119 results about "Composite laminates" patented technology

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.

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 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 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 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.

The application discloses an aramid composite laminated plate and a preparation method and application thereof. Aramid III fabric is used as a matrix, the aramid III fabric is completely soaked in a shear thickening fluid (STF), a layer of polyurethane resin (PU) is uniformly applied after drying, and a hot pressing lamination technology is used to stably combine the matrix and the STF, so that the aramid composite laminated plate is obtained. The application provides a method for stably combining STF and a protective material to prepare the aramid composite laminated plate, and proposes a hybrid preparation scheme for different STF impregnated aramid fabrics. Compared with a traditional bulletproof material, the aramid composite laminated plate has a significantly improved bulletproof performance, and a new idea is provided for application of the STF on bulletproof equipment, and problems such as instability of the STF in the fabric are solved. The application also provides a new application method for improving a ballistic performance of a bulletproof plate by using the STF.

This invention relates to the field of composite material performance prediction technology, specifically to a method for predicting the tensile strength of fiber-reinforced composite laminates by incorporating Puck physical constraint domain adaptation. The method includes: constructing a dataset; constructing a total loss function; constructing and training a tensile strength prediction model; and predicting the tensile strength of the laminates in the new material system. This method fully utilizes physical knowledge and existing material data as prior information, significantly improving the model's cross-material system data utilization capability and engineering applicability, effectively shortening the R&D cycle, and achieving high-precision prediction of key performance indicators of tensile strength in fiber-reinforced composite laminates under new material R&D scenarios.

A composite bollard about which a mooring line can locate. The bollard has at least one bitt projecting upwardly from a base and is defined by a shell construction of a monocoque fibre composite laminate. The bitt is secured by fasteners to a marine vessel in a cantilevered beam manner at the base so that a bending moment applied to the bitt 5 by the mooring line creates resulting tension and compression forces vectored parallel the upwardly direction of the bitt in the shell. At least the tension forces are able to be transferred via the fasteners to the marine vessel.

The present invention relates to a composite laminate (10) comprising at least one substrate layer (20) and at least one coating layer (30) applied on top of the substrate layer (20), said substrate layer (20) being a fabric. The coating layer (30) is a gel formed from silk proteins, the silk proteins being obtained by fermentation of at least one microorganism in a liquid medium.

The present application provides a kind of composite structure. The composite structure includes composite laminate structure and core material assembly;Two composite laminate structures are included in the composite laminate structure, and the core material assembly is located between the two composite laminate structures. The core material assembly includes a first core portion and a second core portion. The distance between the first core portion and the load is less than the distance between the second core portion and the load. The density of the first core portion is greater than the density of the second core portion, which can make the structure lightweight.

A method of forming a structural member is provided. The method includes forming a first uncured composite laminate beam structure by arranging at least one composite material in a first defined configuration. The method further includes forming a second uncured composite laminate beam structure by arranging the at least one composite material in a second defined configuration. The method further includes co-curing the first surface of the first uncured composite laminate beam structure with the first surface of the second uncured composite laminate beam structure to form a composite laminate beam structure, where the composite laminate beam structure is a single continuous structure. The method further includes coupling a surface of the composite laminate beam structure to an inner surface of the skin.

The invention relates to a wavefront measurement method based on a modulation type Shack-Hartmann wavefront sensor, the modulation type Shack-Hartmann wavefront sensor comprises a composite laminated modulation device and a detector, and the composite laminated modulation device is composed of a microlens array and a binary random coding mask. The method comprises the following steps: acquiring a composite diffraction pattern which is collected by a detector and is coherently modulated by a composite laminated modulator; wherein the composite diffraction pattern has diffraction texture features, and the diffraction texture features are obtained by coding after coherent modulation is carried out on high-frequency phase information through a binary random coding mask; reconstructing a high-frequency complex wavefront based on the diffraction texture features by adopting a coherent modulation phase recovery algorithm; and outputting the high-frequency complex wavefront as a wavefront measurement result. According to the scheme provided by the invention, unified measurement of high spatial resolution and wide dynamic range can be realized under the condition of single exposure, so that the inherent limitation of the SHWFS between the spatial resolution and the dynamic range in the related technology is broken through.

