334 results about "Composite laminates" patented technology

The invention relates to the technical field of composite material damage detection, and particularly discloses a composite material damage intelligent detection and modeling method based on ultrasonic point cloud and deep learning, and the method comprises the steps: S1, data collection, S2, ultrasonic data processing, S3, simulation model construction, S4, PVT-RCNN model processing, S5, RI CP processing, and S6, damage model generation. According to the method, an ultrasonic point cloud data acquisition platform and a data processing method are designed, a sufficient composite laminate ultrasonic point cloud data set with obvious features is constructed, a PVT-RCNN model which is based on PV-RCNN and is improved by Swi n Transformer is designed, the feature extraction capability of the model on point cloud is improved, three-dimensional space information of damage is intelligently obtained, and the accuracy of the damage is improved. An RI CP registration algorithm and a damage model generation method are designed, a finite element model with damage is directly generated according to damage point cloud, and the material performance can be obtained through calculation.

The invention provides a manufacturing process of high-heat-insulation ray-proof antibacterial glass. The high-heat-insulation ray-proof antibacterial glass comprises outer-layer glass, a middle functional layer, inner-layer glass and an extensible layer, the manufacturing process comprises a PVB adhesive film preparation process and a laminated glass whole process, wherein the PVB adhesive film preparation process specifically comprises the steps of raw material mixing, melt extrusion, tape casting and coiling; the whole process of the laminated glass comprises the steps of glass pretreatment, interlayer assembly, high-temperature and high-pressure forming and post-treatment and quality inspection. According to the design scheme of the multi-film composite laminated glass, based on the structural characteristics of the laminated glass, a layered ray-blocking customized glass scheme is provided in combination with the combination of heat-insulating PVB films and other films with different functions, and the scheme is suitable for scenes such as sunlight rooms, agricultural planting or market curtain walls and the like.

The invention discloses a multi-modal fusion composite laminated structure low-speed impact positioning method, and relates to the technical field of impact positioning, and the method comprises the steps: obtaining impact response signals of a plurality of strain sensors on a composite laminated structure, and combining the impact response signals into a composite impact signal; taking the envelope entropy as a fitness function, and adopting a moss growth optimization algorithm to optimize a penalty coefficient of successive variational mode decomposition; performing successive variational mode decomposition on the composite impact signal based on the optimal penalty coefficient, and selecting a part of mode component with the maximum energy distribution correlation coefficient to reconstruct a de-noised signal; converting the de-noised signal into a time-frequency spectrogram, and converting an original composite signal into a two-dimensional coding diagram through a relative position matrix algorithm; constructing a multi-modal sample data set containing the time-frequency spectrogram and the coding diagram; and training the multi-modal regression model and carrying out impact positioning. According to the scheme, the modal purity of signal decomposition can be remarkably improved, and the characterization capability and fusion efficiency of multi-modal features are enhanced.

The invention discloses an embedded optical fiber composite material optimization method based on a self-adaptive genetic algorithm, and relates to the field of fiber reinforced composite materials. The method comprises the following steps: selecting layout parameters of optical fiber sensors as design variables, establishing a sensor layout optimization model by taking the minimum number of optical fiber sensors meeting constraint conditions of sensing and covering a whole to-be-monitored area as an optimization target, and solving the model to obtain the optimal layout of the optical fiber sensors; based on the optimal layout of the optical fiber sensor, selecting a layering parameter of the composite material laminated plate as a design variable, taking the condition that the structure does not fail and the sensing covers the whole to-be-monitored area as constraint conditions, and taking the minimization of the total weight and displacement of the structure as an optimization target, establishing a composite material laminated plate optimization model; solving the model to obtain an optimal layering design scheme of the composite laminated plate; and optimizing the embedded optical fiber composite material according to the optimal layering design scheme and the optimal layout of the optical fiber sensor. The method can effectively reduce the calculation cost and improve the optimization efficiency.

