Numerical simulation methods, apparatus, equipment, and media for ignition and combustion of aluminum particles.

Abstract

This application belongs to the field of numerical simulation technology, and relates to a numerical simulation method, apparatus, equipment, and medium for the ignition and combustion of aluminum particles. The method includes: obtaining control variables based on the aluminum particle combustion process, constructing a gas-phase control variable transport equation; considering the change in total gas-phase enthalpy, changing the temperatures on the oxidizer and fuel sides, applying a correction factor to the chemical reaction source term in the gas-phase temperature equation of a one-dimensional opposed flame, and solving the one-dimensional gas-phase opposed flame according to the gas-phase reaction mechanism to obtain a steady-state numerical solution, establishing a four-dimensional chemical reaction database; initializing the flow field, solving the gas-phase control variable transport equation to obtain the current values ​​of the control variables, interpolating and looking up tables in the four-dimensional chemical reaction database to obtain the gas-phase state parameters; when the gas-phase state parameters reach preset conditions, obtaining the thermophysical quantities of the gas phase in the combustion chamber of a solid-fuel propellant missile. This method can improve the speed of numerical simulation.

Description

Technical Field

[0001] This application relates to the field of numerical simulation technology, and in particular to a numerical simulation method, apparatus, equipment and medium for the ignition and combustion of aluminum particles. Background Technology

[0002] Solid-fuel propellant missiles are widely used on the military battlefield due to their advantages such as simple structure, high reliability, and rapid combat response. The exothermic combustion process of solid propellants largely determines engine performance, and therefore has always been a research hotspot. Among various types of solid propellants, metal additives, represented by aluminum, have always played an important role. Adding aluminum particles can not only improve the energy density of the propellant and the specific impulse of the engine, but the condensed phase substances produced by its combustion can also suppress unstable combustion in the propulsion system.

[0003] Numerical simulation, as an important tool for studying the ignition and combustion process of aluminum particles in the combustion chamber of solid-fueled missiles, can obtain the variation laws of particle state parameters and surrounding gas flow field state parameters during the combustion process. Compared with experimental observation methods, it has advantages such as shorter research cycle and lower cost. Currently, considering detailed chemical reaction mechanisms in numerical simulation requires solving a large number of coupled partial differential equations, which results in slow calculation speed. Therefore, this method is impractical for research on industrial-scale combustion chambers.

[0004] To reduce the computational burden of solving chemical reaction mechanisms, methods such as simplified reaction mechanisms, total reaction, and chemical tabulation are commonly employed. The first two methods, by ignoring or partially simplifying the chemical reaction mechanisms, lead to reduced computational accuracy and cannot accurately predict unsteady-state processes such as ignition, flameout, and flame stabilization within solid fuel combustion chambers. Chemical tabulation, through preprocessing, stores scalar values ​​describing the chemical reaction, such as temperature and component concentration, in tables. In subsequent numerical simulations, only the transport equations of the control variables need to be solved, and information such as temperature can be obtained by interpolating the control variables and looking up the tables, without needing to solve the detailed chemical reaction mechanisms. Therefore, the computational cost of numerical simulations can be significantly reduced when considering detailed chemical reaction kinetics. Chemical tabulation was initially applied to the study of gas-phase combustion and has since been extended to spray combustion. Compared to spray combustion, the ignition and combustion process of aluminum particles is more complex, including complex surface chemical reactions and intense heat radiation losses, making traditional chemical tabulation unsuitable for the simulation of solid-fuel missile combustion chambers containing aluminum particles. Summary of the Invention

[0005] Therefore, it is necessary to provide a numerical simulation method, apparatus, equipment, and medium for the ignition and combustion of aluminum particles to address the above-mentioned technical problems. This method can improve the calculation speed of the flow field within a solid fuel missile propulsion system and increase the speed of numerical simulation, while taking into account detailed chemical reaction mechanisms.

[0006] Numerical simulation methods for the ignition and combustion of aluminum particles include:

[0007] Based on the atomic mixing state, thermal state, and reaction process of the gas phase during aluminum particle combustion, the control variables of the aluminum particle combustion process are obtained, and the gas phase control variable transport equation for aluminum particle combustion in air is constructed.

[0008] Considering the change in total enthalpy in the gas phase, the temperatures on the oxidizer side and the fuel side are changed, and a correction factor is applied to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame. Based on the gas phase reaction mechanism, the one-dimensional gas phase opposed flame is solved to obtain the steady-state numerical solution. Through coordinate transformation, a four-dimensional chemical reaction database in the control variable space is established.

[0009] Flow field initialization: Obtain the initial gas phase thermophysical quantities of the initial flow field; Solve the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable;

[0010] Based on the current values ​​of the control variables, interpolation and table lookup are performed on the four-dimensional chemical reaction database to obtain the state parameters of the gas phase;

[0011] When the state parameters of the gas phase reach the preset conditions, the current gas phase thermophysical quantity is obtained, and the current gas phase thermophysical quantity is used as the thermophysical quantity of the gas phase in the combustion chamber of the solid fuel-powered missile.

[0012] In one embodiment, the control variables for the aluminum particle combustion process include, based on the atomic mixing state of the gas phase, the thermal state of the gas phase, and the reaction progress, as follows:

[0013] If we consider the Al atoms in the gas phase as atoms from the fuel side, and the O and N atoms in the gas phase as atoms from the oxidant side, then the atomic composition of the oxidant side can be uniquely determined by X:

[0014]

[0015] In the formula, X represents the mass fraction of oxygen atoms in the gas phase, and Y represents the mass fraction of oxygen atoms in the gas phase. O Y represents the mass fraction of O atoms. N The mass fraction of N atoms;

[0016] If the fuel-side component is Al atoms, then the mixing fraction Z, which describes the mixing process of fuel atoms and oxidant atoms, can be expressed as:

[0017]

[0018] In the formula, Z represents the mass fraction of aluminum atoms in the gas phase, and Y... Al Y represents the mass fraction of Al atoms. Al,OXY represents the mass fraction of aluminum atoms on the oxidant side. Al,f Z represents the mass fraction of aluminum atoms on the fuel side; where Z = 1 corresponds to the fuel side and Z = 0 corresponds to the oxidant side.

