332 results about "Material structure" patented technology

A silicon carbide source material structure for use in a sublimation system for growing single crystal silicon carbide is provided. The silicon carbide source material structure may comprise a first layer and a second layer, the first layer being different from the second layer in at least one property.

A valve seat for a pumping assembly. The valve seat includes a body including a gradient material structure that defines a strike face for the valve seat. The gradient material structure has a first material, a second material spaced from the first material, and a smooth compositional transition between the first material and the second material. In addition, the valve seat includes a bore extending through the body.

The invention relates to the technical field of infrared light machine system thermal deformation prediction, in particular to a multi-material structure thermally induced stress deformation prediction method based on a graph neural network. The method comprises the steps of data set establishment, graph structure establishment, graph neural network model establishment and training and model and parameter optimization. Finite element nodes correspond to graph nodes, finite element edges correspond to graph edges, an encoder-message passing-decoder architecture model is established, and node states are updated through a three-layer physical symmetry message passing mechanism. Physical constraint loss including minimum displacement smoothness constraint and stress continuity constraint is innovatively added into a loss function. Compared with traditional finite element calculation, the method has the advantages that the speed is increased by more than 100 times, high hardware adaptability is achieved, the black box limitation of a data-driven neural network model is broken through, thermally induced stress deformation analysis caused by different material coefficients can be processed, the adaptability to geometric changes is high, and good engineering application value is achieved.

A silicon carbide source material structure for use in a sublimation system for growing crystalline silicon carbide is provided. The silicon carbide source material structure includes a composite shaped solid. The composite shaped solid may be made by casting, extrusion, 3D printing, graphite conversion, or other suitable process.

This invention discloses a rapid modeling method for large-size composite structures with variable thickness solid meshes based on a yarn model, belonging to the field of finite element modeling of fiber-reinforced composite materials. Its core process includes: for a large-size component S to be analyzed, generating yarn models for each ply partition using composite material design software and batch-dividing triangular meshes; similarly, extracting smooth surface profiles from the three-dimensional geometry of the overall component S and generating a structured shell mesh as the base carrier; then, using a voxel hash-accelerated spatial Boolean intersection algorithm to automatically identify the element sets of each ply partition between each yarn mesh and the overall shell mesh, generating a stepped solid mesh through normal offset, ensuring interface compatibility through node merging, and finally assigning material properties and generating an analysis model that can be directly submitted for solution. This invention significantly reduces manual workload and error risk, providing an efficient and reliable preprocessing solution for the curing deformation and strength analysis of composite material structures.

The invention relates to the technical field of composite material structure dynamics analysis, and provides a method and system for predicting the inherent frequency of a three-phase functionally graded composite material conical plate, and the method comprises the steps: employing an improved Halpin-Tsai model to calculate the equivalent parameters of a GPL-containing two-phase composite matrix, solving the equivalent parameters of a three-phase composite layer, and calculating the inherent frequency of the three-phase composite material conical plate. The method comprises the following steps: constructing a nonlinear geometrical relationship between a displacement field and a strain field, calculating a stiffness coefficient of each layer, constructing kinetic energy of the three-phase composite material conical plate, calculating an energy coefficient according to the stiffness coefficient of each layer, constructing potential energy of the conical plate according to the energy coefficient, and constructing a modal displacement function by adopting a Chebyshev polynomial and a boundary function. And establishing a characteristic equation based on a minimum potential energy principle and solving to obtain the inherent frequency of the three-phase composite material conical plate. According to the method, efficient calculation of the inherent frequency of the three-phase composite material conical plate is achieved, and the reliability and engineering application value of structural dynamics analysis are remarkably improved.

The invention belongs to the technical field of aircrafts, and discloses a trigger-containing aircraft composite material energy absorption structure analysis method, which comprises the following steps: establishing an external trigger composite material structure model according to actual working conditions; constructing an intra-layer and inter-layer damage coupled progressive damage model; configuring finite element model parameters adaptive to the composite material; integrating simulation results; the crashworthiness of the coupling trigger structure is adjusted and optimized in combination with basic parameters; repeating the steps to verify the optimization effect; and predicting the strength of the composite material by coupling stress strain and damage transfer, revealing a damage failure mechanism and determining an optimal design. The method has the beneficial effects that the failure mode and the load response of the aircraft structure under different impact loads can be accurately captured, and low initial peak load and high specific energy absorption requirements are considered through multi-type triggering collaborative design; reliable technical support is provided for crashworthiness design of composite aircraft structures of aircraft fuselage frames, wing supports and other key structures in the aerospace field.

