High-strength wrinkle-resistant composite fabric material, fabric and preparation method

Abstract

The application belongs to the technical field of fabric materials, and provides a high-strength wrinkle-resistant composite fabric material, a fabric and a preparation method, the composite fabric material comprises a base layer, a bonding layer and a surface layer which are stacked in sequence; the base layer is formed by weaving skin-core composite fibers, the skin-core composite fibers comprise an inner core and a skin layer wrapping the inner core, the inner core is acrylic multifilament, and the skin layer is polyester fiber; the material of the bonding layer is modified carbon fiber / metal oxide nanoparticle composite epoxy resin; the surface layer is formed by weaving warp and weft, the warp is flax fiber, and the weft is bamboo fiber; the composite fabric material provided by the application is formed by stacking the base layer, the bonding layer and the surface layer, and the prepared composite fabric material has excellent mechanical strength, higher body comfort and the advantages that wrinkles are not easily generated under external force.

Description

Technical Field

[0001] This invention belongs to the field of fabric technology and relates to a high-strength wrinkle-resistant composite fabric material, fabric, and preparation method. Background Technology

[0002] With the continuous development of the economy and society, people's quality requirements for all aspects of life, including clothing, food, housing, and transportation, have also increased. Among these, clothing has become an indispensable product in people's lives. As one of the three essential elements of clothing, fabric not only interprets the style and characteristics of clothing but also directly determines the color and shape of the garment. This requires fabrics to be breathable, comfortable, resistant to deformation, and non-static. In particular, fabrics should not wrinkle after washing to prevent wrinkles from damaging the garment's inherent beauty. However, existing comfortable and breathable fabrics are prone to wrinkling during washing or wearing and are difficult to restore. Meanwhile, wrinkle-resistant fabrics do not meet people's requirements in terms of comfort and breathability.

[0003] CN113123131A discloses a method for finishing knitted fabrics with a low-formaldehyde resin to prevent shrinkage and wrinkles, and the resulting textile. The method includes the following steps: subjecting the knitted fabric to a resin finishing treatment to obtain a finished fabric; subjecting the finished fabric to a setting treatment to obtain a set fabric; and subjecting the set fabric to a circulating air treatment, wherein the circulating air velocity applied to the lower surface of the set fabric is greater than the circulating air velocity applied to the upper surface of the set fabric. However, the textile finishing method provided by this invention is complex, requires expensive equipment, is not easily industrialized, and cannot simultaneously achieve both fabric comfort and high strength.

[0004] CN103572452A discloses a wrinkle-resistant fabric, its production method, and its uses. The fabric is formed from at least cellulose fibers and polyester fibers, and its weave is twill, satin, or double weave. The cellulose fiber content is between 20% and 80% by weight, and the wrinkle resistance of the fabric is level 3 or higher. However, the wrinkle-resistant fabric provided by this invention cannot simultaneously achieve both comfort and high strength.

[0005] Therefore, there is an urgent need to design a new type of fabric that can ensure both breathability and comfort, as well as meet people's demand for wrinkle-resistant fabrics. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the present invention aims to provide a high-strength, wrinkle-resistant composite fabric material, fabric, and preparation method. The composite fabric material provided by the present invention is formed by layering a base layer, an adhesive layer, and a surface layer. The prepared composite fabric material has advantages such as excellent mechanical strength, high comfort, and resistance to wrinkles under external forces.

[0007] To achieve this objective, the present invention adopts the following technical solution:

[0008] In a first aspect, the present invention provides a high-strength wrinkle-resistant composite fabric material, the composite fabric material comprising a base layer, an adhesive layer and a surface layer stacked sequentially;

[0009] The base layer is woven from core-sheath composite fibers, which include an inner core and a sheath layer that wraps the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber.

[0010] The adhesive layer is made of a modified carbon fiber / metal oxide nanoparticle composite epoxy resin.

[0011] The surface layer is formed by weaving warp and weft threads, wherein the warp threads are flax fibers and the weft threads are bamboo fibers.

[0012] The composite fabric material provided by the present invention is formed by layering a base layer, an adhesive layer and a surface layer. The resulting composite fabric material has excellent mechanical strength, high comfort, and is not prone to wrinkling under external force.

[0013] The composite fabric material provided by this invention has a surface layer formed by the cross-weaving of flax and bamboo fibers. Bamboo fibers endow the composite fabric with excellent antibacterial properties, and as a skin-friendly surface layer, they can significantly reduce the generation and spread of bacteria. Flax fibers, on the other hand, possess cool, breathable, smooth, and firm textile characteristics, providing a comfortable and skin-friendly experience when in direct contact with human skin. However, both flax and bamboo fibers are cellulose fibers, containing a significant amount of lignin. Lignin exists in the amorphous regions of cellulose molecules. Due to the presence of lignin, the molecular chains in the amorphous regions of flax and bamboo fibers are prone to stretching and slippage under external forces. Furthermore, the cross-linking of cellulose molecules forms a rigid network structure, resulting in low elongation, poor elasticity, and high brittleness of the surface layer. Therefore, although the surface layer possesses advantages such as comfort, breathability, softness, and skin-friendliness, it is prone to wrinkling during wear and use. Therefore, the present invention combines a base layer with excellent resilience on the surface layer woven from bamboo fiber and flax fiber, and bonds the base layer and the surface layer together through an adhesive layer, thereby obtaining a composite fabric material that takes into account both comfort and wrinkle resistance.

[0014] The composite fabric material provided by this invention has a base layer woven from core-sheath composite fibers, which mainly serves as the overall support framework for the composite fabric material. This provides the composite fabric material with a certain tensile strength, ensures the spinnability of the core-sheath composite fibers, and endows the composite fabric material with excellent deformation recovery capabilities. Specifically, the inner core of the core-sheath composite fibers is acrylic multifilament, which has excellent resilience. Under a 20% elongation condition, the resilience rate of acrylic multifilament can be maintained above 65%. Using acrylic multifilament as the inner core of the core-sheath composite fibers can greatly improve the elasticity of the composite fabric material, thereby giving it excellent wrinkle resistance. Polyester fiber possesses excellent properties such as acid and alkali resistance, abrasion resistance, light resistance, heat resistance, wrinkle resistance, high strength, and high elasticity. It is also resistant to insects and mildew. Therefore, using it as a base layer material makes composite fabrics durable and can significantly improve the service life and overall strength of composite fabrics. In addition, given the poor moisture absorption and breathability of polyester fiber, it does not come into direct contact with the skin when used as a base layer material, thus mitigating the poor comfort caused by its poor moisture absorption and breathability to a certain extent.

[0015] In composite fabrics, the interfacial bonding performance between the base layer and the surface layer directly affects the deformation recovery effect of the fabric. Even if the base layer has excellent deformation recovery capabilities, if the bonding effect with the surface layer is poor, the deformation recovery capabilities of the base layer cannot be smoothly transferred to the surface layer, resulting in wrinkles on the surface layer as well. When the interfacial bonding strength between the base layer and the surface layer is strong, the base layer, as the supporting framework of the fabric, can quickly transfer the deformation recovery capabilities to the surface layer through the adhesive layer between them, allowing the wrinkles on the surface layer to recover under the action of deformation recovery capabilities. Conversely, when the interfacial bonding strength between the base layer and the surface layer is weak, the composite fabric can experience relative displacement between the base layer and the surface layer after being subjected to external forces, or even cause the surface layer to detach. In this case, the wrinkles on the surface layer caused by external forces are difficult to recover through the supporting effect of the base layer. To address this, this invention specifically improves the composition of the adhesive layer between the base layer and the surface layer, designing an epoxy resin composite of modified carbon fiber and metal oxide nanoparticles. This not only improves the interfacial bonding strength between the adhesive layer and the base layer and the surface layer, but also further enhances the overall mechanical properties of the composite fabric.

[0016] As a preferred technical solution of the present invention, the weaving density of the core-sheath composite fiber is 10-20 fibers / cm, for example, it can be 10 fibers / cm, 11 fibers / cm, 12 fibers / cm, 13 fibers / cm, 14 fibers / cm, 15 fibers / cm, 16 fibers / cm, 17 fibers / cm, 18 fibers / cm, 19 fibers / cm or 20 fibers / cm, but it is not limited to the listed values, and other unlisted values ​​within this range are also applicable.

[0017] The thickness of the adhesive layer is 100-150 μm, for example, it can be 100 μm, 105 μm, 110 μm, 115 μm, 120 μm, 125 μm, 130 μm, 135 μm, 140 μm, 145 μm or 150 μm, but is not limited to the listed values, other unlisted values ​​within this range are also applicable.

