Impact-resistant composite laminate and method of making the same

Abstract

The application discloses an impact-resistant composite material laminated plate and a preparation method thereof, and belongs to the technical field of composite material structure design; the composite material laminated plate comprises a thermosetting epoxy resin-based composite material layer and a thermoplastic resin film layer; the thermosetting epoxy resin-based composite material layers are stacked in turn from bottom to top; the thermoplastic resin film layer is embedded in the thermosetting epoxy resin-based composite material layers in a splicing or inserting mode; wherein the number of layers of the thermosetting epoxy resin-based composite material layer is 2n; n is a positive integer and is greater than or equal to 4; the application provides a composite material laminated plate with a unique structure, which can greatly improve the impact resistance and crack propagation blocking capacity under dynamic load of the composite material laminated plate compared with a traditional thermosetting epoxy resin-based composite material laminated plate structure without affecting the structure weight.

Description

Technical Field

[0001] This invention belongs to the field of composite material structural design technology, and particularly relates to an impact-resistant composite laminate and its preparation method. Background Technology

[0002] Fiber-reinforced composite materials (hereinafter referred to as "composite materials") are widely used in defense, aerospace, medical equipment, automotive, and shipbuilding industries due to their excellent specific strength / stiffness, corrosion resistance, multifunctionality, and superior structural designability. Currently, the composite materials used in industry are mainly thermosetting composites, represented by epoxy resin. Although this material system possesses excellent strength and modulus, the inherent characteristics of the resin matrix result in poor damage tolerance and impact resistance, greatly limiting the application of composite materials in engineering. For example, when thermosetting composite materials are subjected to low-velocity impact loads (such as tool drops or heavy object collisions), although the exterior remains intact, the internal structure may suffer some difficult-to-detect damage, such as matrix damage and delamination. This damage will significantly affect the service performance of the composite structure. Therefore, in many structures or components that may face impact loads, composite materials are often not used for safety reasons, forcing the use of more ductile metal materials. This design limitation not only greatly affects the level of structural lightweighting but also brings new problems such as the connection between metals and composite materials. Toughening and modifying traditional thermosetting resin matrices is a major method to improve the structural toughness of composite materials. However, this method has problems such as long research and development cycles, strict operation, and difficult formulation. Therefore, there is an urgent need to propose a faster and more convenient structural design and manufacturing method for traditional composite material systems to improve the impact resistance of composite material structures.

[0003] High-performance thermoplastic polymer materials have attracted widespread attention from industry in recent years due to their advantages such as good toughness, high damage tolerance, good dielectric constant, and ease of processing and molding. However, thermoplastic resins generally have high processing temperatures, high viscosity and poor flowability at high temperatures, making it difficult to effectively composite with fibers, and the processing is difficult and costly. Therefore, organically combining high-performance thermoplastic polymers with traditional epoxy resin composite systems, and organically embedding thermoplastic polymers as structural components into thermosetting composite structures, to fully leverage the advantages of both and improve the overall impact resistance of the structure, is an effective method. Currently, there are many studies on modifying traditional thermoplastic composites with thermoplastic resins from a materials perspective, but such material modification is often limited to laboratory specimen scale research, making mass production difficult and application to large-scale equipment structures impossible. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention proposes an impact-resistant composite laminate. From a structural design perspective, this invention presents an impact-resistant design and fabrication method for a composite laminate structure based on a thermoplastic film. This method does not require fundamental changes to the fabrication process and can be rapidly industrialized using existing composite material manufacturing processes, demonstrating significant application potential.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] One of the technical solutions of the present invention is:

[0007] An impact-resistant composite laminate includes a thermosetting epoxy resin-based composite material layer and a thermoplastic resin film layer, wherein the thermosetting epoxy resin-based composite material layers are stacked sequentially from bottom to top, and the thermoplastic resin film layer is embedded in the thermosetting epoxy resin-based composite material layer by splicing or inserting.

[0008] The number of layers in the thermosetting epoxy resin-based composite material is 2n; n is a positive integer and ≥4.