The invention belongs to the technical field of composite material structure assembling and manufacturing, and particularly relates to a composite material part assembling optimization method. Comprising the following steps: performing curing deformation simulation on a composite material part to obtain a cured deformation molded surface; performing assembly deformation simulation of the deformed molded surface and the assembly fixture based on the state of the assembly fixture; and optimizing an assembly method, an assembly clamp or a composite material part forming die according to the assembly deformation simulation result.

The utility model discloses a fan blade ultrathin and deformation resistant material structure which comprises a fan blade plate, the fan blade plate comprises a first wood layer plate, a second wood layer plate, a wood middle layer plate, a third wood layer plate and a fourth wood layer plate, the wood middle layer plate is connected between the second wood layer plate and the third wood layer plate, and the fourth wood layer plate is connected between the second wood layer plate and the third wood layer plate. Therefore, the first wood layer plate, the second wood layer plate, the wood middle layer plate, the third wood layer plate and the fourth wood layer plate are sequentially connected to form the fan blade plate. According to the fan blade, the strength of the fan blade plate is enhanced through the combination mode of the multiple layers of wood of the ultra-thin and anti-deformation material structure, the situation that the fan blade is deformed or broken due to weather or other external force is avoided, and therefore the stability of the fan is improved, wind resistance is reduced, the rotating efficiency of the fan blade is improved, and meanwhile the wood cutting amount is reduced by more than 30%. At present, a new structure with the thickness of about 4.2 mm can replace an old structure with the thickness of 5.4 mm. The new structure with the thickness of about 5.4 mm can replace the old structure with the thickness of 7.2 mm.

This invention belongs to the field of ceramic composite material manufacturing technology, specifically relating to a method for preparing SiC composite materials based on cold spraying and silicon infiltration. SiC powder is prepared into a suspension, which is then deposited onto a substrate using a cold gas-powered spraying system to form a porous SiC preform coating. The preform coating undergoes post-curing to enhance its cohesive strength. Finally, melt silicon infiltration is performed, causing silicon to react with carbon in the preform to generate a new SiC phase that fills the pores, resulting in a high-density, high-performance SiC composite component. This method combines the advantages of low-temperature forming in cold spraying with silicon infiltration technology. The relatively low substrate temperature during cold spraying effectively avoids the adverse effects of high temperatures on the material structure, maintaining the stability of the original SiC phase. By adjusting the spraying parameters and matching the silicon infiltration process, the free silicon content and the distribution of the newly generated SiC phase in the composite material can be precisely controlled, further improving the material's density and mechanical properties.

The invention discloses an evaluation method, device and equipment for composite material repair consumables and a medium, and relates to the technical field of composite material structure maintenance. A series of controllable disturbance factors are introduced around reference process parameters to simulate actual fluctuation, and the system tests the performance of the repair consumables under non-ideal process conditions, so that the safety boundary of qualified products produced by the repair consumables is determined, and a more comprehensive and practical evaluation system is provided. A process window volume is introduced as an objective and comparable robustness quantitative index, and a process space boundary is efficiently predicted by means of a Gaussian process regression model, so that the problems of high cost and low efficiency of a traditional exhaustion test method are avoided. According to the method, the process robustness for determining the stability of the repair consumables in the actual maintenance environment is converted into the quantifiable and comparable equivalent curing process window and the measurement value thereof, scientific screening of the repair consumables is realized, and the quality risk in actual maintenance operation is remarkably reduced.

The application discloses a lightweight design method for a DD layup composite material rotary body based on a MIGA-SQP hybrid algorithm, relates to the technical field of composite material structure optimization, and comprises the following steps: dividing a composite material rotary body structure into a plurality of design regions, establishing continuous design variables based on a DD layup mode, and establishing a parameterized finite element model template file; establishing a two-stage hybrid optimization strategy; iteratively optimizing the parameterized finite element model template file and the two-stage hybrid optimization strategy; substituting an optimal design scheme into a finite element model for verification; and after verification, generating a manufacturing guidance file according to optimal layup parameters; and the method is used for solving the problems of low optimization efficiency and insufficient utilization of the continuous variable characteristics of the DD layup.

