49 results about "Hybrid mesh" patented technology

The invention discloses a scene preprocessing method for fire simulation, and relates to the technical field of building fire simulation, and the method comprises the steps: calculating a three-dimensional thermal weight through employing a fire propagation dynamics model, and generating a fire dangerous region thermal diagram; through a tensor field generation algorithm, fire behavior main diffusion direction and each axial anisotropic parameter are extracted, and fire behavior grid parameters are generated; through a hybrid grid generator, performing hexahedron dominant grid construction and increasing the grid density of a fire behavior dangerous area to obtain a fire behavior optimization hybrid grid; performing Reynolds number verification and boundary layer matching on the fire behavior optimization hybrid grid through a fire behavior feature adaptive algorithm, and performing iterative correction to generate a fire simulation correction grid; according to the invention, through the hybrid grid generator, the self-adaptive distribution of the grid density of the fire hazard area and the smooth connection of the transition area are realized, so that the grid distribution of the fire hazard area is accurately matched with the fire spreading characteristics.

The invention provides a finite element mesh automatic generation method and system based on multi-geometric-form block mapping. The generation method comprises the steps that a key area, a transition area and a non-key area of a target geometric model are determined; automatically segmenting the target geometric model by using a block partitioning mode; wherein a hexahedron block is constructed in the key area, a multi-geometric-form block is constructed in the transition area, and a block in any form is constructed in the non-key area; after the step 2, mapping the hexahedron block to generate a hexahedron mesh, generating the hexahedron mesh by using the multi-geometric-form block according to a pre-mapping rule, and filling the block in any form by using a target algorithm; and performing quality adjustment on the grid file obtained in the step 3, and outputting a hybrid grid file. By adopting the prediction method and introducing a multi-geometric-form partitioning mode, a user can perform hybrid partitioning on a specified key area to realize automatic generation of the block, so that the success rate of block partitioning is ensured, and the iterative calculation amount of automatically generating the block is reduced.

The invention provides a grid generation method and device for a nuclear power fuel assembly and a computer readable medium, and the method comprises the steps: receiving a geometric file of the nuclear power fuel assembly, and generating a hybrid grid of the nuclear power fuel assembly according to a grid generation strategy and the geometric file, the grid generation strategy comprises the steps that a structured grid is used in a boundary layer of the nuclear power fuel assembly, and an unstructured grid is used in an area outside the boundary layer; the generated hybrid grid is subjected to self-adaptive refinement processing, the self-adaptive refinement processing comprises the steps of recognizing a high-gradient area and increasing the grid density in the high-gradient area, and the high-gradient area refers to the area where the change rate of fluid parameters in space is larger than a preset threshold value when fluid flows along the wall face of the nuclear power fuel assembly. According to the method, the grid density is only increased in a high-gradient region, and relatively thick grids are kept in other regions, so that the resolution of a key region is ensured, and the waste of computing resources is effectively reduced.

The invention discloses an automatic generation method and device for a large-scale unstructured grid of a commercial aircraft. The method comprises the following steps: carrying out geometric segmentation on a computational domain enclosed by a near-field bounding box and a far-field bounding box through a constructed inscribed geometric surface to obtain far-field regions; generating a first surface grid on the surfaces of the aircraft body and the aircraft parts in the near-field region, generating a second surface grid on the inscribed geometric surface of the near-field region and the far-field region, and generating a third surface grid on the surface of the far-field bounding box; generating a non-structural body grid based on the second surface grid and the third surface grid; automatically generating a basic unstructured mixture grid in the near-field region based on the first surface grid; according to the commercial aircraft large-scale non-structural hybrid grid generation method and device, the calculation domains are divided into the calculation sub-domains, automatic generation of the grids of the calculation sub-domains is achieved, then automatic combination of the grids is achieved, the technical bottlenecks that super-large-scale non-structural grids are difficult to generate, the automation degree is low and the like are effectively solved, and the commercial aircraft large-scale non-structural hybrid grid generation method and device are suitable for large-scale aircraft large-scale non-structural hybrid grids. And the simulation efficiency is improved.

