20 results about "Advanced composite materials" patented technology

The invention discloses a high-temperature-resistant water-based polyimide sizing agent for carbon fibers, modified carbon fibers, a resin-based composite material of the modified carbon fibers, a preparation method and application of the resin-based composite material, and belongs to the technical field of advanced composite materials. The sizing agent disclosed by the invention is prepared by carrying out condensation polymerization on aromatic dianhydride and monofunctional aromatic amine to generate polyamide acid and then carrying out an ionizing salt formation process. The sizing agent has excellent storage stability and thermal stability, can effectively improve the wettability of the carbon fiber surface, and significantly improves the interface bonding performance of the carbon fiber reinforced polyimide composite material. The sizing agent provided by the invention can remarkably improve the room-temperature and high-temperature interface bonding strength of the carbon fiber reinforced polyimide composite material, and is suitable for the fields of aerospace, high-end equipment manufacturing and the like.

The invention relates to the technical field of power electronic component manufacturing and advanced composite material application, in particular to a 3D inductor based on the Ampere's law and a method thereof. The three-dimensional precise interlocking winding comprises a functional composite framework, a three-dimensional precise interlocking winding and a magnetic core assembly, according to the system, a framework is formed by compositing a heat-conducting insulating substrate and soft magnetic powder, and air gaps between winding layers are physically filled through step-shaped positioning ribs; the core is that a low-thermal-resistance export path is established by utilizing the high heat conduction characteristic of the framework, and a heat conduction mode is converted from coil-to-air to coil-to-framework; the gradient difference between the core temperature and the surface temperature in the coil is effectively reduced through the embedded heat dissipation array, the heat dissipation problem under the high power density is solved, and the device performance is remarkably improved.

The application discloses a method for researching the influence of random hole geometric deviation on the strength of an aircraft wall plate connecting structure, and relates to the field of advanced composite material connection, and comprises the following steps: determining a characterization parameter of hole geometric deviation of a composite material strip-hole laminated plate test piece; establishing a simulation model of a composite material single-nail connecting structure plug-nail connection without hole geometric deviation; based on the characterization parameter and the simulation model of the composite material single-nail connecting structure plug-nail connection without hole geometric deviation, a simulation model of a composite material single-nail connecting structure interference plug-nail process is established; a simulation model of a composite material connecting structure tensile load is established; based on the simulation model of the composite material connecting structure tensile load, a probability distribution graph of the strength change value of the structure is established, and the strength distribution trend under different geometric deviations is determined; and based on the strength distribution trend under different geometric deviations, a new composite material hole making deviation design criterion is constructed. The application can improve the hole making precision of the connecting hole, and reduce the manufacturing difficulty and cost.

The invention provides a composite material prefabricated body sewing forming method and system, and relates to the technical field of advanced composite material manufacturing. According to the method, on the basis of joint cooperation of a mechanical arm, a modular stitching head and a control system, selection and area matching of stitching processes are completed by analyzing the local thickness, geometric morphology, curvature change and enhancement direction requirements of a composite prefabricated body, and different stitching processes are adopted in different areas of the same prefabricated body for cooperative stitching. In the forming process, the control system conducts unified planning and coordinated control on the motion trail of the mechanical arm, the action of the sewing head and sewing process parameters, and switching and accurate execution of the sewing process are achieved. The method can effectively meet the three-dimensional reinforced forming requirements of complex curved surfaces and special-shaped composite material preforms, improves sewing consistency, reliability and process flexibility, and is suitable for manufacturing preforms of high-performance composite material structures in the fields of aerospace and the like.

The invention belongs to the technical field of advanced composite materials, and particularly relates to a high-temperature-resistant water-based sizing agent, a preparation method thereof and application of the high-temperature-resistant water-based sizing agent in a carbon fiber reinforced polyimide composite material. The water-based sizing agent is prepared by taking an aromatic triamine monomer, aromatic anhydride and an ionized functional agent as raw materials through a controllable condensation polymerization reaction. The high-temperature-resistant and high-temperature-resistant liquid crystal composition has excellent solubility, high-temperature stability and long-term storage stability, and 5% thermal weight loss temperature is higher than 550 DEG C. The sizing agent can significantly improve the interface bonding strength of carbon fibers and a resin matrix. The water-based sizing agent provided by the invention has the characteristics of high temperature resistance and interface enhancement function, can meet the strict requirements of the aerospace field on the mechanical properties of composite materials such as carbon fiber / polyimide in an extreme thermal environment, and has important application value.