The invention provides a trailing edge variable camber airfoil composed of a bistable composite material structure and a design and control method of the trailing edge variable camber airfoil, and relates to the technical field of aircraft design and aerodynamics. Wherein the trailing edge variable camber airfoil sequentially comprises a leading edge section, an airfoil middle section and a trailing edge section in the chordwise direction, a front beam is arranged between the leading edge section and the airfoil middle section, the trailing edge section is fixed to an airfoil rear beam, and the trailing edge section is a core function section and is formed by arranging multiple layers of glass / carbon hybrid bistable composite material structures from top to bottom in the wingspan direction; each glass / carbon hybrid bistable composite material structure has a first stable state and a second stable state which correspond to a first flight state and a second flight state of the airfoil profile respectively, one end of each glass / carbon hybrid bistable composite material structure is fixedly connected to the airfoil profile rear beam, and the other end of each glass / carbon hybrid bistable composite material structure is fixed into a whole through glue joint. According to the invention, the steady-state characteristic of the bistable composite material is utilized, so that non-driven conversion between two stable bending states is realized.

This invention relates to a method for preparing a high-wear-resistant metal-based composite material. This method significantly improves the wear resistance of the material by combining nano-reinforcing particles, surface modification technology, and self-healing capabilities. Aluminum alloy or titanium alloy is selected as the matrix, and nano-sized silicon carbide or alumina particles are used as reinforcing materials. The reinforcing materials are uniformly dispersed using processes such as stir casting, forging, diffusion bonding, infiltration, or powder metallurgy. The composite material structure is then precisely formed using 3D printing technology. The surface of the composite material is treated with a nano-coating or plasma treatment to enhance its wear resistance and corrosion resistance. Furthermore, by embedding microcapsules containing a repair agent into the material, automatic repair of worn areas is achieved, improving the material's reliability and service life. This composite material is particularly suitable for mechanical engineering and automotive manufacturing, especially in the manufacture of automotive brakes under high-wear environments, demonstrating excellent performance and broad application prospects.

A method and system for preparing forged structural parts from TC6 material are disclosed. First, TC6 bar stock is sawn, and the β-phase transformation temperature (Tβ) of the sawn TC6 bar billet is measured. Then, the billet is heated to a high temperature (Tβ-40) ±10℃ in an electric furnace and held to obtain a pre-treated TC6 bar billet. Next, the pre-treated TC6 bar billet undergoes a series of processes in sequence: small-end aggregation, flat forging, bending, flat forging, large-end aggregation, flat forging, large-end forming, flat forging, and intermediate billet treatment to obtain a secondary-treated TC6 bar billet. This secondary-treated TC6 bar billet is then heated to a high temperature (Tβ-40) ±10℃ in an electric furnace and held to obtain a billet to be forged. Finally, it is forged using an electric screw press, followed by heat treatment, isothermal annealing, and physicochemical testing to obtain the machined TC6 material structural part. Finally, the parts are inspected, and qualified parts are stored in the warehouse. This process yields qualified structural parts.

The invention provides a gradient structure metal-oxide-non-oxide composite sliding plate and a preparation method, and relates to the technical field of sliding plate preparation within the steel smelting range. The outer layer of the gradient-structure metal-oxide-non-oxide composite sliding plate is a compact layer with the porosity smaller than or equal to 5%, the thickness ranges from 0.1 micrometer to 20 micrometers, and the phase composition of the gradient-structure metal-oxide-non-oxide composite sliding plate is Ti (C, N), (Al2OC) x (AlN) 1-x and corundum; the internal porosity of the gradient structure metal-oxide-non-oxide composite sliding plate is 10-20%, and the phase composition of the gradient structure metal-oxide-non-oxide composite sliding plate is Ti (C, N), (Al2OC) x (AlN) 1-x, Al-Ti alloy and corundum. The preparation of the metal-oxide-non-oxide refractory material with a compact surface layer structure is realized under the conditions of high temperature, nitrogen and low oxygen partial pressure by virtue of the regulation and control effect of TiO2 on a gas-phase mass transfer product and a material structure in a material sintering process; the method is simple and easy to operate, low in cost, high in efficiency and beneficial to industrial large-scale production and popularization.

The invention discloses a method for evaluating the residual strength of a multi-scale fiber-reinforced flexible pipe under a stretch-bending load, and relates to the technical field of structural strength evaluation of ocean engineering composite materials, and the method comprises the following steps: extracting fiber distribution characteristics by adopting digital image processing based on a scanning electron microscope image; a Monte Carlo method is combined to construct a two-dimensional RVE geometric model of the fiber reinforced structure containing the damp-heat degradation, and macroscopic elastic parameters are predicted; a VUMAT user material subprogram containing dynamic damage is written based on Fortran, damage starting and evolution failure criteria of a fiber reinforced structure are embedded, and the nonlinear coupling evolution process of multiple damage modes such as fiber fracture, matrix cracking and interface debonding is simulated. According to the method, a material-damage-response multi-scale analysis framework is constructed by coupling microscopic material components, a microscopic damage model and macroscopic pipeline structure analysis, the problem that a traditional method lacks multi-scale damage coupling analysis under a complex load is solved, and the residual strength evaluation precision of the pipeline under the action of a stretching-bending combined load is improved.