The invention discloses an aircraft structure grid-oriented overdetermined equation parallel random solving method and system, and relates to the technical field of grid generation, and the method comprises the steps: obtaining a numerical aircraft parameter model; generating a grid by adopting a variational harmonic partial differential equation on the basis of an aircraft parameter model, discretizing the variational harmonic partial differential equation, and establishing an overdetermined linear equation set taking a grid vertex coordinate value as an unknown number after discretization; performing low-rank approximate processing on the overdetermined linear equation set to obtain an overdetermined linear equation set after dimension reduction; a greedy random hybrid Kaczmarz algorithm is adopted to carry out parallel solution on the overdetermined linear equation set after dimension reduction, and an optimal solution is obtained; and mapping the optimal solution to a physical space to generate a hybrid grid, and importing the hybrid grid into an aircraft simulation platform for heat flow analysis. According to the method, parallel optimization is carried out on the solution of an overdetermined equation set generated by a grid, and rapid solution of an overdetermined linear equation set is realized through a greedy random hybrid Kaczmarz algorithm, so that the purpose of improving the grid quality is achieved.

The invention discloses an external mixing type air nozzle atomization process simulation method, which comprises a multi-scale atomization mathematical model and numerical simulation based on the multi-scale atomization mathematical model, the multi-scale atomization mathematical model divides a flow field component into a continuous phase and a dispersed phase based on an Euler-Lagrange coupling method, the Lagrange method is used for describing the movement of small-scale coating particles, and the numerical simulation is carried out based on the continuous phase and the dispersed phase. Establishing a big and small droplet identification conversion mechanism, and selecting Reynolds average simulation to establish a turbulence model; based on numerical simulation of a model, a geometric model is firstly constructed to generate a computational domain, a coordinate system is established, then a key region is divided and encrypted by using a hybrid grid, and simulation is performed by controlling the number of grids in combination with a dynamic adaptive technology. Direct and indirect verification experiments prove that the model is correct; the problems that an existing model is incomplete in description, poor in fidelity and low in calculation efficiency are solved, the time cost is saved, the simulation result is closer to reality, accurate data can be provided for analysis of the atomization phenomenon, and the spraying quality and the production efficiency are improved.

The invention relates to the technical field of high-performance computing, in particular to an unstructured hybrid grid gradient reconstruction method based on GPU acceleration, and solves the problems that a gradient reconstruction method in the prior art is large in calculation amount and high in calculation cost due to the fact that the gradient reconstruction method needs to be executed for multiple times in the iteration process. The method comprises the following steps: carrying out gradient reconstruction by using a least square method, and introducing a JAX architecture in a gradient reconstruction stage to realize parallel computing of a GPU (Graphics Processing Unit); according to the method, non-structured grid gradient reconstruction based on a JAX framework is realized; and the JAX pre-compiles the calculation graph into a highly optimized GPU instruction through an XLA compiler, so that the calculation efficiency is effectively improved. The gradient reconstruction algorithm based on the JAX framework shows excellent operation stability in a stable calculation stage.

The invention provides a fan blade topological optimization method based on a truss-continuum hybrid grid finite element model, and belongs to the technical field of fan blade optimization design. According to the method, a quadrilateral unit is adopted to simulate a composite material base body in the fan blade, a truss unit is adopted to simulate reinforced fibers in the fan blade, a truss-continuum mixed mesh finite element model is constructed, topological optimization is performed on the basis of the truss-continuum mixed mesh finite element model, and therefore the composite material base body in the fan blade is simulated. The structural difference between the composite material matrix and the reinforced fibers is comprehensively considered, the optimization accuracy can be improved, and the expected requirement is met.