[0018] The weaving density of the warp threads is 30-40 threads / cm, for example, it can be 30 threads / cm, 31 threads / cm, 32 threads / cm, 33 threads / cm, 34 threads / cm, 35 threads / cm, 36 threads / cm, 37 threads / cm, 38 threads / cm, 39 threads / cm or 40 threads / cm, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0019] The weft yarn weave density is 25-35 threads / cm, for example, it can be 25 threads / cm, 26 threads / cm, 27 threads / cm, 28 threads / cm, 29 threads / cm, 30 threads / cm, 31 threads / cm, 32 threads / cm, 33 threads / cm, 34 threads / cm or 35 threads / cm, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0020] The warp weave density of the surface layer directly affects the wrinkle resistance of the composite fabric. This invention specifically limits the warp weave density to 30-40 threads / cm. When the warp weave density is less than 30 threads / cm, the surface layer structure becomes too loose, resulting in low rigidity and insufficient mechanical properties. However, when the warp weave density exceeds 40 threads / cm, the friction between the warp and weft threads becomes too great, affecting the deformation recovery ability of the composite fabric and ultimately reducing its wrinkle resistance. At the same time, it also increases the rigidity of the surface layer, reduces its stress resistance, and makes it feel rough.

[0021] In a second aspect, the present invention provides a method for preparing the high-strength wrinkle-resistant composite fabric material described in the first aspect, the method comprising:

[0022] (I) Core-spun yarn with acrylic multifilament as the inner core and polyester fiber as the outer layer to obtain core-sheath composite fiber, and then weave the core-sheath composite fiber to form the base layer;

[0023] (II) Preparation of a reinforcing material composed of modified carbon fiber and metal oxide nanoparticles: The reinforcing material, epoxy resin, curing agent and coupling agent are mixed and extruded by screw extrusion to obtain a bonding material;

[0024] (III) The surface layer is formed by weaving flax fiber as warp and bamboo fiber as weft.

[0025] (IV) Lay an adhesive material on one side of the base layer, cover the adhesive material with a surface layer, and then heat-press and bond to obtain the composite fabric material.

[0026] As a preferred technical solution of the present invention, in step (I), the core-sheath composite fiber is prepared in a core-spun yarn device.

[0027] In the core-sheath composite fiber, the mass ratio of the polyester fiber to the acrylic multifilament is (1.5-3):1, for example, it can be 1.5:1, 1.6:1, 1.7:1, 1.8:1, 1.9:1, 2.0:1, 2.1:1, 2.2:1, 2.3:1, 2.4:1, 2.5:1, 2.6:1, 2.7:1, 2.8:1, 2.9:1 or 3.0:1, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0028] The yarn output speed of the core-spun spinning device is 20-30 m / min, for example, it can be 20 m / min, 21 m / min, 22 m / min, 23 m / min, 24 m / min, 25 m / min, 26 m / min, 27 m / min, 28 m / min, 29 m / min or 30 m / min, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0029] The twist of the polyester fiber is 200-300T / m, for example, it can be 200T / m, 210T / m, 220T / m, 230T / m, 240T / m, 250T / m, 260T / m, 270T / m, 280T / m, 290T / m or 300T / m, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0030] For polyester fibers used in the sheath layer, twist can bind the polyester fibers together and give them a certain degree of cohesion. Therefore, twist directly determines the mechanical properties of the core-sheath composite fiber after processing, as well as the mechanical properties of the base layer woven from the core-sheath composite fiber. When the twist of the polyester fiber is less than 200T / m, the cohesive force and friction between the polyester fibers are small, and the sheath structure formed by the polyester fibers is relatively loose. When subjected to external forces, the polyester fibers are prone to relative displacement, leading to irreversible deformation of the core-sheath composite fiber, thereby reducing the wrinkle recovery ability of the composite fabric material.

[0031] As the twist of polyester fibers increases, the centripetal pressure of the fibers also increases, leading to stronger friction and cohesion between the fibers. This increased interfiber friction and cohesion enhances the load transfer capacity between fibers, giving the sheath a higher load-bearing capacity. Simultaneously, the increased twist angle of the polyester fibers makes the fibers in the sheath more inclined, preventing deformation under axial tension, delaying fiber breakage, and thus increasing the elongation at break.

[0032] When the twist of polyester fibers exceeds 300 T / m, the fibers undergo significant torsion. Excessive cohesion between the fibers leads to severe deformation, resulting in decreased flexural stiffness under external forces and consequently reduced wrinkle recovery of the composite fabric. Furthermore, excessive twist causes the fibers to be tightly packed, where tilting and deformation become dominant, leading to a decrease in initial modulus and breaking strength. Therefore, for a base layer with good wrinkle resistance, the polyester fiber twist should be moderate, and the sheath structure should be relatively compact to maintain adequate cohesion and flexural stiffness.

[0033] As a preferred technical solution of the present invention, in step (II), the reinforcing material is prepared by the following method:

[0034] (1) The carbon fiber was immersed in the oxidant solution and the coupling agent solution in sequence, and the modified carbon fiber was obtained after taking it out; the metal precursor was dispersed in deionized water and stirred evenly to obtain the metal precursor solution.

[0035] (2) The modified carbon fiber is mixed with the metal precursor solution and then subjected to microwave hydrothermal reaction. After the reaction is completed, it is calcined to obtain the reinforced material.

[0036] This invention imparts the deformation recovery capability of the base layer to the surface layer through an adhesive layer, giving the surface layer a certain anti-wrinkle effect. Simultaneously, it promptly transfers external forces on the surface layer to the base layer, preventing irreversible wrinkles caused by prolonged exposure to external forces. The essence of the base layer and surface layer composite is to form an adhesive interface that completely wets both the base layer and the surface layer and can transfer stress loads. Therefore, the adhesive layer formed between the base layer and the surface layer needs to ensure complete contact and wetting with both the base layer and the surface layer. However, due to the relatively rough surfaces of the base layer and the surface layer, when epoxy resin is used as the adhesive material, it is difficult for the epoxy resin matrix to completely contact and wet the base layer and the surface layer. This results in numerous cavity defects between the cured adhesive layer and the base layer and the surface layer, which directly affects the interfacial bonding strength between the base layer, adhesive layer, and surface layer.

[0037] To address this, the present invention incorporates a composite reinforcing material composed of modified carbon fibers and metal oxide nanoparticles into the epoxy resin matrix. Due to the small diameter of the carbon fibers, they can fill the surface depressions of the base and surface layers during hot-pressing, reducing the generation of cavities and defects, improving the wetting ability of the adhesive layer with the base and surface layers, and increasing the area of ​​the connection region between the adhesive layer and the base and surface layers, ultimately enhancing the bonding strength of the base, adhesive layer, and surface layer. However, due to the high surface inertness and low surface energy of carbon fibers, coupled with a lack of chemically active functional groups, their reactivity is low, resulting in poor interfacial performance with the epoxy resin matrix. This leads to numerous cavities at the interface between the carbon fibers and the epoxy resin matrix, directly affecting the wetting effect of the adhesive material. Therefore, although the addition of carbon fibers solves the wetting problem between the adhesive material and the base and surface layers, it also causes wetting problems between the carbon fibers and the epoxy resin matrix within the adhesive material itself, ultimately affecting the wetting effect between the adhesive material and the base and surface layers. Therefore, in order to improve the interfacial properties between carbon fiber and epoxy resin matrix, this invention makes full use of the favorable factors of interfacial effect by oxidizing and modifying carbon fiber to improve the interfacial properties between it and epoxy resin matrix.

[0038] This invention incorporates metal oxide nanoparticles into the adhesive material, which enhances the mechanical strength of the adhesive layer. When the surface layer is subjected to impact load, numerous microcracks can form at the interface between the metal oxide nanoparticles and the epoxy resin matrix. The epoxy resin matrix between the metal oxide nanoparticles also undergoes significant plastic deformation, absorbing a large amount of impact energy and providing a toughening effect, thereby significantly improving the impact strength of the composite fabric material. Furthermore, when the adhesive layer receives external stress transmitted from the surface layer, the metal oxide nanoparticles within the adhesive layer can deflect and separate the cracks, increasing the fracture energy of the adhesive layer and further enhancing the overall impact strength of the composite fabric material.

[0039] In this invention, the oxidized carbon fibers are preferably soaked in an aluminate coupling agent. After soaking in the aluminate coupling agent solution, the carbon fibers do not need to be dried. They are directly taken out and mixed with a metal precursor solution for microwave hydrothermal reaction. At this time, some aluminate coupling agent solution remains in the raw material. When mixed with the metal precursor solution, the residual aluminate coupling agent can bond with the metal precursor, which is beneficial for preparing metal oxide nanoparticles with smaller particle size. At the same time, since it can coat the surface of the metal oxide nanoparticles, it plays a steric hindrance effect, which can reduce the agglomeration problem caused by sintering during the crystal transformation of metal oxide nanoparticles during calcination.