The invention discloses an energy storage-reinforcement integrated rib and a manufacturing method, and relates to the technical field of advanced composite material manufacturing and green building, and the energy storage-reinforcement integrated rib comprises a fiber reinforced composite material rib body. When the FRP rib is used and in the aspect of a product, the FRP rib comprises a hollow tubular bearing framework made of a fiber reinforced composite material, an alkali-resistant anti-corrosion layer formed on the outer surface of the hollow tubular bearing framework and an axial hollow cavity used for containing the replaceable battery unit, a buffer heat conduction layer can be arranged in the cavity, and detachable sealing end covers are arranged at the two ends of the cavity; functions of structural load bearing, environmental corrosion resistance and electric energy storage are integrated. In the aspect of the method, a unique continuous composite pultrusion process is adopted, an alkali-resistant outer layer and a bearing framework are synchronously formed through a hollow mold core, the size and the inner wall quality of a hollow cavity are accurately controlled by utilizing an internal cooling and peelable core mold technology, and a space is reserved for filling of a buffer heat conduction layer.

This invention discloses a method for preparing high aspect ratio boron nitride nanosheets through precursor conversion, belonging to the field of two-dimensional material preparation technology. The method includes the following steps: 1. Uniform blending of a boron nitride precursor and a foaming agent; 2. Programmed temperature foaming and high-temperature sintering of the mixed powder; 3. Liquid-phase fractionation and centrifugation of the sintered powder to prepare high aspect ratio boron nitride nanosheets. This invention achieves high-throughput preparation of boron nitride nanosheets with aspect ratios between 1000 and 3300 through in-situ foaming polymerization by adjusting the type and proportion of the foaming agent. This solves the problems of long processing time, low yield, complex post-processing, and small aspect ratio of the obtained boron nitride nanosheets in traditional boron nitride nanosheet preparation methods, laying the foundation for the industrial preparation of boron nitride nanosheets and their application in the field of advanced composite materials.

The invention discloses a low-dimensional carbon / fiber composite material damping performance optimization preparation method based on interface regulation and control. The method comprises the following steps: step 1, negative pressure impregnation of a nanocarbon macroscopic body; 2, high-speed shearing, mixing and dispersing of the nanocarbon macroscopic body; and step 3, performing interface regulation and control compounding on the carbon fiber fabric and the nano reinforced resin slurry. The core innovation of the method lies in that through gradient compounding of a nanocarbon macroscopic body three-dimensional skeleton and a resin matrix, multi-scale interface structure regulation and control and forming process parameter optimization, a quantitative relation between an interface energy consumption mechanism and the damping performance is established, and synergistic enhancement of the vibration reduction performance and the mechanical performance of the composite material is achieved. According to the invention, full impregnation and uniform dispersion of the nanocarbon macroscopic body in the resin matrix are realized, the problem of obstruction of the nanofiller in the forming process is effectively solved through an interface regulation and control composite process, a composite material laminated board with a controllable structure is formed, and the composite material laminated board is suitable for weight reduction requirements of advanced composite material equipment for aerospace and the like.

The invention discloses an integrated energy storage rib, which relates to the technical field of composite structures and comprises a long-strip-shaped battery core and a packaging protection layer directly formed outside the long-strip-shaped battery core through a fiber winding process, and the long-strip-shaped battery core and the packaging protection layer are combined to form an approximately solid integral component. Preferably, the packaging protection layer is of a multi-layer structure and comprises an insulating buffer layer on the inner layer and a high-strength bearing layer on the outer layer. Through an advanced composite material winding process, fusion of an energy storage element and a structural force bearing element on the microscopic scale is achieved, a traditional building rib material is endowed with the energy storage function, and the structural strength, the interface bonding force, the heat dissipation efficiency and the insulation reliability which are far better than those of a traditional packaging mode are achieved; the integrated energy storage rib is particularly suitable for an intelligent civil engineering structure which needs to integrate the functions of bearing, energy storage, health monitoring and the like.

The invention relates to a CFRP high-quality laser drilling method cooperatively assisted by hydrochloric acid and a zinc plate, and belongs to the technical field of composite material processing. The method comprises the following steps: S1, pretreating the surface of a sample; s2, mounting a sample and accurately positioning the sample; s3, planning a processing path and setting an aperture; s4, determining process parameters; s5, drilling is carried out according to set parameters; and S6, after machining, the heat affected zone, the roundness, the taper and the inner wall roughness of the through hole are measured. According to the method, the hydrochloric acid solution is used for strengthening heat dissipation and promoting chip discharge, meanwhile, the zinc plate is used for absorbing residual heat and regulating and controlling the appearance of an outlet through the interaction between the zinc plate and laser, and therefore the quality of the through hole is remarkably improved, the taper of the through hole is as low as 0.029, the roughness of the inner wall is only 1.097 m, the roundness of an inlet and the roundness of an outlet are as high as 99.4% and 98.1% respectively, and no thermal damage exists in an outlet area. The process is efficient and stable, high-quality through hole preparation of an advanced composite material can be achieved, the application requirement of the high-end equipment field is met, and good engineering application value is achieved.

