Composite material laminated board structure embedded with NiTi alloy wires and preparation method and application of composite material laminated board structure

Abstract

The invention belongs to the technical field of vibration control, and particularly relates to a composite material laminated board structure embedded with NiTi alloy wires and a preparation method and application of the composite material laminated board structure. The preparation method comprises the following steps: respectively fixing two ends of a plurality of NiTi alloy wires on a wire embedding mold to form an alloy wire surface; the first layer plate part and the second layer plate part are symmetrically arranged on the upper surface and the lower surface of the alloy wire surface, an initial pressing bottom plate is arranged below the first layer plate part, and an initial pressing top plate is arranged above the second layer plate part; first pressure is applied to the initial pressing top plate and the initial pressing bottom plate, so that the first layer plate part, the alloy wire surface and the second layer plate part form a prefabricated structure body; and high-temperature and high-pressure curing molding. The composite material laminated board structure is prepared by the method. The laminated board structure can be applied to a wall board of a new energy aircraft. The composite material laminated board structure provided by the invention is light in weight and good in fatigue resistance, the vibration resistance of the composite material structure is enhanced, and the composite material laminated board structure can be integrally processed.

Description

Technical Field

[0001] The invention belongs to the technical field of vibration control, and in particular relates to a composite material laminate structure embedded with NiTi shape memory alloy wires and an application thereof. Background Art

[0002] In recent years, with the extensive application of composite laminate structures in aerospace, new energy vehicles, new energy aircraft and other transportation fields, their performance has been challenged when dealing with complex working conditions. In actual working environments, composite structures will vibrate under external impact or continuous excitation, which will cause failure and damage to the composite structure. Previous solutions to this problem include selecting high-performance composite materials, optimizing composite structure design, and thickening excessive vibration parts. However, since these methods are often accompanied by problems such as difficulty in material selection, high processing costs, high design difficulties, and failure to meet lightweight structural design requirements, these solutions are currently limited in practical application.

[0003] To make up for this shortcoming, designing a vibration damping enhancement structure for composite materials that meets the requirements of strong applicability, low processing difficulty and lightweight design has gradually become the focus of research and practice. For vibration damping devices, although the current devices including dampers can meet the vibration reduction requirements, they often require installation locations and additional energy supply, which cannot meet the space requirements and lightweight design requirements of new energy aircraft. Summary of the invention

[0004] The present invention provides a composite material laminate structure embedded with NiTi shape memory alloy wires, which not only has strong mechanical properties and good anti-vibration effect, but also can realize structural-functional integration in processing and design.

[0005] The technical solution adopted by the present invention to solve the technical problem is:

[0006] A method for preparing a composite laminate structure embedded with NiTi alloy wires, characterized in that it comprises the following steps:

[0007] Step 1, fixing two ends of a plurality of NiTi alloy wires arranged along a first direction and / or a second direction on a wire inserting die respectively to form an alloy wire surface;

[0008] Step 2, laying a first layer plate portion below the alloy wire surface, laying a second layer plate portion above the alloy wire surface, the first layer plate portion and the second layer plate portion are symmetrically arranged, an initial pressure bottom plate is arranged below the first layer plate portion, and an initial pressure top plate is arranged above the second layer plate portion;

[0009] Step 3, applying a first pressure to the initial pressing top plate and the initial pressing bottom plate, so that the first layer plate portion, the alloy wire surface and the second layer plate portion form a prefabricated structure;

[0010] Step 4, cutting the exposed NiTi alloy wire between the prefabricated structure and the wire embedding mold, and curing and molding at high temperature and high pressure to obtain a composite laminate structure embedded with NiTi alloy wire.

[0011] In the above-mentioned method for preparing the composite laminate structure, step 4 uses an autoclave to perform the high temperature and high pressure curing molding.

[0012] In the above-mentioned method for preparing the composite laminate structure, the pressure of the high temperature and high pressure curing molding is 4-5 standard atmospheres, the temperature is 100-150°C, and the processing time of the high temperature and high pressure curing molding is 4-6 hours.

[0013] In the above-mentioned method for preparing the composite laminate structure, the first pressure is the gravity of a mass block of 10-20 kg, and the time for applying the first pressure to the initial pressure top plate and the initial pressure bottom plate is ≥30 minutes.

[0014] In the above-mentioned method for preparing the composite laminate structure, the first direction is the transverse direction and the second direction is the longitudinal direction;

[0015] In the above-mentioned method for preparing the composite laminate structure, the spacing between adjacent NiTi alloy wires is 10 to 30 mm;

[0016] In the above-mentioned method for preparing the composite material laminate structure, the diameter of the NiTi alloy wire is 0.1 to 0.4 mm.

[0017] In the above-mentioned method for preparing the composite laminate structure, the first layer plate portion includes 2N fiber composite material layers, and the second layer plate portion includes 2N fiber composite material layers, wherein N=1, 2, 3, 4, 5.

[0018] In the above-mentioned method for preparing the composite laminate structure, the material of the fiber composite material layer is carbon fiber composite material prepreg or glass fiber composite material.

[0019] In the above-mentioned preparation method of the composite laminate structure, the wire insertion mold includes a square frame, a clamping and fixing block is provided on the square frame, a semicircular groove is provided on the square frame, and a semicircular protrusion is provided on the clamping and fixing block, and the shape and number of the semicircular groove and the semicircular protrusion match each other, so as to fix the NiTi alloy wire;

[0020] In the above-mentioned method for preparing the composite laminate structure, the shapes of the initial pressing top plate and the initial pressing bottom plate match the shape of the square frame and are slightly smaller than the space enclosed by the square frame.

[0021] A composite laminate structure embedded with NiTi alloy wires, the composite laminate structure being prepared by the above-mentioned preparation method, the composite laminate structure comprising: an alloy wire surface, and a first layer plate portion and a second layer plate portion symmetrically arranged along the alloy wire surface; the first layer plate portion and the second layer plate portion are connected to the alloy wire surface by hot pressing and curing.

[0022] An application of a composite laminate structure embedded with NiTi alloy wires, wherein the wall panels of a new energy aircraft are the composite laminate structure embedded with NiTi alloy wires.

[0023] By means of the above technical solution, the present invention has at least the following advantages:

[0024] 1) The present invention proposes a vibration-resistant composite laminate structure design embedded with NiTi shape memory alloy wire, which is not only light in weight and has excellent fatigue resistance, but also has the advantages of enhancing the vibration resistance of the composite structure and integrated processing characteristics.