[0040] In step (1), which is a preferred technical solution of the present invention, the carbon fiber is short-cut carbon fiber.

[0041] The chopped length of the carbon fiber is 4-5 mm, for example, it can be 4.0 mm, 4.1 mm, 4.2 mm, 4.3 mm, 4.4 mm, 4.5 mm, 4.6 mm, 4.7 mm, 4.8 mm, 4.9 mm or 5.0 mm, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0042] The diameter of the carbon fiber monofilament is 6-7 μm, for example, it can be 6.0 μm, 6.1 μm, 6.2 μm, 6.3 μm, 6.4 μm, 6.5 μm, 6.6 μm, 6.7 μm, 6.8 μm, 6.9 μm or 7.0 μm, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0043] Immerse in the oxidant solution for 50-60 minutes, for example, 50 minutes, 51 minutes, 52 minutes, 53 minutes, 54 minutes, 55 minutes, 56 minutes, 57 minutes, 58 minutes, 59 minutes or 60 minutes, but not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0044] The concentration of the oxidant solution is 20-30 mmol / L, for example, it can be 20 mmol / L, 21 mmol / L, 22 mmol / L, 23 mmol / L, 24 mmol / L, 25 mmol / L, 26 mmol / L, 27 mmol / L, 28 mmol / L, 29 mmol / L or 30 mmol / L, but is not limited to the listed values, other unlisted values ​​within this range are also applicable.

[0045] The oxidizing agent solution is any one or a combination of at least two of the following: hydrogen peroxide solution, peracetic acid solution, sodium percarbonate solution, potassium permanganate solution, and potassium hydrogen sulfate solution.

[0046] Soak in the coupling agent solution for 30-40 minutes, for example, 30 minutes, 31 minutes, 32 minutes, 33 minutes, 34 minutes, 35 minutes, 36 minutes, 37 minutes, 38 minutes, 39 minutes or 40 minutes, but not limited to the listed values, other unlisted values ​​within this range are also applicable.

[0047] The mass fraction of the coupling agent in the coupling agent solution is 2-5 wt%, for example, it can be 2.0 wt%, 2.2 wt%, 2.4 wt%, 2.6 wt%, 2.8 wt%, 3.0 wt%, 3.2 wt%, 3.4 wt%, 3.6 wt%, 3.8 wt%, 4.0 wt%, 4.2 wt%, 4.4 wt%, 4.6 wt%, 4.8 wt%, or 5.0 wt%, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0048] The molar concentration of the metal precursor in the metal precursor solution is 1-2.5 mol / L, for example, it can be 1.0 mol / L, 1.1 mol / L, 1.2 mol / L, 1.3 mol / L, 1.4 mol / L, 1.5 mol / L, 1.6 mol / L, 1.7 mol / L, 1.8 mol / L, 1.9 mol / L, 2.0 mol / L, 2.1 mol / L, 2.2 mol / L, 2.3 mol / L, 2.4 mol / L or 2.5 mol / L, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0049] This invention specifically limits the molar concentration of the metal precursor in the metal precursor solution to 1-2.5 mol / L. Within this concentration range, it ensures that the metal precursor can be relatively uniformly dispersed in carbon fiber and epoxy resin. When the molar concentration of the metal precursor exceeds 2.5 mol / L, the content of the metal oxide nanoparticles obtained from the final reaction is too high, which disrupts the continuity of the adhesive layer and leads to a certain degree of decrease in the tensile and flexural strength of the adhesive layer. In addition, when the content of metal oxide nanoparticles is too high, they are prone to agglomeration, resulting in poor dispersibility and the formation of stress defects in the adhesive layer. These defects are easily destroyed under external stress, leading to a decrease in the overall mechanical properties of the composite fabric material.

[0050] The ambient temperature during the stirring process is 40-60℃, for example, it can be 40℃, 42℃, 44℃, 46℃, 48℃, 50℃, 52℃, 54℃, 56℃, 58℃ or 60℃, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0051] The metal precursor is aluminum hydroxide, and the resulting reinforcing material is a modified carbon fiber / nano-alumina composite material.

[0052] As a preferred technical solution of the present invention, in step (2), the mass ratio of the modified carbon fiber to the metal precursor in the metal precursor solution is 1:(30-40), for example, it can be 1:30, 1:31, 1:32, 1:33, 1:34, 1:35, 1:36, 1:37, 1:38, 1:39 or 1:40, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0053] The microwave hydrothermal reaction is carried out in a microwave hydrothermal reactor.

[0054] The microwave hydrothermal reaction time is 20-50 min, for example, it can be 20 min, 22 min, 24 min, 26 min, 28 min, 30 min, 32 min, 34 min, 36 min, 38 min, 40 min, 42 min, 44 min, 46 min, 48 min or 50 min, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0055] The temperature of the microwave hydrothermal reaction is 160-190℃, for example, it can be 160℃, 162℃, 164℃, 166℃, 168℃, 170℃, 172℃, 174℃, 176℃, 178℃, 180℃, 182℃, 184℃, 186℃, 188℃ or 190℃, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0056] This invention utilizes microwave hydrothermal reaction to prepare metal oxide nanoparticles. The microwave hydrothermal reaction is carried out in a high-temperature and high-pressure reaction environment in a microwave hydrothermal reactor, using water as the reaction medium. This allows the metal precursor to dissolve and undergo a chemical reaction to obtain metal oxide nanoparticles. During the microwave hydrothermal reaction, the metal oxide grains gradually grow, and the lattice order and symmetry gradually improve. The pore size of the metal oxide nanoparticles obtained after the microwave hydrothermal reaction is slightly increased. This is because microwave hydrothermal treatment has a pore-expanding effect, while the mild hydrothermal conditions (160-190℃) avoid excessive crystal growth and deep pore expansion, thus preventing a significant decrease in the specific surface area of ​​the metal oxide nanoparticles. Furthermore, the arrangement of the metal oxide nanoparticles on the carbon fiber surface also changes after microwave hydrothermal treatment, transforming from a densely packed structure of small particles to a regularly arranged nanosheet structure. This significantly alters the surface properties of the carbon fiber, making it more conducive to the dissipation and transfer of loads transferred to the surface layer.

[0057] The pressure of the microwave hydrothermal reaction is 1-4 MPa, for example, it can be 1.0 MPa, 1.5 MPa, 2.0 MPa, 2.5 MPa, 3.0 MPa, 3.5 MPa or 4.0 MPa, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0058] The calcination temperature is 1000-1200℃, for example, it can be 1000℃, 1020℃, 1040℃, 1060℃, 1080℃, 1100℃, 1120℃, 1140℃, 1160℃, 1180℃ or 1200℃, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0059] The calcination time is 1-2 hours, for example, it can be 1.0h, 1.1h, 1.2h, 1.3h, 1.4h, 1.5h, 1.6h, 1.7h, 1.8h, 1.9h or 2.0h, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0060] As a preferred embodiment of the present invention, in step (II), the reinforcing material, epoxy resin, curing agent, and coupling agent are added in the following weight proportions:

[0061] 20-30 parts of reinforcing material;

[0062] 50-70 parts epoxy resin;

[0063] 5-15 parts of curing agent;

[0064] 1-5 parts of coupling agent.

[0065] The weight parts of the reinforcing material can be 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, or 30 parts; the weight parts of the epoxy resin can be 50, 52, 54, 56, 58, 60, 62, 64, 66, 68, or 70 parts; the weight parts of the curing agent can be 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, or 15 parts; and the weight parts of the coupling agent can be 1, 2, 3, 4, or 5 parts, but are not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0066] This invention specifically limits the weight of the reinforcing material to 20-30 parts. With increasing reinforcing material content, the tensile strength, flexural strength, and impact strength of the adhesive layer initially increase and then decrease. This is because the addition of the reinforcing material improves the tensile strength of the adhesive. The reinforcing material is uniformly dispersed as deformable particles in the epoxy matrix. When the system is subjected to external force, the metal oxide nanoparticles in the reinforcing material can exert stress concentration, absorbing a large amount of external energy through their own deformation and effectively dissipating and transferring the energy. After being combined with the base layer and surface layer, this can greatly improve the overall impact resistance and flexural performance of the composite fabric. Furthermore, during the subsequent hot-press bonding process, the oxidized carbon fibers in the reinforcing material can interact with the epoxy resin, interpenetrating and intertwining to form a semi-interpenetrating network structure. This interaction causes the epoxy molecular chains to undergo a certain degree of sliding deformation during stress, absorbing some of the load energy, thereby further improving the mechanical properties of the composite fabric. However, when the amount of reinforcing material added exceeds 30 parts, the viscosity of the adhesive material system is too high, making it difficult to disperse evenly and prone to generating air bubbles. The wetting effect with the surface layer and the base layer is also poor, resulting in more air cavity defects in the cured adhesive layer, which leads to a decrease in the mechanical properties of the final adhesive layer.