[0009] Furthermore, the thermosetting epoxy resin-based composite material layer is prepared from unidirectional or woven fiber prepreg;

[0010] The thermoplastic resin film layer is made of thermoplastic polymer; the thermoplastic polymer film has the same thickness as the single-layer fiber prepreg; the thickness is 0.15 mm.

[0011] Furthermore, the fibers in the fiber prepreg are any one of carbon fiber, glass fiber, and Kevlar fiber; preferably carbon fiber, with a curing temperature of 180℃±5℃, close to the glass transition temperature of the thermoplastic polymer used.

[0012] Furthermore, the embedding location does not include the top and bottom layers of the thermosetting epoxy resin-based composite material layer.

[0013] Furthermore, the longitudinal section of the structure formed by the thermoplastic resin film layer inside the thermosetting epoxy resin-based composite material layer is "Z"-shaped or "Ω"-shaped. The longitudinal section is a cross-section perpendicular to the laying plane.

[0014] Furthermore, when the longitudinal section of the structure formed by the thermoplastic resin film layer inside the thermosetting epoxy resin-based composite material layer is "Z" shaped and n=4, the stacking direction of the thermosetting epoxy resin-based composite material layers from bottom to top is defined as the first to eighth layers. The second and third layers, the fourth and fifth layers, and the sixth and seventh layers are each grouped together and cut so that the longitudinal section of each group of thermosetting epoxy resin-based composite material layers is "Z" shaped. The thermoplastic film is inserted across the layers and spliced ​​with the thermosetting epoxy resin-based composite material layers to form a complete structure.

[0015] Furthermore, when the longitudinal section of the structure formed by the thermoplastic resin film layer inside the thermosetting epoxy resin-based composite material layer is "Ω" shaped and n=4, the stacking direction of the thermosetting epoxy resin-based composite material layers from bottom to top is defined as the first to eighth layers. Among them, the second to seventh layers are partially cut so that the longitudinal section of the thermosetting epoxy resin-based composite material layers of the second to seventh layers is "Ω" shaped, and the thermoplastic film is inserted into it to form a complete structure by interlocking with the thermosetting epoxy resin-based composite material layer.

[0016] The two structures of the above composite laminate (spliced ​​and plugged configurations) can change the number of spans, splice / plug length, and relative position of splices / plugs.

[0017] The second technical solution of the present invention:

[0018] A method for preparing an impact-resistant composite laminate is provided, comprising the following steps:

[0019] Step 1: Soften the fiber prepreg.

[0020] Step 2: Lay the fiber prepreg on the lower mold surface according to the laying structure designed above;

[0021] Step 3: Cover the mold, seal the mold, and evacuate the mold.

[0022] Step 4: High-temperature curing and molding. Open the mold, remove the composite material, and obtain a composite laminate based on fiber prepreg with embedded thermoplastic film.

[0023] Furthermore, in step four, the curing temperature is 175–185℃, the pressure is 0.6 MPa–0.8 MPa, and the curing time is ≥180 min.

[0024] Based on the Thomas-Windle melting principle, the interfacial melting rate V is:

[0025]

[0026] In the above formula, D SgThe diffusion coefficient of polymers above the glass transition temperature. t represents the volume fraction threshold of the infiltration surface, and t represents the reaction time. Based on the control of the infiltration rate, the curing conditions in step four are obtained.

[0027] Compared with the prior art, the present invention has the following advantages and technical effects:

[0028] 1. This invention proposes an impact-resistant composite laminate structure and preparation method based on thermoplastic film through configuration design concept. Without affecting the structural weight, it significantly improves the overall impact resistance of the structure, including out-of-plane stiffness, ultimate bearing capacity, and resistance to delamination. Compared with epoxy resin composites without thermoplastic film reinforcement, this invention can increase the peak bearing capacity by 57.1% under drop hammer impact load, and reduce the delamination area after impact by up to 48.5%. This invention effectively improves the impact resistance and crack propagation prevention ability of traditional thermosetting epoxy resin-based composite laminate structures under dynamic loads.

