CN112265337A - Amorphous fiber-based composite material for structural health monitoring and method and application thereof - Google Patents

Amorphous fiber-based composite material for structural health monitoring and method and application thereof Download PDF

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CN112265337A
CN112265337A CN202010922348.1A CN202010922348A CN112265337A CN 112265337 A CN112265337 A CN 112265337A CN 202010922348 A CN202010922348 A CN 202010922348A CN 112265337 A CN112265337 A CN 112265337A
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fiber
amorphous alloy
amorphous
composite material
prepreg
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冯唐锋
赵雄涛
张宇鹏
秦发祥
王欢
董家乐
彭华新
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Zhejiang University ZJU
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Zhejiang University ZJU
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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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/02—Layer formed of wires, e.g. mesh
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to 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
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • 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
    • 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
    • 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
    • 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
    • B32B37/1009—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 using vacuum and fluid pressure
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • 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
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
    • G01N27/72—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables
    • G01N27/82—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws
    • 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
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B2038/0052—Other operations not otherwise provided for
    • B32B2038/0076—Curing, vulcanising, cross-linking
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/20—All layers 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
    • 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
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/212—Electromagnetic interference shielding
    • 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
    • B32B2307/70—Other properties
    • B32B2307/718—Weight, e.g. weight per square meter

Abstract

The invention discloses an amorphous fiber-based composite material for structural health monitoring and a method and application thereof, wherein the preparation method comprises the following steps: s1: the method comprises the following steps of (1) laying continuous amorphous alloy fibers on the surface of a prepreg to obtain an amorphous alloy fiber array prepreg; s2: stacking a plurality of prepregs and amorphous alloy fiber array prepreg layers to obtain an amorphous fiber matrix composite precursor; the amorphous fiber-based composite material precursor contains at least one layer of amorphous alloy fiber array prepreg; s3: and paving the amorphous fiber-based composite material precursor on a plane mould or a curved mould, sealing, vacuumizing, and curing and forming at the temperature of 110-250 ℃ and under the pressure of 0.1-0.6 MPa to obtain the amorphous fiber-based composite material. The composite material integrates the structure and the function into a whole, and has electromagnetic shielding or wave-transmitting capacity, structural health monitoring and excellent mechanical properties. The composite material is oriented to the field of engineering application, can replace a corresponding metal structure on a target body, and has the characteristics of light weight and multiple functions.

Description

Amorphous fiber-based composite material for structural health monitoring and method and application thereof
Technical Field
The invention belongs to the field of composite material preparation and forming, and relates to an amorphous fiber-based composite material for structural health monitoring, and a method and application thereof.
Background
As a new composite material, the fiber reinforced resin-based composite material has the advantages of light weight and high strength, and is widely concerned and applied in the aerospace and automobile industries. With the increasing demand of fiber reinforced composite materials, the multi-functionalization becomes a new trend of the next iterative development of the composite materials; meanwhile, in the service period of the composite material, the material cost can bear complex and long-time fatigue load, and in addition, the performance of the composite material is possibly degraded or even damaged due to the service environmental temperature and humidity change and severe weather. The method is used for effectively monitoring the structural health of the composite material and is of great importance to the whole service process of the composite material. Therefore, a functional composite material for structural health monitoring with excellent mechanical properties and self-induction needs to be developed.
The amorphous alloy fiber is generally a micron-sized metal fiber mainly composed of Co, Fe and Ni elements, and additionally composed of B, Si and other semimetal elements and other trace elements (usually transition metals such as Cr, Mo and Nb), and is formed by rapid solidification of an amorphous state. The preparation method comprises a Uliotvsky-Taylor method, an internal water spinning method, a rapid quenching method, melt drawing, gas atomization and the like at present, wherein the Uliotvsky-Taylor method is the most widely and commercially applied preparation process at present, the diameter of the amorphous alloy fiber prepared by the technology is 1-80 mu m, the length of the fiber can reach kilometer, and the amorphous alloy fiber has good mechanical properties (tensile strength is 1000 MPa). The amorphous alloy fiber has giant magneto-impedance effect and stress-impedance effect, the electromagnetic performance of the amorphous alloy fiber can be regulated and controlled along with a magnetic field, a force field and a temperature field, and the amorphous alloy fiber has obvious advantages in developing composite materials with structural health monitoring function.
