Flow field partitioning adaptive simulation method and device for aircraft flow field multi-component gas mixture analysis

Abstract

The application discloses a flow field partition self-adaptive simulation method and device for aircraft flow field multi-component gas mixture analysis, relates to the technical field of aircraft flow field, and comprises the following steps: acquiring current state data corresponding to a current time step of an aircraft flow field; identifying a first region with a chemical reaction process and a second region without the chemical reaction process in the aircraft flow field based on the current state data; performing a flow field parameter calculation strategy including chemical source term calculation on the first region by using a multi-component gas control equation to obtain a distribution result of aerodynamic characteristics corresponding to the current time step; and performing a flow field parameter calculation strategy without chemical source term calculation on the second region by using the multi-component gas control equation to obtain the distribution result of aerodynamic characteristics corresponding to the current time step. The flow field is identified and divided into two regions with different physical properties, namely, the first region with the chemical reaction and the second region without the chemical reaction, and then, different calculation strategies are performed on the two regions.

Description

Technical Field

[0001] This invention relates to the field of aircraft flow field technology, and in particular to a flow field partitioning adaptive simulation method and apparatus for multi-component gas mixing analysis of aircraft flow fields. Background Technology

[0002] In numerical simulations of aircraft flow fields, complex calculation conditions often result in the mixing of various gas components. Particularly at Mach numbers greater than 5, in hypersonic flow, high speeds lead to intense air compression, converting kinetic energy into heat and generating high temperatures. These high temperatures further induce a series of complex physicochemical phenomena in the air components (primarily O2 and N2), including energy excitation and dissociation reactions, producing NO, O, N, and N2. + O2 + This phenomenon, involving various gas components, is also known as the "high-temperature effect" of gases. Furthermore, depending on the flow state and the shape of the aircraft, the various gas components will continue to mix and react during the flow process, ultimately resulting in a completely different mass fraction distribution of each component in the flow field.

[0003] For flow processes involving multi-component chemical reactions, numerical calculations typically involve solving the continuity equation, component transport equation, momentum equation, and energy conservation equation for the gas mixture separately. This approach is essential when a "high-temperature effect" exists in the flow field, as it leads to more accurate calculations and more reliable data on aerodynamic characteristics and aerothermal environment. However, when the aircraft's flight speed is low and the "high-temperature effect" in the flow field is not significant—meaning no chemical reactions occur between the various gas components—solving all four governing equations becomes overly complex, wastes significant computation time, and reduces the efficiency of the numerical simulation.

[0004] Therefore, for the numerical simulation analysis of multi-component mixed gas flow in aircraft flow fields with or without chemical reactions, a simulation analysis method is needed that can take into account both situations, be fast, accurate, and automatically adapt to different situations, so as to improve the applicability and efficiency of the analysis. Summary of the Invention

[0005] In view of this, the purpose of this invention is to provide a flow field partitioning adaptive simulation method and apparatus for multi-component gas mixing analysis of aircraft flow fields. This method is designed for numerical simulation analysis of multi-component gas mixtures in aircraft flow fields, whether or not chemical reactions are present. It requires a simulation analysis method that simultaneously considers both scenarios and can be fast, accurate, and automatically adapt to different conditions, thereby improving its applicability and analysis efficiency. The specific solution is as follows:

[0006] In a first aspect, this application discloses a flow field partitioning adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields, including:

[0007] Obtain the current state data of the aircraft flow field at the current time step;

[0008] Based on the current state data, a first region in the flow field of the aircraft where a chemical reaction process exists and a second region where a chemical reaction process does not exist are identified.

[0009] A flow field parameter calculation strategy including chemical source term calculation is performed on the first region using the multi-component gas control equation to obtain the aerodynamic characteristic distribution results corresponding to the current time step;

[0010] A flow field parameter calculation strategy that does not include chemical source term calculation is performed on the second region using the multi-component gas governing equation to obtain the aerodynamic characteristic distribution results corresponding to the current time step.

[0011] Optionally, obtaining the current state data corresponding to the current time step of the aircraft flow field includes:

[0012] Extract the flow field characteristic parameters corresponding to the current time step from the aerodynamic characteristic distribution results of the aircraft flow field corresponding to the previous time step;

[0013] The flow field temperature and Damköhler values ​​are determined based on the flow field characteristic parameters corresponding to the current time step, so as to obtain the current state data of the aircraft flow field corresponding to the current time step.

[0014] Optionally, determining the flow field temperature value and the Damköhler value based on the flow field characteristic parameters corresponding to the current time step includes:

[0015] The temperature of each flow field region of the aircraft flow field is extracted from the flow field characteristic parameters corresponding to the current time step to obtain the flow field temperature value;

[0016] The Damköhler value is calculated based on the aircraft geometry, flow velocity, and chemical reaction rate parameters in the flow field characteristic parameters corresponding to the current time step.

