Stab-proof fabric with circular winding-star-shaped laminated composite structure and preparation method thereof

Abstract

The present invention discloses a stab-proof fabric with a circular wound-star-shaped laminated composite structure and a preparation method thereof, and relates to the technical field of stab-proof fabric preparation; the stab-proof fabric with a circular wound-star-shaped laminated composite structure includes a stab-proof armor plate, which is formed by stacking and bonding a winding structure and a laminated structure; the winding structure is a spiral plate obtained by winding a reinforced fiber slice into a rod shape, and the laminated structure is a laminated plate obtained by cutting a reinforced fiber laminate; a plurality of stab-proof armor plates are laid flat and adjacent stab-proof armor plates are arranged alternately in front and back, and the shapes of adjacent stab-proof armor plates are matched and bonded to form a stab-proof layer. The stab-proof fabric of the present invention has excellent stab-proof performance. Under the action of the circular wound structure, the knife tip is blunted, and the energy is dissipated to a larger area, thereby improving the stab-proof performance. The stab-proof armor plate formed by combining the circular wound structure and the star-shaped laminated structure effectively improves the gap stab-proof performance of the stab-proof armor plate.

Description

Technical Field

[0001] The present invention belongs to the technical field of stab-proof fabric preparation, and in particular relates to a stab-proof fabric with a circular winding-star-shaped laminated composite structure and a preparation method thereof. Background Art

[0002] Stab-resistant clothing, designed to protect vital organs from sharp objects like bayonets and daggers, has attracted increasing attention from researchers worldwide in recent years. Currently, stab-resistant clothing is primarily classified into three types: rigid, semi-rigid, and soft. Semi-rigid materials, consisting of rigid armor plates and a flexible base fabric, are widely used in stab-resistant clothing due to their balanced performance and comfort.

[0003] Existing semi-rigid stab-resistant materials still have shortcomings that affect their stab-resistant performance. For example, Chinese Patent (CN201088147U) discloses a protective body bonded with metal sheets for use in making stab-resistant clothing. This protective body is formed by bonding multiple metal sheets to a garment sheet. The resulting stab-resistant clothing is easy to fold, lightweight, and high-strength. However, using metal sheets as the main stab-resistant material significantly increases the weight of the clothing. In addition, this utility model patent improves foldability by changing the shape of the metal sheets, but the linear gaps through them can reduce gap stab resistance. Chinese Patent (CN105544228B) discloses a Z-shaped resin-molded flexible stab-resistant fabric and its preparation method. This fabric uses hot-melt adhesive to adhere Z-shaped resin solids to the surface of the garment fabric in a regular pattern, resulting in reduced weight, comfort, and flexibility. However, relying solely on resin to resist knife impact requires a relatively large thickness (10.2 mm) to meet stab-resistant standards. A Chinese patent (CN213021229U) discloses a new type of bulletproof / stab-proof clothing. The fabric of the protective clothing body includes superimposed fabric layers, and cavities are formed between the fabric layers to install staggered bulletproof / stab-proof armor plates. Compared with traditional bulletproof / stab-proof clothing, the entire protective clothing fabric layer is more close-fitting, more flexible, and more comfortable to wear, and small gaps are formed between the bulletproof / stab-proof armor plates, which are more conducive to ventilation, perspiration and heat dissipation, and more comfortable to wear. However, the resulting cavity will increase the thickness of the overall protective clothing. The non-armor plate installation space in the cavity does not have stab-proof performance. In addition, a knife can easily penetrate the gap between adjacent armor plates from an oblique direction.

[0004] The present invention proposes a stab-proof fabric with a circular winding-star-shaped laminated composite structure and a preparation method thereof. The stab-proof armor plate formed by combining a circular winding structure and a star-shaped laminated structure effectively improves the gap stab-proof performance of the stab-proof armor plate and improves the overall stab-proof performance of the stab-proof fabric. Summary of the Invention

[0005] The purpose of the present invention is to provide a stab-proof fabric with a circular winding-star-shaped laminated composite structure and a preparation method thereof, so as to solve the problems of high cost, large thickness, low energy absorption rate and the like in the prior art stab-proof composite materials mentioned in the above background technology.