Some amorphous fiber-based functional materials with wave-absorbing or shielding functions have been disclosed in the prior art. For example, patent application No. cn200910238377.x discloses an electromagnetic wave absorbing material containing amorphous wire material and a preparation method thereof, and patent application No. cn201510281776.x discloses an amorphous metal fiber composite magnetic shielding wallpaper and a preparation method thereof. Both of the two publications use amorphous wire materials as functional items, but the obtained material has poor overall mechanical properties and is difficult to apply to the actual engineering field.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides an amorphous fiber-based composite material for structural health monitoring and a method and application thereof. The amorphous fiber-based composite material can provide better electromagnetic shielding or frequency-selecting wave-transmitting function, has stronger mechanical property and can be used as a shielding or wave-transmitting material in the engineering field. In addition, based on the giant magneto-impedance effect and the stress impedance effect of the amorphous alloy fiber, the method can be applied to structural health monitoring of the composite material, and the multifunctional performance of the composite material is realized.
The invention adopts the following specific technical scheme:
a preparation method of an amorphous fiber-based composite material for structural health monitoring comprises the following steps:
s1: the method comprises the following steps of (1) laying continuous amorphous alloy fibers on the surface of a prepreg to obtain an amorphous alloy fiber array prepreg; one surface of the amorphous alloy fiber array prepreg is a prepreg layer, and the other surface is one or more amorphous alloy fiber layers; the amorphous alloy fibers on each amorphous alloy fiber layer are arranged in parallel at equal intervals, and the amorphous alloy fibers are continuously not broken in the length direction;
s2: stacking a plurality of prepregs and amorphous alloy fiber array prepreg layers to obtain an amorphous fiber matrix composite precursor; the amorphous fiber-based composite material precursor contains at least one layer of amorphous alloy fiber array prepreg;
s3: and paving the amorphous fiber-based composite material precursor on a plane mould or a curved mould, sealing, vacuumizing, and curing and forming at the temperature of 110-250 ℃ and under the pressure of 0.1-0.6 MPa to obtain the amorphous fiber-based composite material.
Preferably, the prepreg is glass fiber or carbon fiber.
Preferably, the amorphous alloy fiber is cobalt-based or iron-based, has a diameter of 10-50 μm and a continuous length of 300m or more.
Further, the amorphous alloy fiber is prepared by a Uliotvskiy-Taylor glass coating method, a melt drawing method or an internal spinning method.
Preferably, the included angle alpha between the amorphous alloy fibers on the amorphous alloy fiber layers of different layers is more than or equal to 0 degrees and less than or equal to 90 degrees.
Preferably, the amorphous alloy fibers on each amorphous alloy fiber layer are arranged in parallel at equal intervals of 1-12 mm.
Preferably, the specific process for preparing the amorphous alloy fiber array prepreg in S1 is as follows:
s11: winding and fixing the prepreg on the surface of a winding roller of a fiber winding machine;
s12: enabling the amorphous alloy fiber to pass through a wire nozzle of a glue dipping tank and be fixed on the surface of a prepreg on a winding roller; introducing a fiber surface treating agent into the impregnation tank for treating the amorphous alloy fibers to improve the bonding capacity of the amorphous alloy fibers and the prepreg;
s13: and (3) laying amorphous alloy fibers on the surface of the prepreg by using numerical control equipment to obtain the amorphous alloy fiber array prepreg.
Further, the fiber surface treating agent is an ethanol diluted solution containing 0.5-10 wt% of silane coupling agent or an ethanol diluted solution containing epoxy resin.