[0017] Optionally, after obtaining the current state data corresponding to the current time step of the aircraft flow field, the method further includes:

[0018] Determine whether the flow field temperature value of the flow field region in the flow field of the aircraft is greater than a preset temperature threshold to obtain a first determination result;

[0019] The second determination result is obtained by determining whether the Damköhler value of the flow field region in the flow field of the aircraft is greater than a preset flow rate threshold.

[0020] If the first judgment result of the same flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second judgment result is that the Damcohl value is greater than the preset flow rate threshold, then the step of identifying the first region in the flow field of the aircraft containing a chemical reaction process is initiated.

[0021] If the first judgment result for the absence of a common flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second judgment result is that the Damköhler value is greater than the preset flow rate threshold, then it is determined that there is no chemical reaction process in the flow field of the aircraft.

[0022] Optionally, after determining that there is no chemical reaction process in the flow field of the aircraft, the method further includes:

[0023] A flow field parameter calculation strategy is implemented on the aircraft flow field using the single-component gas control equation to obtain the aerodynamic characteristic distribution results corresponding to the current time step.

[0024] Optionally, the governing equation for the single-component gas is:

[0025] ;

[0026] in, Denotes the first conserved variable. , , and They represent Convection flow in three directions , and They represent Viscous flux in three directions, Indicates the incoming Reynolds number, This represents the total density of the gas. Represents the velocity components in the three coordinate directions; It represents the total energy per unit mass of gas.

[0027] Optionally, identifying a first region where a chemical reaction process exists and a second region where no chemical reaction process exists in the aircraft flow field based on the current state data includes:

[0028] The flow field region where the flow field temperature value is greater than the preset temperature threshold and the second judgment result is that the Damköhler value is greater than the preset flow rate threshold is regarded as the first region where a chemical reaction process exists.

[0029] The regions in the flow field of the aircraft other than the first region are considered as the second region where no chemical reaction process occurs.

[0030] Optionally, the governing equation for the multi-component gas is:

[0031] ;

[0032] in, Denotes the second conserved variable. , , and They represent Convection flow in three directions , and They represent Viscous flux in three directions, Indicates the incoming Reynolds number, This represents the total density of the gas. Represents the velocity components in the three coordinate directions; This represents the total energy per unit mass of gas. This represents the density of each component in a multi-component gas. Indicates the chemical source term. , Indicates components The chemical generation source term.

[0033] Optionally, before acquiring the current state data corresponding to the current time step of the aircraft flow field, the method further includes:

[0034] Construct a chemical reaction model library that includes model parameters for various chemical reactions;

[0035] Accordingly, the process of performing the flow field parameter calculation strategy, which includes chemical source term calculation, on the first region using the multi-component gas governing equations also includes:

[0036] The chemical reaction model parameters corresponding to the first region are called from the chemical reaction model library to calculate the chemical source term.

[0037] Secondly, this application discloses a flow field partitioning adaptive simulation device for multi-component gas mixing analysis of aircraft flow fields, comprising:

[0038] The data acquisition module is used to acquire the current state data corresponding to the current time step of the aircraft flow field;

[0039] The region identification module is used to identify, based on the current state data, a first region in the flow field of the aircraft where a chemical reaction process exists and a second region where a chemical reaction process does not exist;

[0040] The first calculation module is used to perform a flow field parameter calculation strategy that includes chemical source term calculation on the first region using the multi-component gas control equation, so as to obtain the aerodynamic characteristic distribution result corresponding to the current time step.

[0041] The second calculation module is used to perform a flow field parameter calculation strategy on the second region without chemical source term calculation using the multi-component gas control equation, so as to obtain the aerodynamic characteristic distribution results corresponding to the current time step.

[0042] As can be seen, this application discloses obtaining the current state data corresponding to the current time step of the aircraft flow field; identifying a first region with chemical reaction processes and a second region without chemical reaction processes in the aircraft flow field based on the current state data; performing a flow field parameter calculation strategy including chemical source term calculation on the first region using the multi-component gas governing equation to obtain the aerodynamic characteristic distribution result corresponding to the current time step; and performing a flow field parameter calculation strategy without chemical source term calculation on the second region using the multi-component gas governing equation to obtain the aerodynamic characteristic distribution result corresponding to the current time step. Thus, based on the real-time flow field state, i.e., the current state data, the flow field is identified and divided into two regions with different physical properties: a first region with chemical reactions and a second region without chemical reactions. Differential calculation strategies are then performed on the two regions: a complete multi-component model including chemical source term calculation is performed on the first region; while a simplified multi-component model without chemical source term calculation is performed on the second region, i.e., only component transport is considered, and chemical reactions are ignored. In the first region where accuracy is required, aerodynamic parameters are calculated accurately by combining high-temperature chemical reactions with the calculation of chemical source terms without sacrificing accuracy. In the second region where no additional complexity is required, the calculation is significantly simplified by disabling the calculation of chemical source terms. The above strategy can respond to changes in the flow field and consider the flow process of hypersonic vehicles with / without chemical reactions. It can determine different data analysis steps according to the actual flow conditions, ensuring the flexibility of the calculation. It can improve the efficiency of the calculation as much as possible while ensuring the accuracy of the calculation, which is conducive to the rapid acquisition of aerodynamic characteristic parameters in the design process of aircraft. Attached Figure Description

[0043] 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.

