A method, device, equipment and storage medium for determining inviscid flux of multi-component thermally perfect gas based on aircraft grid

Abstract

The application discloses a method and device for determining inviscid flux of multi-component thermally perfect gas based on an aircraft grid, equipment and a storage medium, and relates to the technical field of fluid mechanics. The method comprises the following steps: calling a preset thermodynamic database according to the mass fraction of each component in a grid unit to determine local mixed gas constants and a local specific heat ratio; converting relative pressure values on both sides of a grid unit interface into absolute pressure values based on a pressure benchmark reference value; calculating the pressure and density of the intermediate state of the unit interface based on the density, normal velocity and the above-mentioned parameters of adjacent grids, and then estimating the extreme values of the left and right characteristic wave speeds. By using an area vector and a wave speed separation strategy, the numerical flux in a conservative form is determined, and the component transport term is explicitly corrected by the grid motion speed, so that the target inviscid flux is finally obtained, and the efficiency of determining the inviscid flux of the multi-component thermally perfect gas of the aircraft grid is improved.

Description

Technical Field

[0001] This invention relates to the field of fluid mechanics, and in particular to a method, apparatus, device, and storage medium for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid. Background Technology

[0002] Currently, flux splitting schemes are crucial for constructing high-resolution numerical methods in computational fluid dynamics. However, traditional flux differential splitting methods and exact Riemann solvers face significant challenges in modeling thermally complete gases for simulating multicomponent compressible flows. The fundamental difference between thermally complete gas models and ideal gas models lies in the nonlinear variation of their thermodynamic parameters with temperature and composition distribution. This necessitates considering both local thermodynamic states and component mixing effects when calculating characteristic wave velocities.

[0003] In numerical simulations of multicomponent flows, accurate transport of mass fractions is crucial for the stability of the physical field. Existing methods (such as the Roe scheme) often employ linearized Jacobian matrices for wave velocity decomposition, but their applicability to the thermally complete gas equation of state is limited by the following: First, the non-uniform distribution of component-dependent gas constants and specific heat ratios can induce numerical oscillations, easily leading to distorted wave velocity estimates; second, the calculation of temperature-dependent thermodynamic parameters significantly increases computational complexity; and third, the chemical potential equilibrium problem at the multicomponent mixing interface is difficult to handle effectively using traditional flux splitting methods.

[0004] The HLLE scheme (Harten-Lax-van Leer-Einfeldt, an approximate Riemannian solver for calculating interfacial fluxes) is a classical approximate Riemannian solver that constructs fluxes by calculating the sum of left and right states. Furthermore, Einfeldt proposed a characteristic wave velocity estimation method based on sound velocity and velocity, significantly improving computational stability. However, this method has two main drawbacks in multi-component applications: first, the characteristic velocity estimation does not consider the influence of component mass fraction gradients on contact discontinuities; second, in the thermally complete gas model, the coupling between temperature calculation and component mass fraction correction leads to the accumulation of errors in the reconstruction of conserved variables.

[0005] The current industrial-grade CFD (Computational Fluid Dynamics) software mainly uses the following improvement paths for multi-component flux calculation: (1) introducing component-related modified Roe average parameters (such as mixing specific heat ratio); (2) using pressure relaxation techniques to separate wave velocities at different scales; and (3) constructing independent flux limiters for component mass fractions. For example, the multi-component HLLC method has been improved by the assumption of local thermodynamic equilibrium, but this method will produce excessively high numerical dissipation in non-equilibrium flow regions (such as the interaction between shock waves and flame fronts).

[0006] The mathematical description of a thermally complete gas model requires the introduction of a temperature-dependent specific heat ratio. This complex thermodynamic relationship renders the traditional isentropic assumption invalid, necessitating the real-time calculation of local thermodynamic parameters in each computational unit. Current methods employ preprocessing steps to correct the pressure term, but this strategy cannot guarantee entropy conditions under varying specific heat ratios.

[0007] In applications with non-uniform meshes (such as polyhedral meshes), the coupling effect between the interface normal vector and the mesh velocity further exacerbates the complexity of flux calculations. The AUSM series of methods alleviates this problem by separating convective fluxes from pressure fluxes, but introduces mass fraction non-conservation errors at the component mixing interface. Furthermore, existing methods often lead to divergence in characteristic velocity estimations when dealing with extreme conditions (such as ultra-high temperature combustion flows) due to drastic changes in the gas constant R.

[0008] As can be seen from the above, improving the efficiency of determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid is an urgent problem to be solved. Summary of the Invention

[0009] In view of this, the purpose of this invention is to provide a method, apparatus, device, and storage medium for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, which can improve the efficiency of determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid. The specific solution is as follows:

[0010] In a first aspect, this application provides a method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, including:

[0011] The thermodynamic state variables, including the mass fractions of each component, are determined for each grid cell in the aircraft grid. Based on the mass fractions, a function relationship in a preset thermodynamic database is called to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell.

[0012] Determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value.

[0013] The fluid density and normal velocity of each adjacent grid in each of the grid cell interfaces are determined. Based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density and the normal velocity, the intermediate state pressure and intermediate state density of the cell interface are determined. Based on the intermediate state pressure, the intermediate state density and the distribution results of the mass fraction, the extreme values ​​of the left-row characteristic wave velocity and the extreme values ​​of the right-row characteristic wave velocity corresponding to the grid cell interface are estimated.

[0014] The area vector corresponding to the grid cell interface is determined, and a pre-defined wave velocity symbol separation strategy is used to determine the conserved form of the numerical flux passing through the grid cell interface based on the left-row characteristic wave velocity extreme value, the right-row characteristic wave velocity extreme value and the area vector. The component transport term in the numerical flux is explicitly corrected based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

[0015] Optionally, determining the thermodynamic state variables corresponding to the mass fractions of each component in each grid cell of the spacecraft grid, and calling the functional relationships in a preset thermodynamic database based on the mass fractions to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell using the functional relationships, includes:

[0016] The thermodynamic state variables associated with each grid cell in the spacecraft grid corresponding to the spacecraft are determined, and the first and second function relationships stored in the preset thermodynamic database are called based on the mass fraction; the thermodynamic state variables include the mass fractions corresponding to each gas component;

[0017] The local mixed gas constant corresponding to the grid cell is determined by using the first functional relationship and based on the mass fraction corresponding to the grid cell. Then, the local specific heat ratio corresponding to the grid cell is determined by using the second functional relationship and based on the temperature and mass fraction of the current grid cell.

