683 results about "Material structure" patented technology

The invention belongs to the technical field of high polymer material design and intelligent manufacturing, and discloses a machine learning driven epoxy resin based composite material thermal-mechanical property aided design method, which comprises the following steps: S1, data acquisition and feature construction; s2, performing feature screening; s3, constructing and training an interpretable prediction model; s4, carrying out reverse design and optimization; and S5, performing closed-loop verification and updating. According to the method, the quantitative relation of structure-process-performance is constructed through an interpretable machine learning model, and the contribution mechanism of each factor is revealed by means of SHAP analysis. And finally, reversely designing an optimal epoxy resin monomer structure and a matched curing process according to the performance target. The limitation of a traditional trial and error method is broken through, collaborative optimization of the material structure and the forming process can be achieved, and the development efficiency of the epoxy resin-based carbon fiber composite material is remarkably improved.

The invention provides a structural material corrosion damage cross-scale evaluation method and system, and belongs to the field of service performance cross-scale evaluation. The method comprises the following steps: firstly, collecting corrosion data of related structural materials, establishing a structural material service safety evaluation database based on the corrosion data, and then respectively extracting material scale characteristics and structural scale characteristics of corrosion damage of the structural materials; predicting the service life of the structural material according to the scale characteristics of the material; setting a service safety evaluation index of a material scale and measuring the service safety evaluation index; predicting the service life of the structural material according to the structural scale characteristics; setting a service safety evaluation index of a structure scale and measuring the service safety evaluation index; and carrying out cross-scale correlation on the material scale characteristics and the structure scale characteristics, constructing a transmission model for representing the service performance through material-structure cross-scale correlation, fusing the evaluation indexes of the material scale and the structure scale, generating the evaluation index of the structure material, and evaluating the service performance of the structure material. The accuracy and precision of corrosion damage evaluation are improved.

The invention belongs to the technical field of high-performance composite materials, and discloses a carbon fiber reinforced thermoplastic composite material performance database, a construction method and application thereof, and the method comprises the following steps: S1, database structure construction; s2, experimental sample collection and data standardization; s3, feature engineering and variable reduction; s4, training a machine learning model; s5, constructing and verifying an adaptive model; and S6, data expansion and feedback optimization. According to the method, material performance prediction and formula parameter reverse design under target performance are realized through systematic acquisition and normalization processing of three types of data of material components, preparation process and performance characterization and building of a nonlinear mapping model among a material structure, a process and performance through a machine learning method. The database can be used for intelligently recommending a high-performance composite material combination scheme, is suitable for rapid screening and customized development of various thermoplastic composite materials, effectively reduces the research and development cost and development cycle, and improves the material design efficiency.

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.

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 provides a plastic packaging barrel online defect detection method and system based on machine vision and deep learning. According to the method, visible light and thermal image data, aligned in time, of the surface of the plastic packaging barrel are collected, the dynamic range of a thermal image is expanded to enhance the identification degree, then highlight interference is compensated through the mapping relation between a thermal image stable area and a visible light reflection area, and surface reflection suppression is achieved; superposing the processed dual-mode data to generate a multi-mode fusion image, dynamically adjusting the temperature reference value of the fusion image based on the thermal conductivity of the material and the environment temperature of the production line, and positioning an abnormal temperature region; and finally, extracting topological contours and temperature diffusion characteristics of the regions, and inputting a deep learning model to judge material structure attributes and spatial positions of the defects so as to finish online detection. According to the method, thermal and visual data are fused to enhance the perception capability on fine structure defects, and the precision and robustness of online detection of the plastic packaging barrel in a complex illumination environment are remarkably improved.

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.