[0044] Figure 1 This is a flowchart of a flow field partitioning adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields disclosed in this application;

[0045] Figure 2 This application discloses a flowchart of a specific flow field partitioning adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields;

[0046] Figure 3 This application discloses a schematic diagram of a flow field partitioning adaptive simulation device for multi-component gas mixing analysis of aircraft flow fields;

[0047] Figure 4 This is a structural diagram of an electronic device disclosed in this application. Detailed Implementation

[0048] The technical solutions of the embodiments of this application 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 of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0049] In numerical simulations of aircraft flow fields, complex calculation conditions often result in the mixing of various gas components. Particularly at Mach numbers greater than 5, in hypersonic flow, high speeds lead to intense air compression, converting kinetic energy into heat and generating high temperatures. These high temperatures further induce a series of complex physicochemical phenomena in the air components (primarily O2 and N2), including energy excitation and dissociation reactions, producing NO, O, N, and N2. + O2 + This phenomenon, involving various gas components, is also known as the "high-temperature effect" of gases. Furthermore, depending on the flow state and the shape of the aircraft, the various gas components will continue to mix and react during the flow process, ultimately resulting in a completely different mass fraction distribution of each component in the flow field.

[0050] For flow processes involving multi-component chemical reactions, numerical calculations typically involve solving the continuity equation, component transport equation, momentum equation, and energy conservation equation for the gas mixture separately. This approach is essential when a "high-temperature effect" exists in the flow field, as it leads to more accurate calculations and more reliable data on aerodynamic characteristics and aerothermal environment. However, when the aircraft's flight speed is low and the "high-temperature effect" in the flow field is not significant—meaning no chemical reactions occur between the various gas components—solving all four governing equations becomes overly complex, wastes significant computation time, and reduces the efficiency of the numerical simulation.

[0051] Therefore, for the numerical simulation analysis of multi-component mixed gas flow in aircraft flow fields with or without chemical reactions, a simulation analysis method is needed that can take into account both situations, be fast, accurate, and automatically adapt to different situations, so as to improve the applicability and efficiency of the analysis.

[0052] Therefore, this invention provides a flow field partitioning adaptive simulation scheme for multi-component gas mixing analysis of aircraft flow fields. It can perform numerical simulation analysis of multi-component mixed gas flow in aircraft flow fields with or without chemical reactions. There is a need for a simulation analysis method that can take into account both situations and can be fast, accurate and automatically adapt to different situations, thereby improving the applicability and analysis efficiency.

[0053] Reference Figure 1 As shown, this application discloses a flow field partitioning adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields, including:

[0054] Step S11: Obtain the current state data corresponding to the current time step of the aircraft flow field.

[0055] In this embodiment, before obtaining the current state data corresponding to the current time step of the aircraft flow field, the method further includes: constructing a chemical reaction model library that includes model parameters for various chemical reactions. It is understood that for real hypersonic flight, due to the high flight speed, the air around the aircraft is strongly compressed, forming a shock wave. The temperature after the shock wave often reaches thousands or even tens of thousands of K, and the high temperature causes various gas molecules to undergo dissociation, ionization, recombination, and other reaction processes. Therefore, in order to simulate the various chemical reaction processes that occur during flight as realistically as possible in subsequent numerical simulation calculations, it is necessary to construct a chemical reaction model library in advance for possible chemical transformations / reactions during aircraft flight. This model library includes, but is not limited to: component names of various reactants, reaction formulas for each transformation / reaction process, component stoichiometric coefficients, forward and reverse reaction rate coefficients, mole fractions of each component, collision coefficients, physical characteristic parameters, etc. The role of the chemical reaction model library is that, once the characteristic parameters related to the flow field are determined, the chemical reaction processes involved in the flow of the aircraft can be called from the model library through a standardized interface, based on actual conditions such as gas environment type, aircraft surface effects, and thermodynamic temperature conditions. This avoids manually adding chemical reaction model parameters in subsequent calculations and improves the efficiency of calling chemical reaction models.