[0029] 2. This invention introduces a thermoplastic polymer film with higher toughness into a thermosetting composite laminate structure. Upon impact, the plastic deformation of the thermoplastic film reduces impact energy. Simultaneously, based on a reasonable processing technology, the combination of the thermoplastic polymer and the thermosetting resin system is effectively achieved, increasing the interlayer bonding capacity, effectively preventing crack propagation within the structure, and significantly improving the anti-delamination ability of the composite laminate under impact loads.

[0030] 3. The preparation method of the composite laminate based on thermoplastic film is simple to operate, does not require changes to the composite material formula and process parameters, and can be completed in industrial production using existing processes. Compared with the toughening modification of materials, it greatly shortens the research and development cycle and reduces the manufacturing cost. Attached Figure Description

[0031] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments and descriptions of this application are used to explain this application and do not constitute an undue limitation of this application. In the drawings:

[0032] Figure 1 This is a schematic diagram of the composite material laminate of Example 1;

[0033] Figure 2 This is a schematic diagram of the composite material laminate of Example 2;

[0034] Figure 3 This is a schematic diagram of the transition interface between the thermoplastic resin film and the thermosetting prepreg in the composite laminate of the present invention.

[0035] Figure 4Failure modes of composite structures with and without thermoplastic resin films under impact loads are shown in the diagram.

[0036] Figure (a) shows Example 2; Figure (b) shows a comparative example.

[0037] Figure 5 A schematic diagram illustrating the effect of the presence or absence of a thermoplastic resin film on the crack-blocking ability of a composite material structure;

[0038] in, Figure 5 The left figure is a comparative example; the right figure is Example 2. Detailed Implementation

[0039] Various exemplary embodiments of the present invention will now be described in detail. This detailed description should not be considered as a limitation of the present invention, but rather as a more detailed description of certain aspects, features, and embodiments of the present invention.

[0040] It should be understood that the terminology used in this invention is merely for describing particular embodiments and is not intended to limit the invention. Furthermore, with respect to numerical ranges in this invention, it should be understood that each intermediate value between the upper and lower limits of the range is also specifically disclosed. Every smaller range between any stated value or intermediate value within a stated range, and any other stated value or intermediate value within said range, is also included in this invention. The upper and lower limits of these smaller ranges may be independently included or excluded from the range.

[0041] Unless otherwise stated, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. While only preferred methods and materials have been described herein, any methods and materials similar or equivalent to those described herein may be used in the implementation or testing of this invention. All references to this specification are incorporated by way of citation to disclose and describe methods and / or materials associated with those references. In the event of any conflict with any incorporated reference, the content of this specification shall prevail.

[0042] Various modifications and variations can be made to the specific embodiments described in this specification without departing from the scope or spirit of the invention, as will be apparent to those skilled in the art. Other embodiments derived from this specification will also be readily apparent to those skilled in the art. This specification and embodiments are merely exemplary.

[0043] The terms “include,” “including,” “have,” “contain,” etc., used in this article are all open-ended terms, meaning that they include but are not limited to.

[0044] This invention discloses an impact-resistant composite laminate, comprising a thermosetting epoxy resin-based composite material layer and a thermoplastic resin film layer, wherein the thermosetting epoxy resin-based composite material layers are stacked sequentially from bottom to top, and the thermoplastic resin film layer is embedded in the thermosetting epoxy resin-based composite material layers by splicing or inserting.

[0045] The number of layers in the thermosetting epoxy resin-based composite material is 2n; n is a positive integer and ≥4.

[0046] In some embodiments, the thermosetting epoxy resin-based composite material layer is prepared from unidirectional or woven fiber prepreg;

[0047] The thermoplastic resin film layer is made of thermoplastic polymer; the thermoplastic polymer film has the same thickness as the single-layer fiber prepreg; the thickness is 0.15 mm.

[0048] In some embodiments, the fibers in the fiber prepreg are carbon fibers, and the curing temperature is 180℃±5℃, which is close to the glass transition temperature of the thermoplastic polymer used.