[0018] Optionally, determining the pressure reference value corresponding to the aircraft grid, and converting the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value, includes:

[0019] The pressure reference value corresponding to the aircraft grid is determined based on the physical characteristics of the flow field, or the pressure reference value corresponding to the aircraft grid is extracted from the aircraft grid using a preset grid data interface; the pressure reference value satisfies preset physical constraints.

[0020] The mesh cell interface between each adjacent mesh cell in the aircraft mesh is determined, and the first relative pressure value and the second relative pressure value corresponding to the mesh cell interface are determined.

[0021] The pressure reference value is superimposed on the first relative pressure value and the second relative pressure value to obtain the first absolute pressure value and the second absolute pressure value corresponding to the grid cell interface.

[0022] Optionally, determining the fluid density and normal velocity of each adjacent grid cell in each of the grid cell interfaces, so as to determine the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density, and the normal velocity, includes:

[0023] The first adjacent grid and the second adjacent grid corresponding to each of the unit interfaces are determined, and the fluid density and normal velocity corresponding to the first adjacent grid and the second adjacent grid are determined respectively. Then, based on the local mixed gas constant, the local specific heat ratio, the first relative pressure value, the second relative pressure value, the fluid density and the normal velocity corresponding to the first adjacent grid and the second adjacent grid respectively, the intermediate state pressure corresponding to the unit interface is determined.

[0024] Based on the mass fraction distribution, the intermediate pressure, the absolute pressure value, the fluid density, and the local specific heat ratio, determine the geometric mean density and geometric mean mixing specific heat ratio corresponding to the unit interface;

[0025] The intermediate state density and intermediate state sound velocity corresponding to the unit interface are determined based on the geometric mean density and the geometric mean mixing specific heat ratio.

[0026] Optionally, the estimation of the left-row characteristic wave velocity extrema and the right-row characteristic wave velocity extrema corresponding to the grid cell interface based on the distribution results of the intermediate state pressure, the intermediate state density, and the mass fraction includes:

[0027] Determine the first sound velocity and first normal velocity of the first adjacent grid and the second sound velocity and second normal velocity of the second adjacent grid, and determine the distribution results corresponding to each of the mass fractions;

[0028] Using a preset dual correction strategy and based on the first sound velocity, the first normal velocity, the second sound velocity, the second normal velocity, the intermediate state sound velocity, the intermediate state normal velocity, and the distribution results, the extreme values ​​of the left-row characteristic wave velocity and the extreme values ​​of the right-row characteristic wave velocity corresponding to the grid cell interface are estimated; the intermediate state normal velocity is the velocity determined based on the first normal velocity and the second normal velocity.

[0029] Optionally, determining the area vector corresponding to the grid cell interface, and using a preset wave velocity sign separation strategy and based on the left-row characteristic wave velocity extremum, the right-row characteristic wave velocity extremum, and the area vector to determine the conserved form of the numerical flux passing through the grid cell interface, includes:

[0030] Determine the area vector corresponding to the interface of each grid cell in the aircraft grid, and then use a preset wave velocity sign separation strategy to determine the negative wave velocity based on the left-row characteristic wave velocity extreme value and the preset zero value, and determine the positive wave velocity based on the right-row characteristic wave velocity extreme value and the preset zero value;

[0031] The initial gas constant is corrected using the mass fraction to obtain the target gas constant. Based on the target gas constant, the first and second conserved variables corresponding to the grid cell interface are determined. Then, the first flux corresponding to the first conserved variable and the second flux corresponding to the second conserved variable are determined.

[0032] Based on the preset flux format, the negative wave velocity, the positive wave velocity, the first conserved variable, the second conserved variable, the first flux, and the second flux, an intermediate flux corresponding to the grid cell interface is determined, and based on the intermediate flux and the area vector, a numerical flux in the conserved form passing through the grid cell interface is determined.

[0033] Optionally, the explicit correction of the component transport term in the numerical flux based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux includes:

[0034] Determine the current motion state corresponding to the aircraft mesh, determine the mesh motion velocity vector corresponding to the aircraft mesh based on the current motion state, and determine the component of the mesh motion velocity vector in the normal direction of the mesh cell interface based on the mesh motion velocity vector and the normal velocity of the mesh cell interface.

[0035] Obtain the component density and component mass fraction corresponding to the numerical flux, and determine the normal velocity based on the normal velocity and the corresponding normal component of the mesh motion velocity vector. Explicitly correct each component transport term in the numerical flux using the component density, component mass fraction, and normal velocity. Calculate the corrected component flux corresponding to each component, and then integrate the corrected component flux with the numerical flux to obtain the target inviscid flux.

[0036] Secondly, this application provides a device for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, comprising:

[0037] The state variable determination module is used to determine the thermodynamic state variables corresponding to each grid cell in the aircraft grid, including the mass fraction of each component, and to call the function relationship in the preset thermodynamic database based on the mass fraction, so as to use the function relationship to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell;

[0038] The pressure value conversion module is used to determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value.

[0039] The wave velocity extremum determination module is used to determine the fluid density and normal velocity of each adjacent grid in each of the grid cell interfaces, and to determine the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density and the normal velocity. Based on the intermediate state pressure, the intermediate state density and the distribution results of the mass fraction, the module estimates the left-row characteristic wave velocity extremum and the right-row characteristic wave velocity extremum corresponding to the grid cell interface.

[0040] The inviscid flux generation module is used to determine the area vector corresponding to the grid cell interface, and to determine the conserved form of the numerical flux passing through the grid cell interface based on the left-row characteristic wave velocity extreme value, the right-row characteristic wave velocity extreme value and the area vector using a preset wave velocity symbol separation strategy. The module also explicitly corrects the component transport terms in the numerical flux based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

[0041] Thirdly, this application provides an electronic device, comprising:

[0042] Memory, used to store computer programs;

[0043] A processor is used to execute the computer program to implement the aforementioned method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid.

