17 results about "Integration point" patented technology

The invention relates to a novel stable node integral calculation method based on hourglass control, and the method comprises the steps: dividing a problem domain into a triangular or tetrahedral mesh, and dividing a mesh integral domain into a plurality of non-overlapping node integral domains based on nodes in the triangular or tetrahedral mesh; performing node domain smoothing on the node integral domain based on the triangular / tetrahedron strain component of the node to obtain a smooth domain; hourglass control between a node and an adjacent node is constructed in the smooth domain, and hourglass force between the node and the adjacent node is calculated; and superposing the hourglass force borne by the node with the original internal force calculated by node integration to obtain the internal force of a stable node integration method, and solving a discrete motion equation in explicit dynamics based on the internal force of the stable node integration method to obtain a dynamic response. According to the method, the calculation precision based on the unstructured grid is greatly improved, and the advantages that the number of integration points of node integration is small and the grid distortion resistance is high are effectively kept.

The invention provides a sealing assembly completion state solving method and device, and relates to the technical field of sealing element design. Comprising the following steps: acquiring geometric models of an elastic component and a matched component thereof, constructing an assembly initial configuration, performing finite element discretization on a sealing assembly system, and setting an integral point in the elastic component; in the assembly iteration process, corresponding projection points are determined based on the integration points and the component combination where the integration points are located, and the contact force at the integration points is calculated in combination with material parameters, the positions of the projection points and the surface geometric information of the matched components; and uniformly assembling the contact force and the internal elastic force generated by the elastic component under the current configuration into an overall force balance relationship for nonlinear iterative solution until a preset convergence condition is met, thereby obtaining a sealing assembly completion state. According to the method, the sealing assembly completion state can be stably solved under the condition that initial geometric interference exists, and the convergence and calculation stability of assembly simulation are improved by uniformly processing the contact force and the internal elastic force.

The present invention relates to a THINC-based overlapping grid VOF interpolation method and a readable storage medium. The method comprises: obtaining the body center coordinates and Gaussian integration point coordinates of each grid unit in an overlapping grid system; obtaining grid assembly information; selecting an interpolation boundary unit and a corresponding interpolation template; selecting a Gaussian integration point for the selected interpolation boundary unit; calculating the distance from the Gaussian integration point to the grid body center of each contributing unit in the corresponding interpolation template to find the closest contributing unit; judging whether the closest contributing unit is an interface unit, and if not, the fluid volume fraction value of the Gaussian integration point is the fluid volume fraction value of the closest contributing unit; if so, substituting the Gaussian integration point into the THINC function of the closest contributing unit to calculate the fluid volume fraction value of the Gaussian integration point; repeating the above steps to calculate the fluid volume fraction values ​​of all interpolation boundary units in the overlapping grid system, thereby realizing overlapping grid interpolation calculation of the fluid volume fraction field.

The invention discloses a diesel engine cylinder cover mechanical property mapping method, and belongs to the technical field of internal combustion engine structural strength analysis. The method comprises the following steps: acquiring microstructure node data based on casting simulation, and converting the microstructure node data into a node mechanical property field through a material model; after a mixed mapping strategy is adopted, target grid integration point coordinates are determined, source units are traversed in a source grid, whether the target grid integration points are located in the spatial range of the target grid integration points or not is judged, and confirmation is carried out according to the volume coordinate relation; performing high-fidelity interpolation on the integral points in the source units by adopting a shape function; for integral points which cannot be positioned, a k-d tree-based nearest neighbor node averaging method is adopted; and finally, writing the heterogeneous mechanical property field on the integral point into a structure analysis result. The method breaks through the precision and robustness bottlenecks of cross-scale and cross-grid data transmission, solves the problem that the material is difficult to couple with a stress field due to non-uniform material performance distribution, and provides a reliable data basis for high-precision fatigue life prediction of the cylinder cover.

The invention relates to a system architecture automatic design method based on a domain-specific language (DSL). The method comprises the following steps: S1, constructing a DSL file definition system; s2, carrying out service DSL (Digital Subscriber Line) modeling; s3, judging whether expansion is needed or not, if so, turning to S4 after expansion, otherwise, directly turning to S4; s4, after the participants are determined, performing logic writing on the process and the process steps; s5, carrying out system architecture DSL (Digital Subscriber Line) modeling; s6, judging whether the integration point needs to be expanded or defined, if so, turning to S7 after expansion or definition, and otherwise, directly turning to S7; s7, compiling components, interfaces and constraints in detail; s8, binding and mapping business and system architecture field elements; and S9, carrying out automatic analysis, verification and reasoning by adopting a DSL analysis engine, generating a framework blueprint, if abnormity exists in the verification process or business requirements change, turning to S3, and otherwise, directly outputting the framework blueprint and an interface document. Compared with the prior art, the method has the advantages of high design efficiency, high expandability, high accuracy and the like.

