191 results about "Composite laminates" patented technology

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.

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 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.

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 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.

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).

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.

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.

This invention relates to the field of biomimetic impact-resistant composite materials technology, specifically to an impact-resistant sandwich composite laminate with a multi-layered structure inspired by the giant toothed ant and its preparation method. The impact-resistant sandwich composite laminate comprises multiple fiber tube layers and multiple fiber cloth layers, wherein one fiber tube layer is located between two fiber cloth layers; the fiber cloth layers include multiple unidirectional fiber cloth layers and / or multiple woven fiber cloth layers; each fiber tube layer includes at least one columnar fiber tube layer, and each columnar fiber tube layer is composed of an array of multiple columnar fiber tubes arranged in a vertically aligned bundle along its thickness direction. This invention enhances the interlayer bonding strength and load-bearing capacity through the interfacial wave-locking effect of the woven fiber cloth and the interlayer interlocking effect of the columnar fiber tubes. It exhibits excellent impact resistance and energy absorption characteristics, and is not easily delaminated under impact loads, demonstrating high load-bearing capacity and strong damage tolerance, providing promising applications in the field of impact protection.

The invention discloses a preparation method of a large-size amorphous alloy motor stator core, and belongs to the technical field of motor manufacturing. Comprising the following steps: cutting a rectangular laminated sheet of which the length of an iron-based amorphous alloy strip is twice of the width of the strip; cutting a plurality of square high-frequency silicon steel sheets and aluminum alloy sheets of which the side lengths are twice the width of the amorphous strip; two amorphous alloy laminations are flatly laid to form a square, the middle seam of the second layer of laminations is perpendicular to the seam of the previous layer of laminations, the laminations are aligned and alternately stacked in this way, the aluminum sheets and the silicon steel sheets are clamped every certain thickness, and the thin aluminum sheets and the silicon steel sheets are stacked at the two ends of the multi-layer composite laminations; and clamping the composite laminated sheet, carrying out linear cutting, carrying out annealing heat treatment, carrying out vacuum impregnation and curing. According to the method, the stator core with the outer diameter larger than the width of the amorphous strip and smaller than two times of the width of the strip can be manufactured, the middle silicon steel sheets and the thin aluminum sheets increase the mechanical strength of the core, and too high temperature rise of the silicon steel sheets in operation is avoided; and annealing heat treatment is performed after linear cutting, so that the influence of machining stress on the performance of the amorphous alloy is reduced.

The application discloses a kind of carbon fiber reinforced steel plate composite laminated board and preparation method thereof, belong to carbon fiber composite material technical field.The carbon fiber reinforced steel plate composite laminated board disclosed in the application is connected by mixed connection mode of adhesive connection and mechanical connection between steel plate and carbon fiber cloth, and then carbon fiber reinforced steel plate composite laminated board is obtained by moulding technology.The application can fully exert the mechanical properties and lightweight characteristics of high-strength carbon fiber by the new mixed connection mode of mechanical connection and adhesive connection of carbon fiber cloth and steel plate, significantly improves the strength, reliability and stability of steel plate, and increases the heat resistance and corrosion resistance of laminated board, which can effectively reduce the influence of complex geological conditions on the quality of ultra-deep well drill pipe.The laminated board effectively reduces the weight compared with the same thickness steel plate, and greatly reduces the cost compared with pure carbon fiber composite material.

The utility model relates to a nanobubble preparation device based on a resistance thermal effect. The nanobubble preparation device based on the resistance heat effect comprises a box body, the bottom of the box body is fixedly connected with two fixing plates which are arranged in parallel at intervals, the opposite side faces of the two fixing plates are each provided with a plurality of inserting grooves which are distributed at equal intervals in the length direction, and the inserting grooves in the two sides are distributed in a mirror symmetry mode to jointly form a positioning groove of a heat production resistor; the two ends of each heat generation resistor are embedded in the corresponding positioning grooves respectively, a composite heat conduction coating layer is arranged on the surface of each heat generation resistor, the composite heat conduction coating layers are formed by aluminum foil and tin foil in a composite lamination mode and tightly wrap the outer surfaces of the heat generation resistors, and micron-scale channels or nano-scale holes are formed in the surfaces of the composite heat conduction coating layers through laser etching. Therefore, bubble nucleation is promoted. The nanobubble preparation device based on the resistance thermal effect solves the problems of low nanobubble generation efficiency, non-uniform size, poor stability and the like in the prior art.