[0019] When determining the thermal state of the gas phase, i.e., its total enthalpy, a normalized total enthalpy is introduced:

[0020]

[0021] In the formula, h norm Here, h is the normalized total enthalpy, and h is the total enthalpy obtained by solving the gas energy equation. min (Z,X) represents the minimum total enthalpy in the chemical reaction database corresponding to the current mixed state, h max (Z,X) represents the maximum total enthalpy in the chemical reaction database corresponding to the current mixed state;

[0022] From the perspective of reaction process, the gas phase reaction state during the combustion of aluminum particles is modeled, and the reaction progress variable is introduced:

[0023]

[0024] In the formula, Y c As a variable representing the progress of the response, The mass fraction of Al2O3(1) Y represents the mass fraction of Al2O. AlO The mass fraction of AlO;

[0025] The reaction progress variable is normalized to obtain the normalized reaction progress variable:

[0026]

[0027] In the formula, C is the normalized reaction progress variable, and Y c min (Z,X,h norm Y represents the minimum value of the unnormalized reaction progress variable corresponding to the current state. c max (Z,X,h norm ) represents the maximum value of the unnormalized reaction progress variable corresponding to the current state;

[0028] With X, Z, h norm C and C are the control variables for the aluminum particle combustion process.

[0029] In one embodiment, constructing the gas-phase controlled variable transport equation for the combustion of aluminum particles in air includes:

[0030] Based on the control variables, the gas-phase control variable transport equation for the combustion of gaseous aluminum particles in air under laminar flow conditions is constructed:

[0031]

[0032]

[0033]

[0034]

[0035] In the formula, ρ is density, t is time, and u j Let x be the component of the gas phase velocity in the j-direction. j For the j-direction, D Z The second variable is the diffusion coefficient, x i For the i direction, D is the source term for the second variable. X The diffusion coefficient is the first variable. For the source term of the first variable, The diffusion coefficient is the reaction progress variable. Here, α is the source term for the reaction progress variable, and α is the thermal diffusivity. This is the total enthalpy source term in the gas phase due to interphase heat transfer. This is the total enthalpy source term in the gas phase caused by radiative heat transfer.

[0036] In one embodiment, changing the temperature on the oxidant side and the fuel side includes:

[0037] Inlet temperature on the oxidant side:

[0038] T ox =T Air,min +h norm *(T Air,max -T Air,min (14)

[0039] In the formula, T ox T is the inlet temperature on the oxidant side. Air,min To calculate the minimum oxidant inlet temperature within the domain, T Air,max To calculate the maximum value of the oxidant inlet temperature within the domain;

[0040] Fuel-side inlet temperature:

[0041] T f =T Al,min +h norm *(T Al,max -T Al,min (15)

[0042] In the formula, T f T represents the inlet temperature on the fuel side. Al,minTo calculate the maximum inlet temperature of vaporized aluminum within the domain, T Al,min This is to calculate the maximum inlet temperature of vaporized aluminum within the domain.

[0043] In one embodiment, applying a correction factor to the chemical reaction source term in the gas-phase temperature equation for a one-dimensional opposed flame includes:

[0044] Vapor phase temperature equation:

[0045]

[0046] In the formula, For mass flow rate, c ρ ρ is specific heat, T is temperature, z is a one-dimensional coordinate, N is the number of components, λ is thermal conductivity, k is the number of components, and c is the number of components. pk Let j be the specific heat of component k. k,z f is the mass diffusion flux of component k in the z-direction. L h is the correction factor. k For total enthalpy, W represents the chemical reaction rate. k Let be the mass diffusion flux of molar mass in the z-direction;

[0047] The correction factor is assigned the following values:

[0048] f L =f L,min +h norm *(1-f L,min (16)

[0049] In the formula, f L,min This is the lower limit of the correction factor, greater than zero and less than one.

[0050] In one embodiment, solving for a one-dimensional gas-pitch flame to obtain a steady-state numerical solution includes:

[0051] The numerical solution of the counter-current flame under the initial inlet mass flow rate condition is used as the initial solution;

[0052] Based on the initial solution, the mass flow rate of the counter-current flame is gradually increased until the highest flame temperature does not exceed the maximum value of the two inlet temperatures of the counter-current flame, thus obtaining the steady-state numerical solution.

[0053] In one embodiment, interpolating and looking up a table in a four-dimensional chemical reaction database based on the current value of the control variable includes:

[0054] For control variables X and h respectively norm Linear interpolation is used to interpolate multiple data points, and numerical solutions are obtained for the corresponding one-dimensional counter-flame in physical space.

[0055] Based on the control variables Z and C, the numerical solution of the counter-flame obtained in the physical space is transformed to the corresponding space to obtain multiple chemical reaction databases;

[0056] By linearly interpolating multiple data points for each chemical reaction database with respect to control variables Z and C, a four-dimensional chemical reaction database is obtained, and the state parameters of the gas phase are obtained.

[0057] A numerical simulation device for ignition and combustion of aluminum particles includes:

[0058] The modeling module is used to obtain the control variables of the aluminum particle combustion process based on the atomic mixing state, thermal state and reaction process of the gas phase during aluminum particle combustion, and to construct the gas phase control variable transport equation for aluminum particle combustion in air.

[0059] The database construction module is used to consider the change in total enthalpy of the gas phase, change the temperature on the oxidizer side and the fuel side, apply a correction factor to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame, and solve the one-dimensional gas-phase opposed flame according to the gas phase reaction mechanism to obtain the steady-state numerical solution; and establish a four-dimensional chemical reaction database in the control variable space through coordinate transformation.

[0060] The solver module is used for flow field initialization, obtaining the initial gas phase thermophysical quantities of the initial flow field, and solving the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable;

[0061] The lookup module is used to interpolate and look up the table in the four-dimensional chemical reaction database based on the current value of the control variable to obtain the state parameters of the gas phase;

[0062] The output module is used to obtain the current gas phase thermophysical quantity when the gas phase state parameters reach the preset conditions, and to use the current gas phase thermophysical quantity as the thermophysical quantity of the gas phase in the combustion chamber of a solid fuel-powered missile.