[0025] 2) The present invention provides a theoretical analysis method for vibration suppression scheme based on NiTi shape memory alloy wire, which provides a theoretical research approach for the design of embedded wire layout of enhanced structure.

[0026] 3) The present invention discloses the application of an enhanced vibration-resistant composite laminate structure in the field of new energy aircraft, namely: using the processing method of the present invention to manufacture a vibration-resistant enhanced composite laminate, and providing a corresponding manufacturing mold.

[0027] 4) Vibration tests were carried out on the processed vibration damping enhanced composite laminates to verify the feasibility of the method proposed in the present invention.

[0028] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention and implement it according to the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1a It is a schematic diagram of a mold for preparing a composite laminate structure embedded with NiTi alloy wires according to the present invention;

[0030] Figure 1b It is a top view of a wire embedding die used for preparing a composite laminate structure embedded with NiTi alloy wires according to the present invention;

[0031] Figure 1cIt is a partial enlarged view of the long fixed outer frame strip and the clamping and fixing block of the wire inserting die of the present invention;

[0032] Figure 2a It is an exploded structural diagram of a composite laminate structure embedded with NiTi alloy wires of the present invention;

[0033] Figure 2b is a schematic cross-sectional view of a composite laminate structure embedded with NiTi alloy wires of the present invention;

[0034] Figure 3 It is a dynamic model diagram of the vibration-resistant scheme of the composite laminate structure embedded with NiTi alloy wires of the present invention;

[0035] Figure 4a This is a diagram showing the theoretical analysis results of the vibration suppression effect comparison of the vibration-resistant enhancement scheme of Configuration 1 of the present invention;

[0036] Figure 4b This is a diagram showing the theoretical analysis results of the vibration suppression effect comparison of the vibration-resistant enhancement scheme of Configuration 2 of the present invention;

[0037] Figure 5a It is a structural schematic diagram of the vibration suppression experimental verification device under the first boundary condition of the present invention;

[0038] Figure 5b It is a structural schematic diagram of the vibration suppression experimental verification device under the second boundary condition of the present invention;

[0039] Figure 6a It is a vibration reduction effect diagram of the unreinforced composite laminate of the present invention at different temperatures;

[0040] Figure 6b It is a diagram showing the vibration reduction effect of the longitudinally embedded composite laminate of the present invention at different temperatures;

[0041] Figure 6c It is a diagram showing the vibration reduction effect of the laterally embedded composite laminate of the present invention at different temperatures;

[0042] Figure 7a It is an experimental data diagram of the vibration reduction effect of the lateral embedding scheme of the present invention on the vibration damping enhanced composite laminate;

[0043] Figure 7b is an experimental data diagram of the vibration reduction effect of the longitudinal embedding scheme of the present invention on the vibration damping enhanced composite laminate;

[0044] Figure 7c It is an experimental data diagram of the vibration reduction effect of the staggered embedding scheme of the present invention on the vibration damping enhanced composite laminate;

[0045] Figure 8aIt is an experimental data diagram of the vibration reduction effect of multiple resonance peaks of the vibration damping enhanced composite laminate under the acceleration excitation of 0.2g of the present invention;

[0046] Figure 8b It is an experimental data diagram of the vibration reduction effect of multiple resonance peaks of the vibration damping enhanced composite laminate under the acceleration excitation of 0.3g of the present invention;

[0047] Figure 8c It is an experimental data diagram of the vibration reduction effect of the multiple resonance peaks of the vibration damping enhanced composite laminate under the acceleration excitation of 0.5g of the present invention. DETAILED DESCRIPTION

[0048] In order to further explain the technical means and effects adopted by the present invention to achieve the predetermined invention purpose, the specific implementation method, structure, characteristics and effects of the present invention application are described in detail below in combination with the accompanying drawings and preferred embodiments.

[0049] Preparation method example

[0050] This embodiment discloses a method for preparing a composite laminate structure embedded with NiTi alloy wires, comprising the following steps:

[0051] Step 1, fixing two ends of a plurality of NiTi alloy wires arranged along a first direction and / or a second direction on a wire inserting die respectively to form an alloy wire surface;

[0052] Step 2, laying a first layer plate portion below the alloy wire surface, laying a second layer plate portion above the alloy wire surface, the first layer plate portion and the second layer plate portion are symmetrically arranged, an initial pressure bottom plate is arranged below the first layer plate portion, and an initial pressure top plate is arranged above the second layer plate portion;

[0053] Step 3, applying a first pressure to the initial pressing top plate and the initial pressing bottom plate, so that the first layer plate portion, the alloy wire surface and the second layer plate portion form a prefabricated structure;

[0054] Step 4, cutting the exposed NiTi alloy wire between the prefabricated structure and the wire embedding mold, and performing high temperature and high pressure curing and molding (in this embodiment, a hot autoclave is used for the high temperature and high pressure curing and molding), the formed composite plate-like structure is a composite material laminate structure embedded with NiTi alloy wire.

[0055] The composite laminate structure prepared by the preparation method of the composite laminate structure embedded with NiTi alloy wires proposed by the present invention is not only light in weight and excellent in fatigue resistance, but also has the advantages of enhancing the vibration resistance and integrated processing characteristics of the composite structure.

[0056] In the preparation method of the present invention, an alloy wire surface is first prepared, and then a layer plate portion is symmetrically arranged on the upper and lower surfaces of the alloy wire surface, and the layer plate portion and the alloy wire surface are initially fixed by pressure. Since the diameter of the NiTi alloy wire constituting the alloy wire surface is between 0.1 and 0.4 mm, curling is very likely to occur during the preparation of the composite laminate structure, resulting in the prepared composite laminate structure not being consistent with the theoretical modeling analysis state, making the prediction in the theoretical analysis invalid, and also causing stress concentration at the curling location, thereby causing the composite laminate structure to lose dynamic stability and reduce vibration reduction performance.

[0057] In the preparation method of the present invention, by first forming a prefabricated structure, the alloy wire surface added between the first layer plate portion and the second layer plate portion can be embedded in the flexible first layer plate portion and the second layer plate portion through the first pressure applied by the initial pressure top plate and the initial pressure bottom plate, so that the planar structure is basically maintained after the exposed NiTi alloy wire is cut off. In addition, it can also ensure that the cut NiTi alloy wire remains in a straight state.