The invention relates to a damage assessment method and device for a composite material structure and electronic equipment, and relates to the technical field of aircraft maintenance, and the method comprises the steps: obtaining an aircraft typical structure operation and maintenance database and an actual service environment database; extracting structure damage characteristics from the aircraft typical structure operation and maintenance database, and extracting service environment factor data of the aircraft from the actual service environment database; performing clustering analysis on the extracted service environment factor data to obtain a clustering analysis result, and performing correlation analysis on the extracted structure damage features and the clustering analysis result to obtain a correlation analysis result; and based on the correlation analysis result, constructing an evaluation index system, and performing damage evaluation on the composite material structure of the aircraft by using the evaluation index system. According to the scheme, various environmental factors and structural damage characteristics can be comprehensively considered, the service reliability and safety of the structure are evaluated more accurately, a more reliable basis is provided for structure maintenance decision, and potential risks for flight safety are reduced.

The invention belongs to the technical field of material science, and relates to a generation method of a material formula, a target material, an automobile structural part, a vehicle, a device, a medium and electronic equipment. The method comprises the following steps: acquiring target performance data of a target material to be prepared; and inputting the target performance data into a pre-trained material large model, so that the material large model outputs formula data for preparing the target material and corresponding process data. The formula data and the process data of the preparation method are reversely deduced according to the target performance data required by the target material by utilizing the large material model, the large model is introduced into the field of material science, and the generation method of the reverse material formula realizing'target performance driving 'is provided without relying on a large number of manual experiment trials and errors; and the advantages of strong generalization ability and reasoning ability of the large material model are exerted, so that the research and development efficiency and success rate of new materials are improved, and the application scenarios of the large material model are enriched.

The invention discloses a solid rocket engine bearing structure lightweight determination method based on a carbon fiber composite material, and relates to the technical field of composite material structure design, and the method comprises the steps: obtaining the structure size and geometric shape of a fixed body; replacing a titanium alloy material with a carbon fiber composite material, and determining a carbon fiber composite material structure response model based on a finite element modeling method; determining an optimal layering scheme based on structural response sensitivity analysis and a multi-objective optimization method; then determining a thickness optimization scheme based on the structural size and geometric shape of the fixed body and load distribution; determining a reinforcement optimization scheme based on a parametric modeling method; determining a metal reinforcement configuration by adopting a structural rigidity-quality collaborative evaluation method; and finally, determining a lightweight structure of the fixed body based on a composite material layering process design method. The mass of the fixing body structure can be reduced, the mechanical property of the fixing body structure is improved, and the high-performance design requirement of a solid rocket engine is met.

The invention relates to the technical field of material thermal performance testing, and discloses a material heat conductivity coefficient automatic testing method based on a heat flow gradient method. The method comprises the following steps: firstly, constructing a test environment topology network, collecting three-dimensional structure parameters and environment thermodynamic parameters of a tested material, and inputting the parameters into a thermal field simulation system to generate an internal heat flow distribution model; and analyzing internal cavity distribution characteristics according to the three-dimensional structure parameters, matching the internal cavity distribution characteristics with a cavity characteristic-heat source layout mapping table to determine a steady-state heat source layout scheme, and activating a heat flow gradient analysis device when multiple heat sources are needed. A heat conduction parameter database is called, heat source power parameters and temperature acquisition parameters are extracted based on environmental thermodynamic parameters, the heat source power parameters comprise spacing, axial angles and the like, and the temperature acquisition parameters comprise thermocouple types and acquisition frequencies; and finally, simulating temperature field evolution through a heat flow gradient analysis device, outputting and analyzing related data, and generating a parameter optimization instruction to adjust heat source configuration. According to the method, multiple links are coordinated, material structures and environmental factors are integrated, and automation of the testing process is achieved.

The invention relates to the technical field of reliability evaluation of a composite material structure, and particularly discloses an evaluation method for vibration damage mechanical properties of a composite material. The method comprises the following steps: firstly, clamping a composite material test piece on a special test clamp which can be stable and durable in a vibration environment, and carrying out parameter-controllable vibration excitation on a vibration table to simulate damage; then carrying out mechanical property test on the damaged test piece; and finally, based on the vibration data and the mechanical property data, establishing a vibration parameter-performance degradation correlation model by calculating the performance degradation rate, and performing quantitative evaluation on the vibration damage state of the composite material in combination with microscopic damage analysis. According to the invention, the problem that the vibration test and the performance evaluation process are separated and cannot be quantitatively associated in the prior art is solved, the integrated and quantitative analysis from damage simulation to state evaluation is realized, and the environment temperature influence factor is introduced; accurate data support can be provided for safety design and life prediction of the composite material structure in a specific vibration environment.