[0006] To achieve the above objectives, the present invention adopts the following technical solutions:

[0007] The first aspect of the present invention provides a stab-proof fabric with a circular winding-star-shaped laminated composite structure, comprising a stab-proof armor plate,

[0008] The stab-proof armor plate is formed by stacking and bonding a winding structure and a laminated structure;

[0009] The winding structure is a spiral sheet obtained by winding a reinforcing fiber slice into a rod shape, the cross section of the winding structure is a symmetrical figure, the laminated structure is a laminated board obtained by cutting a reinforcing fiber laminate, and the cross section of the laminated structure is the shape of a middle gap surrounded by four winding structures laid flat;

[0010] A plurality of stab-proof nail plates are laid flat and adjacent stab-proof nail plates are arranged alternately in front and back, and the adjacent stab-proof nail plates are matched in shape and bonded to form a stab-proof layer; the stab-proof fabric is provided with at least one stab-proof layer.

[0011] Preferably, the winding structure is a circular winding structure, and the laminated structure is a star-shaped laminated structure;

[0012] The star-shaped cross section of the star-shaped laminated structure is a symmetrical figure obtained by removing the area surrounded by four quarter arcs of the same radius and the circumference of the circular cross section from the circular cross section of the circular winding structure.

[0013] Preferably, it further comprises a base cloth, the stab-proof layer is bonded to the base cloth, and the base cloth is made of a fiber or fabric selected from aramid, ultra-high molecular weight polyethylene, carbon fiber and basalt.

[0014] The second aspect of the present invention provides a method for preparing a stab-resistant fabric having a circular winding-star-shaped laminated composite structure, comprising the following steps:

[0015] S1, preparation of circular coiled structure;

[0016] The reinforcing fiber fabric is cut into long strips, and the long strips of reinforcing fiber fabric are wound into a round rod preform by a motor; the round rod preform is placed in a cylindrical mold and heated and cured to form a composite material round rod; the composite material round rod is evenly cut to obtain a plurality of circular wound structures;

[0017] S2, preparation of star-shaped laminated structures;

[0018] After bonding and stacking the reinforcing fiber fabrics, the composite laminates are pressurized and cured on a flat hot press to form the composite laminates; the composite laminates are cut into star shapes to obtain star-shaped laminate structures;

[0019] S3. Preparation of stab-resistant nail plates;

[0020] The lower portion of the circular wound structure and the upper portion of the star-shaped laminated structure are bonded together by a matrix resin to obtain a stab-resistant nail plate;

[0021] S4. Preparation of stab-resistant fabric with circular winding-star-shaped laminated composite structure;

[0022] A plurality of stab-proof armor plates are alternately bonded one by one on a base fabric through a matrix resin to form an array, thereby obtaining a stab-proof fabric with a circular winding-star-shaped laminated composite structure.

[0023] Preferably, the width of the long strip reinforcing fiber fabric in S1 is 10 to 20 cm, and the length is 180 to 200 cm.

[0024] Preferably, the winding in S1 is a round rod preform, specifically as follows:

[0025] Two core shafts clamp one end of the fabric, and two differential motors with opposite directions are connected to the two ends of the core shaft to rotate and wind the reinforced fiber fabric to form a round rod preform, and then the round rod is pulled out.

[0026] Furthermore, the core shaft is a stainless steel round rod; to avoid a cavity inside the round rod preform, the core shaft can also be a pinhole, the pinhole is connected to a propeller, and when the pinhole is pulled out, the propeller extrude the matrix resin to fill the cavity.

[0027] Preferably, the reinforcing fiber fabric in S1 is a non-woven fabric or a unidirectional prepreg.

[0028] Preferably, the heating and curing in S1 to form the composite material round rod is specifically:

[0029] When the reinforcing fiber fabric is a non-woven fabric, a mold release agent is sprayed on the inner wall of a cylindrical mold, a round rod preform is placed in the cylindrical mold, and a vacuum pump is used to completely impregnate the round rod preform with the matrix resin. The preform is then placed in a vacuum oven. In the vacuum oven, vacuum degassing is first performed at 25° C. for 1 hour, and then curing is performed at a temperature of 60 to 120° C. for 4 to 8 hours before demolding to form a composite material round rod.