[0067] The screw extrusion process is carried out in a twin-screw extruder.

[0068] The screw speed of the twin-screw extruder is 200-300 rpm, for example, it can be 200 rpm, 210 rpm, 220 rpm, 230 rpm, 240 rpm, 250 rpm, 260 rpm, 270 rpm, 280 rpm, 290 rpm or 300 rpm, but is not limited to the listed values, other unlisted values ​​within this range are also applicable.

[0069] The temperature of the twin-screw extruder is 180-200℃, for example, it can be 180℃, 182℃, 184℃, 186℃, 188℃, 190℃, 192℃, 194℃, 196℃, 198℃ or 200℃, but it is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0070] As a preferred technical solution of the present invention, in step (IV), the temperature of the hot pressing is 170-180℃, for example, it can be 170℃, 171℃, 172℃, 173℃, 174℃, 175℃, 176℃, 177℃, 178℃, 179℃ or 180℃, but it is not limited to the listed values, and other unlisted values ​​within this range are also applicable.

[0071] The hot-pressing bonding temperature also affects the interfacial performance between the base layer and the surface layer to a certain extent. The higher the hot-pressing bonding temperature of the composite fabric material, the higher the interfacial bonding strength between the base layer and the surface layer, but at the same time, it will lead to a decrease in mechanical strength. Therefore, in order to balance the interfacial bonding strength and mechanical strength of the composite fabric material, the present invention specifically limits the hot-pressing bonding temperature to 170-180℃.

[0072] The pressure for hot pressing is 0.3-0.4 MPa, for example, it can be 0.3 MPa, 0.31 MPa, 0.32 MPa, 0.33 MPa, 0.34 MPa, 0.35 MPa, 0.36 MPa, 0.37 MPa, 0.38 MPa, 0.39 MPa or 0.4 MPa, but is not limited to the listed values. Other unlisted values ​​within this range are also applicable.

[0073] By way of example, the present invention provides a method for preparing a high-strength wrinkle-resistant composite fabric material, which specifically includes the following steps:

[0074] (1) Preparation of the base layer:

[0075] Polyester fiber and acrylic multifilament are fed into a core-spun spinning device at a mass ratio of (1.5-3):1 for core-spun spinning. The yarn output speed is 20-30 m / min, and the twist of the polyester fiber is 200-300 T / m. After core-spun spinning, a core-sheath composite fiber with an acrylic multifilament core and a polyester fiber sheath is obtained. The core-sheath composite fiber is then woven to form a base layer with a weaving density of 10-20 fibers / cm.

[0076] (2) Preparation of reinforcing materials:

[0077] Short carbon fibers with a chopped length of 4-5 mm and a single filament diameter of 6-7 μm are immersed in an oxidant solution of 20-30 mmol / L for 50-60 min and then dried to obtain oxidized carbon fibers. Subsequently, the oxidized carbon fibers are immersed in a coupling agent solution with a coupling agent mass fraction of 2-5 wt% for 30-40 min and then dried to obtain modified carbon fibers.

[0078] The metal precursor is dispersed in deionized water and stirred at 40-60℃ to obtain a metal precursor solution with a molar concentration of 1-2.5 mol / L.

[0079] Modified carbon fibers and a metal precursor solution were placed in a microwave hydrothermal reactor at a pressure of 1-4 MPa and subjected to a microwave hydrothermal reaction at 160-190℃ for 20-50 min. The mass ratio of modified carbon fibers to the metal precursor in the metal precursor solution was 1:(30-40). After the reaction was completed, the reaction product was calcined at 1000-1200℃ for 1-2 h to obtain a modified and reinforced material composed of modified carbon fibers and alumina nanoparticles.

[0080] (3) Preparation of adhesive materials:

[0081] Add 20-30 parts of the reinforcing material obtained in step (2), 50-70 parts of epoxy resin, 5-15 parts of curing agent and 1-5 parts of coupling agent into a twin-screw extruder, set the screw speed to 200-300 rpm and the extrusion temperature to 180-200℃, and obtain the bonding material by screw extrusion.

[0082] (4) Preparation of the surface layer:

[0083] Flax fiber is used as the warp and bamboo fiber as the weft, and the surface layer is formed by weaving in both directions. The weaving density of the warp is 30-40 threads / cm, and the weft weft is 25-35 threads / cm.

[0084] (5) Preparation of composite fabric materials:

[0085] The adhesive material obtained in step (3) is laid flat on one side of the base layer obtained in step (1), and the surface layer obtained in step (4) is covered on the adhesive material. Hot pressing is performed at a temperature of 170-180℃ and a pressure of 0.3-0.4MPa to form an adhesive layer with a thickness of 100-150μm after the adhesive material melts and solidifies, thus obtaining the composite fabric material.

[0086] Thirdly, the present invention provides a high-strength wrinkle-resistant fabric, which is obtained by cutting the high-strength wrinkle-resistant composite fabric material described in the first aspect.

[0087] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0088] The composite fabric material provided by the present invention is formed by layering a base layer, an adhesive layer and a surface layer. The resulting composite fabric material has excellent mechanical strength, high comfort, and is not prone to wrinkling under external force.

[0089] The composite fabric material provided by this invention has a surface layer formed by the cross-weaving of flax and bamboo fibers. Bamboo fibers endow the composite fabric with excellent antibacterial properties, and as a skin-friendly surface layer, they can significantly reduce the generation and spread of bacteria. Flax fibers, on the other hand, possess cool, breathable, smooth, and firm textile characteristics, providing a comfortable and skin-friendly experience when in direct contact with human skin. However, both flax and bamboo fibers are cellulose fibers, containing a significant amount of lignin. Lignin exists in the amorphous regions of cellulose molecules. Due to the presence of lignin, the molecular chains in the amorphous regions of flax and bamboo fibers are prone to stretching and slippage under external forces. Furthermore, the cross-linking of cellulose molecules forms a rigid network structure, resulting in low elongation, poor elasticity, and high brittleness of the surface layer. Therefore, although the surface layer possesses advantages such as comfort, breathability, softness, and skin-friendliness, it is prone to wrinkling during wear and use. Therefore, the present invention combines a base layer with excellent resilience on the surface layer woven from bamboo fiber and flax fiber, and bonds the base layer and the surface layer together through an adhesive layer, thereby obtaining a composite fabric material that takes into account both comfort and wrinkle resistance.

[0090] The composite fabric material provided by this invention has a base layer woven from core-sheath composite fibers, which mainly serves as the overall support framework for the composite fabric material. This provides the composite fabric material with a certain tensile strength, ensures the spinnability of the core-sheath composite fibers, and endows the composite fabric material with excellent deformation recovery capabilities. Specifically, the inner core of the core-sheath composite fibers is acrylic multifilament, which has excellent resilience. Under a 20% elongation condition, the resilience rate of acrylic multifilament can be maintained above 65%. Using acrylic multifilament as the inner core of the core-sheath composite fibers can greatly improve the elasticity of the composite fabric material, thereby giving it excellent wrinkle resistance. Polyester fiber possesses excellent properties such as acid and alkali resistance, abrasion resistance, light resistance, heat resistance, wrinkle resistance, high strength, and high elasticity. It is also resistant to insects and mildew. Therefore, using it as a base layer material makes composite fabrics durable and can significantly improve the service life and overall strength of composite fabrics. In addition, given the poor moisture absorption and breathability of polyester fiber, it does not come into direct contact with the skin when used as a base layer material, thus mitigating the poor comfort caused by its poor moisture absorption and breathability to a certain extent.

[0091] In composite fabrics, the interfacial bonding performance between the base layer and the surface layer directly affects the deformation recovery effect of the fabric. Even if the base layer has excellent deformation recovery capabilities, if the bonding effect with the surface layer is poor, the deformation recovery capabilities of the base layer cannot be smoothly transferred to the surface layer, resulting in wrinkles on the surface layer as well. When the interfacial bonding strength between the base layer and the surface layer is strong, the base layer, as the supporting framework of the fabric, can quickly transfer the deformation recovery capabilities to the surface layer through the adhesive layer between them, allowing the wrinkles on the surface layer to recover under the action of deformation recovery capabilities. Conversely, when the interfacial bonding strength between the base layer and the surface layer is weak, the composite fabric can experience relative displacement between the base layer and the surface layer after being subjected to external forces, or even cause the surface layer to detach. In this case, the wrinkles on the surface layer caused by external forces are difficult to recover through the supporting effect of the base layer. To address this, this invention specifically improves the composition of the adhesive layer between the base layer and the surface layer, designing an epoxy resin composite of modified carbon fiber and metal oxide nanoparticles. This not only improves the interfacial bonding strength between the adhesive layer and the base layer and the surface layer, but also further enhances the overall mechanical properties of the composite fabric. Attached Figure Description

[0092] Figure 1 The process flow diagrams for preparing the composite fabric materials provided in Examples 1-5 of this invention are shown below.