[0049] In some embodiments, the embedding location does not include the top and bottom layers of the thermosetting epoxy resin-based composite material layer.

[0050] In some embodiments, the longitudinal section of the structure formed by the thermoplastic resin film layer inside the thermosetting epoxy resin-based composite material layer is "Z"-shaped or "Ω"-shaped.

[0051] In some embodiments, when the longitudinal section of the structure formed by the thermoplastic resin film layer inside the thermosetting epoxy resin-based composite material layer is "Z" shaped and n=4, the stacking direction of the thermosetting epoxy resin-based composite material layers from bottom to top is defined as the first to eighth layers, and the second and third layers, the fourth and fifth layers, and the sixth and seventh layers are respectively grouped and cut so that the longitudinal section of each group of thermosetting epoxy resin-based composite material layers is "Z" shaped. The thermoplastic film is inserted across the layers and spliced ​​with the thermosetting epoxy resin-based composite material layers to form a complete structure.

[0052] In some embodiments, when the longitudinal section of the structure formed by the thermoplastic resin film layer inside the thermosetting epoxy resin-based composite material layer is “Ω”-shaped and n=4, the stacking direction of the thermosetting epoxy resin-based composite material layers from bottom to top is defined as the first to eighth layers. The second to seventh layers are partially cut so that the longitudinal section of the thermosetting epoxy resin-based composite material layers of the second to seventh layers is “Ω”-shaped, and the thermoplastic film is inserted therein to form a complete structure by interlocking with the thermosetting epoxy resin-based composite material layer.

[0053] In addition, the present invention also provides a method for preparing an impact-resistant composite laminate, comprising the following steps:

[0054] Step 1: According to the requirements, take out the qualified carbon fiber thermosetting prepreg from the freezer, place it at room temperature (25℃±2℃) for more than 10 hours to soften and adjust, and clean the mold.

[0055] Step 2: Lay carbon fiber prepreg on the lower mold surface according to the designed laying structure;

[0056] Step 3: Cover the mold, seal the mold, and evacuate the mold.

[0057] Step 4: Complete the high-temperature molding process according to the design, open the mold, take out the composite material, and obtain a composite laminate based on fiber prepreg with embedded thermoplastic film.

[0058] In step three, the molding materials used for vacuum layering of the laminate mold should include sealing strips, release films, fiber fabrics, breathable felt, vacuum bags, and metal strips.

[0059] The operation of sealing the mold includes: fixing the prepreg plywood with three rubber strips of the same height as the thickness of the prepreg plywood and a metal strip of the same specification; laying the release film, fiber fabric, and breathable felt on the mold in sequence; attaching the sealing strips along the edge of the mold; and laying the vacuum bag on the breathable felt and making it tightly adhered to the sealing strips.

[0060] In step four, the composite laminate should be cured in an autoclave strictly according to the curing regime, which is as follows:

[0061] 1) Vacuuming is performed, with the pressure inside the vacuum bag not less than 0.08 MPa, and the pressure in the autoclave is 0.6 MPa-0.8 MPa;

[0062] 2) Maintain pressure and heat from room temperature to 180℃±5℃ at a heating rate of 0.5℃ / min-3℃ / min;

[0063] 3) Under a pressure of 0.6MPa-0.8MPa, maintain a constant temperature of 180℃±5℃ for no less than 180min;

[0064] 4) Cool to below 60°C at a cooling rate of no more than 3°C / min (maintain pressure in the autoclave until cooling is complete).

[0065] All raw materials used in the embodiments of this invention were obtained through commercial purchase.

[0066] Unless otherwise specified, the term "parts" used in the embodiments of this invention refers to "parts by weight".

[0067] The technical solution of the present invention will be further illustrated by the following embodiments.