[0056] In this embodiment, flow field characteristic parameters representing the current time step are extracted from the aerodynamic characteristic distribution results of the aircraft flow field corresponding to the previous time step. Based on these flow field characteristic parameters, the flow field temperature value and the Damcohl value are determined to obtain the current state data of the aircraft flow field at the current time step. Specifically, the temperature of each flow field region of the aircraft flow field is extracted from the flow field characteristic parameters corresponding to the current time step to obtain the flow field temperature value. The Damcohl value is calculated based on the aircraft geometry, flow velocity, and chemical reaction rate parameters in the flow field characteristic parameters corresponding to the current time step. It can be understood that for a flow field calculation request at the current time step, the corresponding flow field characteristic parameters are first extracted from the aerodynamic characteristic distribution results of the aircraft flow field after the flow field calculation was performed at the previous time step, and used as the flow field characteristic parameters for the current time step. The aerodynamic characteristic distribution results include the flow field temperature values ​​of each flow field region of the aircraft flow field. The parameters include Mach number (Ma), pressure (p), flow velocity (U), and component mass fraction (Cs). Then, during high Mach number flow, the characteristic time of the flow is determined. (The geometric dimension L of the aircraft divided by the flow velocity, i.e.) =L / U) and characteristic time of chemical processes The ratio of this characteristic time (which is related to the reaction rate constant, concentration, and temperature) is an important characteristic parameter for measuring whether there is a chemical reaction in the flow field, also known as the Damköhler number. The Damköhler number is calculated as follows:

[0057] ;

[0058] In this embodiment, a preset threshold is first used to determine whether a chemical reaction process has been triggered. The flow field temperature is the primary criterion for this determination. This is because the rate constant of a chemical reaction is calculated using the Arrhenius equation, an exponential formula describing the relationship between the rate constant k and temperature T. Therefore, it is widely used in chemical kinetics and numerical simulations. The specific formula is as follows:

[0059] ;

[0060] in, Represents the reaction rate constant. This indicates the pre-exponential factor (frequency factor). Indicates the temperature index. Indicates the activation energy of the reaction. This represents the gas constant.

[0061] Therefore, in the above process, the temperature threshold is mainly used as the main criterion for judgment, for example: a preset temperature threshold T. limitSetting the temperature to 3000 K implies that a chemical reaction might occur in a region of the flow field where the temperature exceeds 3000 K. However, the presence of a chemical reaction in a flow field cannot be determined solely by temperature. Typically, in high Mach number flows, the Damköhler number is also used to determine the presence of a chemical reaction. The Damköhler number is... Specifically, when the aircraft is at a certain location... When the value is much less than 1, it indicates that the flow rate is much faster than the reaction rate. This means that the components at that location have not yet begun to undergo a chemical reaction (or the reaction is very weak) and are already flowing downstream of the aircraft with the gas. In this case, the chemical reaction can be ignored. Conversely, when... If the value is greater than 1 or approximately equal to 1, then the chemical reaction at this point needs to be considered. In summary, the temperature threshold T in this step... limit and The value serves as a typical criterion for determining whether a chemical reaction exists in the flow field, thereby automatically switching the calculation strategy and improving the efficiency of the calculation.

[0062] In this embodiment, a first judgment result is obtained by determining whether the flow field temperature value of a flow field region in the aircraft flow field is greater than a preset temperature threshold; a second judgment result is obtained by determining whether the Damcohl value of a flow field region in the aircraft flow field is greater than a preset flow rate threshold; if the first judgment result for the existence of the same flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second judgment result is that the Damcohl value is greater than the preset flow rate threshold, then the step of identifying a first region in the aircraft flow field where a chemical reaction process exists is initiated; if the first judgment result for the absence of the same flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second judgment result is that the Damcohl value is greater than the preset flow rate threshold, then it is determined that no chemical reaction process exists in the aircraft flow field. It can be understood that after setting the preset temperature threshold to 3000K and the preset flow rate threshold to 1, the flow field temperature values ​​of each flow field region in the aircraft flow field are judged separately. and Are both greater than 3000K and 1? If one or more flow field regions in the aircraft flow field simultaneously satisfy the flow field temperature values... >3000K and If the temperature is greater than 1, then a chemical reaction process is determined to exist in the aircraft's flow field. If no flow field region in the aircraft's flow field simultaneously satisfies the required flow field temperature value... >3000K and If the value is greater than 1, it is determined that there is no chemical reaction process in the flow field of the aircraft.

[0063] In this embodiment, for the case where there is no chemical reaction process in the aircraft flow field, that is, during the calculation, the entire flow field maintains a consistently low flow velocity and the temperature of the flow field is always less than 3000K, a flow field parameter calculation strategy is performed on the aircraft flow field using a single-component gas governing equation to obtain the aerodynamic characteristic distribution result corresponding to the current time step. Specifically, the gas is considered as a whole, that is, the transport of components and the source terms of chemical reactions are not considered. In this case, the number of equations for flow field calculation is small, so the overall calculation efficiency is high, greatly saving the calculation time. The single-component gas governing equation is:

[0064] ;

[0065] in, Denotes the first conserved variable. , , and They represent Convection flow in three directions , and They represent Viscous flux in three directions, Indicates the incoming Reynolds number, This represents the total density of the gas. Represents the velocity components in the three coordinate directions; It represents the total energy per unit mass of gas.