[0058] Through the combined action of the wire embedding mold and the pressing plate provided by the present invention, the alloy wire layer is placed in the middle of the two composite board layers and is parallel to the composite board layers. Since the NiTi alloy wire and the composite prepreg are two materials with different densities, if the NiTi wire layer is not in the middle position (that is, the composite board layer is not symmetrical along the alloy wire mesh surface), it will cause the problem of the center of gravity of the laminate to shift, affecting the dynamic stability of the structure. In addition, the NiTi wire layer cannot "move with the shape" of the laminate, which will cause a "displacement difference" between the NiTi wire and the composite structure. In severe cases, the laminate may be delaminated, affecting its service life.

[0059] After high-temperature and high-pressure curing and molding, the composite laminate structure embedded with NiTi alloy wires can maintain the mechanical properties of the laminate.

[0060] In order to enable the composite laminate structure embedded with NiTi alloy wire to be better formed, the pressure, temperature and processing time of the autoclave are further limited in this embodiment. The pressure of the high temperature and high pressure curing molding is 4 standard atmospheres, the temperature is 120°C, and the processing time of the high temperature and high pressure curing molding is 5 hours.

[0061] The first pressure is the gravity of a 10kg mass block, and the time duration for applying the first pressure to the initial pressure top plate and the initial pressure bottom plate is 30 minutes.

[0062] As a variable implementation, the pressure of the high temperature and high pressure curing molding can also be 5 standard atmospheres.

[0063] As a variable implementation, the temperature of the high temperature and high pressure curing molding can be any value between 100-150°C.

[0064] As a variable implementation, the processing time of the high temperature and high pressure curing molding can be any value between 4 and 6 hours.

[0065] As a variable implementation, the first pressure is the gravity provided by a mass block of any weight of 10-20 kg.

[0066] As a variable implementation manner, the time duration for applying the first pressure to the initial pressure top plate and the initial pressure bottom plate is greater than 30 minutes.

[0067] In order to achieve preliminary fixation of the alloy wire, this embodiment specifically uses a wire insertion mold to fix the two ends of the alloy wire.

[0068] The wire inserting mold includes a square frame, a clamping and fixing block is provided on the square frame, a semicircular groove is provided on the square frame, and a semicircular protrusion is provided on the clamping and fixing block. The shapes and numbers of the semicircular groove and the semicircular protrusion match each other so as to fix the NiTi alloy wire; the shapes of the initial pressing top plate and the initial pressing bottom plate match those of the square frame and are slightly smaller than the space enclosed by the square frame.

[0069] The fixed outer frame strip is provided with a hollow portion for accommodating the clamping and fixing block, and a semicircular groove is provided in the hollow portion.

[0070] The fixed outer frame bars include two short fixed outer frame bars 101 and two long fixed outer frame bars 102. The two long fixed outer frame bars 102 are arranged relatively parallel to each other, and the two short fixed outer frame bars 101 are also arranged relatively parallel to each other, and the shape after the two short fixed outer frame bars 101 and the two long fixed outer frame bars 102 are connected is a rectangle. The number and position of the hollow parts and semicircular grooves arranged on the long fixed outer frame bars 102 are matched, so that the fixed steel wire ropes can be parallel and straight. Similarly, the number and position of the hollow parts and semicircular grooves arranged on the short fixed outer frame bars 101 are matched.

[0071] The shapes of the initial pressing top plate and the initial pressing bottom plate match the inner space of the square frame of the support seat and are slightly smaller than the inner space of the square frame, so that the initial pressing top plate and the initial pressing bottom plate can be initially pressed on the laminated board. During the initial pressing top plate and the initial pressing bottom plate are initially pressed on the laminated board, the support seat of the wire inserting die will not cause any obstruction to the initial pressing process, so that the laminated board and the alloy wire surface can be fully pressed.

[0072] The square frame includes a support base and four fixed outer frame bars, the support base has studs, and the fixed outer frame bars have threaded holes. No additional bolts are needed. By adjusting the connection height of the studs and threaded holes, the height of the square frame can be adjusted. The specific process of assembling the alloy wire is as follows: first fix the support base and the fixed outer frame to form a "mouth" shape, then put the bottom plate inside the "mouth", then put the lower half of the composite material plate, and then perform the wire embedding operation.

[0073] The assembly process of the alloy wire is as follows: first put the alloy wire into the hollow part in the middle of the fixed outer frame strip, that is, put it into the semicircular groove in the hollow part, then put the clamping block on, the semi-cylindrical protrusion in the clamping block fits with the semi-cylindrical groove in the hollow part, and then use bolts to support the fixing block through the threaded holes on the fixing strip, so that one end of the NiTi alloy wire is clamped. After fixing one end of the NiTi alloy wire, straighten the NiTi alloy wire, and then put the straightened other end into the hollow part of the fixed outer frame strip on the other side, and then repeat the operation of fixing the NiTi wire with the clamping block.

[0074] The composite laminate structure prepared by the method for preparing a composite laminate structure embedded with NiTi alloy wires of the present invention comprises from top to bottom: a first layer part, an alloy wire surface and a second layer part, as shown in FIG1 for details.

[0075] The alloy wire surface is spatially located in the middle of the laminate, at the same distance from the top layer and the bottom layer of the laminate. The alloy wire surface is an embedded area of ​​the enhanced anti-vibration material, and the enhanced anti-vibration material is a NiTi shape memory alloy wire material. Preferably, a wire-type NiTi shape memory alloy damping enhancement device with a strong hysteresis anti-vibration damping effect is selected to improve the vibration reduction effect. Furthermore, the diameter range of the NiTi shape memory alloy wire is 0.1-0.4mm. Preferably, a 0.2mm diameter NiTi shape memory alloy wire is selected to ensure the vibration reduction effect, and the prepreg carbon fiber wire in the laminate will not be sheared or broken due to the excessive diameter of the alloy wire.

[0076] In specific implementation, the first direction is horizontal, and the second direction is vertical; that is, the laying method of the NiTi alloy wires may include the following methods: 1) a gold wire surface composed of a plurality of NiTi alloy wires laid horizontally; 2) a gold wire surface composed of a plurality of NiTi alloy wires laid vertically; 3) a gold wire surface composed of a plurality of NiTi alloy wires laid horizontally and a plurality of NiTi alloy wires laid vertically. That is: the alloy wire surface includes a plurality of NiTi shape memory alloy wires arranged vertically; or the alloy wire surface includes a plurality of NiTi shape memory alloy wires arranged horizontally and vertically in an alternating manner.

[0077] In a specific implementation, the spacing between adjacent NiTi alloy wires in the above-mentioned multiple transversely or longitudinally laid NiTi alloy wires is 10 to 30 mm; the diameter of the NiTi alloy wire is 0.1 to 0.4 mm. In a specific implementation, the NiTi alloy wire is a NiTi shape memory alloy wire. The NiTi alloy wire used in this embodiment is a black 0.1 and 0.2 mm nickel-titanium alloy wire purchased from Guangdong Southeast Nickel-Titanium Alloy Materials Co., Ltd.