The invention relates to the technical field of composite material damage repair, in particular to a method for repairing a composite material laminated plate with a fiber guiding characteristic. The repairing method comprises the following steps of pneumatic grinding, patch preparation, surface treatment, cleaning, adhesive film cutting, pasting, adhesive film curing, finishing and the like. According to the method, the adaptive patch is prepared by pneumatically polishing the rectangular cut hole of the stepped surface, the adhesive film is used for curing in the middle, and the adhesive layer is combined with the matched patch, so that a fiber-guided repairing structure is realized; under the condition that the structure repairing strength is guaranteed, the area for removing healthy mother board materials is reduced to the maximum extent, the probability of local stress concentration of a repairing bonding face is reduced, the machining difficulty is lowered, and the universality of repairing design application is improved. And by setting different step lengths, the stress load of the cementing repair surface is more uniform instead of being excessively concentrated on the 0-degree laying layer, so that the repair setting is more reasonable, and the service life of the repaired structure is prolonged.

The invention is suitable for the technical field of composite materials, and provides a laminated composite material toughening intermediate layer and a preparation method thereof, and the preparation method comprises the following steps: obtaining an aramid short fiber wet-laid non-woven felt by using a processing method of a wet non-woven material; then the aramid fiber surface is activated through hydrofluoric acid etching; the preparation method comprises the following steps: grafting soluble polyether-ether-ketone resin with an active end group on the surface of the aramid fiber, and impregnating the aramid fiber at the same time; and the polyetheretherketone resin grafted on the surface of the aramid fiber is re-endowed with crystallinity through acidification reduction reaction of the polyetheretherketone resin grafted on the surface of the aramid fiber. According to the invention, the interface bonding performance of the aramid fiber toughening middle layer in the laminated composite material is regulated and controlled, the interlayer toughness of the carbon fiber reinforced polyether-ether-ketone composite material laminated board can be effectively improved while the original crystallinity of the polyether-ether-ketone resin is maintained, the possibility of interlayer cracking can be obviously reduced, a brand new scheme is provided for interlayer toughening of such materials, and the application prospect is broad. The material has potential application prospects in the fields of aerospace special materials and the like.

The present invention discloses a bionic gradient spiral structure composite laminate and a design and preparation method, belonging to the technical field of composite materials. The composite laminate of the present invention comprises a plurality of fiber spiral units coaxially stacked along the thickness direction; the fiber spiral units are stacked layer by layer through carbon fiber prepreg, and each laid fiber layer is rotated by the same angle compared with the fiber direction of the previous layer, and finally a cumulative rotation of 180° is a unit cycle; different fiber spiral units have different rotation angles. The present invention adjusts the out-of-plane impact damage characteristics and damage distribution of the composite laminate through the synergistic effect of fiber spiral units with different rotation angles, thereby improving the out-of-plane impact resistance of the composite laminate.

This invention discloses a method for calculating the vibration response of a delaminated composite laminate, belonging to the field of structural defect calculation and analysis. The method includes: dividing the composite laminate with delamination defects into delaminated and intact regions based on the damage condition; decoupling the delaminated regions dynamically; describing the vibration characteristics of each component in both the delaminated and intact regions using elastic waves based on elastic wave propagation theory, and establishing vibration state vector expressions for each region; determining the compatibility relationship based on the displacement continuity and internal force equilibrium conditions at the coupling point between the delaminated and intact regions, and establishing structural dynamic equilibrium equations in wave space based on the boundary conditions of the composite laminate; solving the structural dynamic equilibrium equations to obtain the amplitudes of elastic waves of each order; and calculating the vibration response of each region of the composite laminate based on elastic wave theory and amplitude calculation. This invention solves the problem of low computational efficiency in existing methods.