The invention discloses a well periphery flow capacity calculation method based on a hybrid grid. The well periphery flow capacity calculation method comprises the following steps that S1, the hybrid grid is established according to well periphery heterogeneous characteristics; s2, at the beginning of the time step, preliminarily determining fluid pressure in a shaft, and for a large-scale grid, calculating fluid pressure distribution in a matrix rock mass by adopting a seepage numerical model; s3, preliminarily determining the concentration of acid liquor in a shaft, adopting the pressure and the concentration in the shaft as inlet boundary conditions, adopting the recorded large-scale grid boundary fluid pressure as outlet boundary conditions, calculating the growth process of acid etching wormholes in the small-scale grid system by utilizing a wormhole model, and obtaining the change of a porosity field in the small-scale grid system; s4, calculating physical property parameters of the large-scale grid after earthworm hole growth in a single time step; and S5, repeating the steps S2-S4, and carrying out next time step calculation until analog calculation of the whole injection process is completed. According to the invention, the optimal balance between the calculation efficiency and the simulation precision is realized.

The invention discloses a ship fluid computational domain full-automatic non-structural hybrid grid generation method, which comprises the following steps: acquiring a ship geometric model, adding a computational domain bounding box, and generating an initial discrete geometric model consisting of triangular surface grids; acquiring user input control parameters, and generating a size field in combination with the initial discrete geometric model; embedding a symmetric plane and a horizontal plane according to the initial discrete geometric model, generating an initial triangular surface grid with consistent boundaries, and performing re-gridding under the control of a size field to generate a model boundary surface grid; according to a horizontal plane, dividing the boundary surface grid into an upper surface grid and a lower surface grid, and respectively generating an upper boundary layer grid and a lower boundary layer grid which are composed of anisotropic triangular prism units and pyramid units; on this basis, surface grids of the boundary of the computational domain are regenerated at the boundary of the bounding box, tetrahedral grid units are generated under the control of the size field, and therefore the ship fluid computational domain full-automatic non-structural hybrid grid is formed through merging.

The invention discloses an unstructured hybrid grid generation method and device, equipment and a storage medium, and relates to the technical field of computers, and the method comprises the steps: creating an initial octree unit; according to geometric accuracy and a preset criterion, the initial octree unit is subdivided, a plurality of octree leaf units are obtained, and the preset criterion includes that the hierarchy difference between adjacent octree leaf units is not larger than 1, and subunits with the same octree parent unit are jointly subdivided; creating an unstructured grid around the vertex of each octree leaf unit; if the created unstructured grid is a non-standard unit, determining a first type of the unstructured grid; according to the first type of the unstructured grid, subdividing the unstructured grid; obtaining a second type of an unstructured grid adjacent to the subdivided side of the unstructured grid; and according to the second type, subdividing the adjacent unstructured grids to obtain an unstructured hybrid grid. According to the method, the generation process of the unstructured hybrid grid can be simplified.

The invention discloses an aerodynamic calculation method and system based on a non-structural-Cartesian hybrid grid, and belongs to the technical field of fluid mechanics numerical simulation. By receiving and analyzing various input files, generating a hybrid grid, initializing a flow field and combining various calculation methods for solving, a Cartesian grid can be dynamically adjusted according to speed divergence and rotation criteria in the flow field, and finally a calculation result including pressure change at a pressure monitoring point is output. The hybrid grid provided by the invention gives consideration to both complex geometric adaptability and calculation efficiency, various calculation methods meet different requirements, dynamic monitoring and parameter adjustment improve the calculation precision, and the limitation of a traditional method in the aspects of complex geometric shape processing, turbulence simulation and the like can be effectively solved; and high-precision and high-efficiency aerodynamics simulation support is provided for industries such as aerospace, automobiles and buildings.