[0063] A computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program performing the following steps:

[0064] Based on the atomic mixing state, thermal state, and reaction process of the gas phase during aluminum particle combustion, the control variables of the aluminum particle combustion process are obtained, and the gas phase control variable transport equation for aluminum particle combustion in air is constructed.

[0065] Considering the change in total enthalpy in the gas phase, the temperatures on the oxidizer side and the fuel side are changed, and a correction factor is applied to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame. Based on the gas phase reaction mechanism, the one-dimensional gas phase opposed flame is solved to obtain the steady-state numerical solution. Through coordinate transformation, a four-dimensional chemical reaction database in the control variable space is established.

[0066] Flow field initialization: Obtain the initial gas phase thermophysical quantities of the initial flow field; Solve the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable;

[0067] Based on the current values ​​of the control variables, interpolation and table lookup are performed on the four-dimensional chemical reaction database to obtain the state parameters of the gas phase;

[0068] When the state parameters of the gas phase reach the preset conditions, the current gas phase thermophysical quantity is obtained, and the current gas phase thermophysical quantity is used as the thermophysical quantity of the gas phase in the combustion chamber of the solid fuel-powered missile.

[0069] A computer-readable storage medium having a computer program stored thereon, the computer program performing the following steps when executed by a processor:

[0070] Based on the atomic mixing state, thermal state, and reaction process of the gas phase during aluminum particle combustion, the control variables of the aluminum particle combustion process are obtained, and the gas phase control variable transport equation for aluminum particle combustion in air is constructed.

[0071] Considering the change in total enthalpy in the gas phase, the temperatures on the oxidizer side and the fuel side are changed, and a correction factor is applied to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame. Based on the gas phase reaction mechanism, the one-dimensional gas phase opposed flame is solved to obtain the steady-state numerical solution. Through coordinate transformation, a four-dimensional chemical reaction database in the control variable space is established.

[0072] Flow field initialization: Obtain the initial gas phase thermophysical quantities of the initial flow field; Solve the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable;

[0073] Based on the current values ​​of the control variables, interpolation and table lookup are performed on the four-dimensional chemical reaction database to obtain the state parameters of the gas phase;

[0074] When the state parameters of the gas phase reach the preset conditions, the current gas phase thermophysical quantity is obtained, and the current gas phase thermophysical quantity is used as the thermophysical quantity of the gas phase in the combustion chamber of the solid fuel-powered missile.

[0075] The above-mentioned numerical simulation method, apparatus, equipment and medium for aluminum particle ignition and combustion, establish chemical table model for computational fluid dynamics research on aluminum particle ignition and combustion, design numerical simulation method for aluminum particle ignition and combustion in air, establish gas phase control equations for chemical table model, and establish chemical reaction database for aluminum particle combustion in air by solving one-dimensional gas phase opposing flame, and conduct numerical simulation based on this, thereby improving computational efficiency. Attached Figure Description

[0076] Figure 1This is an application scenario diagram of the numerical simulation method for ignition and combustion of aluminum particles in one embodiment;

[0077] Figure 2 This is a flowchart illustrating a numerical simulation method for the ignition and combustion of aluminum particles in one embodiment.

[0078] Figure 3 This is a schematic diagram of a chemical table model for the ignition and combustion of aluminum particles in air in one embodiment;

[0079] Figure 4 This is a schematic diagram of a one-dimensional gas-paired opposing flame in one embodiment;

[0080] Figure 5 Here is a flowchart of the one-dimensional counter-flame solution in one embodiment;

[0081] Figure 6 This is a flowchart of a numerical simulation method for aluminum particle ignition and combustion based on chemical table building under laminar flow conditions in one embodiment.

[0082] Figure 7 This is a flowchart of a numerical simulation method for aluminum particle ignition and combustion under turbulent conditions based on chemical table building, as shown in one embodiment.

[0083] Figure 8 This is a structural block diagram of a numerical simulation device for igniting and burning aluminum particles in one embodiment;

[0084] Figure 9 This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0085] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without inventive effort are within the scope of protection of this application.

[0086] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0087] Furthermore, the use of terms such as "first" and "second" in this application is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of those features. In the description of this application, "multiple sets" means at least two sets, such as two sets, three sets, etc., unless otherwise explicitly specified.

[0088] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0089] Furthermore, the technical solutions of the various embodiments of this application can be combined with each other, but only if they are based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by this application.

[0090] The method provided in this application can be applied to, for example... Figure 1 In the application environment shown, terminal 102 communicates with server 104 via a network. Terminal 102 may include, but is not limited to, various personal computers, laptops, smartphones, tablets, and portable wearable devices. Server 104 may be a server corresponding to various portal websites or work system backends.

[0091] This application provides a numerical simulation method for the ignition and combustion of aluminum particles, such as... Figure 2 As shown, in one embodiment, the method is applied to Figure 1 Taking the terminal in the example, the explanation includes:

[0092] Step 202: Based on the atomic mixing state, thermal state and reaction process of the gas phase during aluminum particle combustion, the control variables of the aluminum particle combustion process are obtained, and the gas phase control variable transport equation for aluminum particle combustion in air is constructed.

[0093] Specifically:

[0094] From the perspective of atomic mass conservation, the atomic mixing state of the gas phase during the combustion of aluminum particles is modeled to obtain the proportion of oxygen atoms and aluminum atoms in the gas phase. The proportion of oxygen atoms in the gas phase is taken as the first variable and the proportion of aluminum atoms in the gas phase is taken as the second variable.

[0095] The thermal state of the gas phase during the combustion of aluminum particles is modeled from the perspective of the conservation of total enthalpy in the gas phase, and the normalized total enthalpy is obtained. The normalized total enthalpy is then used as the third variable.

[0096] The reaction state of the gas phase during the combustion of aluminum particles is modeled from the perspective of the reaction process, and the normalized reaction progress variable is obtained. The normalized reaction progress variable is used as the fourth variable.

[0097] Based on the first, second, third, and fourth variables, a gas-phase controlled variable transport equation for the combustion of aluminum particles in air is constructed.