[0044] Fourthly, this application provides a computer-readable storage medium for storing a computer program, wherein the computer program, when executed by a processor, implements the aforementioned method for determining the viscosity-free flux of a multi-component thermally complete gas based on an aircraft grid.

[0045] As can be seen from the above, before determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, this application needs to determine the thermodynamic state variables corresponding to each grid cell in the aircraft grid, including the mass fraction of each component, and call the functional relationship in the preset thermodynamic database based on the mass fraction to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell; determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value; determine the fluid density and normal velocity of each adjacent grid cell in the interface of each grid cell to determine the local mixing gas constant and local specific heat ratio. The intermediate-state pressure and density of the inter-cell interface are determined by the gas mixture constant, local specific heat ratio, absolute pressure, fluid density, and normal velocity. Based on the distribution of intermediate-state pressure, intermediate-state density, and mass fraction, the extreme values ​​of left-row and right-row characteristic wave velocities corresponding to the inter-cell interface are estimated. The area vector corresponding to the inter-cell interface is determined. Using a preset wave velocity sign separation strategy, the conserved numerical flux passing through the inter-cell interface is determined based on the extreme values ​​of left-row and right-row characteristic wave velocities and the area vector. The component transport term in the numerical flux is explicitly corrected based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

[0046] Therefore, this application first needs to determine the thermodynamic state variables corresponding to the mass fraction of each component in each grid cell of the aircraft grid, and then call the function relationship in the preset thermodynamic database based on the mass fraction to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell. Secondly, it needs to determine the pressure reference value corresponding to the aircraft grid, and then convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value. Finally, it needs to determine the fluid density and normal velocity of each adjacent grid cell in each grid cell interface, based on the local mixed gas constant, local specific heat ratio, and absolute pressure ratio. The intermediate-state pressure and density at the interface of the grid cell are determined by pressure, fluid density, and normal velocity. Based on the distribution of intermediate-state pressure, density, and mass fraction, the extreme values ​​of the left-row and right-row characteristic wave velocities corresponding to the grid cell interface are estimated. Then, the area vector corresponding to the grid cell interface is determined. Using a preset wave velocity sign separation strategy, and based on the extreme values ​​of the left-row and right-row characteristic wave velocities and the area vector, the conserved numerical flux passing through the grid cell interface is determined. Finally, the component transport term in the numerical flux is explicitly corrected based on the grid motion velocity vector corresponding to the aircraft grid to obtain the target inviscid flux. In this way, the efficiency of determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid is improved, thereby enhancing the user experience. Attached Figure Description

[0047] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0048] Figure 1 This is a flowchart of a method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, as disclosed in this application.

[0049] Figure 2 This application discloses a specific method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid.

[0050] Figure 3 This is a schematic diagram comparing the post-shock pressure contour map obtained by different inviscid flux calculation methods disclosed in this application with the baseline pressure contour map.

[0051] Figure 4This is a schematic diagram comparing the wall pressure distribution calculated in this application with other non-viscous formats;

[0052] Figure 5 This is a schematic diagram of the inviscid flux determination device for a multi-component thermally complete gas based on an aircraft grid disclosed in this application.

[0053] Figure 6 This is a structural diagram of an electronic device disclosed in this application. Detailed Implementation

[0054] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0055] Currently, flux splitting schemes are crucial for constructing high-resolution numerical methods in computational fluid dynamics. For simulations of multi-component compressible flows, traditional flux differential splitting methods and accurate Riemann solvers face significant challenges in modeling thermally complete gases. The AUSM series of methods alleviates this problem by separating convective and pressure fluxes, but introduces mass fraction non-conservation errors at the component mixing interface. Furthermore, existing methods often lead to divergence in characteristic velocity estimations when handling extreme conditions due to drastic changes in the gas constant R. Therefore, this application provides a method for determining the inviscid flux of multi-component thermally complete gases based on an aircraft mesh, which improves the efficiency of determining the inviscid flux of multi-component thermally complete gases using an aircraft mesh.

[0056] See Figure 1 As shown, this embodiment of the invention discloses a method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, comprising:

[0057] Step S11: Determine the thermodynamic state variables corresponding to the mass fraction of each component in each grid cell of the aircraft grid, and call the function relationship in the preset thermodynamic database based on the mass fraction to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell using the function relationship.

[0058] In this embodiment, the core of this application lies in achieving a dual improvement in nonlinear stability and physical consistency by introducing a pressure reference value correction mechanism and an adaptive wave velocity estimation strategy. The specific process includes six key steps, each addressing specific shortcomings of existing technologies while maintaining compatibility with industrial-grade CFD code.

[0059] First, this embodiment of the application requires the construction of a thermodynamic parameter field. This is done by calling functions to calculate each element. gas mixture constant Compared with specific heat ratio And the corresponding expression is as follows:

[0060] ;

[0061] ;

[0062] in, This represents the component mass fraction vector for each unit, and the mass fraction vector for the last component is automatically determined by mass conservation constraints.

[0063] Specifically, determining the thermodynamic state variables corresponding to each grid cell in the spacecraft mesh, including the mass fractions of each component, and calling the functional relationships in the preset thermodynamic database based on the mass fractions to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell can include: determining the thermodynamic state variables associated with each grid cell in the spacecraft mesh corresponding to the spacecraft, and calling the first and second functional relationships stored in the preset thermodynamic database based on the mass fractions; the thermodynamic state variables include the mass fractions of each gas component; determining the local mixed gas constant corresponding to the grid cell using the first functional relationship and based on the mass fractions of the grid cell; and then determining the local specific heat ratio corresponding to the grid cell using the second functional relationship and based on the temperature and mass fraction of the current grid cell.

[0064] Step S12: Determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value.

