurality of fiber laying layer groups which are periodically spirally laid in the cavity of the mold at a preset temperature, a preset pressure and a preset time to obtain the fiber spirally laid bionic impact-resistant composite material.
The preparation method of the bionic impact-resistant composite material with the spirally laid fibers is characterized in that the resin is thermosetting resin or thermoplastic resin.
The preparation method of the bionic impact-resistant composite material with the spirally laid fibers is characterized in that the preset temperature, the preset pressure, the preset time and the type of the curing agent used in the hot press molding are determined according to the fiber type of the single-layer fiber cloth and the resin type.
The composite material has the advantages that due to the difference of the layering angles between the adjacent fiber layering groups and the fiber layers in the same fiber layering group, when the composite material is subjected to external impact load, the fiber layering group rotates, the fiber in the same fiber layering group slides, the fiber bridges and the fibers stretch to absorb impact energy, cracks are effectively prevented from expanding between the fiber layers, meanwhile, the periodically changed spiral turning angle of the fiber layering group meets the symmetry criterion in fiber layering design, the scientificity and rationality of design are ensured, and the problems that the traditional fiber composite material is single in layering angle and insufficient in interlaminar impact toughness are effectively solved.
Drawings
FIG. 1 is a schematic structural diagram of a fiber spiral-laid bionic impact-resistant composite material provided by an embodiment of the invention in a single-period fiber triple-spiral laying structure;
FIG. 2 is a front view of the bionic impact-resistant composite material with spirally laid fibers in FIG. 1;
FIG. 3 is a top view of the spirally laid biomimetic impact-resistant composite of FIG. 1;
FIG. 4 is a schematic structural diagram of a fiber lay-up group of the bionic impact-resistant composite material with the fibers laid spirally in FIG. 1;
FIG. 5 is a front view of the fiber layup set of FIG. 4;
FIG. 6 is a top plan view of the fiber layup set of FIG. 4;
FIG. 7 is a schematic structural diagram of a fiber spiral-laid bionic impact-resistant composite material in a single-period fiber double-spiral-laid structure according to an embodiment of the present invention;
FIG. 8 is a front view of the spirally laid biomimetic impact-resistant composite of FIG. 7;
FIG. 9 is a top view of the spirally laid biomimetic impact resistant composite of FIG. 7;
FIG. 10 is a schematic structural diagram of a fiber lay-up set of the biomimetic impact-resistant composite material with the fibers laid in a spiral manner in FIG. 7;
FIG. 11 is a front view of the fiber layup set of FIG. 10;
FIG. 12 is a top plan view of the fiber layup set of FIG. 10;
FIG. 13 is a schematic view of a single helix structure formed by fiber layers having the same sequence in a fiber lay-up;
FIG. 14 is a front view of a single helix construction made up of fiber layers having the same sequence in a fiber lay-up;
fig. 15 is a top view of a single helix of fiber layers having the same order in a fiber lay-up.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer and clearer, the present invention is further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The traditional fiber composite material has a single ply angle, crack damage is easy to transfer among layers, so that the interlayer impact toughness of the fiber reinforced composite material is insufficient, and a series of impact damage such as interlayer stripping, fiber fracture, fiber resin debonding and the like are easy to occur when the fiber reinforced composite material is subjected to impact load. The energy-absorbing and impact-resisting performance of the traditional fiber reinforced composite material part laying structure enters a bottleneck period, and a novel laying structure scheme is urgently needed to be searched for improving the energy-absorbing and impact-resisting performance.
The acantholeph is a deep-sea fish, which has been in 3.5 hundred million years old today, and is covered with a thick layer of fish scale armor to withstand the great pressure of deep sea and to resist predation by predators. The inventor researches and discovers that the echinocandis cava has excellent impact resistance, and the echinocandis cava is beneficial to the double-spiral sheet-shaped fiber structure in the scale, the sheet-shaped structures are spirally arranged at a certain angle, so that when the echinocandis cava is subjected to external impact load, the fiber layer rotates, the fibers in the same fiber layer slide, the fibers are bridged, and the fibers stretch to absorb impact energy, thereby effectively preventing cracks from expanding between layers. The mode of enhancing the impact toughness of the fiber through the fiber spiral laying provides a good idea for realizing the laying design of the fiber composite material and improving the impact toughness.