[0078] Furthermore, the embedding scheme of the NiTi shape memory alloy wire is transverse embedding, longitudinal embedding and transverse and longitudinal staggered embedding, and the spacing between each alloy wire is 10 mm. The embedding scheme of the NiTi shape memory alloy wire is transverse and longitudinal staggered embedding, and the spacing between alloy wires in the same direction is 20 mm.

[0079] In this embodiment, the processing dimensions of the composite laminate structure are selected to be 250 mm in length and 150 mm in width. The spacing of the NiTi alloy wires is 10 mm. As an alternative, the processing dimensions of the fiber composite material layer can range from 50 to 1000 mm in length and width.

[0080] In this embodiment, when the embedding direction of the NiTi shape memory alloy wire is horizontal, the number of embedded wires is 14, and when the embedding direction of the NiTi shape memory alloy wire is vertical, the number of embedded wires is 24. Further, the embedding scheme of the NiTi shape memory alloy wire is horizontal and vertical staggered embedding, and the spacing of the alloy wires in the same direction is 30mm. When the embedding direction of the NiTi shape memory alloy wire is horizontal and vertical staggered embedding, the number of embedded wires is 8 horizontally and 13 vertically.

[0081] In a specific implementation, the first layer board portion includes 2N fiber composite material layers, and the second layer board portion includes 2N fiber composite material layers, wherein N=1, 2, 3, 4, 5.

[0082] The material of the fiber composite material layer is carbon fiber composite material prepreg or glass fiber composite material. The material of the fiber composite material layer is prepreg, which is soft during the initial pressing and wire embedding process and becomes hard after hot pressing.

[0083] In specific implementation, the material of the fiber composite material layer in this embodiment is unidirectional carbon fiber prepreg purchased from Shanghai Xinao Composite Material Technology Research and Development Center, and the specific specification model is T700-12K / 100g / resin 36%.

[0084] The first layer plate portion and the second layer plate portion each include 2N fiber composite material layers. In a specific implementation, the specific value of N can be any value of 1, 2, 3, 4 or 5 according to processing requirements. In this way, the number of layers of the composite material layers of the first layer plate portion and the second layer plate portion are both even numbers and are symmetrically arranged.

[0085] Due to the fiber composite material layer, the laying angle of the fiber composite material layer can be determined according to the direction of the fiber. In a specific implementation, in order to ensure the symmetry of the first layer board part and the second layer board part, the laying angles of the fiber composite material layers in the symmetrical layers of the first layer board part and the second layer board part are the same, and the laying angles are determined according to the direction of the fiber. The laying angle can be 0°, 90° or ±45°. The material selection of the second layer board part needs to be consistent with the material selection of the first layer board part.

[0086] In this embodiment, the processing material of the fiber composite material layer is T700 carbon fiber composite material prepreg, the single layer thickness is 0.1mm, the number of plies of the first layer is 10, and the ply angle is [0°, 90°, 0°, 90°, 0°, 90°, 0°, 90°, 0°, 90°]. When the ply angles are different, attention should be paid to the symmetry of the first layer and the second layer, and the ply angles of the first layer and the second layer should also be symmetrical along the alloy wire plane. The number of plies of the second layer should be consistent with the number of plies of the first layer, so in this embodiment, the number of plies of the second layer is 10. The ply angle of the second layer should be symmetrical with the first layer about the alloy wire plane, and the ply angle of the second layer is [90°, 0°, 90°, 0°, 90°, 0°, 90°, 0°, 90°, 0°].

[0087] In this way, it is possible to place the alloy wire surface between the first layer plate portion and the second layer plate portion, and the first layer plate portion and the second layer plate portion are symmetrically arranged along the alloy wire surface. Therefore, it is possible to directly replace the composite laminate without embedded alloy wire in the prior art. Composite laminates need to be symmetrical about the neutral layer during processing, mainly to avoid warping, deformation or cracking of the laminate due to thermal residual stress or external force, so as to ensure its mechanical properties and structural stability. The specific reasons are: avoiding deformation caused by thermal residual stress, ensuring consistency of mechanical properties, improving dimensional stability and simplifying design and analysis.

[0088] The distribution diagram of each layer and the cross-sectional schematic diagram of the composite laminate structure embedded with NiTi alloy wires are shown in FIG2 .

[0089] In order to further verify the vibration reduction effect of the composite laminate structure embedded with NiTi alloy wires prepared by the preparation method of the present invention. The present invention further tests the vibration resistance of the transverse embedding scheme with 14 transverse embedded wires, the longitudinal embedding scheme with 24 longitudinal wires, and the transverse and longitudinal staggered embedding scheme with 8 transverse wires and 13 longitudinal wires. The present invention provides a theoretical analysis method for vibration suppression schemes based on NiTi shape memory alloy wires, providing a theoretical research approach for the design of embedded wire layout in enhanced structures.

[0090] The dynamic model diagram of the vibration-resistant scheme of the reinforced composite laminate with embedded NiTi shape memory alloy wire of the present invention is shown in Figure 3 Based on the dynamic model, the displacement equation of the composite laminate is established:

[0091]

[0092] Among them, u, v, w are the displacements of the plate structure in the x, y, and z directions. The stress-strain relationship between the plates is:

[0093]

[0094] The dynamic equations of the reinforced composite laminate embedded with NiTi shape memory alloy wires are established using the Hamiltonian principle:

[0095]

[0096] Where T is the kinetic energy of the structure, U is the potential energy of the structure, δ is the symbol of the variation, and δW f is the virtual work of the external force on the laminate structure, δW sma is the virtual work of the vibration impedance provided by the enhanced vibration suppression part composed of NiTi shape memory alloy wire. Further, the various terms in the equation are analyzed:

[0097]

[0098] and is the dimensionless component of the laminate structure in the x and y directions. The stiffness matrix [R] is established based on the classical ABD theory:

[0099]

[0100] Temperature potential U T writing:

[0101]

[0102] The structural kinetic energy T is written as:

[0103]

[0104] Virtual work δW f and δW sma writing:

[0105]

[0106] Where f(t) represents the external force; m and a b represent the structural mass and external acceleration respectively, δw is the structural virtual displacement; f sma represents the damping force provided by the NiTi-SMA shape memory alloy wire; χ is the damping coefficient; Δ hori , Δ vert and Δ cross The Dirac functions representing different embedded reinforcement schemes are related to the embedded position and quantity of NiTi shape memory alloy wires; k1 and k3 are the stiffness terms of NiTi shape memory alloy wires; c1 and r 21 and r 12 is the damping term of NiTi shape memory alloy wire, and these material parameters are given in Table 1.