[0066] Step S12: Based on the current state data, identify the first region in the flow field of the aircraft where a chemical reaction process exists and the second region where a chemical reaction process does not exist.

[0067] In this embodiment, the flow field region where the flow field temperature value is greater than the preset temperature threshold and the second judgment result is that the Damköhler value is greater than the preset flow rate threshold is designated as the first region where a chemical reaction process exists; the other regions in the aircraft flow field besides the first region are designated as the second region where no chemical reaction process exists. It is understood that, for cases where a chemical reaction process is determined to exist in the aircraft flow field, further analysis is conducted on the regions where a chemical reaction process exists and the other regions where no chemical reaction process exists. Based on these differences, a flow field parameter calculation strategy is selected to include or exclude chemical source terms. Specifically, when the aircraft flow field is determined to have a chemical reaction process, the flow field temperature value in the aircraft flow field is... >3000K and The flow field region with a value greater than 1 is divided into the first region, and the other regions are divided into the second region. The first region is the flow field region where chemical reaction processes occur, and the second region is the flow field region where chemical reaction processes do not occur.

[0068] Step S13: Utilize the multi-component gas control equation to perform a flow field parameter calculation strategy that includes chemical source term calculation on the first region, so as to obtain the aerodynamic characteristic distribution result corresponding to the current time step.

[0069] In this embodiment, in the flow field parameter calculation strategy for the first region, the governing equation for the multi-component gas is: ;

[0070] in, Denotes the second conserved variable. , , and They represent Convection flow in three directions , and They represent Viscous flux in three directions, Indicates the incoming Reynolds number, This represents the total density of the gas. Represents the velocity components in the three coordinate directions; This represents the total energy per unit mass of gas. This represents the density of each component in a multi-component gas. Indicates the chemical source term. , Indicates components The chemical generation source term.

[0071] Understandably, as the Mach number of the aircraft increases, the total temperature in the flow field further increases (reaching 3000K or even higher). Components such as O2 and N2 in the flow field undergo chemical processes such as dissociation, ionization, and recombination, resulting in significant changes in the aerodynamic characteristics and aerothermal environment distribution of the entire flow field. For processes involving chemical reactions, the variables involved in calculating the aerodynamic characteristic parameters of the aircraft change, with the addition of the densities of each component of the multi-component gas and chemical source terms. It can be seen that, compared to the governing equations for single-component gases without chemical reactions, processes considering chemical reactions introduce the concepts of multi-component gases and chemical source terms. Therefore, in the solution process, it is necessary to additionally solve the transport equations of the components and the chemical reaction source terms (i.e., the conversion process of matter).

[0072] In this embodiment, during the process of calculating flow field parameters including chemical source terms in the first region using the multi-component gas governing equation, chemical reaction model parameters corresponding to the first region are called from the chemical reaction model library to calculate the chemical source terms. It is understood that, in the analysis of aerodynamic characteristic parameters of flow field regions involving specific chemical reaction processes, based on the gas environment type, aircraft surface effects, and thermodynamic temperature conditions of the first region, the corresponding chemical reaction model parameters are directly called from the pre-built chemical reaction model library without manual addition.

[0073] Step S14: Utilize the multi-component gas governing equations to perform a flow field parameter calculation strategy on the second region that does not include chemical source term calculations, in order to obtain the aerodynamic characteristic distribution results corresponding to the current time step.

[0074] In this embodiment, the flow field parameters of the second region are calculated using the aforementioned multi-component gas governing equations. Specifically, even in the case where chemical reaction processes exist within the aircraft flow field but not in the second region, the transport equations for each component are still solved, i.e., the component densities are analyzed. The evolution process, however, closing the chemical source term in the multi-component gas governing equation, is also about to Setting it to 0 means that the chemical reaction rate is not calculated. Therefore, the unreacted region (second region) still considers transport processes such as component diffusion and convection, but does not update the component changes caused by chemical reactions.

[0075] In this way, in the first region where chemical reactions occur, components are generated or consumed due to the reaction, and these components diffuse to the second region through flow. If the flow field in the second region is calculated using single-component gas governing equations, the spatial distribution and evolution of component concentrations cannot be captured, leading to discontinuous component transport and affecting the physical consistency and computational accuracy of the entire flow field. Therefore, a multi-component framework is maintained throughout the computational domain of the aircraft flow field where chemical reactions occur, with dynamic switching between reactive and non-reactive regions achieved only by calculating source terms. Thus, the unified coupled framework simultaneously accommodates both states, achieving repeatability in both process and code. The calculations for the first and second regions are executed in parallel within the same coupled solution framework, which can handle both multi-component governing equations containing and without chemical source terms.