The invention is inspired by a double-spiral sheet-shaped fiber structure in the natural acanthopoda scales, and aims to solve the problems that the traditional fiber reinforced composite material has a single layer laying angle and is easy to generate impact damages such as interlayer stripping, fiber fracture, fiber resin debonding and the like when being subjected to impact load, the invention provides a fiber spiral laying bionic impact-resistant composite material, as shown in figures 1-12, the composite material comprises: the fiber layer paving groups are arranged in a periodic spiral mode along the paving direction, periodically-changed spiral turning angles are formed between every two adjacent fiber layer paving groups, and the fiber layers in the same fiber layer paving group have preset angle differences. According to the composite material in the embodiment, due to the difference of the layer spreading angles between the adjacent fiber layer spreading groups and the fiber layers in the same fiber layer spreading group, when the composite material is subjected to external impact load, the fiber layer spreading group rotates, fiber slippage, fiber bridging and fiber stretching in the same fiber layer spreading group absorb impact energy, cracks are effectively prevented from expanding between the fiber layers, meanwhile, the periodically changed spiral turning angle of the fiber layer spreading group meets the symmetry criterion in fiber layer spreading design, and the scientificity and rationality of the design are guaranteed. The invention effectively solves the problems of single layer laying angle and insufficient interlayer impact resistance toughness of the traditional fiber composite material by bionic design and optimization of the fiber laying direction, namely a multi-spiral laying structure.
In a specific embodiment, the period of the helix corresponding to a plurality of the fiber lay groups is an integral multiple of 180 °, for example, 180 °, 360 °, 540 °, and the like; the number of cycles for a number of the fiber layup groups is greater than or equal to 1. For example, when the number of cycles corresponding to a plurality of fiber laying layer groups is 1, the composite material is in a single-cycle fiber spiral laying structure; when the number of cycles corresponding to the fiber laying layer groups is 2, the composite material is in a double-cycle fiber spiral laying structure; when the number of cycles corresponding to the fiber laying layer groups is 3, the composite material is of a three-cycle fiber spiral laying structure; and by analogy, when the number of cycles corresponding to the fiber laying layer groups is n, the composite material is in an n-cycle fiber spiral laying structure.
In a specific embodiment, the number of the fiber layers in each fiber group is a non-zero natural number, that is, the number of the fiber layers in each fiber group may be 1, 2, 3, or n, and when the number of cycles corresponding to a plurality of fiber layer groups is 1 and the number of the fiber layers in each fiber group is 1, the composite material is in a single-cycle fiber single-spiral arrangement structure; when the number of cycles corresponding to the plurality of fiber laying layer groups is 1 and the number of fiber layers in each fiber group is 2, that is, each fiber group consists of a fiber layer 1 and a fiber layer 2, the structure of the composite material is a single-cycle fiber double-helix laying structure as shown in fig. 7; when the number of cycles corresponding to the plurality of fiber layer paving groups is 1 and the number of fiber layers in each fiber group is 3, that is, each fiber group is composed of a fiber layer 1, a fiber layer 2 and a fiber layer 3, the structural schematic diagram of the composite material is shown in fig. 1 and is a single-cycle fiber three-spiral paving structure.
Specifically, the helix angle corresponding to a plurality of the fiber ply groups refers to the helix angle between adjacent fiber ply groups, for example, taking the single-period fiber three-helix arrangement structure and the single-period fiber double-helix arrangement structure shown in fig. 1 and 7 as examples, the helix period corresponding to a plurality of the fiber ply groups is 180 °, nine fiber ply groups are included in one helix period, and the helix angle between adjacent fiber ply groups, that is, the helix angle corresponding to a plurality of the fiber ply groups is 22.5 °. The ply thickness of the composite material is determined by the corresponding helical rotation angle and helical period of the fiber ply group, for example, still taking fig. 1 and 7 as an example, when the helical period is 180 ° and the helical angle is 22.5 °, the ply thickness of the composite material is 9 times the thickness of a single fiber ply group; when the helix period is 180 ° and the helix angle is 36 °, the ply thickness of the composite material is 6 times the thickness of the individual fibre ply groups. In order to improve the impact resistance of the composite material, in a specific embodiment, the spiral rotation angle corresponding to a plurality of fiber laying layer groups is 0-90 degrees.
Specifically, the preset angle difference between the fiber layers in the same fiber laying group refers to an angle difference between the fiber layers constituting the fiber laying group. For example, for the single-period fiber triple-helix laid structure in fig. 1 to 6, each fiber layer group is composed of a fiber layer 1, a fiber layer 2, and a fiber layer 3, and the preset angle difference among the fiber layers in the same fiber layer group is the angle difference among the fiber layers 1, 2, and 3 in the same fiber layer group; for the single-period fiber double-helix laying structure in fig. 7 to 12, each fiber laying group is composed of a fiber layer 1 and a fiber layer 2, and the preset angle difference between the fiber layers in the same fiber laying group is the angle difference between the fiber layer 1 and the fiber layer 2 in the same fiber laying group.