The invention relates to a composite material structure damage probability assessment method and device and electronic equipment, and relates to the technical field of aircraft maintenance, and the method comprises the steps: obtaining the structure influence factor data of a to-be-assessed composite material structure; inputting the structure influence factor data into the trained random forest model, and performing damage probability evaluation processing on the to-be-evaluated composite material structure through all decision trees in the random forest model to generate an evaluation result; the evaluation results are subjected to voting processing, the evaluation result with the maximum voting number serves as a predicted structure damage evaluation result of the composite material structure to be evaluated, and the predicted structure damage evaluation result at least comprises slight damage, moderate damage and serious damage. According to the scheme, the limitation of a traditional method in the absence of sensor data is effectively overcome, and the damage prediction requirement under the condition of no sensor data or incomplete data is met.

The invention discloses a manufacturing defect-oriented multi-scale composite material mechanical property prediction method, and belongs to the technical field of composite material mechanical property analysis. The method comprises the following steps: based on a multi-scale representative volume element (RVE) theory, respectively constructing parameterized models containing pores and fiber dislocations in a microscopic scale and a mesoscale; the equivalent elastic parameters under each scale are calculated through a finite element numerical homogenization technology, and an agent model is constructed in combination with an artificial neural network, so that the calculation cost is remarkably reduced, and the high-efficiency cross-scale prediction of the rigidity and strength performance of the composite material is realized. The method overcomes the defect of defect modeling of a traditional model, has high precision and high efficiency, and is suitable for performance evaluation and optimization design of composite material structures in the fields of aerospace, rail transit and the like.

The invention discloses a tunneling parameter optimization and hob abnormal wear avoidance method based on shield cutterhead vibration, and relates to the technical field of tunnel and underground engineering, and the method comprises the steps: collecting three-way vibration signals during tunneling of a shield cutterhead; driving the shield cutter head to execute an in-situ tunneling experiment, and synchronously calculating a vibration signal characteristic value by using the three-way vibration signal; carrying out bin opening detection and statistics on the abrasion type of each hob, and judging the abnormal damage level of the shield cutter head in combination with the material structure information of the hobs; extracting vibration intensity ranges when the shield cutter head is at different abnormal damage grades, and taking the corresponding vibration intensity range when the shield cutter head is at the lowest abnormal damage grade as a target tunneling range; and analyzing whether the vibration intensity of the shield cutter head is in the target tunneling range or not in real time during shield tunneling. According to the invention, the limitation of hysteresis of traditional geological exploration is broken through; hob breakage or eccentric wear accidents caused by geological sudden changes are avoided, and construction safety in complex stratums is remarkably improved.

The invention provides an anti-cracking performance evaluation method and system based on a concrete shrinkage rate. The method comprises the following steps: firstly, collecting shrinkage rate real-time sequence data and an acoustic emission signal flow of a concrete sample in a curing process, separating a high-frequency elastic wave energy attenuation characteristic value from the acoustic emission signal flow, and carrying out space-time coupling on the high-frequency elastic wave energy attenuation characteristic value and a shrinkage rate jump point in the shrinkage rate real-time sequence data to generate a crack initiation tendency index; then obtaining a calibrated crack initiation tendency index based on an ambient temperature hysteresis effect and a temperature drift error of the calibrated crack initiation tendency index, and then outputting an anti-crack performance grade according to a grading deviation degree between a pre-designed grading parameter and a fluctuation range of the calibrated crack initiation tendency index; according to the technical scheme provided by the invention, the essential defect that a traditional method cannot correlate material characteristics with environmental response is overcome, direct quantitative mapping of material structure performance and damage evolution is also realized, and a traceable material-level basis is provided for engineering anti-crack design.