[0107] Table 1 Material parameters of NiTi shape memory alloy wire

[0108]

[0109] Based on the dynamic equation of the vibration suppression scheme of NiTi shape memory alloy wire, the theoretical analysis was carried out, and the amplitude theoretical sweep frequency results of the reinforced composite laminate embedded with NiTi shape memory alloy wire and the ordinary composite laminate (without alloy wire embedded) were compared. The midpoint amplitude of the laminate was selected for comparison, and the effects of the three anti-vibration enhancement schemes were compared, such as Figure 4a and Figure 4b shown.

[0110] As shown in the figure, from a theoretical perspective, the reinforcement scheme calculated by using the mechanical parameters of NiTi shape memory alloy wires of configuration F1 and configuration F2 (lateral embedding: the number of embedded wires is 14; longitudinal embedding: the number of embedded wires is 24; transverse and longitudinal staggered embedding: the number of embedded wires is 8 transversely and 13 longitudinally), can achieve significant vibration suppression of the composite laminate under the three embedding states.

[0111] In order to verify the vibration suppression performance of composite laminates, the present invention establishes a vibration suppression experimental verification platform for enhanced vibration-resistant composite laminates. The vibration suppression experimental verification platform includes an experimental piece and a fixture, a loading system, an environmental simulation device, and a data acquisition system. Furthermore, the experimental piece and fixture, the experimental piece part includes enhanced vibration-resistant and general composite laminates, the experimental fixture is a vibration suppression experimental device, and the vibration suppression experimental verification device is as follows: Figure 5a and Figure 5b As shown. The loading system refers to a system that provides external force for the test piece to vibrate, and can be composed of a vibration table, an exciter or other force-applying devices. Preferably, the present invention uses a vibration table system as the loading system. The environmental simulation device refers to a simulation system that provides the test piece with a simulation of the external environment to which the front wall panel of the cockpit is subjected when a new energy aircraft is in operation. Preferably, the present invention uses a temperature box to provide an experimental environment under different temperatures and humidities for the vibration suppression experiment. The experimental temperature range is -20°C-120°C, and the humidity range is 30% to 98% RH. The data acquisition system refers to a system in which the acceleration sensor on the test piece receives the acceleration signal generated by the vibration during the experiment, and the data acquisition system converts a series of signals into visual experimental results. Preferably, the present invention uses an LMS data processing system.

[0112] The vibration suppression experimental verification device includes a base plate, a support plate, a fixed angle bar, a support frame, a fixed block and a composite laminate. The base plate is fixed to the vibration table platform by bolt connection, and can be adjusted by the position of different mounting holes to simulate different force directions of the composite laminate. Furthermore, the adjustment of the mounting position of the base plate can achieve the force direction of the laminate at 0°, ±45° and 90°. The support plate is installed on the base plate and connected by the fixed angle bar. One section of the support frame is connected to the support plate by bolts, and the other end is connected to the fixed block and the composite laminate. The fixed blocks are installed at each of the four corners of the front and rear sides of the composite laminate, for a total of 8 blocks, and are connected to the support frame by bolts.

[0113] The present invention also discloses a vibration suppression experimental verification platform and a verification method, comprising the following steps:

[0114] Step 1, firstly, prepare a test piece of a reinforced vibration-resistant composite laminate, and prepare a control group test piece, that is, a composite laminate without wire reinforcement;

[0115] Step 2, then design and process the components of the vibration suppression experimental device;

[0116] Step 3, installing the vibration suppression experimental device on the vibration table loading system, and debugging its working frequency range and excitation range, further, the working frequency range is 10-2000 Hz, the excitation range is 0.1-2.0g, g refers to the acceleration of gravity;

[0117] Step 4, the environmental simulation device includes an adjustable temperature cavity and a humidity control module, and is installed on the vibration suppression test device to realize simulation experiments under different temperatures and humidities, and the cavity can isolate the influence of factors such as environmental noise on the vibration test results during the vibration test. Further, a temperature box is selected as the environmental simulation device;

[0118] Step 5, installing a high-precision sensor and determining its installation position on the test piece to obtain accurate measurement data. Furthermore, the present invention uses a high-precision lightweight acceleration sensor to perform vibration suppression experimental tests;

[0119] Step 6: According to the installation process of the vibration suppression test verification device, after debugging the installation status of the experimental piece, start the vibration table to record and analyze the vibration response of the system.

[0120] As shown in Figure 1, the method for preparing a composite laminate structure embedded with NiTi alloy wires provided in this embodiment is a schematic diagram of the structure of a processing mold used in preparing a composite laminate structure embedded with NiTi alloy wires. The NiTi alloy wire can achieve enhanced vibration damping performance of the composite laminate, that is, it can suppress the vibration of the composite laminate. The processing mold of the composite laminate structure embedded with NiTi alloy wires includes a wire embedding mold and a pressing plate (including an initial pressing bottom plate 105 and an initial pressing top plate 106). The wire embedding mold includes four fixed outer frame bars (two short fixed outer frame bars 101 and two long fixed outer frame bars 102 respectively), a support seat 103, a clamping fixing block 104 and a fixing bolt 107. The wire embedding position is as shown in FIG. Figure 2b shown.

[0121] In the processing mold of the composite laminate structure embedded with NiTi alloy wire, the installation quantity and installation relationship of each component are as follows: the two short fixed outer frame bars 101 and the two long fixed outer frame bars 102 are connected by bolts to complete the construction of the square outer frame (the internal space and hollow part of the square outer frame), thereby establishing the wire embedding space of the composite laminate structure; the support seat 103 is connected to the short fixed outer frame bar 101 through its own studs, and the height can be adjusted to achieve the level of the wire embedding mold. Furthermore, this example requires 4 support seats; the clamping and fixing block 104 is installed between the fixed outer frame bars 101 and 102 according to the specific wire embedding needs. In the mounting groove, the semi-cylindrical protrusion on each clamping and fixing block is connected with the semi-cylindrical groove in the mounting groove, and the upper end of the clamping and fixing block is tightened by a fixing bolt installed on the fixed outer frame bar, so that the lower end of the clamping and fixing block is fixed to the mounting groove. Furthermore, the NiTi shape memory alloy wire is fixed between the clamping and fixing block and the mounting groove; the initial pressure bottom plate 105 is placed in the middle of the fixed outer frame, and its upper end is horizontal with the bottom end of the mounting groove between the fixed outer frames 101 and 102, and the initial pressure top plate 106 is horizontally placed on the second layer plate portion 302 of the composite material, so as to press the composite material laminate.