[0098] More specifically:

[0099] Combustion process of aluminum particles: For aluminum particles burning in air, an external heat source is required to ignite the particle group. During the subsequent self-sustaining combustion of the particle dust flame, the aluminum particles are heated from room temperature to melting through radiative heat transfer and interphase heat transfer. Subsequently, the liquid aluminum in the particles undergoes a surface chemical reaction, which accelerates the temperature rise of the particles. At the same time, it consumes oxygen in the air and generates aluminum oxide, which is deposited on the particle surface, thus reducing the oxygen atoms in the gas phase. In the combustion stage, the gaseous aluminum evaporated from the aluminum droplets reacts with the air, thus increasing the aluminum atoms in the gas phase. At the same time, some aluminum oxide is deposited on the particle surface, thus reducing the aluminum and oxygen atoms in the gas phase accordingly.

[0100] From the perspective of atomic mass conservation, the atomic mixing state of the gas phase during the combustion of aluminum particles is modeled, and the mass and heat transfer between the gas phase and aluminum particles is described.

[0101] like Figure 3 As shown, the gas phase within a grid in the computational domain can only contain nitrogen atoms (N) from nitrogen in the air, oxygen atoms (O) from oxygen in the air, or aluminum atoms (Al) evaporated from aluminum particles. Therefore, for the above three-inlet chemical table building system, the mixing state of the gas phase can be uniquely determined based on the following three atomic mass fractions: Y N Y O Y Al , where Y represents the mass fraction.

[0102] If we consider the Al atoms in the gas phase as atoms from the fuel side, and the O and N atoms in the gas phase as atoms from the oxidant side, then the atomic composition of the oxidant side can be uniquely determined by X:

[0103]

[0104] In the formula, X represents the mass fraction of oxygen atoms in the gas phase, and Y represents the mass fraction of oxygen atoms in the gas phase. O Y represents the mass fraction of O atoms. N This represents the mass fraction of N atoms.

[0105] If the fuel component is Al atoms, then the mixing fraction Z, which describes the mixing process of fuel atoms (Al) and oxidant atoms (N and O), can be expressed as:

[0106]

[0107] In the formula, Z represents the mass fraction of aluminum atoms in the gas phase, and Y... Al Y represents the mass fraction of Al atoms. Al,OX Y represents the mass fraction of aluminum atoms on the oxidant side. Al,f Z represents the mass fraction of aluminum atoms on the fuel side; where Z = 1 corresponds to the fuel side and Z = 0 corresponds to the oxidant side.

[0108] Once Z and X are determined, the atomic mixing state of the gas phase can be uniquely determined.

[0109] For example, when the control variable (Z,X) = (0,0.233), it can indicate that the gas phase contains no aluminum atoms, while the mass percentage of oxygen atoms is 0.233, meaning the gas phase mixture is the same as that of air. Figure 3 The grid in (1). When the control variable (Z,X) = (0,0.22), it can be said that there are no aluminum atoms in the gas phase, and the mass percentage of oxygen atoms is 0.22, which is lower than the oxygen content in the air. This is because the surface chemical reaction of aluminum particles causes some oxygen atoms in the gas phase to become oxygen atoms in the aluminum oxide deposited on the particle surface, corresponding to Figure 3 The grid in (2). When the control variable (Z,X)=(0.2,0.21), it can be said that the mass percentage of aluminum atoms in the gas phase is 0.2, and the mass percentage of oxygen atoms on the oxidant side is 0.21, corresponding to Figure 3 In grid (3), compared to grid (2), the mass fraction of aluminum atoms in the gas phase increases due to the evaporation of aluminum droplets during combustion, resulting in an increase in the mixing fraction Z.

[0110] The thermal state of the gas phase during the combustion of aluminum particles is modeled from the perspective of the conservation of total enthalpy in the gas phase, and the mass and heat transfer between the gas phase and aluminum particles is described.

[0111] When determining the thermal state of the gas phase, i.e., its total enthalpy, the main factors affecting the total enthalpy of the gas phase are interphase heat transfer and radiative heat transfer. Therefore, from the perspective of accelerated interpolation and table lookup, a normalized total enthalpy is introduced and defined as follows:

[0112]

[0113] In the formula, hnorm Here, h is the normalized total enthalpy, and h is the total enthalpy obtained by solving the gas energy equation. min (Z,X) represents the minimum total enthalpy in the chemical reaction database corresponding to the current mixed state, h max (Z,X) represents the maximum total enthalpy in the chemical reaction database corresponding to the current mixed state; where h min (Z,X) and h max (Z,X) are functions of Z and X.

[0114] From the perspective of reaction process, the gas phase reaction state during the combustion of aluminum particles is modeled, and the reaction progress variable is introduced:

[0115]

[0116] In the formula, Y c As a variable representing the progress of the response, The mass fraction of Al2O3(1) is given, where (1) represents the liquid phase. Y represents the mass fraction of Al2O. AlO Y is the mass fraction of AlO; where Y is the mass fraction of AlO. C =0 indicates that the gas phase is in a pure mixed state, and no chemical reaction has occurred, while Y C =1 indicates that the chemical reaction has reached equilibrium and the reaction is complete;

[0117] To expedite table lookup, the reaction progress variable is normalized to obtain the normalized reaction progress variable:

[0118]

[0119] In the formula, C is the normalized reaction progress variable, and Y c min (Z,X,h norm Y represents the minimum value of the unnormalized reaction progress variable corresponding to the current state. c max (Z,X,h norm ) represents the maximum value of the unnormalized reaction progress variable corresponding to the current state.

[0120] Let X be the first variable, Z be the second variable, and h be the third variable. norm With C as the third variable and C as the fourth variable, the first, second, third, and fourth variables constitute the control variables. Based on the first, second, third, and fourth variables, the gas-phase control variable transport equation for the combustion of gaseous aluminum particles in air under laminar flow conditions is constructed, which is the chemical table model control equation:

[0121]

[0122]

[0123]

[0124]

[0125] In the formula, ρ is density, t is time, and u j Let x be the component of the gas phase velocity in the j-direction. j For the j-direction, D Z Let x be the diffusion coefficient of the second variable. i For the i direction, D is the source term for the second variable. X The diffusion coefficient is the first variable. For the source term of the first variable, The diffusion coefficient is the reaction progress variable. Here, α is the source term for the reaction progress variable, and α is the thermal diffusivity. This is the total enthalpy source term in the gas phase due to interphase heat transfer. This is the total enthalpy source term in the gas phase due to radiative heat transfer;

[0126] In equations (6) and (7), the two-phase coupled source terms and The following methods can be used to close it:

[0127]

[0128]

[0129] In the formula, This represents the mass exchange of gaseous aluminum between the gas and solid phases caused by the evaporation of aluminum particles. WAl is the relative molecular mass of aluminum. is the relative molecular mass of aluminum oxide. This refers to the mass exchange between the gas and solid phases of condensed alumina caused by alumina deposition on the particle surface. The oxygen consumption is caused by the chemical reaction on the surface of aluminum particles. This represents the relative molecular mass of oxygen.