This invention relates to the field of submersible electric pump (FET) fault diagnosis technology, and particularly to a method and system for FET fault diagnosis based on CFD and deep learning. The method includes constructing a full-channel 3D model, simulating FET faults by modifying key geometric feature parameters, and using a hybrid mesh strategy to divide the mesh; extracting time-domain and frequency-domain features from the simulation data, forming feature vectors from these features, and constructing multi-dimensional labeled simulation data using these feature vectors and multi-dimensional label vectors; constructing a multi-channel deep neural network, training the multi-channel deep neural network using the multi-dimensional labeled simulation data; and deploying the trained multi-channel deep neural network to a well site edge computing gateway to diagnose FET sensor data. This invention utilizes CFD to generate high-quality data to drive deep learning model training, achieving rapid and accurate collaborative diagnosis of multiple faults in FETs.

This invention provides a multi-grid fusion method for numerical simulation of wind turbine wakes in complex terrain. It fuses Cartesian grids of complex terrain, structured or unstructured hybrid grids of the wind turbine region, and anisotropic O-type structured grids of the wake region. By fusing multiple grid types with different topologies and using overlapping grid technology for assembly and interpolation calculations, this method significantly improves wake vortex analysis efficiency and controls computational costs while ensuring the accuracy of wind turbine aerodynamic loads and automated terrain geometry modeling. This enhances the accuracy and efficiency of numerical simulation of wind field wakes.

The invention discloses an immersive image transmission method and system for an AR cinema, and relates to the technical field of AR image transmission, and the method comprises the steps: optimizing a stereo unit set and a NeRF radiation field unit set through a variable weight joint optimization method, predicting the fusion probability of a stereo unit and a NeRF radiation field unit through a space-time Transform fusion method, carrying out the unit fusion according to the fusion probability, and carrying out the unit fusion. And mapping the fused and non-fused units to a three-dimensional grid structure to generate a stereoscopic NeRF hybrid grid. A variable weight joint optimization method is adopted, weights are dynamically calculated and optimized, priority optimization of a high-interaction area, resource allocation efficiency improvement and special effect area detail expression precision improvement are achieved, a space-time Transform fusion method is introduced, the fusion probability is predicted by utilizing a learnable weight matrix, semantic association of a stereoscopic unit and a NeRF unit is enhanced through space-time feature modeling, and the fusion efficiency of the stereoscopic unit and the NeRF unit is improved. Light field breakage and geometric distortion are eliminated, and the rendering quality of the AR cinema scene in the dynamic special effect area is remarkably improved.

The invention discloses a high-energy beam welding stress deformation simulation optimization method based on a pinhole effect, and aims to solve the problems of low simulation precision, poor calculation efficiency, difficulty in process optimization and the like in the prior art. Accurate simulation and efficient optimization are realized through three core modules: a dynamic molten pool behavior modeling module is coupled with energy interaction and dynamic evolution of metal steam in a small hole and a high-energy beam, and a dynamic heat source model is constructed; the stress simulation module is combined with a grain orientation model and a Newton-Raphson iterative algorithm, so that the stress calculation precision is improved; the welding structure rapid simulation module is based on a hybrid grid technology, and adopts an algebraic multi-grid algorithm to improve efficiency and balance precision and efficiency. According to the method, the welding stress deformation can be accurately predicted (the error is smaller than or equal to 10%), the simulation efficiency of a large structure is greatly improved (the simulation efficiency is improved by 1-2 orders of magnitude), the trial and error experiment cost is reduced by 30% or above, and the method is suitable for various high-energy beam welding processes and materials and can be widely applied to the high-end manufacturing fields of aerospace, weaponry and the like.

The invention discloses a hot hybrid simulation method for a T-shaped pipe of a pressurized water reactor core safety injection system, and the method comprises the steps: building a simplified three-dimensional geometric model comprising a safety injection T-shaped pipe through CFD software, dividing grids through a hybrid grid technology, carrying out the local encryption of a core region, and generating a boundary layer grid, the method comprises the following steps: selecting a VOF multiphase flow model, a k-epsilon turbulence model and a Lee phase change mass transfer model for coupling simulation, setting corresponding boundary conditions and initial parameters, and finally, completing solution method setting through a Coupled algorithm discrete format and an interpolation method, performing adaptive time step strategy solution, accurately capturing key thermal hydraulic parameters such as a temperature field, a velocity field, flow pattern evolution and the like, and obtaining the thermal hydraulic parameters. And a mixing condensation process of a safety injection coolant and a main loop high-temperature coolant or steam under an accident condition is simulated. The method not only reduces the time consumption and cost of traditional experiments, but also improves the prediction precision of key phenomena in reactor safety analysis, provides reliable technical support for emergency cooling strategy optimization of a pressurized water reactor nuclear power plant under a water loss accident or a steam pipeline fracture accident, and has important engineering application value.