The invention discloses a preparation method of a continuous carbon fiber reinforced thermoplastic resin composite material. The preparation method comprises the following steps: S1, preparing a continuous carbon fiber reinforced resin prepreg tape; s2, thermoplastic resin electrostatic spinning films are added among multiple layers of continuous carbon fiber reinforced resin matrix composite prepreg tapes prepared in the step S1; and S3, carrying out hot press molding on the multi-layer continuous carbon fiber reinforced resin prepreg tape of which the interlayers are added with the thermoplastic resin electrostatic spinning films obtained in the step S2 to obtain the continuous carbon fiber reinforced resin-based composite material. By adding the electrostatic fiber composite film between the continuous carbon fiber reinforced resin matrix composite prepreg tape layers, the interlayer mechanical property of the composite laminated board is improved, and the preparation process does not change equipment for preparing the continuous carbon fiber reinforced resin matrix composite in the prior art, and is easy to implement and reasonable in economical efficiency.

The invention relates to the technical field of computer simulation, in particular to a composite material laying layer loss design and finite element modeling method, which comprises the following steps of S1, acquiring geometric profiles and laying layer information of all laying layer areas of a composite material part through a CATIA interface, and storing the geometric profiles and the laying layer information as an area list; and S2, by using the CATIA geometric processing capability and the interface, quickly geometrically generating a layer laying and layer losing line in the areas, and realizing the display of layer laying and layer losing. According to the method, by utilizing the interface capacity of CATIA and HyperMesh, information reading of a composite material laying layer area, automatic generation and display of a layer loss line and automatic creation of a finite element model are achieved, the problems of low efficiency and poor accuracy in traditional design modeling are effectively solved, composite material laying layer loss design and finite element modeling can be rapidly and accurately completed, and the method is suitable for large-scale popularization and application. And the quality and efficiency of the composite material structure design are obviously improved.

The invention discloses a side arch biological plate double-core bionic anti-impact structure which is composed of a plurality of bionic structure layers which are vertically stacked and spirally arranged, a double-core bionic interlayer in each bionic structure layer is arranged between a top protection layer and a bottom protection layer, and a bionic plate core layer in each double-core bionic interlayer is designed by imitating the internal structure of a front wing of a beetle. The design of a honeycomb core layer and a small column structure on the honeycomb core layer is adopted, the small column structure is composed of cylindrical holes formed in the honeycomb core layer, the upper ends of the honeycomb core layer and two side arch core layers arranged on the two sides of the honeycomb core layer are all fixed to a top protection layer, and the lower ends of the honeycomb core layer and the two side arch core layers are all fixed to a bottom protection layer; wherein the top protection layer and the bottom protection layer are both made of fiber reinforced resin matrix composite laminated boards, the side arch core layer is made of a hot melt adhesive material, and the bionic plate core layer is made of a fiber reinforced composite material and is manufactured in a 3D printing processing mode. The impact-resistant plastic has the advantages of excellent impact resistance, low manufacturing cost and simple process.

The invention provides a method and system for optimizing the laying angle of a composite material laminated plate of a power battery pack, and relates to the technical field of power battery packs, and the method comprises the following steps: arranging four layers of composite material laminated plates on an upper cover of the power battery pack; obtaining a first-order modal frequency and a vibration mode under the initial laying layer angle through a finite element method; a modal sensitivity function is calculated, and an improved Hamilton-Jacobi equation is generated; solving to obtain a layer laying angle change field and meeting the continuity requirement of an automatic fiber laying process; and iteratively updating until the frequency gain rate is smaller than a preset threshold value, and determining a final layering scheme. According to the method, the anti-vibration performance of the power battery pack upper cover is effectively improved.