The second purpose of the invention is to provide an amorphous fiber-based composite material prepared by any one of the preparation methods.
A third object of the present invention is to provide a use of the amorphous fiber based composite material according to the above for structural health monitoring.
Compared with the prior art, the invention has the following beneficial effects:
1) in the process of preparing the amorphous fiber-based composite material, the semi-automatic fiber laying method of the amorphous alloy fiber is designed and applied, compared with manual fiber laying, the fiber laying efficiency and precision can be greatly improved, and the method has the characteristic of large-scale mass production.
2) The amorphous fiber-based composite material is formed by compounding glass fibers or carbon fiber prepreg and amorphous alloy fiber material, and the obtained composite material has light weight and high strength and has great application value in the field of aerospace; based on the electromagnetic property of the amorphous alloy fiber array, the electromagnetic wave transmission or shielding function of electromagnetic waves can be realized through the array structure design, and the amorphous alloy fiber array has huge application prospects in the civil and military fields.
3) The structural health monitoring of the invention is based on the giant magneto-impedance effect and the stress effect of amorphous alloy fibers, the amorphous alloy fibers are used as composite material embedded sensing components, the structure of the composite material is detected in an electromagnetic sensing mode, and the defects of material internal layering, cracks and the like are detected by utilizing electromagnetic signals.
4) According to the invention, the amorphous alloy fiber array structure is embedded in the traditional structural fiber reinforced resin matrix composite material, so that the multifunctional composite material with excellent mechanical properties and high self-induction capability is prepared. The technical design idea of the invention is to realize the health monitoring of the self-induction structure of the composite material by embedding the amorphous alloy fiber array and utilizing the electromagnetic sensing characteristic of the amorphous alloy array under the condition of not destroying the mechanical property of the original structure and even strengthening the mechanical property of the original structure.
5) The composite material integrates the structure and the function into a whole, and has electromagnetic shielding or wave-transmitting capacity, structural health monitoring and excellent mechanical properties. The composite material is oriented to the field of engineering application, can replace a corresponding metal structure on a target body, and has the characteristics of light weight and multiple functions.
Drawings
Fig. 1 is an SEM image of the Co-based amorphous alloy fiber in example 1;
FIG. 2 is a graph of the reflection parameter (a) and transmission parameter (b) for a composite material of example 1 containing different arrays of amorphous fibers;
FIG. 3 is a graph of microwave reflection parameters for a composite material at different defect locations in example 2;
FIG. 4 is a schematic diagram of the preparation process of the amorphous fiber-based composite material of the present invention.
Detailed Description
The invention will be further elucidated and described with reference to the drawings and the detailed description. The technical features of the embodiments of the present invention can be combined correspondingly without mutual conflict.
As shown in fig. 4, the invention provides a method for preparing an amorphous fiber-based composite material for structural health monitoring, which comprises the following steps:
1) the cobalt-based or iron-based amorphous alloy fiber is prepared by a Uliotvskiy-Taylor glass coating method, a melt drawing method or an internal spinning method. By controlling the preparation parameters such as wire drawing speed, the length of a molten pool stretching area, cooling speed and the like, the amorphous alloy fiber with excellent and continuous performance is obtained, the diameter size of the amorphous alloy fiber is 10-50 mu m, the continuous length of the amorphous alloy fiber is more than 300m, and the amorphous alloy fiber has excellent mechanical property and magnetic property.
Since there are many known methods for preparing amorphous alloy fibers, the method for preparing amorphous alloy fibers by using Ulitovskiy-Taylor method is only used as an example in this embodiment, and the details are as follows:
the alloy raw materials arranged in the glass tube are melted and an external glass shell layer is driven to soften in a high-frequency induction mode, the melted alloy and the softened glass layer are pulled out together through external mechanical stress traction, and the melted alloy and the softened glass layer are wound on a wire collecting roller after flowing through a cooling liquid for subsequent application. The diameter of the amorphous alloy fiber prepared by the method is 1-80 mu m, the thickness of the glass layer can be controlled by adjusting the moving speed of the melt and the glass layer, and the length of the prepared fiber reaches kilometers. In the embodiment, the amorphous alloy fiber with the diameter of 10-50 μm is used for preparing the composite material subsequently.