In a specific embodiment, in order to improve the impact resistance of the composite material, the preset angle difference between the fiber layers in the same fiber layer group is 0 to 90 degrees, as shown in fig. 1, the angle difference between the fiber layer 1 and the fiber layer 2 and the angle difference between the fiber layer 2 and the fiber layer 3 in the same fiber layer group are 45 degrees, and the angle difference between the fiber layer 1 and the fiber layer 3 is 90 degrees; as shown in fig. 7, the angle difference between the fiber layer 1 and the fiber layer 2 in the same fiber lay-up group is 90 °.
In a specific embodiment, the fiber layers in each of the fiber layer groups having the same sequence are periodically spirally arranged along the layer direction, and the fiber layers in each of the fiber layer groups having the same sequence refer to the fiber layers in each of the fiber layer groups at the same layer, for example, in the single-period fiber triple-spiral arrangement structure in fig. 1, each of the fiber layer groups is composed of a fiber layer 1, a fiber layer 2 and a fiber layer 3, so that the fiber layer 1 in each of the fiber layer groups is the fiber layer having the same sequence, the fiber layer 2 in each of the fiber layer groups is the fiber layer having the same sequence, and the fiber layer 3 in each of the fiber layer groups is the fiber layer having the same sequence. In the composite material in this embodiment, not only the plurality of fiber layer sets are periodically and spirally arranged along the layering direction, but also the fiber layers having the same sequence in each fiber layer set are periodically and spirally arranged along the layering direction, and the spiral period and the spiral rotation angle corresponding to the fiber layers having the same sequence in each fiber layer set are the same as the spiral period and the spiral rotation angle corresponding to the plurality of fiber layer sets, that is, the fiber layers having the same sequence in each fiber layer set can be regarded as a single spiral structure in which the spiral period and the spiral rotation angle are the same as those of the whole fiber layer set of the composite material. For example, as shown in fig. 13 to 15, regarding the schematic diagram of the single-helix structure composed of the fiber layers having the same sequence in the fiber lay-up groups of the composite material of fig. 1 and 7, the helix period corresponding to a plurality of the fiber lay-up groups is 180 °, the helix angle is 22.5 °, the fiber layers 1, 2, and 3 in each of the fiber lay-up groups are also periodically and helically laid in the lay-up direction, and the helix period corresponding to the fiber layers 1, 2, and 3 in each of the fiber lay-up groups is 180 °, and the helix angle is 22.5 °.
In a specific embodiment, the fibers in the fiber layer are one or more of carbon fibers, glass fibers, basalt fibers and aramid fibers. The fiber layer is fiber cloth soaked with resin, and the fiber cloth are well combined together through physical and chemical actions by impregnating the resin, so that the mechanical property of the composite material is improved.
The embodiment of the invention also provides a preparation method of the bionic impact-resistant composite material with the spirally laid fibers, wherein the preparation method comprises the following steps:
s100, cutting a plurality of single-layer fiber cloths with different fiber angles, and infiltrating the single-layer fiber cloths with resin;
s200, sequentially paving a plurality of single-layer fiber cloths soaked by resin according to preset angle differences in a manual paving mode to obtain a plurality of fiber paving layer groups;
s300, sequentially paving a plurality of fiber paving layer groups in a manual paving mode according to a preset spiral rotation angle and a preset spiral period, and putting the paved plurality of fiber paving layer groups into a mold cavity;
s400, carrying out hot press molding on a plurality of fiber laying layer groups which are periodically spirally laid in the cavity of the mold at a preset temperature, a preset pressure and a preset time to obtain the fiber spirally laid bionic impact-resistant composite material.
In a specific embodiment, in order to prepare the above fiber spiral-laid bionic impact-resistant composite material, in this embodiment, a fiber cloth cutting machine or a manual cutting machine is used to cut a plurality of single-layer fiber cloths with different fiber angles, and the single-layer fiber cloths are soaked in resin, so that the fiber cloths and the fiber cloths are well combined together through physical and chemical actions by impregnating the resin, thereby improving the mechanical properties of the bionic composite material; then, sequentially paving a plurality of single-layer fiber cloths soaked by resin according to preset angle differences in a manual paving mode to obtain a plurality of fiber paving layer groups; sequentially paving a plurality of fiber layer paving groups in a manual paving mode according to a preset spiral rotation angle and a preset spiral period, and putting the paved fiber layer paving groups into a mold cavity; and finally, carrying out hot press molding on a plurality of fiber laying layer groups which are periodically spirally laid in the cavity of the mold at a preset temperature, a preset pressure and a preset time to obtain the fiber spirally laid bionic impact-resistant composite material.