[0030] When the reinforcing fiber fabric is a unidirectional prepreg, a release agent is sprayed on the inner wall of a cylindrical mold, and the round rod preform is placed in the cylindrical mold and then placed together in a vacuum oven; it is heated at 80°C in the vacuum oven for 30 minutes, then heated to 120-150°C and kept warm for 1-2 hours, and then naturally cooled to 60°C before demolding to form a composite material round rod.

[0031] Preferably, the reinforcing fiber fabric in S2 is one or more of plain, twill and unidirectional pure fabrics or prepregs.

[0032] Preferably, the pressurized curing in S2 is formed into a laminate, specifically:

[0033] When the reinforcing fiber is pure fabric, a release agent is sprayed on the surface of the flat mold, and the pure fabric is evenly brushed with matrix resin and laid layer by layer between the flat molds; the carbon fiber laminate is obtained by curing it in a flat hot press at a pressure of 0.5 to 2 MPa and a temperature of 60 to 120°C for 4 to 8 hours, and then cooling and demoulding.

[0034] When the reinforcing fiber is a prepreg, a release agent is sprayed on the surface of a flat mold, and the prepreg is sequentially layered and placed between the flat molds; the prepreg is heated at 120-150°C for 1-2 hours using a flat hot press at a pressure of 0.5-2 MPa, and then naturally cooled to 60°C before demoulding to obtain a carbon fiber laminate.

[0035] Preferably, the circular wound structure and the star-shaped laminated structure have the same thickness, which is 1 to 3 mm.

[0036] Preferably, the circular cross-section radius of the circular winding structure is 15 to 30 mm.

[0037] Preferably, the matrix resin is E51 epoxy resin.

[0038] Preferably, further comprising S5;

[0039] S5. Alternately bonding a plurality of stab-proof armor plates on the stab-proof layer with the matrix resin to form an array, thereby obtaining a stab-proof fabric with a multi-layer circular winding-star-shaped laminated composite structure.

[0040] Compared with the prior art, the present invention has the following beneficial effects:

[0041] (1) The circular wound-star-shaped laminated composite structure of the present invention has excellent stab-proof performance. The wound material can blunt the tip of the knife and dissipate the energy over a larger area. At the same time, the laminated material maintains structural stability, which can significantly improve the stab-proof performance.

[0042] (2) In the stab-proof fabric of the circular winding-star-shaped laminated composite structure of the present invention, the reinforcement of the winding material and the laminated material are both high-performance fibers, which have high strength and cutting resistance and can greatly absorb puncture energy.

[0043] (3) The stab-proof fabric of the circular winding-star-shaped laminated composite structure in the present invention adopts a stab-proof armor plate formed by combining a circular winding structure and a star-shaped laminated structure, which effectively improves the gap stab-proof performance of the stab-proof armor plate.

[0044] (4) The stab-proof fabric of the circular winding-star-shaped laminated composite structure in the present invention can reduce the thickness of the overall stab-proof material, greatly reducing the cost and thickness of the stab-proof clothing.

[0045] (5) The stab-proof fabric of the circular winding-star-shaped laminated composite structure of the present invention can be used to prepare products in different fields by controlling the thickness and diameter of the winding and laminated structure, including military protective clothing, security clothing, and anti-cut special work clothing. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 Schematic diagram of the structure of the stab-proof fabric with a circular winding-star-shaped laminated composite structure in the present invention;

[0047] Figure 2 A top view of the circular wound structure and the star-shaped laminated structure of the present invention;

[0048] Figure 3 Schematic diagram of the structure of the circular winding-star-shaped laminated composite structure of the present invention;

[0049] Figure 4 Schematic diagram of the mechanism of the circular winding structure in the present invention for blunting the tip of a sharp object;

[0050] Figure 5 Schematic diagram of the gap puncture prevention of the circular winding-star-shaped laminated composite structure of the present invention;

[0051] Figure 6 A comparison diagram of the crack penetration simulation results of the composite structure of the present invention and the existing overlap structure;