[0130] Step 204: Considering the change in total enthalpy of the gas phase, change the temperatures on the oxidizer side and the fuel side, apply a correction factor to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame, and solve the one-dimensional gas-to-opposed flame according to the gas phase reaction mechanism to obtain the steady-state numerical solution; establish a four-dimensional chemical reaction database in the control variable space through coordinate transformation.

[0131] Specifically:

[0132] Considering the change in total enthalpy of the gas phase, the temperatures on the oxidizer side and the fuel side are changed to create opposed flames under different total enthalpy inlet conditions, and the corrected inlet temperature is obtained.

[0133] Considering the change in total enthalpy in the gas phase, a correction factor is applied to the chemical reaction source term in the gas phase temperature equation of a one-dimensional opposed flame to obtain a modified gas phase temperature equation.

[0134] Based on the modified inlet temperature, modified gas phase temperature equation, and gas phase reaction mechanism, the boundary conditions of a one-dimensional gas-phase opposing flame are constructed, and the steady-state numerical solution of the one-dimensional gas-phase opposing flame is obtained. Through coordinate transformation, a four-dimensional chemical reaction database in the control variable space is established.

[0135] More specifically:

[0136] like Figure 4 As shown, the oxidizer side of the counter-flame is a mixture of oxygen and nitrogen, and the fuel side is gaseous aluminum, wherein the ratio of oxygen to nitrogen is determined by the first variable X, i.e., equation (1).

[0137] During the combustion of aluminum particles, the total enthalpy of the gas phase is no longer a conserved scalar due to radiation and interphase heat transfer. However, directly solving for one-dimensional gas phase opposing flames cannot take into account the influence of the above factors and requires processing.

[0138] First, to accurately describe the change in total enthalpy in the gas phase, the temperature of the oxidizer side and the fuel side were changed to create opposed flames under different total enthalpy inlet conditions, and the corrected inlet temperature of the one-dimensional opposed flame was obtained.

[0139] Inlet temperature on the oxidant side:

[0140] T ox =T Air,min +h norm *(T Air,max -T Air,min (14)

[0141] In the formula, T ox T is the inlet temperature on the oxidant side. Air,min To calculate the minimum oxidant inlet temperature within the domain, T Air,max To calculate the maximum value of the oxidant inlet temperature within the domain;

[0142] Fuel-side inlet temperature:

[0143] T f =T Al,min +h norm *(T Al,max -T Al,min (15)

[0144] In the formula, T f T represents the inlet temperature on the fuel side.Al,min To calculate the maximum inlet temperature of vaporized aluminum within the domain, T Al,min To calculate the maximum inlet temperature of vaporized aluminum within the calculation domain;

[0145] Here is a set of suggested values ​​for T. Air,min =T Al,min =300K, T Air,max =T Al,max =2000K.

[0146] The above method is easy to implement and changes the range of inlet temperature variation, which can cover part of the range of variation of total enthalpy in the gas phase during the combustion process of aluminum particles.

[0147] Then, considering the total enthalpy change in the gas phase, a correction factor is applied to the chemical reaction source term in the gas phase temperature equation (i.e., the one-dimensional flame energy equation) of the one-dimensional opposed flame (which can further broaden the range of total enthalpy change in the gas phase covered by the one-dimensional flame) to obtain the modified gas phase temperature equation.

[0148] Vapor phase temperature equation:

[0149]

[0150] In the formula, For mass flow rate, c ρ ρ is specific heat, T is temperature, z is a one-dimensional coordinate, N is the number of components, λ is thermal conductivity, k is the number of components, and c is the number of components. pk Let j be the specific heat of component k. k,z f is the mass diffusion flux of component k in the z-direction. L h is the correction factor. k For total enthalpy, W represents the chemical reaction rate. k Let f be the mass diffusion flux of the molar mass in the z-direction; where the correction factor is used to change the proportion of heat released in the chemical reaction, thereby changing the total enthalpy of the gas phase, and its value ranges from (0-1). L =1 corresponds to an adiabatic flame.

[0151] The correction factor is assigned the following values:

[0152] f L =f L,min +h norm *(1-f L,min (16)

[0153] In the formula, f L,min The lower limit of the correction factor is greater than zero and less than one. Its value is required to make h as defined in equation (3) norm Greater than zero, meaning it guarantees the minimum value h of the total enthalpy of the gas phase in the chemical reaction database. minIt is less than the total gas phase enthalpy h obtained from the transport solution of equation (9) in the numerical simulation;

[0154] The above method, by modifying the exothermic source term of the gas-phase chemical reaction, can greatly broaden the range of total enthalpy change in the gas phase, which is consistent with the actual situation and can fully cover the state of aluminum particle combustion in the air.

[0155] Assuming oxidant mass flow rate With fuel mass flow rate The inlets of the two opposing flames are equal, and the distance between them is 0.1m. This assumption does not affect the universality of the model because the final solved opposing flame data will be transformed into the control variable space. At this point, all boundary conditions for the one-dimensional gas-pitch opposing flame have been determined.

[0156] Based on the modified inlet temperature, modified gas phase temperature equation, and gas phase reaction mechanism (using the reaction mechanism of 8 components and 11 elementary reactions as shown in Table 1), the boundary conditions of a one-dimensional gas-phase opposing flame are constructed, the one-dimensional gas-phase opposing flame is solved, the steady-state numerical solution is obtained, and a four-dimensional chemical reaction database is established.