[0076] In this embodiment, the division of the first and second regions, and the calculation strategies for each region, including or excluding chemical source terms, are dynamically updated during the flow field iteration at each time step. Specifically, at each time step, the ranges of the first and second regions are re-identified and updated based on the flow field temperature and Damköhler values ​​of the current time step, and the calculation strategies executed for each region are adjusted accordingly. It is important to note that the calculations for the first and second regions are performed in parallel within the same coupled solution framework, which can simultaneously handle multi-component control equations including and excluding chemical source terms. That is, the calculation strategies can be dynamically and flexibly switched between different regions of the same flow field, and between different time steps within the same region, based on real-time criteria.

[0077] As can be seen, this application discloses obtaining the current state data corresponding to the current time step of the aircraft flow field; identifying a first region with chemical reaction processes and a second region without chemical reaction processes in the aircraft flow field based on the current state data; performing a flow field parameter calculation strategy including chemical source term calculation on the first region using the multi-component gas governing equation to obtain the aerodynamic characteristic distribution result corresponding to the current time step; and performing a flow field parameter calculation strategy without chemical source term calculation on the second region using the multi-component gas governing equation to obtain the aerodynamic characteristic distribution result corresponding to the current time step. Thus, based on the real-time flow field state, i.e., the current state data, the flow field is identified and divided into two regions with different physical properties: a first region with chemical reactions and a second region without chemical reactions. Differential calculation strategies are then performed on the two regions: a complete multi-component model including chemical source term calculation is performed on the first region; while a simplified multi-component model without chemical source term calculation is performed on the second region, i.e., only component transport is considered, and chemical reactions are ignored. In the first region where accuracy is required, aerodynamic parameters are calculated accurately by combining high-temperature chemical reactions with the calculation of chemical source terms without sacrificing accuracy. In the second region where no additional complexity is required, the calculation is significantly simplified by disabling the calculation of chemical source terms. The above strategy can respond to changes in the flow field and consider the flow process of hypersonic vehicles with / without chemical reactions. It can determine different data analysis steps according to the actual flow conditions, ensuring the flexibility of the calculation. It can improve the efficiency of the calculation as much as possible while ensuring the accuracy of the calculation, which is conducive to the rapid acquisition of aerodynamic characteristic parameters in the design process of aircraft.

[0078] like Figure 2As shown, the present invention also discloses a specific adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields, comprising: within a time step, given the current flow field state, firstly determining whether a chemical reaction exists at a certain point in the flow field, the determination is based on two physical criteria: whether the local temperature exceeds a preset threshold and whether the Damköhler value exceeds a preset flow rate threshold, and based on the above determination results, dividing the process into two main branches.

[0079] If no reaction is determined, the single-component gas governing equation (calorimetric complete gas model) is used for calculation. This path corresponds to a lower flow field temperature and a chemical reaction rate that is much slower than the flow rate. The region is <1). In this model, the gas is treated as a single-component complete gas, and the governing equations do not include component transport and chemical reaction source terms, thus greatly simplifying the calculation and improving efficiency.

[0080] If a reaction is detected, an internal adaptive loop is initiated. This branch corresponds to regions with high temperatures and significant chemical reactions. Its core principle is that instead of applying the same complex model to the entire region, a secondary partitioning process is performed: within the identified reactive regions, more refined local conditions (sub-region temperature gradient or instantaneous...) are considered. The diagram further distinguishes between computational units that are locally unreacted and those that consider chemical reaction source terms. A double-headed arrow in the diagram indicates that these two types of units can be interchanged. This means that as the flow field evolves, the computational strategy for the same spatial location can dynamically and flexibly switch between calculating chemical source terms and ignoring them at different time steps or due to sudden changes in local conditions at different time steps. Ultimately, regardless of the path taken, the computational results for all regions are aggregated and collectively advanced to the flow field iteration step, completing the solution for the current time step and providing updated flow field data for the next time step. This flexible switching approach, compared to the original model where the entire flow field required calculating source terms, maximizes computational efficiency.

[0081] Therefore, based on the aerodynamic characteristic distribution results such as density, velocity, pressure, temperature, and mass fraction of gas components in the obtained flow field, iterative calculations of the flow field are completed. After each iteration step, the presence of chemical reaction processes in the flow field is determined by the flow field judgment criteria, thereby determining the calculation method to be used in the next iteration step. This provides reliable numerical calculation results for engineering design, scientific research analysis, and system optimization, and ultimately improves the flow field calculation efficiency as much as possible while ensuring calculation accuracy.

[0082] Reference Figure 3 As shown, the present invention also discloses a flow field partitioning adaptive simulation device for multi-component gas mixing analysis of aircraft flow fields, comprising:

[0083] Data acquisition module 11 is used to acquire the current state data corresponding to the current time step of the aircraft flow field;

[0084] The region identification module 12 is used to identify, based on the current state data, a first region in the flow field of the aircraft where a chemical reaction process exists and a second region where a chemical reaction process does not exist;

[0085] The first calculation module 13 is used to perform a flow field parameter calculation strategy including chemical source term calculation on the first region using the multi-component gas control equation, so as to obtain the aerodynamic characteristic distribution result corresponding to the current time step.