The present invention relates to a compression test device for a composite laminate with a large length-thickness ratio, belonging to the technical field of composite material testing. It can achieve that the two-side boundaries are kept in a simply supported constraint throughout the compression test process, and the simply supported condition is not easily changed at the moment of failure. The flatness of the loading plane on the length and width surfaces of the plate specimen is also adjusted through a grid device. The device includes: two groups of side supports are respectively arranged at both ends of the bottom installation component, and the specimen is vertically arranged between the two groups of side supports; two groups of bottom constraint plates, four simply supported constraint plates and two groups of out-of-plane adjustable grids are respectively arranged on both sides of the plate-shaped specimen, and the two groups of bottom constraint plates are respectively arranged at the bottom of the plate-shaped specimen, and the four simply supported constraint plates are respectively arranged in pairs at the left and right ends of the plate-shaped specimen; the bottom constraint plates are connected to the bottom installation component, and the simply supported constraint plates are connected to the corresponding side supports; two groups of end constraint plates are respectively arranged on both sides of the top of the plate-shaped specimen and are fixedly connected to the end loading plates arranged thereon, and the end loading plates are connected to the test loading equipment.

The invention discloses an ultrasonic guided wave damage ellipse imaging positioning method and equipment for a layer decreasing composite material laminated plate. The method comprises the following steps: S1, acquiring thickness change direction information of the laminated plate and position coordinates of an excitation transducer and a receiving transducer; s2, according to the material characteristic parameters, simulating and calculating the propagation time of ultrasonic guided waves transmitted from an excitation transducer to any point to generate a first theoretical propagation time map, and simulating and calculating the propagation time of the ultrasonic guided waves transmitted from any point to a receiving transducer to generate a second theoretical propagation time map to generate a second theoretical propagation time map; coupling influence of thickness change and material anisotropy on guided wave propagation is considered in the simulation process; s3, transmitting an ultrasonic guided wave signal, and extracting the actual flight time of a damaged wave packet; s4, calculating theoretical total propagation time, and determining a candidate area where damage exists; and S5, on the basis of repeated operation of the multiple groups of transducer pairs, taking a plurality of candidate region intersections to determine a final damage position. The objective of the invention is to solve the positioning error problem caused by the structural characteristics of a laminated plate in a traditional algorithm, and to realize more accurate damage detection and positioning.

The invention relates to a quick repair method for an assembled composite material. The quick repair method comprises the following steps: S1, manufacturing a composite material laminated plate; s2, cutting the composite material laminated plate; s3, holes are formed in the hexagonal composite material patch units; s4, obtaining a large number of hexagonal composite material patch units; s5, adhering the alkali-free glass fiber cloth; s6, holes are formed in the aluminum alloy plate; s7, the aluminum alloy plate is cut; s8, a large number of aluminum alloy connecting units are obtained; s9, repairing and patch assembling; s10, adjusting the appearance of the curved surface of the assembly structure; s11, the assembly structure is installed; through prefabrication and splicing of a large number of hexagonal composite material patch units and aluminum alloy connecting units, the repairing and manufacturing time of large composite materials is shortened, and the repairing speed is increased; by changing the using number of the hexagonal composite material patch units and the aluminum alloy connecting units, rapid repair of different damage areas can be effectively achieved; by changing the bending shape of the aluminum alloy connecting unit, the damage of the composite materials with different curvatures can be effectively and rapidly repaired.

A composite material damage terahertz imaging method based on two-stage unsupervised learning relates to the field of composite material nondestructive testing, and comprises the following steps: preparing composite material laminated plate samples with different damage thicknesses, collecting time domain terahertz signals, and constructing a label-free single sample damage terahertz data set; constructing a data alignment layer, and carrying out alignment processing on the time domain terahertz signals; a two-stage unsupervised learning framework is adopted, damage features are extracted through a stack auto-encoder, and a pseudo-label data set is generated through spectral clustering; training a convolutional neural network classifier by using the pseudo-label data set, and classifying non-label data; and carrying out terahertz category coding imaging on a classification result to obtain a high-resolution damage two-dimensional image. The method does not depend on any manual intervention and data labels, and intelligent recognition and high-resolution imaging of the internal damage of the composite material in different application scenes are achieved.