[0065] In this embodiment, the present application requires the introduction of a pressure reference value in the interface calculation. This is to convert the pressure variable into the form of absolute pressure:

[0066] ;

[0067] in, The absolute values ​​of the pressure on the left and right sides of the surface. This represents the relative pressure values ​​on the left and right sides of the surface.

[0068] It is worth mentioning that the above strategy solves the problem of negative pressure values ​​that may occur in traditional relative pressure calculations, making it particularly suitable for flow simulations involving vacuum or near-vacuum regions. The pressure reference value can be input by the user or automatically obtained through a grid data interface. It is also noteworthy that when dealing with scenarios with large pressure variations, such as combustion flow fields, the adaptively adjusted pressure reference value effectively balances the advantages of absolute and relative pressure calculations.

[0069] Specifically, determining the pressure reference value corresponding to the aircraft mesh, and converting the relative pressure values ​​on both sides of the mesh cell interface of each mesh cell into absolute pressure values ​​based on the pressure reference value, may include: determining the pressure reference value corresponding to the aircraft mesh based on the physical characteristics of the flow field, or extracting the pressure reference value corresponding to the aircraft mesh from the aircraft mesh using a preset mesh data interface; the pressure reference value satisfies preset physical constraints; determining the mesh cell interface between each adjacent mesh cell in the aircraft mesh, and determining the first relative pressure value and the second relative pressure value corresponding to the mesh cell interface; superimposing the pressure reference value with the first relative pressure value and the second relative pressure value respectively to obtain the first absolute pressure value and the second absolute pressure value corresponding to the mesh cell interface.

[0070] Step S13: Determine the fluid density and normal velocity of each adjacent grid in each of the grid cell interfaces, and determine the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density and the normal velocity. Estimate the left-row characteristic wave velocity extreme value and the right-row characteristic wave velocity extreme value corresponding to the grid cell interface based on the intermediate state pressure, the intermediate state density and the distribution result of the mass fraction. The intermediate state normal velocity is the velocity determined based on the first normal velocity and the second normal velocity.

[0071] In this embodiment, the characteristic wave velocity needs to be estimated and improved; that is, a dual correction strategy is used to calculate the left and right characteristic velocities. and And the corresponding expression is as follows:

[0072] ;

[0073] ;

[0074] in, , , , .

[0075] Furthermore, Density; For speed; For the speed of sound, and These are the normal velocities on the left and right sides of the face, respectively. and The sound speeds on the left and right sides of the plane are respectively; , and These are intermediate variables for velocity, pressure, and speed of sound, respectively. and These are the absolute pressure values ​​for the left and right sides of the face, respectively. and The densities are on the left and right sides of the face, respectively.

[0076] It is worth mentioning that the above characteristic velocity estimation method introduces geometric mean density. Geometric mean specific heat ratio This approach maintains contact discontinuity resolution while avoiding the non-physical interpretation of wave velocity caused by traditional arithmetic averaging. In particular, the introduction of a pressure reference value enables… The calculation satisfies Due to the physical constraints, this design exhibits significant advantages in handling high-pressure combustion flow fields. For example, in the simulation of turbine blade cooling channels, it can effectively suppress non-physical mixing phenomena caused by pressure oscillations.

[0077] Specifically, determining the fluid density and normal velocity of each adjacent grid cell at the interface of each grid cell, and then determining the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, local specific heat ratio, absolute pressure value, fluid density, and normal velocity, can include: determining the first and second adjacent grid cells corresponding to each cell interface; determining the fluid density and normal velocity corresponding to the first and second adjacent grid cells respectively; then determining the intermediate state pressure corresponding to the cell interface based on the local mixed gas constant, local specific heat ratio, first relative pressure value, second relative pressure value, fluid density, and normal velocity corresponding to the first and second adjacent grid cells respectively; determining the geometric mean density and geometric mean mixed specific heat ratio corresponding to the cell interface based on the mass fraction distribution, intermediate state pressure, absolute pressure value, fluid density, and local specific heat ratio; and determining the intermediate state density and intermediate state sound velocity corresponding to the cell interface based on the geometric mean density and geometric mean mixed specific heat ratio.

[0078] Furthermore, estimating the extreme values ​​of the left-row and right-row characteristic wave velocities corresponding to the grid cell interface based on the distribution results of intermediate state pressure, intermediate state density, and mass fraction can include: determining the first sound velocity and first normal velocity of the first adjacent grid and the second sound velocity and second normal velocity of the second adjacent grid, and determining the distribution results corresponding to each mass fraction; using a preset dual correction strategy and based on the first sound velocity, first normal velocity, second sound velocity, second normal velocity, intermediate state sound velocity, intermediate state normal velocity, and distribution results to estimate the extreme values ​​of the left-row and right-row characteristic wave velocities corresponding to the grid cell interface; the intermediate state normal velocity is the velocity determined based on the first normal velocity and the second normal velocity.

[0079] Step S14: Determine the area vector corresponding to the grid cell interface, and use a preset wave velocity symbol separation strategy and based on the left-row characteristic wave velocity extreme value, the right-row characteristic wave velocity extreme value and the area vector to determine the conserved form of the numerical flux passing through the grid cell interface. Explicitly correct the component transport term in the numerical flux based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

[0080] In this embodiment, the present application requires the construction of a conservation variable based on the gas constant corrected for mass fraction. And the corresponding expression is as follows:

[0081] ;

[0082] ;

[0083] ;

[0084] in, For density-conserving variables, Let x, y, and z be the momentum conservation variables. It is a variable that is conserved for energy; The velocity in the x, y, and z directions; This is the velocity vector.

[0085] Furthermore, it can always Through temperature The component mass fraction is calculated, and the corresponding expression is shown below:

[0086] ;

[0087] in, Let be the specific internal energy function of each component.