[0052] Figure 7 This is a quasi-static puncture load-displacement curve diagram of the circular winding-star-shaped laminated composite structure of the present invention;

[0053] Figure 8 This is a dynamic puncture load-time curve diagram of the circular winding-star-shaped laminated composite structure of the present invention;

[0054] In the figure: 1. Circular winding structure; 2. Star-shaped laminated structure; 3. Base fabric; 4. Gap area. DETAILED DESCRIPTION

[0055] The following will provide a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0056] Example 1:

[0057] In this embodiment, the reinforcing fiber fabric of the circular winding structure 1 is a carbon fiber unidirectional prepreg with a surface density of 150g / m 2 , thickness is 0.14mm. Star-shaped laminated structure 2 uses carbon fiber plain prepreg with a surface density of 200g / m2 and a thickness of 0.22mm. The matrix resin is epoxy resin E51. Base fabric 3 uses aramid plain woven fabric with a surface density of 200g / m 2 The warp and weft density is 90×90 (roots / 10cm) and the thickness is 0.26mm.

[0058] The preparation process of the stab-proof fabric is as follows:

[0059] (1) Cut the carbon fiber unidirectional prepreg into pieces of 231 cm long and 10 cm wide, with the length direction being the fiber direction. Two motors symmetrically hold two round rods with a diameter of 1.5 mm, and two adjacent round rods clamp one end of the unidirectional prepreg. Use the motor to rotate and wind to form a composite material round rod preform with a diameter of 2 cm. Place the preform in a cylindrical mold, heat it in an oven at 80°C for 30 minutes, then heat it to 130°C and keep it warm for 1.5 hours, then naturally cool it to 60°C and demold it to obtain a wound composite material round rod. Figure 2 As shown in (a), the composite material is cut into a wound disc with a diameter of 2 cm and a thickness of 2 mm by a diamond wire saw.

[0060] (2) Cut the carbon fiber plain weave prepreg and carbon fiber unidirectional prepreg into 30cm×30cm size, spray the release agent on the surface of the flat mold, and cut the carbon fiber plain weave prepreg and carbon fiber unidirectional prepreg into 30cm×30cm size. 10 -Plain weave layers are placed between flat plate molds. After heating at 130℃ for 1.5h with a pressure of 0.5MPa using a flat hot press, the laminate is naturally cooled to 60℃ and then demoulded to obtain a carbon fiber laminate. Figure 2 As shown in (b), the composite material is cut into star-shaped laminates with a diameter of 2 cm and a thickness of 2 mm by a diamond wire saw.

[0061] (3) Figure 3 As shown, the wound composite material disc and the star-shaped laminated composite material are bonded by epoxy resin, and the epoxy resin is filled into the cavity of the wound composite material by negative pressure, thereby finally forming a circular wound-star-shaped laminated composite structure.

[0062] (4) Using resin to alternately bond the composite structure on the aramid woven fabric to form a stab-proof fabric with a circular winding-star-shaped laminated composite structure, such as Figure 1 shown.

[0063] The surface density of the stab-proof fabric in this embodiment is only 6266.78g / m2, and the protection area is 0.25m 2 The weight is only 1.57kg and the thickness is 4mm.

[0064] The protective fabric produced in this example was tested using the GA68-2019 Public Security Industry Standard for Police Stab-Resistant Clothing. The results demonstrated that the protective fabric fully met the technical requirements for Class A stab-resistant clothing as specified in the standard. Furthermore, it met the high-energy level protection level 1 requirement of the NIJ Standard-0115.00 for human stab-resistant clothing, demonstrating no penetration.

[0065] Example 2:

[0066] In this embodiment, the reinforcing fiber fabric of the circular winding structure 1 is 12K carbon fiber flat cloth with a surface density of 300g / m 2 , with a thickness of 0.17mm. The reinforcing fiber of the star-shaped laminated structure 2 is 3K carbon fiber plain woven fabric with a surface density of 240g / m 2 , thickness is 0.32mm, warp and weft density is 60×60 (threads / 10cm). Base fabric 3 is made of basalt fiber plain woven fabric with a surface density of 200g / m 2 The warp and weft density is 100×100 (threads / 10cm), the thickness is 0.18mm, and the resin is epoxy resin E51.