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 application discloses a composite material structure bushing reinforcing method based on electromagnetic loading, which uses electromagnetic loading to complete the bushing reinforcement of the composite material structure, and obvious beneficial effects are obtained compared with traditional methods. The method proposes a process parameter calculation method for the reinforcement process of the structure to solve the problem that existing devices and methods cannot be applied to the bushing reinforcement of the composite material structure. The radial compressive stress around the hole is obtained through the Lame formula and the elastic stress-strain relationship of the composite material, and then the total resistance of dynamic extrusion friction in the reinforcement process is obtained through the Coulomb friction theory, and the process parameters are determined in combination with the mathematical model of the electromagnetic force. The application can realize the calculation of the reinforcement process parameters of the composite material bushing with different structures and sizes, and is used for guiding the reinforcement of the dynamic cold extrusion composite material bushing structure.

The application discloses a kind of building material structural performance grading progressive detection method and system, belong to building structure detection technical field.The method includes three progressive detection steps: first, the appearance and coating of building bare steel structure are detected, if abnormal, mark as low-risk component and carry out next-level detection;Then, the geometric deformation, crack and stress state of low-risk component are detected, if abnormal, mark as high-risk component and carry out next-level detection;Finally, destructive detection is carried out on high-risk component, to verify its key performance, if abnormal, mark as unqualified component and immediately reinforce or replace.The method also includes environmental monitoring, life prediction and other functions, and is matched with the corresponding detection system.The application realizes early risk identification and accurate evaluation of building steel structure through grading progressive detection strategy, improves detection efficiency, reduces detection cost, and provides effective protection for building structure safety.

The invention provides a composite material damage type identification method based on multiple characteristic parameters of an acoustic emission signal, which comprises the following steps: designing and carrying out an acoustic emission signal acquisition test aiming at a composite material damage evolution behavior; key acoustic emission signal features are screened out based on a principal component analysis method, and the corresponding relation between a clustering result and a damage form is verified; a transient damage contribution index is proposed based on a clustering result to represent the contribution degree of each damage to the overall damage at a certain moment, and a damage function is proposed in combination with strain energy. The method effectively solves the bottleneck problems of high feature redundancy and serious mode confusion of the traditional acoustic emission signal, perfects the spatial correlation model of the energy release rate and the damage mode in the composite material progressive damage theory, provides an experimental basis for establishing an anisotropic damage constitutive equation considering the laying layer direction, and has a wide application prospect. And a new method is provided for online monitoring of a composite material structure under a complex working condition.

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 provides a design method of high-temperature-resistant particles for energy storage of a thermal power plant, and belongs to the technical field of ultrahigh-temperature fluidized energy storage.The design method comprises the steps that a game optimization model is established to determine a basic formula of an energy storage material, and a contribution value jitter increasing and expanding algorithm is adopted to construct a sparse heat conduction matrix; a particle dispersion path optimization algorithm is used for controlling distribution of a hexagonal boron nitride heat conduction enhancer, expanded graphite and carbon fibers are mixed according to the proportion of 3: 1, a silane coupling agent is added for high-temperature composite treatment, a uniform coating layer is formed through an anti-oxidation coating precursor, and the particle size of particles is controlled within the range of 50-200 micrometers through airflow classification. And finally, a surface modifier and a fluidity improver are added to finish surface treatment in a high-temperature fluidized bed, so that the technical problems of material structure failure and heat storage performance degradation caused by thermal stress accumulation in a repeated thermal cycle process of the energy storage particles in a high-temperature environment are solved.

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 structural mechanics and computational mechanics, and particularly relates to a composite material fan blade composite crack propagation simulation method, program and equipment and a storage medium. According to the method, key rotation and a failure judgment criterion based on a key deflection angle are introduced into the conventional state near-field dynamic model, so that the crack propagation behavior of the composite material under the shear or mixed mode load can be more accurately captured and simulated. According to the flat plate mapping method, the improved PD model suitable for the flat plate is successfully expanded and applied to the fan blade airfoil section, the problem of complex geometric modeling is solved, and the flat plate mapping method is suitable for complex geometric structures. According to the method, a near-field dynamics method is adopted, crack paths do not need to be preset or grid reconstruction does not need to be carried out, and complex expansion behaviors such as spontaneous bifurcation and merging of cracks can be naturally simulated; the PD model can be used for meticulously describing the mechanical behaviors and crack evolution of each layer and interlayer in the laminated plate, including intra-layer cracking and interlayer layering.