This invention discloses a method for joint evaluation and optimization of buckling and bending of arbitrary quadrilateral laminates based on physical information neural networks, relating to the field of composite material structure design technology. The method, for arbitrary quadrilateral laminates, first constructs a method based on classical laminate theory... USA The stiffness matrix explicitly reflects the influence of ply parameters, and a physical domain is transformed to a reference domain through a bitriangular affine mapping to establish a physical information neural network mechanical model. The model is trained with the goal of minimizing the total potential energy or Rayleigh quotient, solving for the buckling factor and layer-by-layer strain limits, and adapting to four typical boundary conditions through a boundary embedding function. Subsequently, using ply angle and thickness as variables, optimization is performed using a genetic algorithm, with the goal of minimizing mass, and the buckling factor and strain limits as constraints. The final output is the optimal ply scheme that satisfies specific boundary conditions. This invention can optimize ply angle and thickness while satisfying buckling stability and strain strength constraints.

This invention discloses a method for extracting orthogonal radiative eigenmodes in lossy structures. For electromagnetic structures containing lossy materials, resistive loading, and other dissipation mechanisms, this invention obtains the scattering T-matrix of the structure under a preset incident mode basis. Utilizing the property that the T-matrix is ​​a complex symmetric matrix under reciprocity conditions, the Autonne-Takagi decomposition method is used to decompose this complex symmetric matrix, yielding a set of mutually orthogonal radiative eigenmodes in the sense of radiated power and their corresponding radiated intensity parameters. The obtained radiative eigenmodes can be used for mode decomposition and physical interpretation of the radiation and scattering characteristics of lossy structures, and are applicable to the design and optimization of various practical lossy electromagnetic structures such as resistive-loaded antennas, scatterers containing dielectric losses, and absorbing material structures.

The invention discloses a composite material multi-scale image finite element analysis method considering manufacturing characteristics, and belongs to the technical field of special-shaped composite material structure multi-scale analysis. CT scanning is carried out on the special-shaped composite material structure, an internal image of the special-shaped composite material structure is obtained, statistical parameters of manufacturing characteristics are extracted through an image processing technology, and mesoscopic representative volume units are classified according to the statistical parameters; secondly, a self-consistent clustering analysis method is adopted for model unified order reduction, and an efficient solving database is constructed; mapping corresponding cell element categories according to defect characteristics of each region of the component, realizing scale solution through a concurrent multi-scale framework and a homogenization method, and predicting mechanical response and damage evolution of the structure; and finally, revealing a physical mechanism that macroscopic damage expands along a low-performance weak band based on spatial distribution of cell categories. The method has high calculation efficiency and prediction authenticity, and an effective tool is provided for performance evaluation and process optimization of the defect-containing composite material component.

The present application relates to the technical field of composite material structure monitoring, in particular to a composite material structure damage identification method based on acoustic emission wavelet packet energy characteristics, which comprises: S1, obtaining acoustic emission signal data of the composite material and performing pretreatment; S2, using a wavelet base function and a discrete wavelet inverse transform to perform wavelet packet decomposition on the denoised acoustic emission signal data of the composite material; S3, obtaining the processed acoustic emission signal data of the composite material, and extracting the characteristic energy of each acoustic emission signal data; S4, using a clustering method to perform clustering analysis and completing the composite material structure damage identification. The present application uses acoustic emission signals as the basis for analysis, uses wavelet transform and k-means clustering to accurately realize the structure damage identification and judgment of the composite material, can realize dynamic and continuous monitoring, is not affected by the complexity of the structure, has wide applicability, and is suitable for various composite materials.

The application discloses a multi-objective optimization design method and related device for clamping a metal wedge-shaped anchoring joint of a composite structure, and relates to the technical field of anchoring of marine engineering composite material structures. The method comprises constructing a mechanical-bonding composite three-dimensional finite element model based on the geometric components of the metal wedge-shaped anchoring joint. Numerical simulation is performed on the multiple geometric design variables through experimental design, and key design variables affecting anchoring strength, clamping stress and joint weight are screened through variance analysis. The steepest ascent method is used to determine the optimization direction, and a quantitative mapping relationship between the design variables and the optimization objectives is constructed in the optimization region using the response surface method to establish a high-precision surrogate model. The maximum anchoring strength, the minimum clamping stress and the minimum joint weight are taken as the objectives, the surrogate model is used as an objective function evaluator, a multi-objective genetic algorithm is applied for collaborative optimization, an optimal solution set is obtained, and the optimal geometric structure parameter combination of the metal wedge-shaped anchoring joint is determined according to requirements.