[0067] The preparation process of the stab-proof fabric is as follows:

[0068] (1) Evenly mix epoxy resin and curing agent in a mass ratio of 3:1 and pour into the impregnation tank, and cut the carbon fiber non-woven fabric into pieces with a length of 190 cm and a width of 10 cm. Two motors symmetrically fix two stainless steel needles with a diameter of 1.5 mm and a length of 150 mm to clamp one end of the fabric. The motor rotates to form a wound composite material round rod preform with a diameter of 30 cm. Connect one end of the two stainless steel needles to the syringe and fix them on the injection pump. Inject epoxy resin into the syringe, start the injection pump and slowly withdraw the needle to obtain a dense preform. Place the preform in a cylindrical mold, degas at 25°C for 1 hour in a vacuum oven, and heat at 60°C for 8 hours to solidify it into a composite material round rod. Figure 2 As shown in (a), the composite material is cut into a wound disc with a diameter of 3 cm and a thickness of 2 mm by a diamond wire saw.

[0069] (2) Cut the carbon fiber plain woven fabric into a size of 30cm×30cm, and evenly coat the mixed resin on 8 layers of carbon fiber cloth. Place the carbon fiber cloth in a two-layer flat mold and cure it on a flat hot press at a pressure of 0.5MPa and a temperature of 60℃ for 8h to obtain a carbon fiber laminate. Figure 2 As shown in (b), the composite material is cut into star-shaped laminates with a diameter of 3 cm and a thickness of 2 mm by a diamond wire cutting machine.

[0070] (3) Figure 3As shown, the wound composite material disc and the star-shaped laminated composite material are bonded by epoxy resin to form a circular wound-star-shaped laminated composite structure.

[0071] (4) Figure 1 As shown, the composite structure is alternately bonded to the basalt woven fabric using resin to form a stab-proof fabric with a circular winding-star-shaped laminated composite structure.

[0072] The surface density of the stab-proof fabric in this embodiment is only 6029.83 g / m 2 , protection area is 0.25m 2 The weight is only 1.51kg and the thickness is 4mm.

[0073] The protective fabric produced in this example was tested using the GA68-2019 Public Security Industry Standard for Police Stab-Resistant Clothing. The results demonstrated that the protective fabric fully met the technical requirements for Class A stab-resistant clothing as specified in the standard. Furthermore, it met the high-energy level protection level 1 requirement of the NIJ Standard-0115.00 for human stab-resistant clothing, demonstrating no penetration.

[0074] Example 3:

[0075] In this embodiment, the reinforcing fiber fabric of the circular winding structure 1 is 12K carbon fiber flat cloth with a surface density of 300g / m 2 , with a thickness of 0.17mm. The star-shaped laminated structure 2 uses carbon fiber plain prepreg and carbon fiber unidirectional prepreg, with thicknesses of 0.22mm and 0.14mm respectively. The base fabric 3 uses ultra-high molecular weight polyethylene plain woven fabric with a surface density of 130g / m 2 The warp and weft density is 90×90 (threads / 10cm), the thickness is 0.24mm, and the resin is epoxy resin E51.

[0076] The preparation process of the stab-proof fabric is as follows:

[0077] (1) Evenly mix epoxy resin and curing agent in a mass ratio of 3:1 and pour into the impregnation tank, and cut the carbon fiber non-woven fabric into pieces with a length of 190 cm and a width of 10 cm. Two motors symmetrically fix two stainless steel needles with a diameter of 1.5 mm and a length of 150 mm to clamp one end of the fabric. The motor rotates to form a wound composite material round rod preform with a diameter of 30 cm. Connect one end of the two stainless steel needles to the syringe and fix them on the injection pump. Inject epoxy resin into the syringe, start the injection pump and slowly withdraw the needle to obtain a dense preform. Place the preform in a cylindrical mold, degas at 25°C for 1 hour in a vacuum oven, and heat at 60°C for 8 hours to solidify it into a composite material round rod. Figure 2 As shown in (a), the composite material is cut into a wound disc with a diameter of 3 cm and a thickness of 2 mm by a diamond wire saw.