[0086] The second calculation module 14 is used to perform a flow field parameter calculation strategy that does not include chemical source term calculation on the second region using the multi-component gas control equation, so as to obtain the aerodynamic characteristic distribution result corresponding to the current time step.

[0087] It is evident that the region identification module, the first calculation module, and the second calculation module enable the complex flow field partitioning adaptive logic to be executed efficiently, stably, and repeatedly, balancing accuracy and efficiency, and also improving the reliability of the device when integrated into existing computational fluid dynamics software or simulation systems.

[0088] Furthermore, embodiments of this application also disclose an electronic device, Figure 4 This 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.

[0089] Figure 4 This is a schematic diagram of the structure of an electronic device 20 provided in an embodiment 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 flow field partitioning adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields disclosed in any of the foregoing embodiments. Alternatively, the electronic device 20 in this embodiment may specifically be an electronic computer.

[0090] 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.

[0091] The processor 21 may include one or more processing cores, such as a quad-core processor or an octa-core processor. The processor 21 may be implemented using at least one hardware form selected from DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 21 may also include a main processor and a coprocessor. The main processor, also known as a CPU (Central Processing Unit), is used to process data in the wake-up state; the coprocessor is a low-power processor used to process data in the standby state. In some embodiments, the processor 21 may integrate a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the screen. In some embodiments, the processor 21 may also include an AI (Artificial Intelligence) processor, which is used to handle computational operations related to machine learning.

[0092] 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.

[0093] The operating system 221 manages and controls the various hardware devices and computer programs 222 on the electronic device 20 to enable the processor 21 to perform calculations and processing on the massive amounts of data 223 in the memory 22. It can be Windows Server, Netware, Unix, Linux, etc. The computer program 222, in addition to including a computer program capable of performing the flow field partitioning adaptive simulation method for multi-component gas mixing analysis of an aircraft flow field, which is executed by the electronic device 20 according to any of the aforementioned embodiments, may further include computer programs capable of performing other specific tasks. The data 223 may include data received by the electronic device from external devices, as well as data collected by its own input / output interface 25.

[0094] Furthermore, this application also discloses a computer-readable storage medium for storing a computer program; wherein, when the computer program is executed by a processor, it implements the aforementioned adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields. Specific steps of this method can be found in the corresponding content disclosed in the foregoing embodiments, and will not be repeated here.

[0095] 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.

[0096] 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. The steps of the methods or algorithms described in conjunction with the embodiments disclosed herein can be implemented directly in hardware, software modules executed by a processor, or a combination of both. The software module may be located in random access memory (RAM), memory, read-only memory (ROM), electrically programmable read-only memory (EPROM), electrically erasable programmable read-only memory (EEPROM), registers, hard disks, removable disks, CD-ROMs (Compact Disc-Read Only Memory), or any other form of storage medium known in the art.

[0097] 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.

[0098] The solution provided by the present invention has been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only for helping to understand the method and core ideas of the present invention. 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 the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A flow field partitioning adaptive simulation method for multi-component gas mixing analysis of aircraft flow fields, characterized in that, include: Obtain the current state data of the aircraft flow field at the current time step; Based on the current state data, a first region in the flow field of the aircraft where a chemical reaction process exists and a second region where a chemical reaction process does not exist are identified. A flow field parameter calculation strategy including chemical source term calculation is performed on the first region using the multi-component gas control equation to obtain the aerodynamic characteristic distribution results corresponding to the current time step; A flow field parameter calculation strategy that does not include chemical source term calculation is performed on the second region using the multi-component gas governing equation to obtain the aerodynamic characteristic distribution results corresponding to the current time step; The acquisition of the current state data corresponding to the current time step of the aircraft flow field includes: Extract the flow field characteristic parameters corresponding to the current time step from the aerodynamic characteristic distribution results of the aircraft flow field corresponding to the previous time step; The flow field temperature and Damköhler values ​​are determined based on the flow field characteristic parameters corresponding to the current time step, so as to obtain the current state data of the aircraft flow field corresponding to the current time step. After obtaining the current state data corresponding to the current time step of the aircraft flow field, the method further includes: Determine whether the flow field temperature value of the flow field region in the flow field of the aircraft is greater than a preset temperature threshold to obtain a first determination result; The second determination result is obtained by determining whether the Damköhler value of the flow field region in the flow field of the aircraft is greater than a preset flow rate threshold. If the first judgment result of the same flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second judgment result is that the Damcohl value is greater than the preset flow rate threshold, then the step of identifying the first region in the flow field of the aircraft containing a chemical reaction process is initiated. If the first judgment result for the absence of a common flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second judgment result is that the Damköhler value is greater than the preset flow rate threshold, then it is determined that there is no chemical reaction process in the flow field of the aircraft.