[0093] Figure 2 The above are schematic diagrams of the structures of the composite fabric materials prepared in Examples 1-5 of this invention.

[0094] Figure 3 A photograph of the crease recovery angle of the composite fabric material prepared in Example 1 of this invention;

[0095] Figure 4 This is a photograph of the crease recovery angle of the composite fabric material prepared in Comparative Example 11 of the present invention;

[0096] Figure 5 This is a photograph of the composite fabric material prepared in Example 1 of the present invention before washing;

[0097] Figure 6 This is a photograph of the composite fabric material prepared in Example 1 of the present invention after washing.

[0098] Figure 7 This is a photograph of the composite fabric material prepared in Comparative Example 11 of the present invention after washing.

[0099] Figure 8 This is a cross-sectional electron microscope image of the core-sheath composite fiber prepared in Example 1 of the present invention.

[0100] Among them, 1-base layer; 2-adhesive layer; 3-top layer. Detailed Implementation

[0101] The technical solutions of the present invention will be described in detail below with reference to specific embodiments and accompanying drawings. The embodiments described herein are specific implementations of the present invention, used to illustrate the concept of the present invention; these descriptions are explanatory and exemplary, and should not be construed as limiting the implementation methods or the scope of protection of the present invention. In addition to the embodiments described herein, those skilled in the art can employ other obvious technical solutions based on the content disclosed in the claims and specification of this application. These technical solutions include those that make any obvious substitutions and modifications to the embodiments described herein.

[0102] Example 1

[0103] This embodiment provides a method for preparing a high-strength, wrinkle-resistant composite fabric material, such as... Figure 1 As shown, the preparation method specifically includes the following steps:

[0104] (1) Preparation of base layer 1:

[0105] Polyester fiber and acrylic multifilament were fed into a core-spun spinning device at a mass ratio of 1.5:1 for core-spun spinning. The yarn output speed was 20 m / min, and the twist of the polyester fiber was 200 T / m. After core-spun spinning, a core-sheath composite fiber with an acrylic multifilament core and a polyester fiber sheath was obtained (e.g., ...). Figure 8 As shown, a distinct core-sheath structure can be seen. The core-sheath composite fibers are woven to form the base layer 1, and the weaving density of the core-sheath composite fibers is 10 fibers / cm.

[0106] (2) Preparation of reinforcing materials:

[0107] Short carbon fibers with a chopped length of 4 mm and a single filament diameter of 6 μm were immersed in a 20 mmol / L hydrogen peroxide solution for 60 min and then dried to obtain oxidized carbon fibers. Subsequently, the oxidized carbon fibers were immersed in an aluminate coupling agent solution with a mass fraction of 2 wt% for 40 min and then dried to obtain modified carbon fibers.

[0108] Aluminum hydroxide was dispersed in deionized water and stirred evenly at 40°C to obtain an aluminum hydroxide solution with a molar concentration of 1 mol / L.

[0109] Modified carbon fiber and aluminum hydroxide solution were added into a microwave hydrothermal reactor. The pressure inside the microwave hydrothermal reactor was 1 MPa. The microwave hydrothermal reaction was carried out at 160℃ for 50 min. The mass ratio of modified carbon fiber to aluminum hydroxide in the aluminum hydroxide solution was 1:30. After the reaction was completed, the reaction product was calcined at 1000℃ for 2 h to obtain a modified and reinforced material composed of modified carbon fiber and aluminum oxide nanoparticles.

[0110] (3) Preparation of adhesive materials:

[0111] 20 parts of the reinforcing material obtained in step (2), 60 parts of epoxy resin, 15 parts of diethylenetriamine and 5 parts of KH560 coupling agent were put into a twin-screw extruder. The screw speed was set to 200 rpm and the extrusion temperature was 200℃. The adhesive material was obtained by screw extrusion.

[0112] (4) Prepare surface layer 3:

[0113] Flax fiber is used as the warp and bamboo fiber as the weft, and the two are woven together to form the surface layer 3. The warp weaving density is 30 threads / cm and the weft weaving density is 25 threads / cm.

[0114] (5) Preparation of composite fabric materials:

[0115] The adhesive material obtained in step (3) is laid flat on one side surface of the base layer 1 obtained in step (1), and the surface layer 3 obtained in step (4) is covered on the adhesive material. Hot pressing is performed at a temperature of 170°C and a pressure of 0.4 MPa, so that the adhesive material melts and solidifies to form an adhesive layer 2 with a thickness of 100 μm, resulting in the following: Figure 2 The composite fabric material shown.

[0116] like Figure 2 As shown, the composite fabric material prepared in this embodiment includes a base layer 1, an adhesive layer 2, and a surface layer 3, which are stacked sequentially. The base layer is woven from core-sheath composite fibers, which include an inner core and a sheath layer enclosing the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber. The adhesive layer is made of modified carbon fiber / metal oxide nanoparticle composite epoxy resin. The surface layer is woven from warp and weft threads, with flax fiber as the warp and bamboo fiber as the weft. The weaving density of the core-sheath composite fibers is 10 threads / cm, the thickness of the adhesive layer is 100μm, the warp weaving density is 30 threads / cm, and the weft weaving density is 25 threads / cm.

[0117] Example 2

[0118] This embodiment provides a method for preparing a high-strength, wrinkle-resistant composite fabric material, such as... Figure 1 As shown, the preparation method specifically includes the following steps:

[0119] (1) Preparation of base layer 1:

[0120] Polyester fiber and acrylic multifilament are fed into a core-spun spinning device at a mass ratio of 2:1 for core-spun spinning. The yarn output speed is 23 m / min and the twist of the polyester fiber is 230 T / m. After core-spun spinning, a core-sheath composite fiber with an acrylic multifilament core and a polyester fiber sheath is obtained. The core-sheath composite fiber is woven to form the base layer 1 with a weaving density of 12 fibers / cm.

[0121] (2) Preparation of reinforcing materials:

[0122] Short carbon fibers with a chopped length of 4.2 mm and a single filament diameter of 6.3 μm were immersed in a 23 mmol / L sodium percarbonate solution for 58 min and then dried to obtain oxidized carbon fibers. Subsequently, the oxidized carbon fibers were immersed in an aluminate coupling agent solution with a mass fraction of 2.5 wt% for 38 min and then dried to obtain modified carbon fibers.

[0123] Aluminum hydroxide was dispersed in deionized water and stirred at 45°C to obtain an aluminum hydroxide solution with a molar concentration of 1.5 mol / L.

[0124] Modified carbon fiber and aluminum hydroxide solution were added into a microwave hydrothermal reactor. The pressure inside the microwave hydrothermal reactor was 2 MPa. The microwave hydrothermal reaction was carried out at 170℃ for 40 min. The mass ratio of modified carbon fiber to aluminum hydroxide in the aluminum hydroxide solution was 1:32. After the reaction was completed, the reaction product was calcined at 1050℃ for 1.8 h to obtain a modified and reinforced material composed of modified carbon fiber and aluminum oxide nanoparticles.

[0125] (3) Preparation of adhesive materials:

[0126] 30 parts of the reinforcing material obtained in step (2), 50 parts of epoxy resin, 15 parts of diethylenetriamine and 5 parts of KH550 coupling agent were put into a twin-screw extruder. The screw speed was set to 220 rpm and the extrusion temperature was 195°C. The adhesive material was obtained by screw extrusion.

[0127] (4) Prepare surface layer 3:

[0128] Flax fiber is used as the warp and bamboo fiber as the weft, and the two are woven together to form the surface layer 3. The warp weaving density is 32 threads / cm and the weft weaving density is 25 threads / cm.

[0129] (5) Preparation of composite fabric materials:

[0130] The adhesive material obtained in step (3) is laid flat on one side surface of the base layer 1 obtained in step (1), and the surface layer 3 obtained in step (4) is covered on the adhesive material. Hot pressing is performed at a temperature of 172°C and a pressure of 0.38 MPa, so that the adhesive material melts and solidifies to form an adhesive layer 2 with a thickness of 120 μm, resulting in the following: Figure 2 The composite fabric material shown.