2) And (3) laying the continuous amorphous alloy fibers obtained by the method on the surface of the prepreg so as to obtain the amorphous alloy fiber array prepreg. The prepreg may be made of glass fiber or carbon fiber. The method comprises the following specific steps:
winding the prepreg on a circular core mold roller with the diameter of 10-100cm and the length of 100 cm. And (3) enabling the amorphous alloy fiber to pass through a wire nozzle of a glue dipping tank, filling a fiber surface treating agent into the glue dipping tank, and then fixing the fiber surface treating agent on the prepreg surface on the winding roller. According to different performance requirements, design calculation is carried out to obtain the spacing distribution of the amorphous alloy fibers, the spacing distribution, the wire winding speed and the wire winding length of the amorphous alloy fibers are adjusted through numerical control equipment, and then wire distribution is carried out, and finally the amorphous alloy fiber array prepreg is obtained.
One surface of the amorphous alloy fiber array prepreg is a prepreg layer, and the other surface is one or more amorphous alloy fiber layers. The one or more amorphous alloy fiber layers jointly form a function and sensing unit, and are the core of the whole amorphous fiber-based composite material.
The amorphous alloy fibers on each amorphous alloy fiber layer are arranged in parallel at equal intervals of 1-12 mm, the amorphous alloy fibers on adjacent amorphous alloy fiber layers are mutually continuous and have no fracture in the middle, and the included angle alpha between the amorphous alloy fibers on the amorphous alloy fiber layers on different layers is not less than 0 degree and not more than 90 degrees. That is, the orientation between the different layers can be selected from 0 ° to 90 °, a two-dimensional or three-dimensional array structure composed in parallel, orthogonal or skew manner. The control of the induction area inside the composite material is realized through the structural design of the amorphous alloy fiber array, such as the spacing and the included angle of the alloy fibers.
The fiber surface treatment agent can adopt epoxy resin or ethanol diluted solution containing 0.5-10 wt.% of silane coupling agent, and is used for treating the amorphous alloy fiber to improve the bonding capacity of the amorphous alloy fiber and the prepreg. Wherein the silane coupling agent has the following structural formula: Y-R-Si (OR)3Y is an organofunctional group, SiOR is a siloxy group, and R is an alkyl group.
3) And stacking a plurality of prepregs and amorphous alloy fiber array prepreg layers to obtain an amorphous fiber-based composite material precursor, wherein the amorphous fiber-based composite material precursor contains at least one layer of amorphous alloy fiber array prepreg. That is to say, the prepreg and the amorphous alloy fiber array prepreg are layered at different layering angles and in different layering sequences, and the obtained amorphous fiber-based composite material precursor is provided with at least one layer of prepreg and at least one layer of amorphous alloy fiber array prepreg. The laying sequence of the prepreg and the amorphous alloy fiber array prepreg can be set according to actual conditions, so that the function and sensing units in the amorphous alloy fiber array prepreg are positioned on the surface or any position inside the whole amorphous fiber matrix composite material. The stacking angle between adjacent layers can also be adjusted as required.
4) And paving the amorphous fiber-based composite material precursor on a plane mould or a curved mould, putting the amorphous fiber-based composite material precursor into a vacuum bag, and vacuumizing until the pressure in the bag is within the range of 94.6-104.7 kPa for prepressing. After sealing and vacuumizing, putting the mixture into a vacuum autoclave or a vacuum oven, and curing and forming the mixture under the conditions of 110-250 ℃ and 0.1-0.6 MPa, wherein the specific steps are as follows:
heating to 110-250 ℃ at the heating rate of 2.4 ℃/min, preserving heat for 2 hours, naturally cooling along with the furnace, pressurizing to 0.62MPa at the pressure of 0.07MPa/min, maintaining the pressure for 270min, and then reducing to the atmospheric pressure at the pressure reduction rate of 0.07 MPa/min.