[0068] Example 1

[0069] like Figure 1 As shown, an impact-resistant composite laminate has a spliced ​​structure. It consists of eight layers of thermosetting epoxy resin-based composite material and three layers of thermoplastic resin film. Each thermosetting epoxy resin-based composite material layer is composed of unidirectional or woven fiber prepreg, and each thermoplastic material layer consists of a single thermoplastic film. The stacking direction from bottom to top is defined as layers one through eight. The thermosetting epoxy resin-based composite material layers, except for the first and eighth layers, are cut. The thermoplastic film is inserted across layers, into the second and third, fourth and fifth, and sixth and seventh layers respectively, forming a "Z"-shaped spliced ​​structure (longitudinal section), which, together with the corresponding thermosetting epoxy resin-based composite material layers, forms a complete structure.

[0070] The method for preparing the impact-resistant composite laminate of this structure is as follows:

[0071] 1) Take out the qualified carbon fiber thermosetting prepreg from the freezer and place it at room temperature (25°C) for 10 hours to soften and adjust it. Clean the mold with acetone and industrial alcohol in turn.

[0072] 2) According to requirements, the prepreg and thermoplastic resin film are cut to the size that matches the mold size using CNC cutting equipment;

[0073] 3) Lay the first layer of thermosetting prepreg on the lower mold according to the design concept, then cut the corresponding layers and insert the thermoplastic resin film to form a Z-shaped splicing structure. During the laying process, remove the release paper on both sides of the thermosetting prepreg and clean the surface of the thermoplastic resin film with IPA solution.

[0074] 4) After laying, cover with the mold, seal the edges with high-temperature sealing rubber, and finally cover with a vacuum bag, sealing it with sealing strips. Connect the vacuum pump and maintain the vacuum pressure below 0.08MPa;

[0075] 5) Push the mold and the trolley into the autoclave for high-temperature molding. Set the curing pressure to 0.06MPa, maintain the pressure, and heat from room temperature to 185℃ at a heating rate of 2℃ / min, and hold for 180min.

[0076] 6) Cool to 50°C at a cooling rate of 3°C / min, then open the can and remove the mold;

[0077] 7) Open the mold, remove the relevant auxiliary materials, and obtain the spliced ​​composite laminate structure.

[0078] Example 2

[0079] like Figure 2 As shown, an impact-resistant composite laminate has an interlocking structure. It consists of eight layers of thermosetting epoxy resin-based composite material and three layers of thermoplastic resin film. Each thermosetting epoxy resin-based composite material layer is composed of unidirectional or woven fiber prepreg, and each thermoplastic resin film layer consists of a single thermoplastic film. The stacking direction from bottom to top is defined as layers one through eight. The thermosetting epoxy resin-based composite material layers, except for the first and eighth layers, are locally cut to create material notches. The thermoplastic film is then inserted into the notches of the second and third, fourth and fifth, and sixth and seventh layers, forming an "Ω"-shaped interlocking structure (longitudinal section), thus forming a complete structure with the corresponding thermosetting epoxy resin-based composite material layers.

[0080] The method for preparing the impact-resistant composite laminate of this structure is as follows:

[0081] 1) Take out the qualified carbon fiber thermosetting prepreg from the freezer and place it at room temperature (25°C) for 10 hours to soften and adjust it. Clean the mold with acetone and industrial alcohol in turn.

[0082] 2) According to requirements, the prepreg and thermoplastic resin film are cut to the size that matches the mold size using CNC cutting equipment;

[0083] 3) Lay the first layer of thermosetting prepreg on the lower mold according to the design concept, then cut the corresponding layers and insert the thermoplastic resin film to form an Ω-shaped splicing structure. During the laying process, remove the release paper on both sides of the thermosetting prepreg and clean the surface of the thermoplastic resin film with IPA solution.

[0084] 4) After laying, cover with the mold, seal the edges with high-temperature sealing rubber, and finally cover with a vacuum bag, sealing it with sealing strips. Connect the vacuum pump and maintain the vacuum pressure below 0.08MPa;

[0085] 5) Push the mold and the trolley into the autoclave for high-temperature molding. Set the curing pressure to 0.06MPa, maintain the pressure, and heat from room temperature to 185℃ at a heating rate of 2℃ / min, and hold for 180min.