[0131] like Figure 2 As shown, the composite fabric material prepared in this embodiment includes a base layer 1, an adhesive layer 2, and a surface layer 3 stacked sequentially. The base layer 1 is woven from core-sheath composite fibers, which include an inner core and a sheath layer enclosing the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber. The adhesive layer 2 is made of modified carbon fiber / metal oxide nanoparticle composite epoxy resin. The surface layer 3 is woven from warp and weft threads, with flax fiber as the warp and bamboo fiber as the weft. The weaving density of the core-sheath composite fibers is 12 threads / cm, the thickness of the adhesive layer 2 is 120 μm, the warp weaving density is 32 threads / cm, and the weft weaving density is 25 threads / cm.

[0132] Example 3

[0133] This embodiment provides a method for preparing a high-strength, wrinkle-resistant composite fabric material, such as... Figure 1 As shown, the preparation method specifically includes the following steps:

[0134] (1) Preparation of base layer 1:

[0135] Polyester fiber and acrylic multifilament are fed into a core-spun spinning device at a mass ratio of 2:1 for core-spun spinning. The yarn output speed is 25m / min and the twist of the polyester fiber is 250T / m. After core-spun spinning, a core-sheath composite fiber with an acrylic multifilament core and a polyester fiber sheath is obtained. The core-sheath composite fiber is woven to form the base layer 1 with a weaving density of 15 fibers / cm.

[0136] (2) Preparation of reinforcing materials:

[0137] Short carbon fibers with a chopped length of 4.5 mm and a single filament diameter of 6.5 μm were immersed in a 25 mmol / L potassium permanganate solution for 55 min and then dried to obtain oxidized carbon fibers. Subsequently, the oxidized carbon fibers were immersed in an aluminate coupling agent solution with a mass fraction of 3 wt% for 35 min and then dried to obtain modified carbon fibers.

[0138] Aluminum hydroxide was dispersed in deionized water and stirred evenly at 50°C to obtain an aluminum hydroxide solution with a molar concentration of 2 mol / L.

[0139] Modified carbon fiber and aluminum hydroxide solution were added into a microwave hydrothermal reactor. The pressure inside the microwave hydrothermal reactor was 3 MPa. The microwave hydrothermal reaction was carried out at 180℃ for 30 min. The mass ratio of modified carbon fiber to aluminum hydroxide in the aluminum hydroxide solution was 1:35. After the reaction was completed, the reaction product was calcined at 1100℃ for 1.5 h to obtain a modified and reinforced material composed of modified carbon fiber and aluminum oxide nanoparticles.

[0140] (3) Preparation of adhesive materials:

[0141] 25 parts of the reinforcing material obtained in step (2), 64 parts of epoxy resin, 10 parts of triethylenetetramine and 1 part of KH560 coupling agent were put into a twin-screw extruder. The screw speed was set to 250 rpm and the extrusion temperature was 190°C. The adhesive material was obtained by screw extrusion.

[0142] (4) Prepare surface layer 3:

[0143] Flax fiber is used as the warp and bamboo fiber as the weft, and the two are woven together to form the surface layer 3. The warp weaving density is 35 threads / cm and the weft weaving density is 30 threads / cm.

[0144] (5) Preparation of composite fabric materials:

[0145] The adhesive material obtained in step (3) is laid flat on one side surface of the base layer 1 obtained in step (1), and the surface layer 3 obtained in step (4) is covered on the adhesive material. Hot pressing is performed at a temperature of 175°C and a pressure of 0.35 MPa, so that the adhesive material melts and solidifies to form an adhesive layer 2 with a thickness of 130 μm, resulting in the following: Figure 2 The composite fabric material shown.

[0146] like Figure 2 As shown, the composite fabric material prepared in this embodiment includes a base layer 1, an adhesive layer 2, and a surface layer 3 stacked sequentially. The base layer 1 is woven from core-sheath composite fibers, which include an inner core and a sheath layer enclosing the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber. The adhesive layer 2 is made of modified carbon fiber / metal oxide nanoparticle composite epoxy resin. The surface layer 3 is woven from warp and weft threads, with flax fiber as the warp and bamboo fiber as the weft. The weaving density of the core-sheath composite fibers is 15 threads / cm, the thickness of the adhesive layer 2 is 130 μm, the warp weaving density is 35 threads / cm, and the weft weaving density is 30 threads / cm.

[0147] Example 4

[0148] This embodiment provides a method for preparing a high-strength, wrinkle-resistant composite fabric material, such as... Figure 1 As shown, the preparation method specifically includes the following steps:

[0149] (1) Preparation of base layer 1:

[0150] Polyester fiber and acrylic multifilament are fed into a core-spun spinning device at a mass ratio of 2.5:1 for core-spun spinning. The yarn output speed is 28m / min and the twist of the polyester fiber is 280T / m. After core-spun spinning, a core-sheath composite fiber with an acrylic multifilament core and a polyester fiber sheath is obtained. The core-sheath composite fiber is woven to form base layer 1 with a weaving density of 18 fibers / cm.

[0151] (2) Preparation of reinforcing materials:

[0152] Short carbon fibers with a chopped length of 4.8 mm and a single filament diameter of 6.7 μm were immersed in a 28 mmol / L potassium bisulfate solution for 53 min and then dried to obtain oxidized carbon fibers. Subsequently, the oxidized carbon fibers were immersed in an aluminate coupling agent solution with a mass fraction of 4 wt% for 32 min and then dried to obtain modified carbon fibers.

[0153] Aluminum hydroxide was dispersed in deionized water and stirred at 55°C to obtain an aluminum hydroxide solution with a molar concentration of 2 mol / L.

[0154] Modified carbon fiber and aluminum hydroxide solution were added into a microwave hydrothermal reactor. The pressure inside the microwave hydrothermal reactor was 3 MPa. The microwave hydrothermal reaction was carried out at 180℃ for 30 min. The mass ratio of modified carbon fiber to aluminum hydroxide in the aluminum hydroxide solution was 1:38. After the reaction was completed, the reaction product was calcined at 1150℃ for 1.2 h to obtain a modified and reinforced material composed of modified carbon fiber and aluminum oxide nanoparticles.

[0155] (3) Preparation of adhesive materials:

[0156] 20 parts of the reinforcing material obtained in step (2), 70 parts of epoxy resin, 5 parts of triethylenetetramine and 5 parts of KH570 coupling agent were put into a twin-screw extruder. The screw speed was set to 280 rpm and the extrusion temperature was 185°C. The adhesive material was obtained by screw extrusion.

[0157] (4) Prepare surface layer 3:

[0158] Flax fiber is used as the warp and bamboo fiber as the weft, and the two are woven together to form the surface layer 3. The warp weaving density is 38 threads / cm and the weft weaving density is 32 threads / cm.

[0159] (5) Preparation of composite fabric materials:

[0160] The adhesive material obtained in step (3) is laid flat on one side surface of the base layer 1 obtained in step (1), and the surface layer 3 obtained in step (4) is covered on the adhesive material. Hot pressing is performed at a temperature of 178°C and a pressure of 0.32 MPa, so that the adhesive material melts and solidifies to form an adhesive layer 2 with a thickness of 140 μm, resulting in the following: Figure 2 The composite fabric material shown.

[0161] like Figure 2 As shown, the composite fabric material prepared in this embodiment includes a base layer 1, an adhesive layer 2, and a surface layer 3 stacked sequentially. The base layer 1 is woven from core-sheath composite fibers, which include an inner core and a sheath layer enclosing the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber. The adhesive layer 2 is made of modified carbon fiber / metal oxide nanoparticle composite epoxy resin. The surface layer 3 is woven from warp and weft threads, with flax fiber as the warp and bamboo fiber as the weft. The weaving density of the core-sheath composite fibers is 18 threads / cm, the thickness of the adhesive layer 2 is 140 μm, the warp weaving density is 38 threads / cm, and the weft weaving density is 32 threads / cm.

[0162] Example 5

[0163] This embodiment provides a method for preparing a high-strength, wrinkle-resistant composite fabric material, such as... Figure 1 As shown, the preparation method specifically includes the following steps:

[0164] (1) Preparation of base layer 1:

[0165] Polyester fiber and acrylic multifilament are fed into a core-spun spinning device at a mass ratio of 3:1 for core-spun spinning. The yarn output speed is 30m / min and the twist of the polyester fiber is 300T / m. After core-spun spinning, a core-sheath composite fiber with an acrylic multifilament core and a polyester fiber sheath is obtained. The core-sheath composite fiber is woven to form the base layer 1 with a weaving density of 20 fibers / cm.

[0166] (2) Preparation of reinforcing materials:

[0167] Short carbon fibers with a chopped length of 5 mm and a single filament diameter of 7 μm were immersed in a 30 mmol / L peracetic acid solution for 50 min and then dried to obtain oxidized carbon fibers. Subsequently, the oxidized carbon fibers were immersed in an aluminate coupling agent solution with a mass fraction of 5 wt% for 30 min and then dried to obtain modified carbon fibers.