The invention relates to a low-cost and high-precision unmanned aerial vehicle control surface integral forming method, and belongs to the technical field of advanced composite material manufacturing. According to the method, the core force bearing part of the control surface of the unmanned aerial vehicle breaks through the traditional step-by-step manufacturing mode of composite material forming and metal piece post-assembly, and integrated compression molding of the metal connecting piece and the composite material control surface is achieved. Through the technical means of precise positioning of the metal connecting piece, compression molding and forming integration of the composite material and the like, integrated forming of the metal connecting piece and the composite material is achieved, and the problem that traditional control surface manufacturing needs separate part manufacturing, machining and manual assembling is solved. The prepared unmanned aerial vehicle control surface has the advantages of being high in qualified rate, high in forming precision, high in production efficiency, low in cost, good in structural integrity and the like.

The invention discloses a composite flapping wing structure based on a chiral / anti-chiral core layer, relates to the technical field of advanced composite material structure design, metamaterial structure design and application and the like, and aims to solve the problems of stress concentration, complex driving, low efficiency and the like in underwater flapping wing propulsion. The structure comprises chiral / reverse chiral core layers, flexible skin layers and the like which are alternately arranged, the chiral / reverse chiral core layer realizes uniform stress distribution during deformation through negative Poisson's ratio characteristics, and the flexible skin layer enhances shear transfer and reduces flow resistance. Compared with a traditional connecting rod flapping wing mechanism, the structure driving efficiency and reliability are improved, the driving structure is simplified, the deformation characteristic of the flapping wing mechanism is more flexible, and therefore the flapping wing mechanism can adapt to the more complex and multi-mode working environment.

The invention belongs to the technical field of advanced composite materials, and discloses a high-hardness and high-toughness recyclable CFEP-SiC composite material and a preparation method thereof. The CFEP-SiC composite material is prepared from the following raw materials in percentage by weight: 55.7 to 58.5 percent of T800-grade carbon fiber, 17.5 to 18.9 percent of bisphenol A type epoxy resin, 7.0 to 7.6 percent of alicyclic epoxy resin, 7.0 to 7.6 percent of a DDS curing agent, 0.9 to 1.1 percent of a CTBN prepolymer, 3.4 to 3.8 percent of alpha-SiC nanoparticles, 1.6 to 2.0 percent of beta-SiC whiskers, 0.25 to 0.35 percent of hydrophobic gas-phase SiO2, 0.35 to 0.45 percent of a silane coupling agent, 0.25 to 0.35 percent of a dispersing agent, 0.15 to 0.25 percent of a microcapsule catalyst and 1.6 to 2.0 percent of core-shell structure particles. Through collaborative design of multi-scale toughening, multi-dimensional reinforcing and controllable recycling functional units and in combination with a resin transfer molding (RTM) process, the hardness and toughness of the composite material are remarkably improved, the composite material is endowed with the recoverable characteristic, and the application requirements of the aerospace field are met.

This invention provides a silicon-chain acrylic liquid crystal photosensitive resin and its preparation method. A compound containing mesocrystalline units with -OH terminals, EHC, and catalyst 1 are mixed and reacted to obtain solution A. NaOH is added dropwise to solution A to remove the water generated in the reaction. After continuing the reaction, the product is filtered, and excess EHC is removed from the filtrate to obtain solution B. Solution B is mixed with methanol / acetone, and the resulting crystals are washed, filtered, and dried to obtain liquid crystal epoxy resin C. C is mixed with an inhibitor and reacted, then acrylic acid and catalyst 2 are added dropwise to react and obtain acrylic liquid crystal photosensitive resin D. D is mixed with 1,1',3,3'-dimethyldisiloxane, and a solvent, catalyst 3, and inhibitor are added to carry out a hydrosilylation reaction to obtain silicon-chain acrylic liquid crystal photosensitive resin E. The silicon-chain acrylic liquid crystal photosensitive resin provided by this invention can be widely used in artificial muscles, actuators, shape memory, smart devices, and some highly elastic advanced composite materials.

The invention relates to the technical field of wave-absorbing materials, in particular to a broadband wave-absorbing resin-based composite material and a preparation method thereof. The composite material is prepared by compounding epoxy resin, triglycidyl isocyanurate, a tri (2-aminoethyl) amine curing agent partially coordinated with Fe < 3 + >, poly (perylenetetracarboxylic dianhydride-thiourea), surface-modified Fe3O4 (at) SiC core-shell nanoparticles and the like through a specific process. During preparation, the functional components are uniformly dispersed in the resin matrix, and then the resin matrix is subjected to cross-linking molding through a segmented heating curing process. The material realizes efficient electromagnetic wave absorption in a broadband range through a multi-polarization mechanism and a magnetic-dielectric synergistic effect, has good mechanical strength and stability, and is suitable for the field of advanced composite materials with strict requirements on wave absorbing performance.