The invention relates to the technical field of composite structure protection stickers, and particularly discloses a composite layered protection sticker for a folding screen and a production process of the composite layered protection sticker. The invention discloses a composite layered protection paste for a folding screen. The composite layered protection paste sequentially comprises a polymeric membrane layer, ultra-thin flexible glass, a polymeric membrane layer and a functional coating from bottom to top, the polymeric membrane layer is prepared from the following components in parts by mass: 40 to 50 parts of alicyclic epoxy resin, 20 to 30 parts of hydroxyl-terminated polyisobutene, 5 to 10 parts of hydroxyl-terminated polybutadiene, 8 to 10 parts of modified vinyl alkoxy silane, 5 to 7 parts of modified nano silicon dioxide, 30 to 40 parts of curing agent, 0.4 to 0.6 part of catalyst and 30 to 50 parts of solvent; the composite layered protective paste prepared by the invention has excellent advantages in bending resistance and impact resistance.

The utility model discloses an integrated clamp for testing the tension and compression performance of a composite laminate after impact. The integrated clamp comprises a bottom plate, two side supporting plates, four side clamps, two middle anti-instability baffles, two bottom clamps, a top cover plate and two top clamps, in the tensile property test stage, a plurality of fifth screw holes are formed in the two ends of the test piece in the X-axis direction, and a plurality of first bolts penetrate through the third screw holes in the top clamp and the bottom clamp to be screwed into the fifth screw holes. According to the invention, through reasonable and exquisite cooperation and connection of the subsystems, the support can be simply, practically and effectively provided for the composite material laminate containing initial impact damage, so that the support is provided for stretching, compression and tension-compression cyclic loading performance tests after the composite material laminate is impacted.

The invention discloses a zero-Poisson-ratio composite material honeycomb core and a preparation method thereof, and belongs to the field of composite material forming. The honeycomb core comprises multiple layers of rib plates and multiple layers of stretching curved wall honeycombs, the rib plates are bonded between every two adjacent layers of stretching curved wall honeycombs and on the outer side of the stretching curved wall honeycomb on the outermost layer, and the multiple stretching curved wall honeycombs of each layer of stretching curved wall honeycombs are arranged in a matrix mode. A unit-cell concave hexagonal curved-wall honeycomb is formed between two adjacent stretching curved-wall honeycombs and rib plates, so that the zero Poisson ratio of the whole honeycomb structure is realized. The method comprises the following steps: designing the shapes of the prepreg and the demolding cloth; positioning the prepreg and the demolding cloth by using a positioning tool, and stacking the prepreg and the demolding cloth according to a specified sequence; for the thermosetting or thermoplastic fiber reinforced prepreg, a composite laminated plate is cured in a gradient manner by adopting a hot pressing process or a composite laminated plate is cured by adopting a mold pressing process; and finally, cutting, stretching, secondary curing, cooling and demolding cloth removal are carried out. The method is used for preparing the zero-Poisson-ratio composite material honeycomb core.

The invention provides an ultrasonic imaging detection method for full-depth defects of a composite material laminated plate, and belongs to the field of nondestructive testing. According to the method, ultrasonic C scanning and ultrasonic B scanning are combined for imaging detection, firstly, an A scanning waveform emitted by a transducer and reflected back on the bottom face of the detected composite material laminated plate is obtained, then, the position of an imaging signal gate is set, and the initial position of the gate is located in front of an interface wave signal in the A scanning signal; the end position of the gate is located behind a bottom wave signal in the A scanning signal, no other interference signals are collected except interface waves, bottom waves and signals between the interface waves and the bottom waves, and finally, C scanning imaging and B scanning imaging are conducted on the signals in the gate. The ultrasonic pulse reflection method is adopted to realize full-thickness non-blind-area defect detection of the composite laminated plate, the defect of blind area detection of the ultrasonic pulse reflection method is overcome, the detection method is simple and convenient, the operation is easy, and the detection result is accurate and reliable.