The invention relates to a simple human chest impact response modeling method with efficient calculation, and mainly solves the problems of high calculation cost and low efficiency of a high-precision finite element model in the traditional explosive shock wave lung injury research. The method comprises the following steps: geometrically simplifying the chest of a human body, simplifying ribs into equal-height cylinders, and simplifying lungs into solid spheres; the method comprises the following steps of: performing hybrid grid division, performing adaptive grid (dynamic encryption based on a Zienkiewicz-Zhu error estimator and a Hessian matrix anisotropic size field) on muscular tissues, and performing hexahedral structured grid (generated through a parameterized mapping method to ensure unit quality) on bones and lungs; material setting: endowing muscles, bones and lungs with standardized linear elastic material parameters, and simulating the interaction between an explosion flow field and a human body through Euler-Lagrange coupling. The model only contains 2676 units, the calculation time is shortened to half an hour from several weeks, and the memory demand is reduced to 14 MB from 200 MB.

The invention provides a multi-grid fusion method for fan wake flow numerical simulation in complex terrains. A Cartesian grid of a complex terrain, a structural or non-structural hybrid grid of a fan area and an anisotropic O-shaped structural grid of a wake area are fused, multiple grid types of different topologies are fused, and assembly and interpolation calculation are realized based on an overlapping grid technology, so that the aerodynamic load precision of the fan and automatic modeling of terrain geometry are ensured, and the accuracy of the aerodynamic load of the fan is improved. The trailing vortex analysis efficiency is remarkably improved, the calculation cost is controlled, and the precision and efficiency of wind field wake flow numerical simulation are improved.

The invention belongs to the technical field of model processing, and particularly discloses a data center air field CFD complex geometric model rapid mesh generation method, which comprises the following steps: S1, geometric preprocessing: cleaning a data center complex geometric model, removing a detail structure which has extremely small influence on air field simulation, simplifying the model complexity, and performing model repair, checking and repairing a broken surface and a gap in the geometric model; s2, region decomposition: dividing the whole data center geometric model into a plurality of sub-regions according to the structural characteristics of the data center geometric model; s3, grid division is carried out, grid division is carried out on the plurality of sub-regions, and grid division comprises structured grids, unstructured grids and mixed grids; and S4, grid optimization, quality inspection is carried out, grid units with poor quality are screened out by calculating parameters of aspect ratios and Jacobian determinants of grids, the grids with poor quality are optimized, and grid smoothing and local encryption or sparseness are adopted.

The application belongs to the field of aerospace and fluid mechanics, and discloses an aircraft internal and external flow field structure grid division method based on a non-matching interface, which comprises the following steps: decomposing the aircraft shape into two topological subdomains of an external flow field, an inlet duct and an internal flow field of a tail nozzle, and connecting each subdomain through a pair of completely coinciding interfaces; wherein the internal flow field of the inlet duct and the tail nozzle adopts an O-type topological structured grid, the external flow field adopts a C-type topological structured grid, and the nodes of the O-type topological structured grid and the C-type topological structured grid can slide on the interface. The problems that the adaptability of the non-structured grid is poor in the near-wall boundary layer region, the calculation amount is large, and the mixed grid is difficult to maintain the overall field conservation and high precision in the current numerical simulation of the internal and external flow coupling of the complex aircraft shape are solved.