And finally, carrying out simple surface cleaning and machining on the cured and formed material to obtain the amorphous fiber-based composite material.
In the above preparation method, the preparation method and the layering sequence arrangement of the fibers are known to those skilled in the art, and those skilled in the art can select suitable process parameters and layering sequence according to specific requirements.
The amorphous fiber-based composite material prepared by the invention can be applied to functional raw materials for electromagnetic protection, radar stealth and the like in aviation, ship and other projects, and has selectable electromagnetic shielding or wave-transmitting functions. In addition, the amorphous fiber-based composite material can be applied to the fields of nondestructive structural health monitoring in the fields of aviation, ships and warships and the like, and has the function of monitoring the structural health condition of the material under the condition of not damaging the original mechanical property structure or even strengthening the original mechanical property.
The amorphous fiber-based composite material provided by the invention can realize different functions such as shielding, wave transmission, composite material structure health monitoring and the like by optimizing the amorphous alloy fiber array structure. The performance of the amorphous fiber-based composite material is S obtained by a vector network analyzer in the test11And S21Reflection coefficient by parameter estimation R: r ═ S11)2Wave-transparent coefficient T: t ═ S21)2And wave absorption coefficient A: a ═ 1- (S)11)2-(S21)2To characterize. The composite material test in the embodiment of the invention uses the waveguide for testing, but in practical application, the test method includes but is not limited to waveguide test.
Example 1:
the diameter of the Co-based amorphous alloy fiber prepared by adopting a Ulitovsky-Taylor method is 22 mu m, the thickness of a glass layer is 2.5 mu m, and the appearance of the Co-based amorphous alloy fiber is shown in figure 1.
Winding a glass fiber prepreg of 300 x 300mm on a winding roll of a fiber winding machine, and obtaining numerical control parameters through calculation: x62.0 and Y1910.08, setting the winding speed as 100, pouring 2 wt% of ethanol solution of silane coupling agent as a surfactant into a dipping tank, winding, and obtaining the amorphous alloy fiber array prepreg with the fiber spacing of 5mm under the parameters. The included angles between the two layers of amorphous alloy fibers are 60 degrees and 90 degrees, so that two layers of amorphous alloy fibers are respectively obtained, and the actual structure is shown in an inset of a figure 2.
According to [0,90, 90, 0 ]]4sAnd (3) laying up, and enabling a function and sensing unit in the amorphous alloy fiber array prepreg to be positioned between the 8 th layer and the 9 th layer to obtain the amorphous fiber-based composite material precursor. And then curing the amorphous fiber matrix composite material by a vacuum autoclave under the conditions of 0.6MPa and 120 ℃ to obtain the amorphous fiber matrix composite material.
Example 2:
the same amorphous alloy fiber as in example 1 was used. Obtaining an amorphous alloy fiber array with the wire spacing of 2mm by the same wire winding parameters, and then adopting 600 x 700mm glass fiber prepreg according to the specification of [0,90, 90, 0 ]]2sAnd (3) layering, and enabling the function and sensing units in the amorphous alloy fiber array prepreg to be positioned between the 4 th layer and the 5 th layer to obtain the amorphous fiber-based composite material precursor. And then, curing the material through a vacuum autoclave under the conditions of 0.5MPa and 120 ℃ to obtain the amorphous fiber-based composite material.
The composite material has obvious microwave response capability to the damage of a prefabricated wafer in the composite material, and the position of the defect or damage in the composite material can be preliminarily judged according to the change of different microwave reflection and absorption parameters, as shown in fig. 3.