In a specific embodiment, the resin for infiltrating the single-layer fiber cloths is commercial thermoplastic resin such as epoxy resin or thermosetting resin. The preset temperature, the preset pressure, the preset time and the type of the curing agent used in the hot press molding are determined according to the fiber type of the single-layer fiber cloth and the resin type.
In summary, the invention provides a bionic impact-resistant composite material with spirally laid fibers and a preparation method thereof, and the preparation method comprises the following steps: the fiber layer paving groups are arranged in a periodic spiral mode along the paving direction, periodically-changed spiral turning angles are formed between every two adjacent fiber layer paving groups, and the fiber layers in the same fiber layer paving group have preset angle differences. According to the composite material, due to the difference of the layering angles between the adjacent fiber layering sets and the fiber layers in the same fiber layering set, when the composite material is subjected to external impact load, the fiber layering sets rotate, and the fiber in the same fiber layering set slides, bridges and stretches to absorb impact energy, so that cracks are effectively prevented from expanding between the fiber layers, meanwhile, the periodically-changed spiral turning angle of the fiber layering sets meets the symmetry criterion in fiber layering design, the scientificity and rationality of design are guaranteed, and the problems that the traditional fiber composite material is single in layering angle and insufficient in interlaminar impact toughness are effectively solved.
It is to be understood that the system of the present invention is not limited to the above examples, and that modifications and variations may be made by one of ordinary skill in the art in light of the above teachings, and all such modifications and variations are intended to fall within the scope of the appended claims.
Claims (3)
1. A method for preparing a bionic impact-resistant composite material with spirally laid fibers, wherein the composite material comprises the following components:
the fiber layer paving groups are arranged in a periodic spiral mode along the paving direction, periodically-changed spiral turning angles are formed between every two adjacent fiber layer paving groups, and preset angle differences exist among the fiber layers in the same fiber layer paving group;
the fiber layers with the same sequence in each fiber laying layer group are periodically and spirally laid along the laying direction;
the spiral period and the spiral rotation angle corresponding to the fiber layers with the same sequence in each fiber laying group are the same as those corresponding to a plurality of fiber laying groups;
the spiral period corresponding to the fiber laying groups is integral multiple of 180 degrees, and the period number corresponding to the fiber laying groups is more than or equal to 1; the spiral rotation angle corresponding to the fiber laying layer groups is 0-90 degrees;
the preset angle difference is 0-90 degrees, and the number of the fiber layers in each fiber laying layer group is a non-zero natural number;
the fibers in the fiber layer are one or more of carbon fibers, glass fibers, basalt fibers and aramid fibers;
the preparation method comprises the following steps:
cutting a plurality of single-layer fiber cloths with different fiber angles, and infiltrating the single-layer fiber cloths with resin;
sequentially paving a plurality of single-layer fiber cloths soaked by resin according to preset angle differences in a manual paving mode to obtain a plurality of fiber paving layer groups;
sequentially paving a plurality of fiber layer paving groups in a manual paving mode according to a preset spiral rotation angle and a preset spiral period, and putting the paved fiber layer paving groups into a mold cavity;
and carrying out hot press molding on a plurality of fiber laying layer groups which are periodically spirally laid in the cavity of the mold at a preset temperature, a preset pressure and a preset time to obtain the fiber spirally laid bionic impact-resistant composite material.
2. The method for preparing the bionic impact-resistant composite material with the spirally laid fibers as claimed in claim 1, wherein the resin is thermosetting resin or thermoplastic resin.
3. The method for preparing the bionic impact-resistant composite material with the spirally laid fibers as claimed in claim 1, wherein the preset temperature, the preset pressure, the preset time and the type of the curing agent used in the hot press molding are determined according to the fiber type and the resin type of the single-layer fiber cloth.
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| CN114228283A (en) * | 2021-12-02 | 2022-03-25 | 南京航空航天大学 | Multi-level flexible protection structure imitating Chinese sturgeon back bone scales and fish skin |
| CN114274609B (en) * | 2022-01-09 | 2023-11-21 | 吉林大学 | Fiber reinforced composite material component based on combined bionic and multi-point die forming method thereof |
| CN115230247B (en) * | 2022-08-17 | 2023-12-05 | 沈阳工业大学 | Multi-region high-strength-toughness bionic impact-resistant composite structure |
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| JP6152887B2 (en) * | 2015-12-10 | 2017-06-28 | 横浜ゴム株式会社 | High pressure hose |
| CN106738999A (en) * | 2016-12-09 | 2017-05-31 | 江苏理工学院 | A kind of polyaxial carbon fibre composite car battery box and its manufacture method |
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