[0122] In specific implementation, the processing flow of the processing mold of the composite laminate structure embedded with NiTi alloy wire can be carried out according to the following steps:

[0123] Step 1: placing the first layer plate portion 301 horizontally on the initial pressure bottom plate 105;

[0124] Step 2: Connect the short fixed outer frame strip 101 and the long fixed outer frame strip 102 in sequence by installing bolts 107, and adjust the height of the support base 103 to ensure that the fixed outer frame is level;

[0125] Step 3: According to the requirements of the wire embedding reinforcement solution, the NiTi shape memory alloy wire 201 is placed in the semi-cylindrical groove of the mounting groove of the fixed outer frame, and then the clamping and fixing block 104 is placed thereon and tightened with mounting bolts;

[0126] Step 4: It should be noted that after fixing one end of the NiTi shape memory alloy wire 201, the other end thereof needs to be fixed after being tightened to ensure that the NiTi shape memory alloy wire in the wire embedding space is embedded in the neutral layer of the composite laminate in a straight line;

[0127] Step 5: After the above-mentioned wire embedding work is completed, the second layer plate portion 302 of the composite material is placed on the bottom layer 301 and the wire-embedded NiTi shape memory alloy wire 201, and then horizontally covered with the initial pressure top plate 106 and pressed tightly;

[0128] After the above steps are completed, the internal processing of the vibration damping enhanced composite laminate has been completed, and the next step is to form the experimental piece. In the first step, a heavy object is placed on the initial pressure top plate 106 to press the experimental piece. Preferably, a 10kg mass block is selected to press for 30 minutes; in the second step, after the pressing is completed, the heavy object is removed, and then the NiTi shape memory alloy wire part between the outside of the vibration damping enhanced composite laminate and the fixed outer frame of the processing mold is cut off to take out the experimental piece; in the third step, the experimental piece embedded with the NiTi shape memory alloy wire is hot-pressed and cured to complete the final molding of the experimental piece. Preferably, an autoclave is selected for high-temperature and high-pressure processing and molding, the pressure is selected to be 4 standard atmospheres, the temperature is 120°C, and the processing time is 5 hours. The alloy wire and the layer plate part are hot-pressed and cured together, and the physical properties of the layer plate part do not change. The alloy wire and the composite laminate are tightly fixed together.

[0129] The present invention proposes a dynamic analysis method based on wire embedding design, constructs a vibration suppression model, verifies the anti-vibration performance under various layout schemes, and verifies its performance through an experimental test platform. The present invention is suitable for the vibration control needs of new energy aircraft and aerospace fields, and provides new theoretical and technical support for the design and application of efficient anti-vibration structures.

[0130] like Figure 5a As shown, this embodiment provides a vibration suppression test platform and a specific process for verifying the vibration suppression capability of a composite laminate structure embedded with NiTi alloy wires. The vibration suppression verification platform includes a vibration suppression test verification device (test piece and fixture), a loading system, an environmental simulation device and a data acquisition system. The vibration suppression test device includes an experimental device base plate 401, a support plate 402, a fixed angle material 403, a support frame 404, a fixed block 405-1 and a vibration damping enhanced composite laminate 406. The installation process of the vibration suppression test verification device can be carried out according to the following steps during specific implementation:

[0131] Step 1: According to the preparation method of the composite laminate structure embedded with NiTi alloy wires, the processing of the vibration damping enhanced composite laminate is completed, and the components of the fixture part in the vibration suppression experimental verification device are processed;

[0132] Step 2: The bottom plate 401 of the experimental device is fixed on the loading system by installing bolts. Preferably, the present invention uses a vibration table system as the loading system, and the bottom plate 401 is installed on the vibration table platform;

[0133] Step 3: The support plate 402 is vertically mounted on the base plate 401, and the two components are fixed by the fixing angle bar 403. Furthermore, the fixing angle bar is connected to the support plate and the base plate respectively by fixing bolts;

[0134] Step 4: One end of the support frame 404 is connected to the support plate 402 by bolts, and the other end is connected to the test piece composed of the fixing block 405-1 and the composite laminate 406 by bolts;

[0135] Step 5: The fixing blocks are installed at the four corners of the composite laminate 406, 4 at the front and 4 at the back, and are installed on the support frame 404 by bolts. Furthermore, the composite laminate 406 has holes at the corresponding positions of the four corners of the laminate according to the installation requirements to meet the installation requirements on the experimental device.

[0136] The above is the installation process of the vibration suppression test verification device. After completing the above work, the vibration suppression capability verification of the vibration damping enhanced composite laminate can be carried out. The specific process of the vibration suppression capability verification can be carried out according to the following steps during the specific implementation:

[0137] Step 1, installing the vibration suppression experimental device on the vibration table loading system, and debugging its working frequency range and excitation range, further, the working frequency range is 20-1000 Hz, the excitation range is 0.1-2.0g, g refers to the acceleration of gravity;

[0138] Step 2, the environmental simulation device includes an adjustable temperature cavity and a humidity control module, and is installed on the vibration suppression test device to realize simulation experiments under different temperatures and humidities, and the cavity can isolate the influence of factors such as environmental noise on the vibration test results during the vibration test. Further, a temperature box is selected as the environmental simulation device;

[0139] Step 3, installing a high-precision sensor and determining its installation position on the test piece to obtain accurate measurement data. Furthermore, the present invention uses a high-precision lightweight acceleration sensor to perform vibration suppression experimental tests;

[0140] Step 4: According to the installation process of the vibration suppression test verification device, after debugging the installation status of the experimental piece, start the vibration table to record and analyze the vibration response of the system.

[0141] After the above steps are completed, a vibration suppression experiment can be performed to verify the vibration suppression capability of the enhanced structure designed by the present invention. In order to fully verify the vibration suppression capability, the present invention carried out two groups of vibration test experiments to verify the vibration suppression capability of the vibration suppression scheme provided by the present invention at different temperatures, and the vibration suppression capability of different NiTi shape memory alloy wire embedding schemes.