The present application provides a large-scale composite material detection method based on infrared and ultrasonic data fusion, which utilizes the infrared large-scale rapid advantage to rapidly locate the impact marks on the surface of the composite material, cooperates with ultrasonic positioning detection to obtain detailed data of the impact defects, and finally realizes rapid positioning and accurate detection of the defects of the large-scale composite material structure.

This invention discloses a material selection method, system, equipment, and medium for predicting the life of cemented carbide cutting tools based on operating parameters. It relates to the field of cemented carbide cutting tool manufacturing technology. The method includes: collecting cutting force distribution and temperature gradient data using a stress sensing array and a temperature sensing array in the tool tip region; constructing stress-temperature-wear synergistic effect data; calculating fatigue damage characteristic values ​​based on the synergistic effect data to obtain wear prediction correction coefficients; compensating the tool tip stress field using the correction coefficients to output life prediction data; designing a carbide phase gradient distribution structure based on the synergistic effect data and fatigue damage characteristic values; adjusting the carbide grain orientation angle in conjunction with the wear prediction correction coefficients and life prediction data; and outputting optimal material structure parameters to achieve optimized selection of cemented carbide cutting tool materials. This invention improves the accuracy of tool life prediction and realizes dynamic optimization of material structure.

The invention relates to a digital twinning method for forecasting the real-time bearing capacity of a composite material bearing cylinder structure based on field data inversion, and belongs to the technical field of composite material structure health monitoring and digital twinning crossing. The method is directly oriented to health monitoring and safety evaluation of the structure during the in-service period. The core function is to sense the current damage state of the structure in real time and dynamically forecast the future bearing capacity of the structure. According to the invention, the urgent demand of instantly judging the structural safety in the key stages of launching preparation, task execution and the like of spacecrafts such as rockets is met. According to the invention, the application scene of digital twinning is changed from post-maintenance to pre-warning and monitoring in the event, and the conversion from simulation maintenance to guarantee operation is realized.

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.

The application discloses a multi-material structure topology optimization method, which innovatively applies Tsai-Wu criterion to multi-material structure topology optimization design, introduces a double-filter interface identification strategy, realizes accurate extraction of an interface phase field, and constructs a gradient interface finite element model based on a material proportion, then establishes an interface tension and compression state adaptive constraint method, and further adopts an adaptive threshold strategy to dynamically control the constraint tightness, so that full compression of the multi-material interface is realized at the algorithm level.

The invention discloses an isogeometric transient dynamics topological optimization method and system of a functional gradient plate structure, and belongs to the field of topological optimization design of functional gradient structures. According to the method, the problems of collaborative optimization of the gradient direction in the gradient material plane and the multi-material structure topology under the transient load effect and the like are solved. According to the technical key points, an isogeometric transient dynamics finite element analysis model of the functional gradient plate structure is constructed based on a reduced Gaussian integral method; constructing a smooth projection scheme and a material interpolation scheme of design variables of the functional gradient plate structure, and providing a transient dynamic topological optimization model of the functional gradient plate structure by taking the density of a control point and the volume fraction of a strong material attached to a plate unit as the design variables and the minimization of dynamic flexibility as a target; constructing a time domain adjoint equation of the topological optimization model, and obtaining sensitivity information of the target function; and finally, obtaining the optimal anti-vibration design of the functional gradient plate structure convenient for engineering application. The device is used for structural light-weight vibration reduction design of large engineering equipment under the strong vibration working condition.

The application provides a kind of shipboard aviation equipment composite material damage D-S evidence theory nondestructive evaluation method, belongs to the field of shipboard aviation equipment nondestructive evaluation, it includes the following steps: at time, the triaxial damage area characteristics and triaxial vibration frequency characteristics of the composite material structure of shipboard aviation equipment are synchronously acquired and stored;The triaxial damage area characteristics and triaxial vibration frequency characteristics at time are compared respectively, and the corresponding triaxial damage area change degree and triaxial vibration frequency change degree are obtained;The identification framework of D-S evidence theory is established, and the triaxial mass function of the composite material structure is calculated respectively;According to the created D-S damage judgment model, the classification judgment and early warning of the composite material damage of shipboard aviation equipment are carried out.The application can realize the real-time classification evaluation of the dynamic damage of the composite material component of shipboard aviation equipment, and provide data support for the condition-based maintenance of shipboard aviation equipment.