[0088] It is worth mentioning that the embodiments of this application have made three improvements to the definition of traditional conserved variables: First, the always able to The calculation introduces independent specific internal energy functions for each component. Secondly, the momentum equation is constructed by explicitly including an area factor, which makes the normal momentum flux... It can accurately match the geometric properties of polyhedral meshes; thirdly, it performs mass fraction weighted reconstruction on the component equations to ensure... The global conservation of energy is achieved. Therefore, the above-mentioned method of constructing conservation variables can more accurately capture changes in chemical potential in multi-component systems compared to the mixed-variable processing of the traditional Roe scheme, especially in the simulation of autoignition in combustion flow fields, thus avoiding prediction errors in ignition delay caused by energy conservation errors.

[0089] Specifically, determining the area vector corresponding to each grid cell interface, and then using a preset wave velocity sign separation strategy and based on the left-row characteristic wave velocity extremum, the right-row characteristic wave velocity extremum, and the area vector to determine the conserved numerical flux passing through the grid cell interface, can include: determining the area vector corresponding to each grid cell interface in the spacecraft grid, then using the preset wave velocity sign separation strategy and based on the left-row characteristic wave velocity extremum and a preset zero value to determine the negative wave velocity, and based on the right-row characteristic wave velocity extremum and a preset zero value to determine the positive wave velocity; correcting the initial gas constant using mass fraction to obtain the target gas constant, and determining the first and second conserved variables corresponding to the grid cell interface based on the target gas constant, then determining the first flux corresponding to the first conserved variable and the second flux corresponding to the second conserved variable; determining the intermediate flux corresponding to the grid cell interface based on the preset flux format, negative wave velocity, positive wave velocity, first conserved variable, second conserved variable, first flux, and second flux, and determining the conserved numerical flux passing through the grid cell interface based on the intermediate flux and the area vector.

[0090] In this embodiment, flux calculation is required. Specifically, the improved HLLE format is used to calculate the interface flux. Its innovation lies in introducing a wave velocity sign separation strategy to obtain the corresponding flux to be processed.

[0091] ;

[0092] Positive and negative wave velocities can be defined as follows:

[0093] ;

[0094] ;

[0095] Finally, through area weighting factors Perform flux scaling to obtain the conserved form of numerical flux:

[0096] ;

[0097] It is worth noting that the above-mentioned processing method exhibits stronger stability when dealing with reverse flow (such as in the recirculation region) compared to the traditional HLLE method. Especially at the asymmetric interfaces of three-dimensional polyhedral meshes, the separate calculation of positive and negative wave velocities effectively avoids non-physical energy transfer during flux mixing. Furthermore, in the flux mixing formula... and The introduction of this item enables the embodiments of this application to maintain sufficient numerical dissipation in low Mach number flows, which is crucial for turbulent mixing simulation in the combustion chamber.

[0098] Furthermore, the embodiments of this application require component transport corrections. Addressing the common issue of component mass fraction conservation in multi-component systems, the embodiments of this application require explicit handling during flux calculation. An actively solved component equation, employing density-velocity-mass fraction coupled flux:

[0099] ;

[0100] in, The speed of the grid movement.

[0101] Understandably, the aforementioned correction eliminates component transport errors caused by non-uniform meshes. In applications involving three-dimensional polyhedral meshes, this correction strategy achieves precise handling of dynamic mesh motion by separating mesh velocity from normal velocity. For example, in simulating rotor-stator interactions, this correction effectively suppresses component mass fraction oscillations caused by mesh deformation. Compared to the passive scalar transport strategy employed in traditional methods, the active correction mechanism of this application maintains conservation while avoiding the computational overhead introduced by additional component limiters.

[0102] Specifically, to obtain the target inviscid flux, the component transport terms in the numerical flux are explicitly corrected based on the grid motion velocity vector corresponding to the spacecraft grid. This can include: determining the current motion state corresponding to the spacecraft grid, determining the grid motion velocity vector corresponding to the spacecraft grid based on the current motion state, and determining the component of the grid motion velocity vector in the normal direction of the grid cell interface based on the grid motion velocity vector and the normal velocity of the grid cell interface; obtaining the component density and component mass fraction corresponding to the numerical flux, and determining the normal velocity based on the normal velocity and the corresponding normal component of the grid motion velocity vector, so as to explicitly correct each component transport term in the numerical flux using the component density, component mass fraction and normal velocity, calculate the corrected component flux corresponding to each component, and then integrate the corrected component flux and the numerical flux to obtain the target inviscid flux.

[0103] In one specific implementation, the program flow corresponding to the embodiment of this application is implemented based on the data interface of the polyhedral mesh structure and the array of conserved variables, and the corresponding flowchart is shown below. Figure 2 As shown: First, in the initialization phase, basic data is obtained through the mesh object, including the surface normal vector array (xfn, yfn, zfn), interface area (area), steady-state control flag (steady), and normal mesh velocity (vgn), used to initialize the thermodynamic parameter field. Second, in the iterative calculation phase, for each interface (i_face from 0 to len), the following operations are performed: obtain the interface adjacent cell indices c1 and c2; extract the interface normal components areax, areay, areaz; copy the original left and right variables to temporary arrays QL and QR; correct the pressure term to absolute pressure form; calculate the left and right mixed gas constants RgasL, RgasR and specific heat ratios gammaL, gammaR; calculate the left and right temperatures TL and TR through the equation of state; calculate the left and right sound velocities cL and cR; construct intermediate state variables u_star, p_star, rho_star, and c_star; estimate the left and right characteristic wave velocities SL and SR and correct outliers; construct the left and right conserved variables WL and WR and fluxes FL and FR; finally, obtain the target inviscid flux array.

[0104] Furthermore, Figure 3 This is a schematic diagram comparing the pressure contour distribution after shock wave calculated with a reference for different inviscid fluxes. The pressure contour distribution calculated by the method proposed in this application is closer to the reference. Figure 4 This is a schematic diagram comparing the wall pressure distribution calculated according to the embodiments of this application with other inviscid methods, where phi is the tangential angle, deg is in degrees, and the unit corresponding to phi / deg is degrees, p is the wall pressure, and p_10 is the pressure after the shock wave. Figure 4 It is evident that the wall pressure obtained by the method proposed in this application embodiment is more accurate than that obtained by the Roe scheme (i.e., an approximate Riemann solver based on characteristic lines) and the AUSMPW+ scheme (i.e., a flux vector splitting scheme).