The application belongs to the technical field of advanced composite materials and structure engineering, and particularly relates to a lightweight anti-seismic composite material and a preparation method thereof. The material is a sandwich structure, comprising upper and lower panels and an intermediate core layer. The upper and lower panels are composed of a resin matrix and carbon fibers in which metal nanoparticles are in-situ compounded. The intermediate core layer is prepared by laser selective melting or precise sheet metal folding to obtain a negative Poisson's ratio metal lattice core layer and then subjected to surface roughening treatment. A core-shell damping emulsion is prepared on the surface of the core layer by a step-by-step emulsion polymerization method, and a functional damping coating is formed by coating and solidification. The panels and the core layer are compounded and solidified by a vacuum-assisted resin transfer molding process. Through multi-scale collaborative design, the lightweight, high strength, high damping and excellent impact resistance are synergistically optimized, the structure has high integrity and high designability, and is suitable for building seismic mitigation, lightweight transportation and high-end equipment protection.

The invention discloses a modeling method for a composite lattice sandwich propeller blade CAE model, and belongs to the field of ship propulsion technology and advanced composite structure design. The method comprises the following steps: 1, constructing a three-dimensional geometric model of lattice unit cells; 2, reconstructing a blade entity model based on the geometric shape value point data of the target propeller, and determining a designed space boundary and a reference shape; 3, generating a first equidistant curved surface and a second equidistant curved surface on the inner side of the paddle solid model from outside to inside, and dividing the paddle solid model into a composite panel domain, a layering base domain and a dot matrix sandwich domain; fourthly, Boolean intersection operation is conducted on the remaining dot matrix cell element array located in the dot matrix sandwich domain, and a dot matrix sandwich structure precisely attached to the boundary of the dot matrix sandwich domain is obtained; and 5, performing Brinell addition operation on the composite material panel domain, the laying layer base domain and the lattice sandwich structure to form a complete composite material lattice sandwich propeller blade CAE (Computer Aided Engineering) model. The method is used for modeling the CAE model of the composite lattice sandwich propeller blade.

The invention provides a composite material plate as well as a preparation method and application thereof, and relates to the technical field of advanced composite materials. The composite material plate is mainly composed of a hybrid resin matrix and a reinforced fiber body, and the hybrid resin matrix is mainly prepared from organic silicon resin, phenolic resin, a ceramic precursor polymer, a functional auxiliary agent and the like; through the design of a ternary hybrid resin matrix and the mixing of reinforced fiber bodies, the unification of extreme high temperature resistance and high structural strength is realized, so that the prepared composite material plate has ultrahigh fire resistance (1500 DEG C oxygen-acetylene flame 30 min +), high structural strength (the tensile strength is greater than or equal to 320 MPa, and the bending resistance is greater than or equal to 280 MPa) and good process adaptability; meanwhile, the composite material plate prepared by the invention also has relatively low density, realizes the unification of light weight and high structural strength, can replace a metal fireproof plate, is suitable for light-weight fireproof structural members such as a battery upper cover and a fireproof plate, and has important application value.

This invention relates to the field of power electronic component manufacturing and advanced composite material application technology, specifically a 3D inductor based on Ampere's law and its method; it includes a functional composite skeleton, a 3D precision interlocking winding, and a magnetic core assembly; the system uses a thermally conductive insulating matrix and soft magnetic powder composite molded skeleton, and physically fills the air gap between winding layers through stepped positioning ribs; its core is to utilize the high thermal conductivity of the skeleton to establish a low thermal resistance heat dissipation path, changing the heat conduction mode from coil to air to coil directly to the skeleton; this invention effectively reduces the temperature gradient difference between the core temperature and the surface temperature inside the coil through an embedded heat dissipation array, solving the heat dissipation problem under high power density and significantly improving device performance.

The application relates to the field of monomer synthetic chemistry and discloses a continuous preparation process of benzocyclobutene primary product, which comprises a continuous vacuum cracking section and a refrigeration impurity removal section, a temperature rising HCl removal and extraction section, a washing, drying and extractant recovery section. The process solves the defects of low yield of the benzocyclobutene primary product synthesized by the vacuum cracking method, intermittent reaction, the fact that HCl components in the cracking product cannot be effectively recovered, the fact that the product is easy to emulsify in the washing process of the cracking product, and the fact that the alkali solution is large in quantity. The benzocyclobutene primary product prepared by the application can be used as a raw material for preparing electronic-grade benzocyclobutene, and is favorable for solving the current problems in chips, semiconductors and advanced composite materials.