The invention discloses a wafer defect detection and regulation method and system, a medium and a product, and relates to the technical field of semiconductors. The method comprises the following steps: collecting microstructure image data and material structure spectrum data of a cutting edge of a wafer; fusing the depth geometric features of the microscopic morphology image data and the depth spectral features of the material structure spectral data to generate a composite defect feature vector; according to the composite defect feature vector, obtaining the category and the severity level of the defect, inputting the category and the severity level as input parameters into a stress simulation model based on finite element analysis to obtain a stress distribution prediction result containing a stress concentration condition; matching and outputting a regulation and control strategy identifier capable of optimizing the stress concentration condition from a preset regulation and control strategy library; and according to the regulation and control strategy identifier, a regulation and control instruction containing the specific process parameters is generated, and the regulation and control instruction is sent to downstream packaging equipment or a repair unit. By implementing the technical scheme, wafer defects can be accurately detected.

The invention discloses a composite material connecting rod structure, and relates to the technical field of composite material structure design and manufacturing, in particular to a light high-strength composite material connecting rod which comprises a composite material rod body, a flange connector, a flange clamp, an adjustable clamp and a tensile bolt set. The composite material rod body is made of fiber reinforced resin matrix composites through a winding or laying winding process, and reinforcing areas and transition oblique angles are arranged at the two ends of the composite material rod body. The adjustable clamp and the flange clamp are in interference fit with the end of the rod body through built-in inclination and surface texture, the flange connector is connected with the clamp through the tensile bolt set, and efficient transmission of tension and compression loads is achieved. Through the integrated combined structural design, the problems of stress concentration and interface failure caused by traditional glue joint or screw joint are solved, the bearing capacity, environmental adaptability and reliability of the connecting rod are remarkably improved, and the connecting rod is suitable for the high-load fields such as aerospace, high-speed rails and heavy machinery.

The invention discloses a method and device for predicting transverse mechanical properties of a composite material, and a storage medium, and belongs to the technical field of composite materials. The method comprises the following steps: firstly, establishing a mesoscopic representative volume element model considering fiber random distribution and diameter fluctuation; constructing a transverse mechanical property database of the composite material; establishing a CNN model and an ANN model by taking the RVE microstructure image and physical structure parameters such as fiber volume fraction, clustering degree, uniformity and diameter distribution as input; analyzing and verifying the equivalent characterization capability of ANN input parameters on image features, and establishing a CNN-ANN fusion modeling strategy; and carrying out interpretability analysis on the optimized ANN model, and quantifying the contribution degree and the influence direction of each microstructure parameter to the mechanical property. According to the method, efficient and accurate performance prediction with physical interpretability can be realized under the multi-source uncertainty condition, the experiment and calculation cost can be reduced, and the reliability and engineering application value of the composite material structure design can be improved.

The invention discloses a plugging particle, a preparation method, application and a grouting material, the plugging particle is of a core-shell structure and comprises a force-bearing inner core, the force-bearing inner core is coated with an expansion functional layer, and the expansion functional layer is coated with a delayed hydrogel outer film layer; wherein the inner core is made of one or more of quartz sand, kaolin and inorganic fibers; the expansion functional layer comprises modified bentonite and a super absorbent polymer; the delayed hydrogel outer film layer comprises a water-soluble film; the particle size of the blocking particles is 0.5 to 2.5 mm; through material structure optimization and response mechanism design of the functional plugging particles and the special grouting liquid, the automatic plugging function in the grouting process without mechanical triggering, a chemical expanding agent and a complex plugging device is achieved; and the method is suitable for scenes with high requirements on plugging precision, construction efficiency and structural stability in complex rock mass crack grouting engineering.