[0168] Aluminum hydroxide was dispersed in deionized water and stirred at 60°C to obtain an aluminum hydroxide solution with a molar concentration of 2.5 mol / L.

[0169] Modified carbon fiber and aluminum hydroxide solution were added into a microwave hydrothermal reactor. The pressure inside the microwave hydrothermal reactor was 4 MPa. The microwave hydrothermal reaction was carried out at 190℃ for 20 min. The mass ratio of modified carbon fiber to aluminum hydroxide in the aluminum hydroxide solution was 1:40. After the reaction was completed, the reaction product was calcined at 1200℃ for 1 h to obtain a modified and reinforced material composed of modified carbon fiber and aluminum oxide nanoparticles.

[0170] (3) Preparation of adhesive materials:

[0171] 22 parts of the reinforcing material obtained in step (2), 68 parts of epoxy resin, 7 parts of triethylenetetramine and 3 parts of KH550 coupling agent were put into a twin-screw extruder. The screw speed was set to 300 rpm and the extrusion temperature was 180°C. The adhesive material was obtained by screw extrusion.

[0172] (4) Prepare surface layer 3:

[0173] Flax fiber is used as the warp and bamboo fiber as the weft, and the two are woven together to form the surface layer 3. The warp weaving density is 40 threads / cm and the weft weaving density is 35 threads / cm.

[0174] (5) Preparation of composite fabric materials:

[0175] The adhesive material obtained in step (3) is laid flat on one side surface of the base layer 1 obtained in step (1), and the surface layer 3 obtained in step (4) is covered on the adhesive material. Hot pressing is performed at a temperature of 180°C and a pressure of 0.3 MPa, so that the adhesive material melts and solidifies to form an adhesive layer 2 with a thickness of 150 μm, resulting in the following: Figure 2 The composite fabric material shown.

[0176] like Figure 2 As shown, the composite fabric material prepared in this embodiment includes a base layer 1, an adhesive layer 2, and a surface layer 3 stacked sequentially. The base layer 1 is woven from core-sheath composite fibers, which include an inner core and a sheath layer enclosing the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber. The adhesive layer 2 is made of modified carbon fiber / metal oxide nanoparticle composite epoxy resin. The surface layer 3 is woven from warp and weft threads, with flax fiber as the warp and bamboo fiber as the weft. The weaving density of the core-sheath composite fibers is 20 threads / cm, the thickness of the adhesive layer 2 is 150 μm, the warp weaving density is 40 threads / cm, and the weft weaving density is 35 threads / cm.

[0177] Comparative Example 1

[0178] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the twist of the polyester fiber in step (1) is adjusted to 150T / m, while other process parameters and operating steps are exactly the same as in Example 1.

[0179] Comparative Example 2

[0180] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the twist of the polyester fiber in step (1) is adjusted to 350T / m, while other process parameters and operating steps are exactly the same as in Example 1.

[0181] Comparative Example 3

[0182] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the molar concentration of aluminum hydroxide in the aluminum hydroxide solution in step (2) is adjusted to 0.5 mol / L. Other process parameters and operating steps are exactly the same as in Example 1.

[0183] Comparative Example 4

[0184] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the molar concentration of aluminum hydroxide in the aluminum hydroxide solution in step (2) is adjusted to 3 mol / L. Other process parameters and operating steps are exactly the same as in Example 1.

[0185] Comparative Example 5

[0186] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the amount of reinforcing material added in step (3) is adjusted to 15 parts by weight, while other process parameters and operating steps are exactly the same as in Example 1.

[0187] Comparative Example 6

[0188] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the amount of reinforcing material added in step (3) is adjusted to 35 parts by weight, while other process parameters and operating steps are exactly the same as in Example 1.

[0189] Comparative Example 7

[0190] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the weaving density of the warp threads in step (4) is adjusted to 20 threads / cm, while the other process parameters and operating steps are exactly the same as in Example 1.

[0191] Comparative Example 8

[0192] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the weaving density of the warp threads in step (4) is adjusted to 50 threads / cm, while the other process parameters and operating steps are exactly the same as in Example 1.

[0193] Comparative Example 9

[0194] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the temperature of hot pressing in step (5) is adjusted to 160°C, while other process parameters and operating steps are exactly the same as in Example 1.

[0195] Comparative Example 10

[0196] This comparative example provides a method for preparing a composite fabric material. The difference from Example 1 is that the temperature of hot pressing in step (5) is adjusted to 190°C, while other process parameters and operating steps are exactly the same as in Example 1.

[0197] Comparative Example 11

[0198] This comparative example provides a method for preparing a fabric material. The difference between this comparative example and Example 1 is that steps (1), (2), (3) and (4) are omitted in this comparative example. The fabric material is woven only with flax fiber and bamboo fiber. Other process parameters and operation steps are exactly the same as in Example 1.

[0199] To better evaluate the comprehensive performance of the composite fabric materials prepared by the present invention, the composite fabric materials prepared in Examples 1-5 and Comparative Examples 1-11 were tested as follows:

[0200] (1) Flatness test:

[0201] According to GB / T13769-2009 "Test Method for Evaluating the Appearance Smoothness of Fabrics after Washing", the smoothness of the composite fabric materials prepared in Example 1 and Comparative Example 11 was tested. The smoothness of the fabric materials (such as...) was tested. Figure 5 (As shown) After washing repeatedly 10 times, lay flat to dry. The dried fabric should look like this. Figure 6 and Figure 7 As shown.

[0202] Depend on Figure 6 and Figure 7It can be clearly seen that the composite fabric material prepared in Example 1 can still maintain a high degree of flatness after washing and drying, which is almost the same as the flat state before washing; while the composite fabric material prepared in Comparative Example 11 has a lot of wrinkles after washing and drying, and it is difficult to fully restore after stretching. This shows that the composite fabric material prepared by the preparation method provided by the present invention has excellent anti-wrinkle ability.

[0203] (2) Breathability test:

[0204] According to GB / T5453-1997 "Textiles - Determination of air permeability of fabrics", the air permeability of the composite fabric materials prepared in Examples 1-5 and Comparative Examples 1-11 was tested, and the test results are shown in Table 1.

[0205] (3) Tensile property test:

[0206] According to GB / T24218.102-2022 "Textiles - Test Methods - Part 102: Determination of Tensile Elasticity", the composite fabrics prepared in Examples 1-5 and Comparative Examples 1-11 were tested using an electronic fabric tensile strength tester. The elastic recovery rate of the fabrics at a constant elongation of 5% was tested, and the test results are shown in Table 1.

[0207] (4) Crease recovery angle test:

[0208] According to the perpendicular method in GB / T3819-1997 "Textiles - Determination of Crease Recovery - Recovery Angle Method", the crease recovery angle of the composite fabrics prepared in Examples 1-5 and Comparative Examples 1-11 was tested using a fabric crease elasticity meter. The test results are shown in Table 1.

[0209] The crease recovery angles of the composite fabric materials prepared in Example 1 and Comparative Example 11 are as follows: Figure 3 and Figure 4 As shown, by Figure 3 and Figure 4 The comparison shows that the crease recovery angle of the composite fabric material prepared in Example 1 is greater than that of the composite fabric material prepared in Comparative Example 11. The larger the crease recovery angle, the stronger the wrinkle resistance of the composite fabric material.

[0210] (5) Bond strength test:

[0211] According to the standard FZ / T01085-2018 "Test Method for Peel Strength of Adhesive Liners", the peel strength of the composite fabric materials prepared in Examples 1-5 and Comparative Examples 1-11 was tested using an isorheological elongation tester. The test results are shown in Table 1.

[0212] Table 1. Performance test results of the composite fabric materials prepared in Examples 1-5 and Comparative Examples 1-11

[0213]

[0214] As can be seen from the test data provided in Table 1, the composite fabric materials prepared in Examples 1-5 of the present invention have excellent breathability, anti-wrinkle effect and bonding strength, which can greatly meet people's stringent requirements for clothing fabrics and have great market promotion value and wide application scenarios.

[0215] The test data from Example 1, Comparative Example 1, and Comparative Example 2 show that the elastic recovery rate and crease recovery angle in Comparative Example 1 are both lower than those in Example 1. While the elastic recovery rate and crease recovery angle in Comparative Example 2 are comparable to those in Example 1, its air permeability is significantly lower. This is because the twist of the polyester fibers in Comparative Example 1 is too low, resulting in a looser skin structure. Under external force, the polyester fibers are prone to relative displacement, leading to irreversible deformation of the core-skin composite fibers and thus reducing the wrinkle recovery ability of the composite fabric. Conversely, the excessive twist of the polyester fibers in Comparative Example 2 reduces the initial modulus and breaking strength of the composite fabric, and also affects its air permeability.