[0157] Table 1. Detailed Chemical Reaction Mechanism of Aluminum-Air

[0158]

[0159] To obtain the state of the counter-current flame under different reaction progress variables, the steady-state numerical solution of the one-dimensional counter-current flame obtained in this step requires adjusting the flame elongation ratio. This is achieved by changing the inlet mass flow rate to create counter-current flames under different elongation ratio conditions. Specifically, the process is as follows: First, a numerical solution for the counter-current flame under the condition of the smallest possible inlet mass flow rate m0 is obtained as the initial solution, which is considered to correspond to the chemical reaction equilibrium state, i.e., the source terms of each component are approximately zero. Then, based on the initial solution, the mass flow rate of the counter-current flame is gradually increased until the maximum flame temperature does not exceed the maximum value of the two inlet temperatures of the counter-current flame, at which point the flame is considered extinguished and corresponds to a pure mixing state. It should be noted that the value of the smallest possible inlet mass flow rate m0 is based on the principle that reducing the inlet mass flow rate from m0 to 0.5 times m0 results in an increase of no more than 1% in the maximum flame temperature.

[0160] The specific process for solving a one-dimensional gas-phase opposing flame is as follows: Figure 5 As shown.

[0161] Step 206: Initialize the flow field. Obtain the initial gas phase thermophysical quantities of the initial flow field. Based on the aluminum particle ignition and combustion sub-model, solve the gas phase control variable transport equation to obtain the current value of the control variable.

[0162] Specifically:

[0163] Calculate the initial flow field and obtain the initial gas phase thermophysical quantities of the initial flow field;

[0164] The initial gas phase thermophysical quantities are input into the aluminum particle ignition and combustion sub-model to update the particle state and obtain the two-phase coupled source term.

[0165] The current values ​​of the control variables are obtained by solving the gas phase control equations under laminar flow conditions based on the two-phase coupled source terms.

[0166] More specifically:

[0167] The current values ​​of the four control variables can be determined by solving equations (6) to (9).

[0168] Step 208: Based on the current value of the control variable, perform interpolation lookup on the four-dimensional chemical reaction database to obtain the state parameters of the gas phase.

[0169] Specifically:

[0170] The gas phase state parameter φ can be obtained by interpolation and table lookup from a four-dimensional chemical reaction database, that is:

[0171] φ=φ(Z,C,X,h norm (12)

[0172] The state parameters of the gas phase include temperature, kinetic viscosity, thermal conductivity, compressibility, reaction progress variable source term, and mass fraction of each component.

[0173] For φ(Z,C,X,h) norm A four-dimensional chemical reaction database was used to analyze the control variables X and h. norm Linear interpolation was performed on 11 and 21 data points (both suggested values) within the range [0,1]. Subsequently, the corresponding one-dimensional counter-flame was subjected to... Figure 5 The numerical solution is obtained using the method shown. Based on the definitions of the mixing fraction Z and the reaction progress variable C, as shown in equations (2) and (5), the series of numerical solutions of the opposing flame obtained in the physical space are transformed to the (Z,C) space, resulting in an 11×21 chemical reaction database. Furthermore, each chemical reaction database is linearly interpolated with 101 and 101 data points (both suggested values) for the control variables Z and C in the range [0,1], ultimately yielding a 101×101×11×21 four-dimensional chemical reaction database. In addition, the maximum and minimum values ​​of the total enthalpy of the gas phase required for normalization are stored in two two-dimensional databases h. max (Z,X) and h min In (Z,X), the maximum and minimum values ​​of the reaction progress variables required for normalization are stored in two three-dimensional databases Y. c max (Z,X,hnorm ) and Y c min (Z,X,h norm In this database, the total memory required is approximately 500MB per core.

[0174] Step 210: When the state parameters of the gas phase reach the preset conditions, the current gas phase thermophysical quantity is obtained, and the current gas phase thermophysical quantity is used as the thermophysical quantity of the gas phase in the combustion chamber of the solid fuel-powered missile.

[0175] When the state parameters of the gas phase do not meet the preset conditions, the current gas phase thermophysical quantity is obtained. The current gas phase thermophysical quantity is input into the aluminum particle ignition and combustion sub-model, and the gas phase control equation is solved again to obtain the next value of the control variable. Based on the next value of the control variable, the four-dimensional chemical reaction database is interpolated and a table is looked up to obtain the next state parameter of the gas phase. This process continues until the next state parameter of the gas phase meets the preset conditions, and the next gas phase thermophysical quantity is obtained. The next gas phase thermophysical quantity is then used as the thermophysical quantity of the gas phase in the combustion chamber of a solid fuel-powered missile.

[0176] like Figure 6 The flowchart shows the numerical simulation method for aluminum particle ignition and combustion based on chemical table establishment under laminar flow conditions. First, after initializing the calculated flow field, the particle state is updated according to the aluminum particle ignition and combustion sub-model, and the two-phase coupled source terms are obtained; second, the gas phase control equation under laminar flow conditions is solved to obtain the control variables required to query the chemical reaction database; third, according to the control variables, the thermophysical quantities of the gas phase are obtained by interpolation and table lookup in the chemical reaction database, including the source terms of temperature and chemical reaction progress variables (in formula (8)). ), component concentration, kinetic viscosity coefficient, etc.; finally, if the calculation meets the predetermined conditions, stop, otherwise repeat the above steps.

[0177] like Figure 7 The diagram shows the flowchart of a numerical simulation method for aluminum particle ignition and combustion based on chemical tables under turbulent conditions. Compared with the numerical simulation method under laminar flow conditions, the numerical simulation method under turbulent flow conditions requires, on the basis of laminar flow, the Eulerian random field method to obtain the probability density distribution of the control variables at the subgrid scale. Subsequently, interpolation and table lookup are performed based on the first moments of the control variables to obtain the corresponding thermophysical quantities.