[0105] As can be seen from the above, the embodiments of this application first need to determine the thermodynamic state variables corresponding to each grid cell in the aircraft grid, including the mass fraction of each component, and then call the function relationship in the preset thermodynamic database based on the mass fraction to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell; secondly, determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value; and thirdly, determine the fluid density and normal velocity of each adjacent grid cell in each grid cell interface to determine the local mixed gas constant, local specific heat ratio, and local specific heat ratio. The intermediate-state pressure and density at the interface of the grid cells are determined by absolute pressure, fluid density, and normal velocity. Based on the distribution of intermediate-state pressure, density, and mass fraction, the extreme values ​​of the left-hand and right-hand characteristic wave velocities corresponding to the grid cell interface are estimated. Then, the area vector corresponding to the grid cell interface is determined. Using a preset wave velocity sign separation strategy, and based on the extreme values ​​of the left-hand and right-hand characteristic wave velocities and the area vector, the conserved numerical flux passing through the grid cell interface is determined. Finally, the component transport term in the numerical flux is explicitly corrected based on the grid motion velocity vector corresponding to the aircraft grid to obtain the target inviscid flux. In this way, the efficiency of determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid is improved, thereby enhancing the user experience.

[0106] Accordingly, see Figure 5 As shown, this application also provides a device for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, comprising:

[0107] The state variable determination module 11 is used to determine the thermodynamic state variables corresponding to each grid cell in the aircraft grid, including the mass fraction corresponding to each component, and to call the function relationship in the preset thermodynamic database based on the mass fraction, so as to use the function relationship to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell;

[0108] The pressure value conversion module 12 is used to determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure value on both sides of the grid cell interface of each grid cell into an absolute pressure value based on the pressure reference value.

[0109] The wave velocity extremum determination module 13 is used to determine the fluid density and normal velocity of each adjacent grid in each of the grid cell interfaces, to determine the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density and the normal velocity, and to estimate the left-row characteristic wave velocity extremum and the right-row characteristic wave velocity extremum corresponding to the grid cell interface based on the intermediate state pressure, the intermediate state density and the distribution results of the mass fraction.

[0110] Inviscid flux generation module 14 is used to determine the area vector corresponding to the grid cell interface, and to determine the conserved form of the numerical flux passing through the grid cell interface based on the left-row characteristic wave velocity extreme value, the right-row characteristic wave velocity extreme value and the area vector using a preset wave velocity sign separation strategy. The module also explicitly corrects the component transport terms in the numerical flux based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

[0111] In some specific embodiments, the state variable determination module 11 may specifically include:

[0112] A thermodynamic state variable determination unit is used to determine the thermodynamic state variables associated with each grid cell in the spacecraft grid corresponding to the spacecraft, and to call the first function relationship and the second function relationship stored in the preset thermodynamic database based on the mass fraction; the thermodynamic state variables include the mass fraction corresponding to each gas component;

[0113] A gas mixture constant determination unit is used to determine the local gas mixture constant corresponding to the grid cell using the first functional relationship and based on the mass fraction corresponding to the grid cell, and then to determine the local specific heat ratio corresponding to the grid cell using the second functional relationship and based on the temperature and mass fraction of the current grid cell.

[0114] In some specific embodiments, the pressure value conversion module 12 may specifically include:

[0115] The pressure reference value determination unit is used to determine the pressure reference value corresponding to the aircraft grid based on the physical characteristics of the flow field, or to extract the pressure reference value corresponding to the aircraft grid from the aircraft grid using a preset grid data interface; the pressure reference value satisfies preset physical constraints.

[0116] The pressure value determination unit is used to determine the grid cell interface between each adjacent grid cell in the aircraft grid, and to determine the first relative pressure value and the second relative pressure value corresponding to the grid cell interface.

[0117] The pressure value superposition unit is used to superimpose the pressure reference value with the first relative pressure value and the second relative pressure value respectively to obtain the first absolute pressure value and the second absolute pressure value corresponding to the grid unit interface.

[0118] In some specific embodiments, the wave velocity extreme value determination module 13 may specifically include:

[0119] An intermediate state pressure determination unit is used to determine the first adjacent grid and the second adjacent grid corresponding to the interface of each unit, to determine the fluid density and normal velocity corresponding to the first adjacent grid and the second adjacent grid respectively, and then to determine the intermediate state pressure corresponding to the interface of the unit based on the local mixed gas constant, the local specific heat ratio, the first relative pressure value, the second relative pressure value, the fluid density and the normal velocity corresponding to the first adjacent grid and the second adjacent grid respectively.

[0120] A density determination unit is used to determine the geometric mean density and geometric mean mixing specific heat ratio corresponding to the unit interface based on the distribution results of the mass fraction, the intermediate state pressure, the absolute pressure value, the fluid density, and the local specific heat ratio.

[0121] The sound velocity determination unit is used to determine the intermediate state density and intermediate state sound velocity corresponding to the unit interface based on the geometric mean density and the geometric mean specific heat ratio.

[0122] In some specific embodiments, the wave velocity extreme value determination module 13 may specifically include:

[0123] The distribution result determination unit is used to determine the first sound velocity and the first normal velocity of the first adjacent grid and the second sound velocity and the second normal velocity of the second adjacent grid, and to determine the distribution result corresponding to each of the mass fractions;

[0124] The characteristic wave velocity extremum determination unit is used to estimate the left-row characteristic wave velocity extremum and the right-row characteristic wave velocity extremum corresponding to the grid cell interface based on the first sound velocity, the first normal velocity, the second sound velocity, the second normal velocity, the intermediate state sound velocity, the intermediate state normal velocity and the distribution result using a preset dual correction strategy; the intermediate state normal velocity is the velocity determined based on the first normal velocity and the second normal velocity.

[0125] In some specific embodiments, the non-viscous flux generation module 14 may specifically include:

[0126] An area vector determination unit is used to determine the area vector corresponding to the interface of each grid cell in the aircraft grid. Then, it uses a preset wave velocity sign separation strategy and determines the negative wave velocity based on the left-row characteristic wave velocity extreme value and the preset zero value, and determines the positive wave velocity based on the right-row characteristic wave velocity extreme value and the preset zero value.