[0142] Vibration reduction capability at different temperatures:

[0143] This embodiment conducts vibration tests on the vibration damping effect of the vibration damping enhanced composite laminate at different temperatures. The results are shown in FIG6 , where Figure 6a Represents the midpoint frequency sweep test data of a composite laminate without structural reinforcement, Figure 6b and Figure 6c The midpoint frequency sweep test data of the vibration damping reinforced composite laminate with longitudinal embedding and transverse embedding are respectively represented. Furthermore, the frequency sweep range of the loading device is 200-1100Hz, the acceleration excitation provided by the vibration table is 0.3g, the temperature range provided in the temperature box is -20℃-115℃, and the experimental data are summarized with each 15℃ as an observation temperature. The results show that the enhanced design of the embedded NiTi shape memory alloy wire provided by the present invention can achieve vibration suppression at different temperatures and different embedding schemes. Preferably, the vibration reduction effect of transverse embedding is better.

[0144] The vibration damping effect test of the vibration damping enhanced composite laminate at different temperatures can be carried out according to the following steps:

[0145] Step 1: According to the specific process of the vibration suppression capability verification, the vibration suppression test device shown is installed on the vibration table platform, and then the test piece is installed on the vibration suppression test device. Further, a high-precision lightweight acceleration sensor is installed at the midpoint of the test piece. Preferably, the acceleration sensor in this example is installed by gluing;

[0146] Step 2: Install the environmental simulation device, preferably a temperature box in this example, on the vibration suppression test device to provide a constant temperature and humidity space for the test piece, and set the temperature to -20°C. Furthermore, the test piece in this step is the unreinforced composite laminate;

[0147] Step 3: After debugging the installation status of the vibration suppression experimental device and the environmental simulation device, start the vibration table to perform a vibration test. The acceleration excitation range of the vibration test is 0.1-2.0g, preferably 0.3g in this example, and the frequency range of the vibration test is 10-2000Hz, preferably 200-1100Hz in this example. Further, after the vibration test is completed, the data acquisition system can obtain the amplitude-frequency response curve result of the experimental piece. In this example, the data acquisition system is preferably an LMS system;

[0148] Step 4: After the experimental test in step 3 is completed, the experimental results of the unreinforced composite laminate at -20°C can be obtained, and then the temperature box is turned on and the temperature is set to -5°C. After the temperature stabilizes, the operation of step 3 is repeated. Further, the temperature is set to 10 / 25 / 40 / 55 / 70 / 85 / 100 / 115°C in sequence, and each time is accompanied by the operation of step 3. In this way, the frequency sweep results of the unreinforced composite laminate at different temperatures can be obtained;

[0149] Step 5: Open the temperature box, take out the experimental piece therein, that is, the unreinforced composite laminate, replace it with a longitudinally embedded vibration damping enhanced composite laminate, repeat the operations of steps 2, 3 and 4, and obtain the frequency sweep results of the longitudinally embedded vibration damping enhanced composite laminate at different temperatures;

[0150] Step 6: Open the temperature box again, take out the experimental piece, replace it with a laterally embedded vibration damping enhanced composite laminate, repeat the operations of steps 2, 3 and 4, and obtain the frequency sweep results of the laterally embedded vibration damping enhanced composite laminate at different temperatures;

[0151] Step seven: The frequency sweep data of the unreinforced composite laminates and the longitudinally and transversely embedded vibration damping enhanced composite laminates obtained in steps four, five and six at different temperatures are sorted and visualized as images to obtain the vibration suppression law of the enhanced design embedded with NiTi shape memory alloy wire provided by the present invention.

[0152] After the above steps are completed, the vibration test method for the vibration damping effect of the vibration damping enhanced composite laminate at different temperatures provided in this example has been introduced. Based on this example, it can be experimentally proved that the enhanced design embedded with NiTi shape memory alloy wire provided by the present invention can achieve vibration suppression at different temperatures.

[0153] Vibration reduction effects of different embedding solutions:

[0154] Considering the vibration reduction adaptability of the enhanced design under various conditions, this embodiment carries out multi-resonance peak and global vibration reduction research of composite laminates under different boundary conditions, and discusses the vibration reduction effect of the horizontal and vertical staggered embedding method. By changing the fixed block 405-1 in the vibration suppression experimental verification device to a fixed frame 405-2, the boundary condition can be changed to global fixation of the four sides, such as Figure 5b As shown, further, by changing the installation position of the sensor, the vibration data at different positions can be measured. Preferably, in this example, the midpoint position (a / 2, b / 2) and the left point position (a / 4, b / 2) are selected, and the vibration reduction effects of the three embedding schemes are discussed, as shown in Figures 7 and 8. Figure 7 discusses the influence of different NiTi memory alloy wire diameters and different embedding schemes on the vibration reduction effect. Preferably, the diameter of the NiTi shape memory alloy wire is selected as 0.1mm and 0.2mm, the embedding scheme is selected as lateral embedding, longitudinal embedding and transverse and longitudinal staggered embedding, the installation position is the midpoint, and the acceleration excitation is selected as 0.2g. The results show that different wire diameters and embedding schemes can effectively achieve vibration suppression, and the embedding scheme of 0.2mm wire has less effect on the natural frequency of the system, and the effects of lateral embedding and staggered embedding are more obvious. Figure 8 discusses the vibration reduction of multiple resonance peaks, the embedding scheme is selected as lateral embedding, longitudinal embedding and transverse and longitudinal staggered embedding, the installation position is the left point, and the acceleration excitation is selected as 0.2g, 0.3g and 0.5g. The results show that the enhanced design embedded with NiTi shape memory alloy wire can achieve vibration reduction of multiple resonance peaks under different excitation conditions. Generally speaking, the multi-band vibration reduction effect is better with the horizontal and vertical staggered embedding.

[0155] Among them, the first boundary condition is to fix the four corners of the laminate and then conduct a vibration test; the second boundary condition is to fix the four corners and four sides of the laminate and then conduct the test. The experimental results show that the three embedding schemes can effectively improve the vibration resistance of the composite laminate. The three embedding schemes can achieve vibration reduction for the two-order resonance peaks of the composite laminate. The longitudinal embedding and staggered embedding schemes can achieve a vibration reduction efficiency of more than 60% for the first-order resonance, and the transverse embedding and staggered embedding schemes can achieve a vibration reduction efficiency of more than 50% for the second-order resonance. In general, the staggered embedding reinforcement scheme can more effectively achieve vibration reduction for the composite laminate.