[0078] (2) Cut the carbon fiber plain weave prepreg and carbon fiber unidirectional prepreg into 30cm×30cm size, spray the release agent on the surface of the flat mold, and cut the carbon fiber plain weave prepreg and carbon fiber unidirectional prepreg into 30cm×30cm size. 10 -Plain weave layers are placed between flat plate molds. After heating at 130℃ for 1.5h with a pressure of 0.5MPa using a flat hot press, the laminate is naturally cooled to 60℃ and then demoulded to obtain a carbon fiber laminate. Figure 2 As shown in (b), the composite material is cut into star-shaped laminates with a diameter of 3 cm and a thickness of 2 mm by a diamond wire cutting machine.

[0079] (3) Figure 3 As shown, the wound composite material disc and the star-shaped laminated composite material are bonded by epoxy resin to form a circular wound-star-shaped laminated composite structure.

[0080] (4) Figure 1 As shown, the composite structure is alternately bonded to the ultra-high molecular weight polyethylene plain woven fabric using resin to form a stab-proof fabric with a circular winding-star-shaped laminated composite structure.

[0081] The surface density of the stab-proof fabric in this embodiment is only 6140.19 g / m 2 , protection area is 0.25m 2 The weight is only 1.53kg and the thickness is 4mm.

[0082] The protective fabric produced in this example was tested using the GA68-2019 Public Security Industry Standard for Police Stab-Resistant Clothing. The results demonstrated that the protective fabric fully met the technical requirements for Class A stab-resistant clothing as specified in the standard. Furthermore, it met the high-energy level protection level 1 requirement of the NIJ Standard-0115.00 for human stab-resistant clothing, demonstrating no penetration.

[0083] Example 4:

[0084] In this embodiment, the circular winding structure 1 uses carbon fiber unidirectional prepreg with a thickness of 0.135 mm. The reinforcing fiber of the star-shaped laminated structure 2 is 3K carbon fiber plain woven fabric with an area density of 240 g / m 2 , thickness is 0.32mm, warp and weft density is 60×60 (threads / 10cm). The matrix resin is epoxy resin E51. The base fabric 3 is aramid plain weave fabric with a surface density of 200g / m 2 The warp and weft density is 90×90 (roots / 10cm) and the thickness is 0.26mm.

[0085] The preparation process of the stab-proof fabric is as follows:

[0086] (1) Cut the carbon fiber unidirectional prepreg into pieces of 231 cm long and 10 cm wide, with the length direction being the fiber direction. Two motors symmetrically hold two round rods with a diameter of 1.5 mm, and two adjacent round rods clamp one end of the unidirectional prepreg. Use the motor to rotate and wind to form a composite material round rod preform with a diameter of 2 cm. Place the preform in a cylindrical mold, heat it in an oven at 80°C for 30 minutes, then heat it to 130°C and keep it warm for 1.5 hours, then naturally cool it to 60°C and demold it to obtain a wound composite material round rod. Figure 2 As shown in (a), the composite material is cut into a wound disc with a diameter of 2 cm and a thickness of 2 mm by a diamond wire saw.

[0087] (2) Cut the carbon fiber plain woven fabric into a size of 30cm×30cm, and evenly coat the mixed resin on 8 layers of carbon fiber cloth. Place the carbon fiber cloth in a two-layer flat mold and cure it on a flat hot press at a pressure of 0.5MPa and a temperature of 60℃ for 8h to obtain a carbon fiber laminate. Figure 2 As shown in (b), the composite material is cut into star-shaped laminates with a diameter of 2 cm and a thickness of 2 mm by a diamond wire cutting machine.

[0088] (3) Figure 3 As shown, the wound composite material disc and the star-shaped laminated composite material are bonded by epoxy resin to form a circular wound-star-shaped laminated composite structure.

[0089] (4) Figure 1 As shown, the composite structure is alternately bonded to the aramid woven fabric using resin to form a stab-proof fabric with a circular winding-star-shaped laminated composite structure.

[0090] The surface density of the stab-proof fabric in this embodiment is only 5973.24 g / m 2 , protection area is 0.25m 2 The weight is only 1.49kg and the thickness is 4mm.