The invention belongs to the field of composite material residual stress detection, and particularly relates to a method for testing residual stress of a laying process SiCf / SiC composite material matrix, which comprises the following steps of: preparing a SiCf / SiC composite material flat plate with a laying layer of [(90-degree) 3 / (0-degree) 6 / (90-degree) 3] by adopting a prepreg-infiltration process, and then cutting a straight strip sample on the flat plate; the method comprises the following steps: designing samples with a specific layering sequence by utilizing a distribution rule of residual stress in 0-degree layering and 90-degree layering of a layering composite material, and acquiring a laminate material modulus EX, a material modulus E0 in a 0-degree direction and a material modulus E90 in a 90-degree direction by utilizing different samples; and finally, calculating the residual compressive stress of the matrix by utilizing a residual stress theoretical formula based on a beam theory. According to the test scheme designed by the invention, the relationship between the residual stress and the bending curvature is established based on the beam theory of the composite laminate, and a plurality of modulus parameters of the material and the interlayer fracture toughness of the material can be obtained in the test process of the residual stress.

Disclosed herein is a thermal composite laminated cell comprising a negative electrode, a plurality of positive electrodes, and a separator, the separator comprising a first separator and a second separator, the negative electrode being attached to and between the first separator and the second separator to form a composite laminate comprising a plurality of body portions and a plurality of bending portions arranged alternately and continuously, the bending portions being provided with partially cut structures, the positive electrodes each being arranged between adjacent body portions in a thickness direction of the negative electrode, a projection in the thickness direction of the positive electrode falling completely within a planar area of the body portions. The present application overcomes the problem of poor alignment of the existing composite laminated cell, and has the advantages of good alignment and stable performance.

The invention relates to a panel assembly for a vehicle, the panel assembly comprising a composite laminated panel (10) having an inner panel (1), an outer panel (3) adjacent to the inner panel (1), and a thermoplastic intermediate panel (2) bonding the inner and outer panels (1, 3) together. A through-hole (16) extends between an inner surface (12) of the inner panel (1) and an outer surface (14) of the outer panel (3) on the laminated panel (10), and a gasket (20) provides a seal between the through-hole (16) and a sensor (40) located within the through-hole (16), the gasket surrounding the sensor (40) in a manner that fixes the sensor (40) to the laminated panel (10).

This application relates to the technical field of composite structure protective films, and specifically discloses a composite laminated protective film for a folding screen and its production process. A composite laminated protective film for a folding screen comprises, from bottom to top in sequence, a polymer film layer, an ultra-thin flexible glass, a polymer film layer, and a functional coating; the preparation raw materials of the polymer film layer include the following components: 40 to 50 parts by mass of alicyclic epoxy resin, 20 to 30 parts by mass of hydroxyl-terminated polyisobutylene, 5 to 10 parts by mass of hydroxyl-terminated polybutadiene, 8 to 10 parts by mass of modified vinyl alkoxysilane, 5 to 7 parts by mass of modified nano-silica, 30 to 40 parts by mass of a curing agent, 0.4 to 0.6 parts by mass of a catalyst, and 30 to 50 parts by mass of a solvent; the composite laminated protective film prepared in this application shows excellent advantages in anti-bending performance and impact resistance.

Disclosed herein are multilayer composite laminates comprising continuous fibers and a polymer matrix comprising a poly(arylene sulfide) (PAS) polymer, a polyetherimide (PEI) polymer, and a polyamide-imide (PAI) polymer.

A method for optimizing the laying trajectory of laying tapes of each layer of a composite laminate with an opening is disclosed. The method is designed to construct a local coordinate system with the center of the opening on the composite laminate as the origin, and to define the laying trajectory of the laying tapes of each layer of the composite laminate based on the streamline cluster of the ideal fluid cylinder. This can reduce the number of laying tapes of each layer cut by the opening and reduce the degree of damage to the force transmission path. In addition, a global coordinate system is established with the center of the opening on the composite laminate as the origin. The laying tape laying angles corresponding to each finite element mesh of the geometric model of the composite laminate in the local coordinate system are transformed into the corresponding laying tape laying angles in the global coordinate system by coordinate transformation, and finite element calculation is performed. Taking the strength of the composite laminate as the optimization target, the laying trajectory of the laying tapes of each layer of the composite laminate is obtained, and the laying trajectory of each layer of the laying tape is optimized to ensure the strength of the composite laminate.