[0156] The research on multiple resonance peaks and global vibration reduction of composite laminates under different boundary conditions can be carried out in the following steps:

[0157] Step a: According to the specific process of the vibration suppression capability verification, the vibration suppression experimental device shown is installed on the vibration table platform, and then the experimental piece is installed on the vibration suppression experimental device, and further a high-precision lightweight acceleration sensor is installed at the left point of the experimental piece by gluing;

[0158] Step b: starting the vibration table to perform a vibration test, wherein the acceleration excitation range of the vibration test is 0.1-2.0g, preferably 0.2g, 0.3g and 0.5g in this example, and the frequency range of the vibration test is 10-2000Hz, preferably 90-480Hz in this example, and the data acquisition system can obtain the amplitude-frequency response curve result of the experimental piece, and the data acquisition system in this example is preferably an LMS system, and the experimental piece in this step is the unreinforced composite laminate;

[0159] Step c: after the experimental test in step b is completed, the experimental piece is removed and replaced with the laterally embedded vibration damping enhanced composite laminate, an acceleration sensor is installed, and the experimental process of step b is repeated;

[0160] Step d: After the experimental test in step b is completed, the experimental piece is removed and replaced with the longitudinally embedded vibration damping enhanced composite laminate, an acceleration sensor is installed, and the experimental process of step b is repeated;

[0161] Step e: after the experimental test in step b is completed, the experimental piece is removed and replaced with the vibration damping enhanced composite laminate with the horizontal and vertical staggered embedding, an acceleration sensor is installed, and the experimental process of step b is repeated;

[0162] Step f: The frequency sweep data of the unreinforced composite laminate and the longitudinally and transversely embedded vibration damping enhanced composite laminate obtained in steps c, d and e are sorted and visualized as images to obtain the multi-resonance peaks and global vibration reduction experimental results of the enhanced design embedded with NiTi shape memory alloy wire provided by the present invention under different boundary conditions.

[0163] Structural embodiment

[0164] The present embodiment discloses a composite laminate structure embedded with NiTi alloy wires, the composite laminate structure being prepared by the preparation method in the above-mentioned embodiment, the composite laminate structure comprising: an alloy wire surface, and a first layer plate portion and a second layer plate portion symmetrically arranged along the alloy wire surface; the first layer plate portion and the second layer plate portion are connected to the alloy wire surface by hot pressing and curing.

[0165] The composite laminate structure can tightly fix the alloy wire between the two layer parts, and can stabilize the alloy wire on the alloy wire surface. The alloy wire surface is embedded in the two layer parts through high temperature and high pressure, so that the alloy wire does not have too much deviation. In the preparation method example, a vibration test was conducted on the processed vibration damping enhanced composite laminate, verifying the feasibility of using the composite laminate structure in the example as a vibration reduction material.

[0166] Application Examples

[0167] This embodiment discloses an application of a composite laminate structure embedded with NiTi alloy wires, specifically, a wall panel of a new energy aircraft is the composite laminate structure embedded with NiTi alloy wires described in the above embodiment. The composite laminate is simulated as a front wall panel of a new energy aircraft cockpit for enhanced vibration resistance design, and the composite laminate simulating the front wall panel of the new energy aircraft cockpit includes enhanced vibration resistance and general composite laminates.

[0168] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification, equivalent change and modification made to the above embodiment according to the technical essence of the present invention still falls within the scope of the technical solution of the present invention.

Claims

1. A method for preparing a composite laminate structure embedded with NiTi alloy wires, characterized in that: The steps include: Step 1, fixing two ends of a plurality of NiTi alloy wires arranged along a first direction and / or a second direction on a wire inserting die respectively to form an alloy wire surface; Step 2, laying a first layer plate portion below the alloy wire surface, laying a second layer plate portion above the alloy wire surface, the first layer plate portion and the second layer plate portion are symmetrically arranged, an initial pressure bottom plate is arranged below the first layer plate portion, and an initial pressure top plate is arranged above the second layer plate portion; Step 3, applying a first pressure to the initial pressing top plate and the initial pressing bottom plate, so that the first layer plate portion, the alloy wire surface and the second layer plate portion form a prefabricated structure; Step 4, cutting the exposed NiTi alloy wire between the prefabricated structure and the wire embedding mold, and curing and molding at high temperature and high pressure to obtain a composite laminate structure embedded with NiTi alloy wire.

2. The method for preparing a composite laminate structure according to claim 1, characterized in that: In step 4, a hot-pressing tank is used for high-temperature and high-pressure curing and molding.

3. The method for preparing a composite laminate structure according to claim 1, characterized in that: In step 4, the pressure of the high temperature and high pressure curing molding is 4-5 standard atmospheres, the temperature is 100-150° C., and the processing time of the high temperature and high pressure curing molding is 4-6 hours.

4. The method for preparing a composite laminate structure according to claim 1, characterized in that: The first pressure is the gravity of a mass block of 10-20 kg, and the time for applying the first pressure to the initial pressure top plate and the initial pressure bottom plate is ≥30 minutes.

5. The method for preparing a composite laminate structure according to claim 1, characterized in that: The first direction is the horizontal direction, and the second direction is the vertical direction; The spacing between adjacent NiTi alloy wires is 10 to 30 mm; The diameter of the NiTi alloy wire is 0.1-0.4 mm.

6. The method for preparing a composite laminate structure according to claim 1, characterized in that: The first layer plate portion includes 2N fiber composite material layers, and the second layer plate portion includes 2N fiber composite material layers, wherein N=1, 2, 3, 4, 5.

7. The method for preparing a composite laminate structure according to claim 6, characterized in that: The fiber composite material layer is made of carbon fiber composite material prepreg or glass fiber composite material.

8. The method for preparing a composite laminate structure according to claim 1, characterized in that: The wire inserting die comprises a square frame, a clamping and fixing block is provided on the square frame, a semicircular groove is provided on the square frame, and a semicircular protrusion is provided on the clamping and fixing block, and the shapes and quantities of the semicircular groove and the semicircular protrusion match each other, so as to fix the NiTi alloy wire; The shapes of the initial pressure top plate and the initial pressure bottom plate match the shape of the square frame and are slightly smaller than the space enclosed by the square frame.

9. A composite laminate structure embedded with NiTi alloy wires, characterized in that: The composite laminate structure is prepared by the preparation method according to any one of claims 1 to 8, and the composite laminate structure comprises: An alloy wire surface, and a first layer plate portion and a second layer plate portion symmetrically arranged along the alloy wire surface; The first layer plate portion and the second layer plate portion are connected to the alloy wire surface by hot pressing and curing.

10. An application of a composite laminate structure embedded with NiTi alloy wires, characterized in that: The wall panel of the new energy aircraft is the composite laminate structure embedded with NiTi alloy wires as described in claim 9.

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