According to the invention, the amorphous alloy fiber array structure is embedded in the traditional structural fiber reinforced resin matrix composite material, so that the multifunctional composite material with excellent mechanical properties and high self-induction capability is prepared. The technical design idea of the invention is that under the condition of not destroying the mechanical property of the original structure, even strengthening the mechanical property of the original structure, the self-induction structure health monitoring of the composite material can be realized by embedding the amorphous alloy fiber array and utilizing the electromagnetic sensing characteristic of the amorphous alloy array in the fields of aviation, ships and warships and the like.
The above-described embodiments are merely preferred embodiments of the present invention, which should not be construed as limiting the invention. Various changes and modifications may be made by one of ordinary skill in the pertinent art without departing from the spirit and scope of the present invention. Therefore, the technical scheme obtained by adopting the mode of equivalent replacement or equivalent transformation is within the protection scope of the invention.

Claims (10)

1. A preparation method of an amorphous fiber-based composite material for structural health monitoring is characterized by comprising the following steps:
s1: the method comprises the following steps of (1) laying continuous amorphous alloy fibers on the surface of a prepreg to obtain an amorphous alloy fiber array prepreg; one surface of the amorphous alloy fiber array prepreg is a prepreg layer, and the other surface is one or more amorphous alloy fiber layers; the amorphous alloy fibers on each amorphous alloy fiber layer are arranged in parallel at equal intervals, and the amorphous alloy fibers are continuously not broken in the length direction;
s2: stacking a plurality of prepregs and amorphous alloy fiber array prepreg layers to obtain an amorphous fiber matrix composite precursor; the amorphous fiber-based composite material precursor contains at least one layer of amorphous alloy fiber array prepreg;
s3: and paving the amorphous fiber-based composite material precursor on a plane mould or a curved mould, sealing, vacuumizing, and curing and forming at the temperature of 110-250 ℃ and under the pressure of 0.1-0.6 MPa to obtain the amorphous fiber-based composite material.
2. The production method according to claim 1, wherein the prepreg is a glass fiber or a carbon fiber.
3. The preparation method according to claim 1, wherein the amorphous alloy fiber is a cobalt-based or iron-based amorphous alloy fiber, the diameter is 10-50 μm, and the continuous length is more than 300 m.
4. The preparation method of claim 3, wherein the amorphous alloy fiber is prepared by a Uliotvsky-Taylor glass cladding method, a melt drawing method or an internal spinning method.
5. The preparation method according to claim 1, wherein the included angle α between the amorphous alloy fibers in the amorphous alloy fiber layers of different layers is 0 ° < α > 90 °.
6. The preparation method of claim 1, wherein the amorphous alloy fibers on each amorphous alloy fiber layer are arranged in parallel at equal intervals of 1-12 mm.
7. The preparation method according to claim 1, wherein the specific process for preparing the amorphous alloy fiber array prepreg in S1 is as follows:
s11: winding and fixing the prepreg on the surface of a winding roller of a fiber winding machine;
s12: enabling the amorphous alloy fiber to pass through a wire nozzle of a glue dipping tank and be fixed on the surface of a prepreg on a winding roller; introducing a fiber surface treating agent into the impregnation tank for treating the amorphous alloy fibers to improve the bonding capacity of the amorphous alloy fibers and the prepreg;
s13: and (3) laying amorphous alloy fibers on the surface of the prepreg by using numerical control equipment to obtain the amorphous alloy fiber array prepreg.
8. The method according to claim 7, wherein the fiber surface treatment agent is an ethanol diluted solution containing 0.5 to 10 wt% of a silane coupling agent or an ethanol diluted solution containing an epoxy resin.
9. An amorphous fiber-based composite material prepared by the preparation method according to any one of claims 1 to 8.
10. Use of an amorphous fiber-based composite material according to claim 9 for structural health monitoring.
CN202010922348.1A 2020-09-04 2020-09-04 Amorphous fiber-based composite material for structural health monitoring and method and application thereof Pending CN112265337A (en)

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