[0091] The protective fabric produced in this example was tested using the GA68-2019 Public Security Industry Standard for Police Stab-Resistant Clothing. The results demonstrated that the protective fabric fully met the technical requirements for Class A stab-resistant clothing as specified in the standard. Furthermore, it met the high-energy level protection level 1 requirement of the NIJ Standard-0115.00 for human stab-resistant clothing, demonstrating no penetration.

[0092] Experimental verification:

[0093] The stab-proof fabric obtained by the preparation method of the present invention can wrap the sharp tip in a spiral form when a sharp object pierces the circular winding structure of the stab-proof fabric of the present invention, effectively blunting the tip and hindering the penetration of the sharp object. Figure 4The circular coiled structure dissipates energy in all directions through crack propagation, effectively reducing penetration displacement and improving the material's puncture resistance.

[0094] The star-shaped laminated structure of the present invention can effectively fill the gaps between adjacent circular winding structures, while the arc-shaped overlapping structure can eliminate through-type gaps and improve the material gap puncture resistance. Figure 5 The arc-shaped and vertically dislocated gap area 4 can prevent the knife from piercing, so the stab-proof material liner with stab-proof performance and comfort can be formed without using the base fabric at the bottom for bonding.

[0095] The circular winding structure and the star-shaped laminated structure prepared in Example 1 were used to conduct gap penetration experiments and compared with the conventional overlapped structure of the prior art. The conventional overlapped structure was also overlapped using the reinforced fiber composite material in Example 1. Figure 6 As shown, the gap puncture stress of the composite structure of the present invention is higher than that of the conventional structure, and the puncture energy is absorbed earlier and more.

[0096] The circular wound structure and the star-shaped laminated structure prepared in Example 1 were used to carry out a puncture load test. Figure 7 As shown in Figure 2, under quasi-static puncture, the peak load of the star-shaped laminated-circular wound composite structure is 1346.46N, and the peak load of the circular wound-star-shaped laminated composite structure is 1678.47N. Figure 8 As shown in the figure, under dynamic puncture, the peak load of the star-shaped laminated-circular wound composite structure is 1081 N, and the peak load of the circular wound-star-shaped laminated composite structure is 1255 N. This flexible fabric has high puncture resistance.

[0097] The above description is only used to help understand the method and core essence of the present invention, but the scope of protection of the present invention is not limited thereto. For those skilled in the art, equivalent replacements or modifications based on the technical solutions and inventive concepts of the present invention within the technical scope disclosed by the present invention should be included in the scope of protection of the present invention. In summary, the contents of this specification should not be understood as limiting the present invention.

Claims

1. A stab-proof fabric with a circular winding-star-shaped laminated composite structure, including a stab-proof nail plate, characterized in that: The stab-proof armor plate is formed by stacking and bonding a winding structure and a laminated structure; The winding structure is a spiral sheet obtained by winding a reinforcing fiber slice into a rod shape, the cross section of the winding structure is a symmetrical figure, the laminated structure is a laminated board obtained by cutting a reinforcing fiber laminate, and the cross section of the laminated structure is the shape of a middle gap surrounded by four winding structures laid flat; The winding structure is a circular winding structure (1), and the laminated structure is a star-shaped laminated structure (2); the star-shaped cross section of the star-shaped laminated structure (2) is a symmetrical figure obtained by removing the area enclosed by four quarter-circular arcs of the same radius and the circumference of the circular cross section from the circular winding structure (1); A plurality of stab-proof nail plates are laid flat and adjacent stab-proof nail plates are arranged alternately in front and back, and the adjacent stab-proof nail plates are matched in shape and bonded to form a stab-proof layer; the stab-proof fabric is provided with at least one stab-proof layer.

2. The stab-proof fabric of the circular winding-star-shaped laminated composite structure according to claim 1, characterized in that: It also includes a base fabric (3), the stab-proof layer is bonded to the base fabric (3), and the base fabric (3) is made of a fiber or fabric selected from aramid, ultra-high molecular weight polyethylene, carbon fiber, and basalt.