The present invention discloses a wing boundary simulation method based on the normal direction of the airfoil curved surface, a terminal device and a storage medium. After obtaining the wing curved boundary information, the integration degree of the curved unit is judged, the arc length is determined according to different integration degrees, and then the Gaussian integration point is determined according to the arc length. Finally, the numerical integral is obtained, which greatly improves the accuracy of the numerical integration calculation and indirectly improves the calculation accuracy of the simulation result.

The invention provides a plate spinning solid shell unit modeling and simulation visualization method based on ABAQUS, and belongs to the field of spinning forming numerical simulation. The method comprises the following steps of: constructing a calculation module by using a Fortran language and packaging the calculation module into a VUEL subprogram which can be called by ABAQUS; a subprogram VUSDFLD used for redefining variables on the integration points is written in the Fortran language; a three-dimensional finite element model of plate spinning is established in the ABAQUS; and calling an ABAQUS / Explicit solver and a subprogram to perform plate spinning simulation to obtain an ODB result file, constructing a result file reconstruction tool based on a Python secondary development technology of the ABAQUS, extracting node data of a calculation component and unit integral point data of a storage component, and creating a new ODB file for visualization. The method solves the problem that the simulation result of the user-defined entity shell unit (such as VUEL) in the ABAQUS cannot be directly written into the ODB file, so that post-processing visualization is difficult.

The application discloses a finite element analysis method, device and equipment and a computer readable storage medium. The method comprises the following steps: receiving a composite material two-dimensional section finite element analysis task, and obtaining each current integration point; in the macro finite element solving process of the composite material two-dimensional section finite element analysis task, calculating a macro strain vector corresponding to each current integration point; transferring the macro strain vector to a neural operator micro agent model through a Fortran and Python mutual operation interface, and outputting an equivalent stress vector; assembling a stiffness matrix and a residual vector of the macro finite element by using the equivalent stress vector; repeating the step of obtaining each current integration point until the convergence of the macro finite element solving is determined according to the stiffness matrix and the residual vector, and it is determined that the finite element analysis of the composite material two-dimensional section finite element analysis task is completed. The application realizes seamless integration with an existing engineering finite element platform, is general in framework, and is easy to extend.

The present invention discloses a method for predicting the creep deformation of a turbine disk based on a coupled creep constitutive model. Aiming at the creep deformation of the turbine disk under a complex multi-stress field, the relationship curve between creep strain and time at different stress levels is obtained by means of a uniaxial creep test of a standard test bar. According to the combined time-hardening creep constitutive model and the θ-parameter method creep constitutive model, the material creep characteristic parameters at different stress levels are obtained. In the CREEP user subroutine provided by the finite element software ABAQUS, the two constitutive models are coupled and calculated by applying environmental stress to each integration point. The creep strain and creep deformation of each integration point are calculated within each time increment step to predict the creep deformation of the turbine disk under different stresses. This method overcomes the problem of being unable to accurately predict the creep deformation behaviors of both the low-stress and high-stress parts in an aero-engine turbine disk simultaneously, and can predict the creep deformation under a complex stress field.

This invention discloses a method and system for calculating finite element data based on a material constitutive model, relating to the field of finite element simulation technology for metal stamping forming. The method includes: calculating the trial stress at the i-th increment step based on the strain increment at the element mesh integration point and the stress at the (i-1)-th increment step; calculating the yield function value based on the Von Mises yield criterion, using the trial stress, the strain at the (i-1)-th increment step, and the equivalent plastic strain rate; if the yield function value does not meet the preset yield condition, marking the trial stress as the actual simulated stress at the i-th increment step and obtaining the corresponding actual simulated strain; if the yield function value meets the preset yield condition, calculating the actual simulated stress at the element mesh integration point and the corresponding actual simulated strain at the i-th increment step based on the plastic flow law. This invention, when applied to finite element software, can accurately and effectively calculate finite element simulation data.

An analogue simulation method for the oxidation behavior of a C / SiC composite material component comprises the following steps that A1, Abaqus software is used for modeling the component, space coordinates of all integration points of the component are obtained, and an oxidation starting surface is designated; a2, writing a Python program, dividing grids based on a Delaunay algorithm, calculating the shortest distance from any integral point to all oxidation starting surfaces, and outputting the shortest distance; a3, compiling a C / SiC composite material oxidation analysis Umat subprogram based on Abaqus software by adopting a Fortran language, and reading shortest distance information; and A4, based on an existing C / SiC composite material oxidation diffusion mathematical model, a C / SiC finite element analysis model is established, and the oxidation expansion process of the component under different loads and temperatures is obtained.