The multilayer fabric 403 comprises two sheets 600, 900 of woven tows of fibres which are impregnated with a polymer 903 and adhered together. Each sheet is woven in a satin weave with long floats on

The invention relates to a composite material structure damage characterization and evaluation method under an icebreaking load, and belongs to the technical field of ship and ocean engineering equipment. Comprising the steps of preparing a composite material sample, preparing an ice body model, carrying out a collision test, and carrying out multi-dimensional damage characterization and damage evaluation. The composite material sample comprises a composite material laminated plate and a composite material sandwich beam. Carrying out macroscopic, internal and microscopic damage characterization on the composite material laminated plate, and carrying out macroscopic and microscopic internal damage characterization on the composite material sandwich beam. And according to multi-scale characterization results under different energy collisions, comprehensive evaluation of the multi-scale damage of the composite material structure is completed. Aiming at the defects of multi-focus composite material preparation and lack of a composite material structure damage characterization and evaluation method under an icebreaking load in the prior art, a composite material laminated plate and sandwich beam damage characterization system suitable for equipment such as a polar aircraft and an icebreaker is constructed, and special coverage of damage characterization and evaluation under an ice layer collision scene is realized. And actual engineering requirements are met.

This application relates to the field of material structure health monitoring technology, and in particular to a method, device, equipment, storage medium, and computer program product for damage identification of composite laminates. The method involves acquiring structural description information of the laminate to be tested, constructing an analysis model of the laminate, and determining a parameter space; solving for multiple natural frequencies for different combinations of damage parameters within the parameter space, and establishing a vibration feature sample library that pairs natural frequency features with damage parameters; employing a hybrid intelligent modeling strategy based on the sample library, utilizing swarm intelligence to optimize neural network parameters, and training candidate identification models with multiple natural frequencies as input and damage parameters as output; selecting a target identification model based on preset engineering requirements constraints, collecting vibration signals, and extracting multiple natural frequencies consistent with the sample library to form the vibration features to be tested; after random noise processing and frequency offset correction of the vibration features to be tested, inputting them into the target identification model, and outputting the damage parameter identification results.

The invention relates to a transient liquid phase connection method based on a composite laminated structure, belongs to the technical field of power semiconductor packaging interconnection, and mainly solves the problems of poor joint reliability and poor high-temperature service performance caused by insufficient solder wettability and narrow process window in the traditional transient liquid phase connection technology. According to the method, a symmetric composite laminated structure of a Cu substrate / Sn-Cu soldering paste / Cu-Ni alloy sheet / Sn-Cu soldering paste / Cu substrate is constructed, optimized printing process parameters are combined, and the good wetting characteristic of the Sn-Cu soldering paste and the microalloying effect of the Ni element in the Cu-Ni alloy sheet are utilized in the welding process, so that the interface bonding quality is remarkably improved, and the formation of (Cu, Cu)-Cu-Ni alloy sheets at low temperature is promoted; and a high-melting-point and compact all-intermetallic compound joint mainly comprising Ni) Sn. The obtained joint is low in porosity and high in heat conductivity and has excellent mechanical and thermal reliability at high temperature, the process is compatible with an existing production line, and a high-feasibility and low-cost packaging solution is provided for a high-power semiconductor device.

To provide assemblies, systems, and methods of lightning strike protection for aircraft composite structures.SOLUTION: The lightning strike protection material assembly 10 includes a lightning strike expanded metal foil layer 16 having a lightning strike expanded metal foil 18 and a resin-infused scrim layer having a non-metallic scrim infused with an infusion resin 45 having a tailored viscosity and a tailored cure profile. The lightning strike protection assembly 10 is configured to be laid up on and co-cured with an uncured composite laminate assembly having a plurality of structural ply layers pre-impregnated with a structural resin. The structural resin has a structural resin viscosity and a structural resin cure profile that are different from the tailored viscosity and the tailored cure profile, thereby preventing intermixing of the structural resin and the infusion resin during co-curing and allowing the infusion resin to effectively encapsulate the lightning strike expanded metal foil 18 and form a cured lightning strike protected composite structure 80 capable of achieving a defined resin boundary.SELECTED DRAWING: Figure 2D

Proposed are a two-dimensional vertical composite laminate including graphene and hexagonal boron nitride and a method of fabricating the same. The composite laminate includes a first layer and a second layer positioned on the first layer, in which the first layer includes a first boron nitride layer containing hexagonal boron nitride or a first graphene layer containing graphene, and the second layer includes a second boron nitride layer containing hexagonal boron nitride or a second graphene layer containing graphene. The composite laminate allows for the control of the twist angle and stacking order of each layer, so that the composite laminate can have the desired crystal structure, crystal thickness, and composition to exhibit novel physical properties.