[0127] A gas constant determination unit is used to correct the initial gas constant using the mass fraction to obtain the target gas constant, and to determine the first and second conserved variables corresponding to the interface of the grid cell based on the target gas constant. Then, it determines the first flux corresponding to the first conserved variable and the second flux corresponding to the second conserved variable.

[0128] The numerical flux determination unit is used to determine the intermediate flux corresponding to the grid cell interface based on a preset flux format, the negative wave velocity, the positive wave velocity, the first conserved variable, the second conserved variable, the first flux, and the second flux, and to determine the conserved form of the numerical flux passing through the grid cell interface based on the intermediate flux and the area vector.

[0129] In some specific embodiments, the non-viscous flux generation module 14 may specifically include:

[0130] A grid motion velocity vector determination unit is used to determine the current motion state corresponding to the aircraft grid, to determine the grid motion velocity vector corresponding to the aircraft grid based on the current motion state, and to determine the component of the grid motion velocity vector in the normal direction of the grid cell interface based on the grid motion velocity vector and the normal velocity of the grid cell interface.

[0131] The inviscid flux generation subunit is used to obtain the component density and component mass fraction corresponding to the numerical flux, and to determine the normal velocity based on the normal velocity and the corresponding normal component of the mesh motion velocity vector. The component density, component mass fraction and normal velocity are used to explicitly correct each component transport term in the numerical flux, and the corrected component flux corresponding to each component is calculated. Then the corrected component flux and the numerical flux are integrated to obtain the target inviscid flux.

[0132] Furthermore, embodiments of this application also disclose an electronic device, Figure 6This is a structural diagram of an electronic device 20 according to an exemplary embodiment. The content of the diagram should not be construed as limiting the scope of this application. Specifically, the electronic device 20 may include: at least one processor 21, at least one memory 22, a power supply 23, a communication interface 24, an input / output interface 25, and a communication bus 26. The memory 22 stores a computer program, which is loaded and executed by the processor 21 to implement the relevant steps in the method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid disclosed in any of the foregoing embodiments. Furthermore, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0133] In this embodiment, the power supply 23 is used to provide operating voltage for each hardware device on the electronic device 20; the communication interface 24 can create a data transmission channel between the electronic device 20 and external devices, and the communication protocol it follows can be any communication protocol applicable to the technical solution of this application, and is not specifically limited here; the input / output interface 25 is used to acquire external input data or output data to the outside world, and its specific interface type can be selected according to specific application needs, and is not specifically limited here.

[0134] In addition, the memory 22, as a carrier for resource storage, can be a read-only memory, random access memory, disk or optical disk, etc. The resources stored thereon can include operating system 221, computer program 222, etc., and the storage method can be temporary storage or permanent storage.

[0135] The operating system 221 is used to manage and control the various hardware devices on the electronic device 20 and the computer program 222, which may be Windows Server, Netware, Unix, Linux, etc. In addition to including a computer program capable of performing the method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, which is executed by the electronic device 20 according to any of the foregoing embodiments, the computer program 222 may further include computer programs capable of performing other specific tasks.

[0136] Furthermore, this application also discloses a computer-readable storage medium for storing a computer program; wherein, when executed by a processor, the computer program implements the aforementioned method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid. Specific steps of this method can be found in the corresponding content disclosed in the foregoing embodiments, and will not be repeated here.

[0137] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the apparatus disclosed in the embodiments, since it corresponds to the method disclosed in the embodiments, the description is relatively simple; relevant parts can be referred to in the method section.

[0138] Those skilled in the art will further recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, the components and steps of the various examples have been generally described in terms of functionality in the foregoing description. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0139] The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly by hardware, a software module executed by a processor, or a combination of both. The software module can be located in random access memory (RAM), main memory, read-only memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art.

[0140] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0141] The technical solutions provided in this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, characterized in that, include: The thermodynamic state variables, including the mass fractions of each component, are determined for each grid cell in the aircraft grid. Based on the mass fractions, a function relationship in a preset thermodynamic database is called to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell. Determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value. The fluid density and normal velocity of each adjacent grid in each of the grid cell interfaces are determined. Based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density and the normal velocity, the intermediate state pressure and intermediate state density of the cell interface are determined. Based on the intermediate state pressure, the intermediate state density and the distribution results of the mass fraction, the extreme values ​​of the left-row characteristic wave velocity and the extreme values ​​of the right-row characteristic wave velocity corresponding to the grid cell interface are estimated. The area vector corresponding to the grid cell interface is determined, and a pre-defined wave velocity symbol separation strategy is used to determine the conserved form of the numerical flux passing through the grid cell interface based on the left-row characteristic wave velocity extreme value, the right-row characteristic wave velocity extreme value and the area vector. The component transport term in the numerical flux is explicitly corrected based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

2. The method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid according to claim 1, characterized in that, The process of determining the thermodynamic state variables corresponding to the mass fractions of each component in each grid cell of the spacecraft grid, and calling the functional relationships in a preset thermodynamic database based on the mass fractions to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell using the functional relationships, includes: The thermodynamic state variables associated with each grid cell in the spacecraft grid corresponding to the spacecraft are determined, and the first and second function relationships stored in the preset thermodynamic database are called based on the mass fraction; the thermodynamic state variables include the mass fractions corresponding to each gas component; The local mixed gas constant corresponding to the grid cell is determined by using the first functional relationship and based on the mass fraction corresponding to the grid cell. Then, the local specific heat ratio corresponding to the grid cell is determined by using the second functional relationship and based on the temperature and mass fraction of the current grid cell.