This invention relates to the field of geophysical exploration technology, specifically to a well-to-surface electromagnetic forward modeling method, apparatus, and storage medium. The method includes: S1, modeling based on an octree mesh; S2, constructing vector Nédélec basis functions on the elements based on Gauss integration points and Gauss-Legendre-Lobatto (GLL) integration points set in the elements; S3, deriving the governing equations of the well-to-surface electromagnetic finite element method starting from Maxwell's equations; S4, constructing block diagonal preconditions and solving using an iterative method; S5, after exiting the iteration, calculating the electromagnetic response using the iterative model. This invention significantly reduces the number of elements in the mesh while maintaining model accuracy, thereby reducing computational costs. Higher-order shape functions are constructed and used in the forward modeling calculation to improve the accuracy of the numerical solution.

This invention provides an AI-adaptive finite element mesh and integral optimization method, system, medium, and device, belonging to the field of finite element simulation technology. The method includes: dividing the target region into an initial mesh and setting integration points; performing a preliminary simulation to obtain the physical field distribution; extracting physical field gradient data; constructing an input feature set by combining geotechnical medium parameters, mesh, and integration point information; training an AI optimization model using a physical information neural network to generate a dynamically adjusted scheme; and after performing a secondary simulation, re-inputting the updated gradient data into the AI ​​model, iteratively optimizing based on the topology change rate and physical field error until convergence. This invention aligns with geotechnical mechanics and seepage laws, avoids purely data-driven biases, significantly reduces redundant calculations while ensuring computational accuracy, and significantly improves the simulation efficiency and accuracy of physical fields such as stress, strain, and seepage. It is suitable for complex geological and nonlinear working conditions and has a high level of automation and intelligence.

The invention discloses a wing boundary simulation method based on an airfoil curved object plane normal, a terminal device and a storage medium, after wing curved boundary information is obtained, the integration degree of a curved unit is judged, the arc length is determined according to different integration degrees, then a Gaussian integration point is determined according to the arc length, and finally a numerical integration is obtained. The accuracy of numerical integration calculation is greatly improved, and then the accuracy of simulation result calculation is indirectly improved.

The application discloses an extrusion deformation state detection method and system, electronic equipment and a storage medium, and relates to the technical field of extrusion deformation detection. The method comprises the following steps: determining the deformation calculation method corresponding to each node / integration point according to the initial data of each time step in a time step iteration manner, and then determining the extrusion deformation data of the target measured object at the time step according to the corresponding deformation calculation method of each node / integration point, and obtaining the extrusion deformation state of the object at all time points through time step iteration. The application selects the corresponding deformation calculation method for deformation operation according to different nodes / integration points, retains the operation advantages of the time-space stable node integration algorithm and the node smooth finite element algorithm, and can realize high-precision and high-efficiency extrusion deformation state detection.

This application provides a method and apparatus for solving the completed state of a sealed assembly, relating to the field of sealing component design technology. It includes: acquiring the geometric model of an elastic component and its mating components and constructing an initial assembly configuration; discretizing the sealed assembly system using finite element methods and setting integration points in the elastic component; during the assembly iteration process, determining the corresponding projection point based on the integration point and the component combination it contains, and calculating the contact force at the integration point by combining material parameters, the projection point position, and the surface geometry information of the mating components; and unifying the contact force and the internal elastic force generated by the elastic component under the current configuration into a unified force balance relationship for nonlinear iterative solution until a preset convergence condition is met, thereby obtaining the completed state of the sealed assembly. This application can stably solve the completed state of a sealed assembly even with initial geometric interference, and improves the convergence and computational stability of the assembly simulation by uniformly handling the contact force and internal elastic force.

The invention discloses a high-precision polygon cross-order solving method and coupling analysis application, and belongs to the technical field of geotechnical engineering numerical analysis methods. The method comprises the following steps: S1, taking a grid, a material, a load and an output data file as input of a calculation model; s2, acquiring node numbers contained in each unit and corresponding node position coordinates, unit types, material parameters and integral points; s3, obtaining a material constitutive matrix of each unit in the S1; s4, determining the position of an integral point of each unit, and obtaining a feature value and a feature vector; s5, calculating a strain matrix value and a shape function at each integral point of the polygon unit; s6, obtaining a mass matrix and a stiffness matrix at each integration point; and S7, based on S1 to S6, numerical solution is carried out according to the working conditions needing to be calculated. According to the method, the combination of a cross-scale grid analysis method and a cross-order analysis method can be realized, and the contradiction between the solving precision and the calculation efficiency is balanced; the method can perform refined bending analysis on the polygonal unit, solves the problem of first-order unit shearing self-locking, and has relatively high analysis performance and universality.