The application belongs to the field of composite structure layer design of aircraft structure, and particularly relates to a composite laminate layer proportion optimization method, step S1: in the aircraft design process, the design load and the aircraft structure layout are determined, the design allowable value of the composite material applied to the aircraft is determined, including the axial allowable strain epsilon ad , the shear allowable strain gamma ad ; step S2: based on the external load of the aircraft structure and the specific layout, the load characteristic value T of the aircraft to be layered structure is calculated, and the load characteristic value T represents the trend characteristics of the axial load and the shear load of the aircraft to be layered structure; step S3: a plurality of preset proportion composite laminates in a layering library are obtained, and the material characteristic value T m of the composite laminates is calculated; step S4: based on the structure load characteristic value T, the composite laminate with the material characteristic value T m matching the load characteristic value T is selected. The relationship between the structure and the material is quantified, so that the structure material selection is more intuitive and optimal.

The invention relates to the technical field of composite boards, in particular to a composite laminated board with excellent flame retardant property and mechanical property. In order to solve the problem that in the prior art, reinforcing layers are all made of carbon fiber materials, and cost is high, the composite laminated board with the excellent flame retardant property and mechanical property is provided and comprises a thermoplastic resin layer, a carbon fiber cloth layer and a glass fiber cloth layer, and the thermoplastic resin layer and the carbon fiber cloth layer are arranged adjacently. The carbon fiber cloth layer and the glass fiber cloth layer are adjacently arranged, and the thermoplastic resin layer comprises polyetherimide and polycarbonate. According to the invention, the glass fiber cloth layer with lower cost is used for replacing part of the carbon fiber cloth layer for compounding to form the composite laminated board, so that the overall manufacturing cost of the composite laminated board is reduced, and meanwhile, the prepared composite laminated board can still maintain relatively ideal performance in flame-retardant effect and mechanical strength.

The utility model relates to the technical field of metal composite laminates, in particular to a composite metal laminate with high impact resistance, which comprises two aluminum alloy plate layers, polypropylene fiber reinforced layers are arranged between the two aluminum alloy plate layers, two polypropylene fiber reinforced layers are arranged between the two aluminum alloy plate layers, and the polypropylene fiber reinforced layers are arranged between the two aluminum alloy plate layers. Two natural rubber layers are arranged between the two polypropylene fiber reinforced layers, a thermoplastic polyurethane layer is arranged between the two natural rubber layers, and an ethylene-vinyl acetate copolymer adhesive layer is arranged between the aluminum alloy plate layer and the polypropylene fiber reinforced layers. An ethylene-acrylic acid copolymer adhesive layer is arranged between the natural rubber layer and the polypropylene fiber reinforced layer. According to the metal composite laminate, the composite metal laminate with high impact resistance is obtained on the premise that few metal layers are used and the machining difficulty is reduced.

The invention relates to a wafer-level film stress regulation and control method, module and device. The method comprises the following steps: constructing a stress regulation and control module according to set parameters and a structure, and integrating the constructed stress regulation and control module at a set position of a semiconductor device; wherein the stress regulation and control module comprises a stress regulation and control layer, and the stress regulation and control layer adopts a metal / medium composite laminated structure; in the wafer manufacturing process, a target net stress value needed by a current wafer is obtained through a manufacturing execution system, the optimal thickness proportion needed by a stress regulation and control layer for achieving the target net stress value is calculated through an internal stress prediction model, and the manufacturing execution system generates a technological formula according to the optimal thickness proportion; and the deposition equipment is driven to deposit the stress regulation and control layer under the optimal thickness ratio. By designing the independent stress regulation and control module, it can be ensured that the crystallization quality, the stoichiometric ratio and the electrical / piezoelectric performance of the functional film are not sacrificed, and linear, accurate and predictable stress control over the wafer is achieved.