[0178] The above-mentioned numerical simulation method for aluminum particle ignition and combustion establishes a chemical table model for computational fluid dynamics research on aluminum particle ignition and combustion. A numerical simulation method for aluminum particle ignition and combustion in air is designed. Based on the unique surface chemical reaction process in the aluminum particle ignition and combustion process, a gas phase control equation suitable for the chemical table model of aluminum particle combustion is established. At the same time, by combining the adjustment of one-dimensional flame temperature boundary conditions with the setting of chemical reaction source term correction factors and solving the one-dimensional gas phase opposing flame method, a chemical reaction database for aluminum particle combustion in air is established to solve the problem of the small range of total enthalpy change in the gas phase in the traditional chemical table model. Numerical simulation is then performed on this basis. This method establishes a chemical reaction database and performs interpolation lookup. Since the chemical reaction database is stored in the computer memory before calculation, only the transport equations of the control variables need to be solved during the calculation process, i.e., formulas (6)-(9), without needing to solve the complex detailed chemical reaction mechanism. Thus, while ensuring the calculation accuracy of the combustion model, the calculation speed is greatly improved, and the calculation efficiency of the simulation of flow combustion in the combustion chamber of solid fuel-powered missiles is improved.

[0179] It should be understood that, although Figure 2 The steps in the flowchart are shown sequentially as indicated by the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order in which these steps are executed, and they can be performed in other orders. Figure 2 At least some of the steps in the process may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed in turn or alternately with other steps or at least some of the sub-steps or stages of other steps.

[0180] This application also provides a numerical simulation device for the ignition and combustion of aluminum particles, such as... Figure 8 As shown, in one embodiment, it includes: a modeling module 802, a database construction module 804, a solution module 806, a table lookup module 808, and an output module 810, wherein:

[0181] Modeling module 802 is used to obtain the control variables of the aluminum particle combustion process based on the atomic mixing state of the gas phase, the thermal state of the gas phase, and the reaction process during the aluminum particle combustion process, and to construct the gas phase control variable transport equation for the combustion of aluminum particles in air.

[0182] The database module 804 is used to consider the change in total enthalpy of the gas phase, change the temperature of the oxidizer side and the fuel side, apply a correction factor to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame, and solve the one-dimensional gas phase opposed flame according to the gas phase reaction mechanism to obtain the steady-state numerical solution; and establish a four-dimensional chemical reaction database in the control variable space through coordinate transformation.

[0183] The solver module 806 is used for flow field initialization, to obtain the initial gas phase thermophysical quantities of the initial flow field, and to solve the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable.

[0184] The lookup module 808 is used to perform interpolation lookup on the four-dimensional chemical reaction database based on the current value of the control variable to obtain the state parameters of the gas phase.

[0185] The output module 810 is used to obtain the current gas phase thermophysical quantity when the state parameters of the gas phase reach the preset conditions, and to use the current gas phase thermophysical quantity as the thermophysical quantity of the gas phase in the combustion chamber of the solid fuel-powered missile.

[0186] Specific limitations regarding the numerical simulation device for aluminum particle ignition and combustion can be found in the limitations of the numerical simulation method for aluminum particle ignition and combustion described above, and will not be repeated here. Each module in the aforementioned device can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device in hardware form, or stored in the memory of a computer device in software form, so that the processor can call and execute the operations corresponding to each module.

[0187] In one embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as follows: Figure 9 As shown, the computer device includes a processor, memory, network interface, display screen, and input devices connected via a system bus. The processor provides computing and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The network interface is used to communicate with external terminals via a network connection. When executed by the processor, the computer program implements a numerical simulation method for the ignition and combustion of aluminum particles. The display screen can be an LCD screen or an e-ink screen. The input devices can be a touch layer covering the display screen, buttons, a trackball, or a touchpad mounted on the computer device casing, or an external keyboard, touchpad, or mouse.

[0188] Those skilled in the art will understand that Figure 9 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0189] In one embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program, the processor executing the computer program to implement the steps of the method described above.

[0190] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the steps of the method described above.

[0191] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, storage, databases, or other media used in the embodiments provided in this application can include non-volatile and / or volatile memory. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), dual data rate SDRAM (DDRSDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM), etc.

[0192] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0193] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A numerical simulation method for the ignition and combustion of aluminum particles, characterized in that, include: Based on the atomic mixing state, thermal state, and reaction process of the gas phase during aluminum particle combustion, the control variables of the aluminum particle combustion process are obtained, and the gas phase control variable transport equation for aluminum particle combustion in air is constructed. Considering the change in total enthalpy in the gas phase, the temperatures on the oxidizer side and the fuel side are changed. A correction factor is applied to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame. Based on the gas phase reaction mechanism, the one-dimensional gas phase opposed flame is solved to obtain the steady-state numerical solution. A four-dimensional chemical reaction database is established in the control variable space through coordinate transformation; Flow field initialization: Obtain the initial gas phase thermophysical quantities of the initial flow field; Solve the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable; Based on the current values ​​of the control variables, interpolation and table lookup are performed on the four-dimensional chemical reaction database to obtain the state parameters of the gas phase; When the state parameters of the gas phase reach the preset conditions, the current gas phase thermophysical quantity is obtained, and the current gas phase thermophysical quantity is used as the thermophysical quantity of the gas phase in the combustion chamber of the solid fuel-powered missile.

2. The numerical simulation method for the ignition and combustion of aluminum particles according to claim 1, characterized in that, Based on the atomic mixing state, thermal state, and reaction process of the gas phase during aluminum particle combustion, the control variables for the aluminum particle combustion process include: If we consider the Al atoms in the gas phase as atoms from the fuel side, and the O and N atoms in the gas phase as atoms from the oxidant side, then the atomic composition of the oxidant side can be uniquely determined by X: In the formula, X represents the mass fraction of oxygen atoms in the gas phase, and Y represents the mass fraction of oxygen atoms in the gas phase. O Y represents the mass fraction of O atoms. N The mass fraction of N atoms; If the fuel-side component is Al atoms, then the mixing fraction Z, which describes the mixing process of fuel atoms and oxidant atoms, can be expressed as: In the formula, Z represents the mass fraction of aluminum atoms in the gas phase, and Y... Al Y represents the mass fraction of Al atoms. Al,OX Y represents the mass fraction of aluminum atoms on the oxidant side. Al,f Z represents the mass fraction of aluminum atoms on the fuel side; where Z = 1 corresponds to the fuel side and Z = 0 corresponds to the oxidant side. When determining the thermal state of the gas phase, i.e., its total enthalpy, a normalized total enthalpy is introduced: In the formula, h norm Here, h is the normalized total enthalpy, and h is the total enthalpy obtained by solving the gas energy equation. min (Z,X) represents the minimum total enthalpy in the chemical reaction database corresponding to the current mixed state, h max (Z,X) represents the maximum total enthalpy in the chemical reaction database corresponding to the current mixed state; From the perspective of reaction process, the gas phase reaction state during the combustion of aluminum particles is modeled, and the reaction progress variable is introduced: In the formula, Y c As a variable representing the progress of the response, The mass fraction of Al2O3(1) Y represents the mass fraction of Al2O. AlO The mass fraction of AlO; The reaction progress variable is normalized to obtain the normalized reaction progress variable: In the formula, C is the normalized reaction progress variable, and Y c min (Z,X,h norm Y represents the minimum value of the unnormalized reaction progress variable corresponding to the current state. c max (Z,X,h norm ) represents the maximum value of the unnormalized reaction progress variable corresponding to the current state; With X, Z, h norm C and C are the control variables for the aluminum particle combustion process.