[0086] 6) Cool to 50°C at a cooling rate of 3°C / min, then open the can and remove the mold;

[0087] 7) Open the mold, remove the relevant auxiliary materials, and obtain the plug-in composite laminate structure.

[0088] Comparative Example

[0089] In this embodiment, a control specimen was prepared. The specimen was a composite laminate structure made of eight layers of carbon fiber reinforced epoxy resin prepreg. There was no thermoplastic resin film in the laminate structure. Each layer of thermosetting epoxy resin-based composite material was composed of unidirectional or woven fiber prepreg. The layup method was consistent with the prepreg layup in Examples 1 and 2.

[0090] The preparation method of this sample is as follows:

[0091] 1) Take out the qualified carbon fiber thermosetting prepreg from the freezer and place it at room temperature (25°C) for 10 hours to soften and adjust it. Clean the mold with acetone and industrial alcohol in turn.

[0092] 2) According to requirements, the prepreg and thermoplastic resin film are cut to the size that matches the mold size using CNC cutting equipment;

[0093] 3) Lay the thermosetting prepreg in the same layup sequence as the samples in Examples 1 and 2, and remove the release paper on both sides of the thermosetting prepreg during the laying process;

[0094] 4) After laying, cover with the mold, seal the edges with high-temperature sealing rubber, and finally cover with a vacuum bag, sealing it with sealing strips. Connect the vacuum pump and maintain the vacuum pressure below 0.08MPa;

[0095] 5) Push the mold and the trolley into the autoclave for high-temperature molding. Set the curing pressure to 0.06MPa, maintain the pressure, and heat from room temperature to 185℃ at a heating rate of 2℃ / min, and hold for 180min.

[0096] 6) Cool to 50°C at a cooling rate of 3°C / min, then open the can and remove the mold;

[0097] 7) Open the mold, remove the relevant auxiliary materials, and obtain a pure thermosetting composite laminate structure.

[0098] Effect verification

[0099] Impact resistance test

[0100] (1) To verify the improvement of the impact resistance of thermoplastic polymer film on thermosetting composite laminate structure, composite laminates prepared in Examples 1 and 2 were used to conduct drop hammer impact tests according to ASTM D7136 / D7136-7 standards. The test conditions were: energy set at 15J, and a hemispherical hammer with a diameter of 8mm was used. Then, a composite laminate structure prepared in the same proportion was used as a reference under the same standards and conditions.

[0101] Based on the free-fall motion of the hammer from its initial position (where the initial position is the hammer height, approximately 3m, automatically calculated by the experimental machine based on a 15J impact energy), the initial velocity V0 of the hammer can be calculated as follows:

[0102]

[0103] In the above formula, M is the mass of the hammer, and K... b Let H be the bending stiffness of the composite plate and H be the hammer height. From this, the impact indentation depth X(t) and impact load P(t) can be further calculated:

[0104]

[0105]

[0106] The impact resistance of composite laminates is evaluated based on the above indicators.

[0107] The result is:

[0108] The composite laminate prepared in Example 1 had an ultimate bearing capacity (i.e., impact load) of 4.2 kN and an indentation depth of 2.3 mm. Ultrasonic C-scan was used to characterize the delamination damage of the laminated half-structure after impact, and the measured delamination area was approximately 7.3 cm². 2 ;

[0109] The composite laminate prepared in Example 2 had an ultimate bearing capacity of 4.4 kN and an indentation depth of 2.1 mm. Ultrasonic C-scan was used to characterize the delamination damage of the laminated half-structure after impact, and the measured delamination area was approximately 6.9 cm². 2 ;

[0110] The comparative composite laminate exhibited an ultimate bearing capacity of 2.8 kN and an indentation depth of 5.4 mm. Ultrasonic C-scan was used to characterize the delamination damage of the laminated half-structure after impact, and the measured delamination area was approximately 13.4 cm². 2 .