This invention discloses an immersive image transmission method and system for AR cinemas, relating to the field of AR image transmission technology. The method includes optimizing a stereoscopic unit set and a NeRF radiant field unit set using a variable-weight joint optimization method; predicting the fusion probability of stereoscopic units and NeRF radiant field units using a spatiotemporal Transformer fusion method; performing unit fusion based on the fusion probability; and mapping fused and unfused units onto a 3D mesh structure to generate a stereoscopic-NeRF hybrid mesh. The variable-weight joint optimization method dynamically calculates optimization weights, prioritizing optimization of high-interaction areas, improving resource allocation efficiency, and enhancing the detail expression accuracy of special effects areas. The spatiotemporal Transformer fusion method is introduced, utilizing a learnable weight matrix to predict the fusion probability. Spatiotemporal feature modeling enhances the semantic association between stereoscopic units and NeRF units, eliminating light field breaks and geometric distortions, and significantly improving the rendering quality of AR cinema scenes in dynamic special effects areas.

The invention provides a numerical simulation method for the leaching process of a nickel pressurized stirred tank reactor, which comprises the following steps: creating a geometric model of the nickel pressurized stirred tank reactor, adopting a structured-unstructured mixed grid division mode for the geometric model, and performing grid division on a computational domain of the geometric model to obtain a grid file; constructing a multiphase flow numerical model in the reaction kettle; setting process conditions corresponding to the nickel leaching process in the grid file, and coupling and solving the multiphase flow numerical model to obtain simulation data of flow field characteristic indexes in the reaction kettle in the nickel leaching process; constructing a solid model which is scaled down in equal proportion, and scaling the stirring speed and the gas flow based on a similarity criterion; carrying out a water simulation experiment, and measuring entity experiment data of flow field characteristic indexes; comparing the simulation data with the entity experiment data to correct parameters of the multiphase flow numerical model; different process conditions are set in batches, the corrected multiphase flow numerical model is solved in a coupling mode, and simulation data of the leaching process of the reaction kettle under the different process conditions are obtained. The simulation precision can be improved.

The present disclosure relates to the technical field of computational fluid dynamics, and in particular, provides a topology method, device, equipment, storage medium and product for a hybrid grid. The method includes: dividing the data points included in the nodes in the grid file based on the number of processes for generating grid cells to obtain the data points that each process needs to perform topology on; obtaining the latest N data points in terms of topology order from the data points that the i-th process needs to perform topology on; obtaining target data points whose attributes include grid types from the N data points; determining the topology starting point of the (i + 1)-th process based on the target data points and the data points that the (i + 1)-th process needs to perform topology on, and performing grid topology on the N data points and the data points that the (i + 1)-th process needs to perform topology on based on the topology starting point. By dividing the data points under the nodes among multiple processes and having the multiple processes process in parallel to perform grid topology on the data points, the topology efficiency and processing speed are improved.

The present application discloses a method and device for automatically generating a large-scale unstructured grid for a commercial aircraft. The computational domain enclosed by the near-field bounding box and the far-field bounding box is geometrically segmented by the constructed inscribed geometric surface to obtain each far-field region; a first surface grid is generated on the surface of the aircraft body and each component of the aircraft in the near-field region, a second surface grid is generated on the inscribed geometric surface between the near-field region and the far-field region, and a third surface grid is generated on the surface of the far-field bounding box; an unstructured grid is generated based on the second surface grid and the third surface grid; a basic unstructured hybrid grid is automatically generated in the near-field region based on the first surface grid; the unstructured grids in each computational sub-domain are automatically merged to obtain a large-scale unstructured hybrid grid for the commercial aircraft. The present application realizes the automatic generation of grids from the division of the computational domain to each computational sub-domain, and then to the automatic merging of grids, effectively solving technical bottlenecks such as difficulties in generating ultra-large-scale unstructured grids and low automation, and improving the simulation efficiency.