3. The numerical simulation method for the ignition and combustion of aluminum particles according to claim 2, characterized in that, The gas-phase controlled variable transport equations for the combustion of aluminum particles in air include: Based on the control variables, the gas-phase control variable transport equation for the combustion of gaseous aluminum particles in air under laminar flow conditions is constructed: In the formula, ρ is density, t is time, and u j Let x be the component of the gas phase velocity in the j-direction. j For the j-direction, D Z Let x be the diffusion coefficient of the second variable. i For the i direction, D is the source term for the second variable. X The diffusion coefficient is the first variable. For the source term of the first variable, The diffusion coefficient is the reaction progress variable. Here, α is the source term for the reaction progress variable, and α is the thermal diffusivity. This is the total enthalpy source term in the gas phase due to interphase heat transfer. This is the total enthalpy source term in the gas phase caused by radiative heat transfer.

4. The numerical simulation method for the ignition and combustion of aluminum particles according to claim 3, characterized in that, Changing the temperature on the oxidizer side and the fuel side includes: Inlet temperature on the oxidant side: T ox =T Air,min +h norm *(T Air,max -T Air,min ) (14) In the formula, T ox T is the inlet temperature on the oxidant side. Air,min To calculate the minimum oxidant inlet temperature within the domain, T Air,max To calculate the maximum value of the oxidant inlet temperature within the domain; Fuel-side inlet temperature: T f =T Al,min +h norm *(T Al,max -T Al,min ) (15) In the formula, T f T represents the inlet temperature on the fuel side. Al,min To calculate the maximum inlet temperature of vaporized aluminum within the domain, T Al,min This is to calculate the maximum inlet temperature of vaporized aluminum within the domain.

5. The numerical simulation method for the ignition and combustion of aluminum particles according to claim 4, characterized in that, Applying correction factors to the chemical reaction source terms in the gas-phase temperature equation for a one-dimensional opposed flame includes: Vapor phase temperature equation: In the formula, For mass flow rate, c p ρ is specific heat, T is temperature, z is a one-dimensional coordinate, N is the number of components, λ is thermal conductivity, k is the number of components, and c is the number of components. pk Let j be the specific heat of component k. k,z f is the mass diffusion flux of component k in the z-direction. L h is the correction factor. k For total enthalpy, W represents the chemical reaction rate. k Let be the mass diffusion flux of molar mass in the z-direction; The correction factor is assigned the following values: f L =f L,min +h norm *(1-f L,min ) (16) In the formula, f L,min This is the lower limit of the correction factor, greater than zero and less than one.

6. The numerical simulation method for ignition and combustion of aluminum particles according to any one of claims 1 to 5, characterized in that, Solving for a one-dimensional gas-pitch flame yields steady-state numerical solutions, including: The numerical solution of the counter-current flame under the initial inlet mass flow rate condition is used as the initial solution; Based on the initial solution, the mass flow rate of the counter-current flame is gradually increased until the highest flame temperature does not exceed the maximum value of the two inlet temperatures of the counter-current flame, thus obtaining the steady-state numerical solution.

7. The numerical simulation method for ignition and combustion of aluminum particles according to any one of claims 2 to 5, characterized in that, Based on the current values ​​of the control variables, the interpolation lookup table in the four-dimensional chemical reaction database includes: For control variables X and h respectively norm Linear interpolation is used to interpolate multiple data points, and numerical solutions are obtained for the corresponding one-dimensional counter-flame in physical space. Based on the control variables Z and C, the numerical solution of the counter-flame obtained in the physical space is transformed to the corresponding space to obtain multiple chemical reaction databases; By linearly interpolating multiple data points for each chemical reaction database with respect to control variables Z and C, a four-dimensional chemical reaction database is obtained, and the state parameters of the gas phase are obtained.

8. A numerical simulation device for the ignition and combustion of aluminum particles, characterized in that, include: The modeling module is used to obtain the control variables of the aluminum particle combustion process based on the atomic mixing state, thermal state and reaction process of the gas phase during aluminum particle combustion, and to construct the gas phase control variable transport equation for aluminum particle combustion in air. The library module is used to consider the change in total enthalpy of the gas phase, change the temperature on the oxidizer side and the fuel side, apply a correction factor to the chemical reaction source term in the gas phase temperature equation of the one-dimensional opposed flame, and solve the one-dimensional gas phase opposed flame according to the gas phase reaction mechanism to obtain the steady-state numerical solution. A four-dimensional chemical reaction database is established in the control variable space through coordinate transformation; The solver module is used for flow field initialization, obtaining the initial gas phase thermophysical quantities of the initial flow field, and solving the gas phase control variable transport equation based on the aluminum particle ignition and combustion sub-model to obtain the current value of the control variable; The lookup module is used to interpolate and look up the table in the four-dimensional chemical reaction database based on the current value of the control variable to obtain the state parameters of the gas phase; The output module is used to obtain the current gas phase thermophysical quantity when the gas phase state parameters reach the preset conditions, and to use the current gas phase thermophysical quantity as the thermophysical quantity of the gas phase in the combustion chamber of a solid fuel-powered missile.

9. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 7.

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