The present disclosure provides a system and method for real-time visualization of a material during ultrasonic non-destructive testing. The system includes a graphical user interface (GUI) capable of showing a three-dimensional (3-D) image of a composite laminate constructed of a series of two-dimensional (2-D) cross sections. The GUI is capable of displaying the 3-D image as each additional 2-D cross section is scanned by an ultrasonic testing apparatus in real time or near real time, including probable defect regions that contain a flaw such as a hole, crack, wrinkle, or foreign object within the composite. Furthermore, in one embodiment, the system includes an artificial intelligence capable of highlighting defect areas within the 3-D image in real time or near real time and providing data regarding each defect area, such as the depth, size, and / or type of each defect.

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.

A laminate with improved substrate shape resemblance and moisture resistance may include a plurality of layers. The plurality of layers may be structured in various orders, or layups. Each layer of the plurality of layers may have a specific thickness, weight / areal density, and / or other features, such as orientation, relative to one or more of the other layers.

A method for manufacturing a multi-layered and multi-functional thermoplastic composite structure includes supplying a plurality of reinforcing layers including continuous reinforcing fibers and thermoplastic resin to an intermittent press; and supplying at least one functional layer to the intermittent press adjacent to the plurality of reinforcing layers. The at least one functional layer is selected from a group consisting of an electromagnetic shielding layer and a thermal runaway protection layer. The method includes heating and pressing the plurality of reinforcing layers and the at least one functional layer to form a composite laminate.

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

Laminating device for laminating several layers (35) arranged in a stack (36) to form a laminate composite (38), comprising at least one laminating tool (11) which includes an upper tool (32) and a lower tool (33) and at least one laminating plate (12) in each case, between which a stack (36) of several layers (35) is arranged to form a laminate composite (38), wherein the at least one metallic laminating plate (12) has a thermal conductivity of 50-80 W / mK, characterized in that at least one sealing element (41) is provided between the laminate plate (12) and an upper tool or lower tool (32, 33), which, after the laminate plates (12) are brought together with the respective upper tool and lower tool (32, 33), forms a fluid-fillable pressure chamber (46).

The present invention relates to a method and system for ultrasonic imaging of the out-of-plane fiber orientation of composite materials using half-layer resonance frequency enhancement. The method uses half the resonance frequency of a single-layer prepreg as the center frequency of the excitation signal to complete ultrasonic imaging of the out-of-plane fiber orientation of a thick composite material. First, the resonance frequency of the single-layer prepreg is determined, and an ultrasonic probe is used to perform water immersion ultrasonic testing on the composite laminate. Then, the reflected signals at each position on the scanning path are collected and band-pass filtered and Hilbert transformed respectively to locate the front wall and the back wall of the composite laminate. The instantaneous phase at the front wall is used to determine the position of the interlayer resin. Finally, the interlayer resin positions corresponding to each filtered reflection signal are presented in a graph to achieve ultrasonic imaging of the out-of-plane fiber orientation of the composite material. Compared with the prior art, the present invention has the advantages of increasing the effective imaging thickness, improving imaging accuracy, and reliability.

The invention relates to the field of airplane composite material maintenance, and particularly discloses a composite material layering damage in-situ prefabrication method based on chemical reaction, which comprises the following steps: cutting prepregs, and obtaining the prepregs with corresponding quantity and angle; calculating the volume V and the mole number n of the required gas; calculating the mass of the required chemical reagent according to the mole number n of the required gas; laying a predetermined number of layers of prepregs, and then spreading a chemical reagent at the laying position on the prepregs; a preset number of layers of prepregs are laid on the upper portion where the chemical reagent is laid; and the laid composite laminated plate is heated and pressurized to be cured, and gas generated by decomposition forms a cavity in the composite laminated plate after curing is completed. In the paving and manufacturing process of the composite material, a small amount of chemical reagent capable of generating gas through thermal decomposition is arranged between prepreg paving layers, in the heating and curing process of the composite material, the chemical reagent is decomposed to generate gas, and then layering damage can be prefabricated in the composite material.