2. The flow field zoned adaptive simulation method for aircraft flow field multi-component gas mixture analysis of claim 1, wherein, The determination of the flow field temperature value and the Damköhler value based on the flow field characteristic parameters corresponding to the current time step includes: The temperature of each flow field region of the aircraft flow field is extracted from the flow field characteristic parameters corresponding to the current time step to obtain the flow field temperature value; The Damköhler value is calculated based on the aircraft geometry, flow velocity, and chemical reaction rate parameters in the flow field characteristic parameters corresponding to the current time step.

3. The flow field zoned adaptive simulation method for aircraft flow field multi- component gas mixture analysis of claim 1, wherein, After determining that there is no chemical reaction process in the flow field of the aircraft, the method further includes: A flow field parameter calculation strategy is implemented on the aircraft flow field using the single-component gas control equation to obtain the aerodynamic characteristic distribution results corresponding to the current time step.

4. The flow field zoned adaptive simulation method for aircraft flow field multi-component gas mixture analysis of claim 3, wherein, The governing equation for the single-component gas is: ； in, Denotes the first conserved variable. , , and They represent Convection flow in three directions , and They represent Viscous flux in three directions, Indicates the incoming Reynolds number, This represents the total density of the gas. Represents the velocity components in the three coordinate directions; It represents the total energy per unit mass of gas.

5. The flow field zoned adaptive simulation method for aircraft flow field multi-component gas mixture analysis of claim 1, wherein, The process of identifying a first region in the aircraft flow field where a chemical reaction process exists and a second region where a chemical reaction process does not exist based on the current state data includes: The flow field region where the flow field temperature value is greater than the preset temperature threshold and the second judgment result is that the Damköhler value is greater than the preset flow rate threshold is regarded as the first region where a chemical reaction process exists. The regions in the flow field of the aircraft other than the first region are considered as the second region where no chemical reaction process occurs.

6. The flow field zoned adaptive simulation method for aircraft flow field multi-component gas mixture analysis of claim 1, wherein, The governing equation for the multi-component gas is: ； in, Denotes the second conserved variable. , , and They represent Convection flow in three directions , and They represent Viscous flux in three directions, Indicates the incoming Reynolds number, This represents the total density of the gas. Represents the velocity components in the three coordinate directions; This represents the total energy per unit mass of gas. This represents the density of each component in a multi-component gas. Indicates the chemical source term. , Indicates components The chemical generation source term.

7. The flow field zoned adaptive simulation method for aircraft flow field multi-component gas mixture analysis of any of claims 1 to 6, wherein, Before acquiring the current state data corresponding to the current time step of the aircraft flow field, the method further includes: Construct a chemical reaction model library that includes model parameters for various chemical reactions; Accordingly, the process of performing the flow field parameter calculation strategy, which includes chemical source term calculation, on the first region using the multi-component gas governing equations also includes: The chemical reaction model parameters corresponding to the first region are called from the chemical reaction model library to calculate the chemical source term.

8. A flow field partitioning adaptive simulation device for multi-component gas mixing analysis of aircraft flow fields, characterized in that, include: The data acquisition module is used to acquire the current state data corresponding to the current time step of the aircraft flow field; The region identification module is used to identify, based on the current state data, a first region in the flow field of the aircraft where a chemical reaction process exists and a second region where a chemical reaction process does not exist; The first calculation module is used to perform a flow field parameter calculation strategy that includes chemical source term calculation on the first region using the multi-component gas control equation, so as to obtain the aerodynamic characteristic distribution result corresponding to the current time step. The second calculation module is used to perform a flow field parameter calculation strategy that does not include chemical source term calculation on the second region using the multi-component gas control equation, so as to obtain the aerodynamic characteristic distribution result corresponding to the current time step; The data acquisition module is specifically used to extract flow field characteristic parameters corresponding to the current time step from the aerodynamic characteristic distribution results of the aircraft flow field corresponding to the previous time step; and to determine the flow field temperature value and the Damköhler value based on the flow field characteristic parameters corresponding to the current time step, so as to obtain the current state data of the aircraft flow field corresponding to the current time step. The device further includes: determining whether the flow field temperature value of a flow field region in the aircraft flow field is greater than a preset temperature threshold to obtain a first determination result; determining whether the Damcohl value of a flow field region in the aircraft flow field is greater than a preset flow rate threshold to obtain a second determination result; if the first determination result for the existence of the same flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second determination result is that the Damcohl value is greater than the preset flow rate threshold, then the step of identifying a first region in the aircraft flow field where a chemical reaction process exists is initiated; if the first determination result for the existence of the same flow field region is that the flow field temperature value is greater than the preset temperature threshold, and the second determination result is that the Damcohl value is greater than the preset flow rate threshold, then it is determined that there is no chemical reaction process in the aircraft flow field.

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