[0216] The test data from Examples 1, 3, and 4 show that the elastic recovery rate, crease recovery angle, and peel strength of Comparative Examples 3 and 4 are all lower than those of Example 1, especially the peel strength, which is significantly lower. This is because the molar concentration of the metal precursor in Comparative Example 3 is too low, resulting in a smaller content of metal oxide nanoparticles, which cannot effectively exert their mechanical reinforcing effect, thus affecting the interfacial bonding strength between the base layer 1 and the surface layer 3. In Comparative Example 4, the molar concentration of the metal precursor is too high, which disrupts the continuity of the adhesive layer 2, leading to a certain degree of decrease in the tensile and flexural strength of the adhesive layer 2. Furthermore, the excessively high content of metal oxide nanoparticles easily leads to agglomeration and poor dispersibility, forming stress defect points in the adhesive layer 2. These defects are easily destroyed under external stress, resulting in a decrease in the interfacial properties of the composite fabric material, making it easy for the base layer 1 and the surface layer 3 to detach under external force.

[0217] The test data from Examples 1, 5, and 6 show that the elastic recovery rate, crease recovery angle, and peel strength of Comparative Examples 5 and 6 are all lower than those of Example 1, especially the peel strength, which is significantly lower. This is because the amount of reinforcing material added in Comparative Example 5 is too low, failing to effectively exert the interfacial reinforcement effect of the reinforcing material, thus affecting the interfacial bonding strength between the base layer 1 and the surface layer 3. In contrast, the amount of reinforcing material added in Comparative Example 6 is too high, resulting in excessive viscosity of the adhesive material system, making it difficult to disperse evenly and prone to generating air bubbles. This also leads to poor wetting of the surface layer 3 and the base layer 1, resulting in numerous air void defects in the cured adhesive layer 2, ultimately causing a decrease in the mechanical properties of the final adhesive layer 2.

[0218] The test data from Example 1, Comparative Example 7, and Comparative Example 8 show that the air permeability, elastic recovery rate, and crease recovery angle of Comparative Example 7 and Comparative Example 8 are all lower than those of Example 1. This is because the warp weaving density in Comparative Example 7 is too low, resulting in an overly loose structure of surface layer 3, lower rigidity, and insufficient mechanical properties. Conversely, the warp weaving density in Comparative Example 8 is too high, leading to excessive friction between the warp and weft threads, which affects the deformation recovery ability of the composite fabric material and ultimately reduces its wrinkle resistance.

[0219] As can be seen from the test data of Example 1, Comparative Example 9 and Comparative Example 10, the elastic recovery rate and crease recovery angle of Comparative Example 9 and Comparative Example 10 are both smaller than those of Example 1. This is because the hot-pressing temperature in Comparative Example 9 is too low and the hot-pressing temperature in Comparative Example 10 is too high, which affects the interfacial bonding strength and mechanical strength between the base layer 1 and the surface layer 3.

[0220] As can be seen from the test data of Example 1 and Comparative Example 11, the elastic recovery rate and crease recovery angle of Comparative Example 11 are much smaller than those of Example 1. This is because the present invention adopts a composite structure of base layer 1, adhesive layer 2 and surface layer 3. The adhesive layer 2 imparts the deformation recovery ability of base layer 1 to surface layer 3, so that surface layer 3 has a certain anti-wrinkle effect. At the same time, the external force on surface layer 3 is promptly transmitted to base layer 1 to prevent surface layer 3 from developing irreversible wrinkles due to long-term external force. Therefore, on the basis of the high strength of surface layer 3 itself, the composite fabric material is also given an overall anti-wrinkle effect.

[0221] The applicant declares that the above description is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Those skilled in the art should understand that any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention fall within the protection and disclosure scope of the present invention.

Claims

1. A high-strength, wrinkle-resistant composite fabric material, characterized in that, The composite fabric material comprises a base layer, an adhesive layer, and a surface layer stacked sequentially. The base layer is woven from core-sheath composite fibers, which include an inner core and a sheath layer that wraps the inner core. The inner core is acrylic multifilament, and the sheath layer is polyester fiber. The adhesive layer is made of a modified carbon fiber / metal oxide nanoparticle composite epoxy resin. The surface layer is formed by weaving warp and weft threads in both directions, wherein the warp threads are flax fibers and the weft threads are bamboo fibers; The weaving density of the warp threads is 30-40 threads / cm; The twist of the polyester fiber is 200-300 T / m; The composite fabric material was prepared using the following method: (I) Core-spun yarn with acrylic multifilament as the inner core and polyester fiber as the outer layer to obtain core-sheath composite fiber, and then weave the core-sheath composite fiber to form the base layer; (II) Preparation of a reinforcing material composed of modified carbon fiber and metal oxide nanoparticles: The reinforcing material, epoxy resin, curing agent and coupling agent are mixed and extruded by screw extrusion to obtain a bonding material; (III) The surface layer is formed by weaving flax fiber as warp and bamboo fiber as weft. (IV) Lay an adhesive material on one side of the base layer, cover the adhesive material with a surface layer, and then heat-press and bond it to obtain the composite fabric material; In step (II), the reinforcing material is prepared using the following method: (1) The carbon fiber was immersed in the oxidant solution and the coupling agent solution in sequence, and the modified carbon fiber was obtained after taking it out; The metal precursor was dispersed in deionized water and stirred until homogeneous to obtain a metal precursor solution. (2) The modified carbon fiber is mixed with the metal precursor solution and then subjected to microwave hydrothermal reaction. After the reaction is completed, it is calcined to obtain the reinforcing material. The mass ratio of the modified carbon fiber to the metal precursor in the metal precursor solution is 1:(30-40). In step (II), the reinforcing material, epoxy resin, curing agent, and coupling agent are added in the following proportions by weight: 20-30 parts of reinforcing material; 50-70 parts epoxy resin; 5-15 parts of curing agent; 1-5 parts coupling agent; In step (IV), the temperature of the hot-press bonding is 170-180℃.

2. The high-strength wrinkle-resistant composite fabric material according to claim 1, characterized in that, The weaving density of the core-sheath composite fiber is 10-20 fibers / cm; The thickness of the adhesive layer is 100-150 μm; The weft yarn weaving density is 25-35 threads / cm.

3. The high-strength wrinkle-resistant composite fabric material according to claim 1, characterized in that, In step (I), the core-sheath composite fiber is prepared in a core-spun yarn device; In the core-sheath composite fiber, the mass ratio of the polyester fiber to the acrylic multifilament is (1.5-3):1; The yarn output speed of the core-spun spinning device is 20-30 m / min.

4. The high-strength wrinkle-resistant composite fabric material according to claim 1, characterized in that, In step (1), the carbon fiber is short-cut carbon fiber; The short cut length of the carbon fiber is 4-5 mm; The diameter of the single filament of the carbon fiber is 6-7 μm; Immerse in the oxidant solution for 50-60 minutes; The concentration of the oxidant solution is 20-30 mmol / L; The oxidizing agent solution is any one or a combination of at least two of the following: hydrogen peroxide solution, peracetic acid solution, sodium percarbonate solution, potassium permanganate solution, and potassium hydrogen sulfate solution. Soak in the coupling agent solution for 30-40 minutes; The coupling agent solution contains 2-5 wt% coupling agent. The molar concentration of the metal precursor in the metal precursor solution is 1-2.5 mol / L; The ambient temperature during the stirring process is 40-60℃; The metal precursor is aluminum hydroxide, and the resulting reinforcing material is a modified carbon fiber / nano-alumina composite material.

5. The high-strength wrinkle-resistant composite fabric material according to claim 1, characterized in that, In step (2), the microwave hydrothermal reaction is carried out in a microwave hydrothermal reactor; The microwave hydrothermal reaction time is 20-50 minutes. The temperature of the microwave hydrothermal reaction is 160-190℃; The pressure of the microwave hydrothermal reaction is 1-4 MPa; The calcination temperature is 1000-1200℃; The calcination time is 1-2 hours.

6. The high-strength wrinkle-resistant composite fabric material according to claim 1, characterized in that, In step (II), the screw extrusion process is carried out in a twin-screw extruder; The screw speed of the twin-screw extruder is 200-300 rpm; The temperature of the twin-screw extruder is 180-200℃.

7. The high-strength wrinkle-resistant composite fabric material according to claim 1, characterized in that, In step (IV), the pressure of the hot-press bonding is 0.3-0.4 MPa.

8. A high-strength anti-wrinkle fabric, characterized in that, The high-strength wrinkle-resistant fabric is obtained by cutting the high-strength wrinkle-resistant composite fabric material as described in any one of claims 1 to 7.

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