The invention provides a light guide assembly which comprises a waveguide layer, a first optical adhesive layer, a second optical adhesive layer and a lens layer which are sequentially arranged in a stacked mode, the hardness of the first optical adhesive layer is larger than that of the second optical adhesive layer, and the thickness of the first optical adhesive layer is smaller than that of the second optical adhesive layer. The surface, connected with the second optical adhesive layer, of the lens layer is a curved surface. The invention further provides a head-mounted device, a manufacturing method of the light guide assembly and a composite type fitting glue structure.

A hot melt adhesive film having no urethane group [-NH-C (O)-O-] comprises a polyester base material layer having a moisture permeability of 5000 g / m < 2 > * 24 hr or less and a hot melt adhesive layer provided on the polyester base material layer. The hot melt adhesive layer comprises regenerated copolyester. The regenerated copolyester has a melting point of from 80 DEG C to 130 DEG C, a glass transition temperature of from-60 DEG C to 10 DEG C, and a heat enthalpy of from 5 J / g to 30 J / g. The regenerated copolyester is obtained by processing a polyester recovery regenerated material component, and the regenerated copolyester comprises 50 to 100 mol% of a first carboxylic ester chain segment represented by a formula (I), 0 to 35 mol% of a second carboxylic ester chain segment represented by a formula (II), and 0 to 15 mol% of a third carboxylic ester chain segment represented by a formula (III) based on the regenerated copolyester. The regenerated copolyester has more than 20 wt% of a recycled component derived from a polyester recycled material component. The invention also provides a composite laminated body without the carbamate group, which comprises the hot melt adhesive film without the carbamate group. The definitions of R11, R21, R31 and R32 refer to the description and the claims.

The invention discloses a forming method for reducing curing deformation of a composite material laminated board through non-isothermal curing. The forming method specifically comprises the following steps: step 1, determining a curing shrinkage generation area of a laminated composite material; step 2, constructing a first stage of a non-isothermal curing period, namely a rapid heating stage; step 3, constructing a second stage of the non-isothermal curing period, namely a slow heating stage; and step 4, constructing a third stage of the non-isothermal curing period, namely a cooling stage. The invention solves the problem that the existing curing molding process is easy to cause the deformation of the laminated composite material laminate.

The present invention provides a plasma-resistant composite laminate comprising a substrate, a first adhesion layer and a first plasma-resistant layer. The substrate has an upper surface, and the first adhesion layer is disposed between the upper surface of the substrate and the first plasma-resistant layer. An arithmetic average roughness (Ra) of the upper surface of the substrate is from 2 μm to 10 μm, a porosity of the first adhesion layer is from 0.05% to 10%, a porosity of the first plasma-resistant layer is from 0.03% to 6%, and a ratio of the porosity of the first adhesion layer relative to the porosity of the first plasma-resistant layer ranges from 1.6 to 333.33. The plasma-resistant composite laminate described has good performance on adhesion, thereby reducing the incidence of peeling during plasma treatment, and thus prolonging the lifetime of plasma reaction chamber.

This invention relates to a multi-objective interval optimization method for uncertain composite material structures, comprising the following steps: (1) Considering the uncertainty of parameters such as Young's modulus and material density, an interval uncertainty optimization model for composite laminate structures with different material thicknesses under given ply angles and material distributions is established. (2) An interval multi-objective optimization algorithm based on non-probabilistic set theory is used to solve the uncertain composite material structure optimization model. In the solution process, an initial composite material optimization model set is established using the Latin hypercube sampling method; the interval uncertainty analysis calculation of the total mass and first-order vibration frequency of the composite material is performed based on the interval dimension-by-dimensional analysis method; the interval non-dominated sorting is performed based on the dominance probability calculation method and the interval crowding calculation method of non-probabilistic set theory to achieve elite selection of composite material optimization models; iterative optimization is performed until the optimal composite material optimization model set is obtained. This invention will explore a new solution for the structural design optimization of composite materials with uncertainty.