3. The method for preparing the stab-proof fabric with a circular winding-star-shaped laminated composite structure according to claim 2, characterized in that: The steps include: S1. Preparation of circular coiled structure (1); Cutting the reinforcing fiber fabric into long strips, and using a motor to wind the long strips of reinforcing fiber fabric into a round rod preform; placing the round rod preform in a cylindrical mold, heating and curing it to form a composite material round rod; uniformly cutting the composite material round rod to obtain a plurality of circular winding structures (1); S2, preparation of star-shaped laminated structure (2); After bonding and stacking the reinforced fiber fabrics, the composite laminate is formed into a composite material laminate by pressurizing and curing on a flat hot press; the composite material laminate is cut into a star shape to obtain a star-shaped laminate structure (2); S3. Preparation of stab-resistant nail plates; The lower portion of the circular wound structure (1) and the upper portion of the star-shaped laminated structure (2) are bonded together by a matrix resin to obtain a stab-proof nail plate; S4. Preparation of stab-resistant fabric with circular winding-star-shaped laminated composite structure; A plurality of stab-proof armor plates are alternately bonded one by one on a base fabric (3) through a matrix resin in the positive and negative directions to form an array, thereby obtaining a stab-proof fabric with a circular winding-star-shaped laminated composite structure.

4. The method for preparing the stab-proof fabric with a circular winding-star-shaped laminated composite structure according to claim 3, characterized in that: The reinforcing fiber fabric in S1 is a non-woven fabric or a unidirectional prepreg.

5. The method for preparing the stab-proof fabric with a circular winding-star-shaped laminated composite structure according to claim 4, characterized in that: The heating and curing in S1 to form a composite material round rod is specifically as follows: When the reinforcing fiber fabric is a non-woven fabric, a release agent is sprayed on the inner wall of a cylindrical mold, a round rod preform is placed in the cylindrical mold, and a vacuum pump is used to completely impregnate the round rod preform with the matrix resin. The preform is then placed in a vacuum oven. In the vacuum oven, vacuum degassing is first performed at 25°C for 1 hour, and then curing is performed at a temperature of 60-120°C for 4-8 hours before demolding to form a composite material round rod. When the reinforcing fiber fabric is a unidirectional prepreg, a release agent is sprayed on the inner wall of a cylindrical mold, and the round rod preform is placed in the cylindrical mold and then placed together in a vacuum oven; it is heated at 80°C in the vacuum oven for 30 minutes, then heated to 120-150°C and kept warm for 1-2 hours, and then naturally cooled to 60°C before demolding to form a composite material round rod.

6. The method for preparing the stab-proof fabric with a circular winding-star-shaped laminated composite structure according to claim 3, characterized in that: The reinforcing fiber fabric in S2 is one or more of plain, twill and unidirectional pure fabrics or prepregs.

7. The method for preparing the stab-resistant fabric with a circular winding-star-shaped laminated composite structure according to claim 6, characterized in that: The pressurized curing step in S2 is used to form a laminate, specifically: When the reinforcing fiber is pure fabric, a release agent is sprayed on the surface of the flat mold, and the pure fabric is evenly brushed with matrix resin and laid layer by layer between the flat molds; the carbon fiber laminate is obtained by curing it in a flat hot press at a pressure of 0.5-2 MPa and a temperature of 60-120°C for 4-8 hours, and then cooling and demoulding. When the reinforcing fiber is prepreg, a release agent is sprayed on the surface of the flat mold, and the prepreg is sequentially layered and placed between the flat molds; it is heated at 120-150°C for 1-2 hours using a flat hot press at a pressure of 0.5-2 MPa, and then naturally cooled to 60°C before demoulding to obtain a carbon fiber laminate.

8. The method for preparing the stab-proof fabric with a circular winding-star-shaped laminated composite structure according to claim 3, characterized in that: The circular winding structure (1) and the star-shaped laminated structure (2) have the same thickness, which is 1 to 3 mm.

9. The method for preparing the stab-proof fabric with a circular winding-star-shaped laminated composite structure according to claim 3, characterized in that: The circular cross-section radius of the circular winding structure (1) is 15-30 mm.

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