3. The method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid according to claim 1, characterized in that, The step of determining the pressure reference value corresponding to the aircraft grid, and converting the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value, includes: The pressure reference value corresponding to the aircraft grid is determined based on the physical characteristics of the flow field, or the pressure reference value corresponding to the aircraft grid is extracted from the aircraft grid using a preset grid data interface; the pressure reference value satisfies preset physical constraints. The mesh cell interface between each adjacent mesh cell in the aircraft mesh is determined, and the first relative pressure value and the second relative pressure value corresponding to the mesh cell interface are determined. The pressure reference value is superimposed on the first relative pressure value and the second relative pressure value to obtain the first absolute pressure value and the second absolute pressure value corresponding to the grid cell interface.

4. The method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid according to claim 3, characterized in that, The step of determining the fluid density and normal velocity of each adjacent grid cell in each of the aforementioned grid cell interfaces, and determining the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density, and the normal velocity, includes: The first adjacent grid and the second adjacent grid corresponding to each of the unit interfaces are determined, and the fluid density and normal velocity corresponding to the first adjacent grid and the second adjacent grid are determined respectively. Then, based on the local mixed gas constant, the local specific heat ratio, the first relative pressure value, the second relative pressure value, the fluid density and the normal velocity corresponding to the first adjacent grid and the second adjacent grid respectively, the intermediate state pressure corresponding to the unit interface is determined. Based on the mass fraction distribution, the intermediate pressure, the absolute pressure value, the fluid density, and the local specific heat ratio, determine the geometric mean density and geometric mean mixing specific heat ratio corresponding to the unit interface; The intermediate state density and intermediate state sound velocity corresponding to the unit interface are determined based on the geometric mean density and the geometric mean mixing specific heat ratio.

5. The method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid according to claim 4, characterized in that, The estimation of the left-row and right-row characteristic wave velocity extrema corresponding to the grid cell interface based on the distribution results of the intermediate state pressure, the intermediate state density, and the mass fraction includes: Determine the first sound velocity and first normal velocity of the first adjacent grid and the second sound velocity and second normal velocity of the second adjacent grid, and determine the distribution results corresponding to each of the mass fractions; Using a preset dual correction strategy and based on the first sound velocity, the first normal velocity, the second sound velocity, the second normal velocity, the intermediate state sound velocity, the intermediate state normal velocity, and the distribution results, the extreme values ​​of the left-row characteristic wave velocity and the extreme values ​​of the right-row characteristic wave velocity corresponding to the grid cell interface are estimated; the intermediate state normal velocity is the velocity determined based on the first normal velocity and the second normal velocity.

6. The method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid according to claim 1, characterized in that, The step of determining the area vector corresponding to the grid cell interface, and using a preset wave velocity sign separation strategy and based on the left-row characteristic wave velocity extremum, the right-row characteristic wave velocity extremum, and the area vector to determine the conserved form of the numerical flux passing through the grid cell interface, includes: Determine the area vector corresponding to the interface of each grid cell in the aircraft grid, and then use a preset wave velocity sign separation strategy to determine the negative wave velocity based on the left-row characteristic wave velocity extreme value and the preset zero value, and determine the positive wave velocity based on the right-row characteristic wave velocity extreme value and the preset zero value; The initial gas constant is corrected using the mass fraction to obtain the target gas constant. Based on the target gas constant, the first and second conserved variables corresponding to the grid cell interface are determined. Then, the first flux corresponding to the first conserved variable and the second flux corresponding to the second conserved variable are determined. Based on the preset flux format, the negative wave velocity, the positive wave velocity, the first conserved variable, the second conserved variable, the first flux, and the second flux, an intermediate flux corresponding to the grid cell interface is determined, and based on the intermediate flux and the area vector, a numerical flux in the conserved form passing through the grid cell interface is determined.

7. The method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, according to any one of claims 1 to 6, is characterized in that, The explicit correction of the component transport term in the numerical flux based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux includes: Determine the current motion state corresponding to the aircraft mesh, determine the mesh motion velocity vector corresponding to the aircraft mesh based on the current motion state, and determine the component of the mesh motion velocity vector in the normal direction of the mesh cell interface based on the mesh motion velocity vector and the normal velocity of the mesh cell interface. Obtain the component density and component mass fraction corresponding to the numerical flux, and determine the normal velocity based on the normal velocity and the corresponding normal component of the mesh motion velocity vector. Explicitly correct each component transport term in the numerical flux using the component density, component mass fraction, and normal velocity. Calculate the corrected component flux corresponding to each component, and then integrate the corrected component flux with the numerical flux to obtain the target inviscid flux.

8. A device for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid, characterized in that, include: The state variable determination module is used to determine the thermodynamic state variables corresponding to each grid cell in the aircraft grid, including the mass fraction of each component, and to call the function relationship in the preset thermodynamic database based on the mass fraction, so as to use the function relationship to determine the local mixed gas constant and local specific heat ratio corresponding to each grid cell; The pressure value conversion module is used to determine the pressure reference value corresponding to the aircraft grid, and convert the relative pressure values ​​on both sides of the grid cell interface of each grid cell into absolute pressure values ​​based on the pressure reference value. The wave velocity extremum determination module is used to determine the fluid density and normal velocity of each adjacent grid in each of the grid cell interfaces, and to determine the intermediate state pressure and intermediate state density of the cell interface based on the local mixed gas constant, the local specific heat ratio, the absolute pressure value, the fluid density and the normal velocity. Based on the intermediate state pressure, the intermediate state density and the distribution results of the mass fraction, the module estimates the left-row characteristic wave velocity extremum and the right-row characteristic wave velocity extremum corresponding to the grid cell interface. The inviscid flux generation module is used to determine the area vector corresponding to the grid cell interface, and to determine the conserved form of the numerical flux passing through the grid cell interface based on the left-row characteristic wave velocity extreme value, the right-row characteristic wave velocity extreme value and the area vector using a preset wave velocity symbol separation strategy. The module also explicitly corrects the component transport terms in the numerical flux based on the grid motion velocity vector corresponding to the spacecraft grid to obtain the target inviscid flux.

9. An electronic device, characterized in that, include: Memory, used to store computer programs; A processor for executing the computer program to implement the method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, Used to store a computer program, wherein the computer program, when executed by a processor, implements the method for determining the inviscid flux of a multi-component thermally complete gas based on an aircraft grid as described in any one of claims 1 to 7.

Images