The embodiment of the invention provides a grid generation method and system for the reverse jet flow interference problem of a rocket, and the method comprises the steps: dividing the rocket into two regions according to the aerodynamic interference intensity of a jet flow interference flow field; respectively generating structural / non-structural hybrid grids for the two areas according to the reverse jet flow field structure of the rocket; and solving the structured grid and the non-structured grid through a structured grid solver and a non-structured grid solver respectively. According to the method, the advantages of the structured grid and the unstructured grid are fully utilized, the structure is reasonable, the calculation precision and the grid generation efficiency are both considered, and the grid generated according to the strategy is suitable for high-precision simulation of the reverse jet disturbing flow field of the rocket.

The present disclosure relates to the technical field of computational fluid dynamics, and in particular provides a parallel reading method based on CGNS hybrid grids, including the following steps: S1: Calculate the upper and lower limits that the process needs to read in according to the number of CGNS grid vertices, and each process reads in the grid data between the upper and lower limits of the process respectively; S2: Communicate the point information of the last n points of the previous process to the next process; after each process analyzes the points, determine which points may be grid cell type data as possible topological starting points; S3: Generate all possible grid topologies based on the set of possible topological starting points; S4: Determine the unique grid topology of other processes through communication according to the process with the determined grid topology information; repeat this loop until all processes find the unique network topology. The present disclosure significantly improves the efficiency of data reading and processing by parallel reading and processing CGNS hybrid grid data.

The application discloses a rotating machine inner flow non-structure mixed grid generation method with dynamic and static interference surfaces, and comprises the following steps: reading rotating machine geometric model data by using a geometric engine Open CASCADE, giving boundary attributes of the geometric model, dividing the geometric model into a main body and a secondary body, and giving boundary attributes of the main body and the secondary body; defining symmetric edges and surface edges according to the boundary attributes of the main body and the secondary body, and generating a triangular surface grid on the main body; generating an anisotropic triangular prism unit on the main body according to the triangular surface grid; regenerating a triangular surface grid and a quadrilateral surface grid on the main body according to the triangular prism unit; generating a quadrilateral surface grid on the secondary body according to the quadrilateral surface grid of the main body; generating a hexahedron unit and a pyramid unit on the secondary body according to the quadrilateral surface grid of the secondary body; and generating a tetrahedron unit on the main body according to the pyramid unit.

The application discloses a scene preprocessing method for fire simulation, and relates to the technical field of building fire simulation, comprising the following steps: calculating three-dimensional thermal power weight by using a fire spread dynamics model, and generating a thermal map of a fire danger area; extracting a main diffusion direction of the fire and each axial anisotropy parameter by using a tensor field generation algorithm, and generating fire grid parameters; constructing a hexahedral leading grid by using a hybrid grid generator, increasing the grid density of the fire danger area, and obtaining an optimized hybrid grid of the fire; and checking the Reynolds number and matching the boundary layer of the optimized hybrid grid of the fire by using a fire feature self-adaptive algorithm, and iteratively correcting to generate a fire simulation correction grid; by using the hybrid grid generator, the application realizes self-adaptive distribution and smooth connection of the grid density of the fire danger area, so that the grid distribution of the fire danger area is accurately matched with the fire spread characteristics.

This invention relates to the field of geophysical exploration technology and discloses a three-dimensional polarizability inversion method based on cross-gradient constraints. The method includes the following steps: acquiring apparent resistivity observation data d_obsr and equivalent apparent resistivity observation data d_obsη; performing hybrid mesh partitioning on the computational domain to generate a hybrid mesh model containing triangular prism elements, tetrahedral elements, and pyramidal elements; and performing three-dimensional resistivity forward modeling based on the hybrid mesh model to obtain the total field potential. This three-dimensional polarizability inversion method based on cross-gradient constraints, by employing a hybrid mesh (combination of triangular prism, tetrahedral, and pyramidal elements) partitioning technique, can accurately fit undulating surfaces, fundamentally eliminating the terrain influence error caused by mesh simplification. Measured data show that the forward modeling response error at steep terrain measurement points can be reduced from 5.1% to 1.5% using traditional methods, effectively suppressing false anomalies and making the anomaly boundary more clearly delineated.