[0111] (2) Based on the drop hammer impact test, SEM was used to observe the failure of the specimens after impact. It can be seen that, due to the introduction of the thermoplastic resin film, when the laminate structure is subjected to impact load, the thermoplastic resin can effectively absorb energy through local deformation, preventing crack propagation from the upper and lower parts, thus preventing overall failure of the composite laminate structure and maintaining a certain degree of load-bearing capacity. Figure 4 As shown in (a). In comparison, Figure 4 In the comparative sample in (b), due to the absence of a thermoplastic resin film, the thermosetting composite material can only dissipate energy through fracture and delamination. Therefore, a failure mode occurs that extends throughout the overall thickness of the structure, such as... Figure 5 As shown.

[0112] The above are merely preferred embodiments of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An impact-resistant composite laminate, characterized in that, The composite material layer comprises a thermosetting epoxy resin-based composite material layer and a thermoplastic resin film layer, the thermosetting epoxy resin-based composite material layer is stacked from bottom to top, and the thermoplastic resin film layer is embedded in the thermosetting epoxy resin-based composite material layer in a splicing or inserting manner; the thermosetting epoxy resin-based composite material layer is prepared from unidirectional or fabric fiber prepreg; The number of layers of the thermosetting epoxy resin-based composite material layer is 8; The longitudinal section of the structure formed by the thermoplastic resin film layer in the thermosetting epoxy resin-based composite material layer is "Z" type or "Ω" type; When the longitudinal section of the structure formed by the thermoplastic resin film layer in the thermosetting epoxy resin-based composite material layer is "Z" type, the stacking direction of the thermosetting epoxy resin-based composite material layer is defined as the first to eighth layers from bottom to top, the second, third, fourth, fifth, sixth and seventh layers are respectively taken as a group, cutting is performed, the longitudinal section of each group of thermosetting epoxy resin-based composite material layers is "Z" type, the thermoplastic film is inserted across the layers, and the thermosetting epoxy resin-based composite material layer is spliced to form a complete structure; When the longitudinal section of the structure formed by the thermoplastic resin film layer in the thermosetting epoxy resin-based composite material layer is "Ω" type, the stacking direction of the thermosetting epoxy resin-based composite material layer is defined as the first to eighth layers from bottom to top, the second to seventh layers are partially cut, the longitudinal section of the thermosetting epoxy resin-based composite material layers of the second to seventh layers is "Ω" type, the thermoplastic film is inserted, and the thermosetting epoxy resin-based composite material layer is inserted to form a complete structure.

2. A composite laminate panel according to claim 1, wherein, The thermoplastic resin film layer is prepared from thermoplastic resin or polymer; the thickness of the thermoplastic resin film is the same as that of a single layer of fiber prepreg.

3. The impact-resistant composite laminate of claim 1, wherein, The fiber in the fiber prepreg is any one of carbon fiber, glass fiber and Kevlar fiber.

4. The impact-resistant composite laminate of claim 1, wherein, The embedded position does not include the topmost layer and the bottommost layer of the thermosetting epoxy resin-based composite material layer.

5. A method of manufacturing the impact-resistant composite laminate panel according to claim 1, characterized by, The method comprises the following steps: Step one, softening treatment of fiber prepreg; Step two, laying the first layer of thermosetting prepreg on the lower mold, then cutting the corresponding layers, inserting the thermoplastic resin film, and forming a "Z" type splicing structure, and removing the isolation paper on both sides of the thermosetting prepreg during the laying process, and cleaning the surface of the thermoplastic resin film with IPA solution; Or, laying the first layer of thermosetting prepreg on the lower mold, then cutting the corresponding layers, inserting the thermoplastic resin film, and forming a "Ω" type splicing structure, and removing the isolation paper on both sides of the thermosetting prepreg during the laying process, and cleaning the surface of the thermoplastic resin film with IPA solution; Step three, covering the upper mold, sealing the mold, and vacuumizing the mold; Step four, high-temperature curing and molding, opening the mold, taking out the composite material, and obtaining a composite laminate with embedded thermoplastic film based on fiber prepreg.

6. The production method according to claim 5, wherein The temperature of the high-temperature curing in step four is 175-185 DEG C, the pressure is 0.6-0.8 MPa, and the curing time is greater than or equal to 180 min.

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