Aircraft radiation heat assessment method, device, equipment and storage medium

Abstract

The present application provides a method, device, equipment and storage medium for evaluating radiation heat of an aircraft, and specifically relates to the technical field of radiation heat evaluation of an aircraft. The method comprises: obtaining the initial value of the spectral radiation intensity of the unit boundary solid angle unit and the initial value of the spectral radiation intensity of the solid angle unit according to the temperature of the unit boundary sub-solid angle unit and the sub-solid angle unit; obtaining the unit boundary flux according to the initial value of the spectral radiation intensity of the solid angle unit and the initial value of the spectral radiation intensity of the unit boundary solid angle unit; obtaining the unit boundary flux according to the initial value of the spectral radiation intensity of the solid angle unit; obtaining the spectral radiation intensity of the wall unit based on the radiation transmission equation according to the unit boundary flux; obtaining the wall radiation heat flux value according to the spectral radiation intensity of the wall unit, and evaluating the radiation heat of the aircraft to be tested according to the wall radiation heat flux value. The method improves the accuracy of the wall radiation heat flux value and does not occupy too much computer memory.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft radiation heat evaluation, and in particular to an aircraft radiation heat evaluation method, device, equipment and storage medium. Background Art

[0002] During hypersonic flight, the high-temperature gas generated by the shock layer will produce strong radiation heating on the wall surface. As the flight speed increases further, the radiation heating will also increase sharply, and eventually occupy the main part of the entire aerodynamic heating. At the same time, the jet tail flame produced by the operation of the aircraft engine will also produce strong radiation heating on the bottom of the aircraft. In order to solve the radiation heating of the aircraft by the high-temperature medium, the finite volume method can generally be used to solve the radiation transfer equation to calculate the radiation heating of the high-temperature medium on the aircraft wall. When solving the radiation transfer equation using the finite volume method, it is necessary not only to divide the aircraft into grid units, but also to divide the solid angle in each grid unit to form a solid angle set. The finer the solid angle division, the more accurate the solution of the radiation transfer equation and the more accurate the calculation result of the wall radiation heat flux value.

[0003] However, when the number of solid angle divisions increases, the time to solve the radiation transfer equation and the amount of computational memory consumed increase exponentially. Due to the limitation of computer memory, only a limited number of solid angle divisions can be performed in actual engineering calculations, which makes the calculated wall radiation heat flux value fluctuate and the accuracy decreases.

[0004] Therefore, due to the limitation of computer memory, inaccurate calculated radiation heat flux values ​​are an existing problem. Summary of the invention

[0005] In view of this, the purpose of the present application is to provide an aircraft radiation heat assessment method, device, equipment and storage medium to solve the above-mentioned problems and improve the calculation accuracy of the radiation heat flux value under limited computer memory.

[0006] In a first aspect, an embodiment of the present application provides a method for evaluating radiant heat of an aircraft, which is applied to a simulation device, wherein the simulation device pre-creates an unstructured grid based on the aircraft to be tested, wherein the unstructured grid has a plurality of grid cells, and a cell boundary is set between every two adjacent grid cells; each grid cell is divided according to a preset number of solid angle cells to obtain a plurality of solid angle cells; each solid angle cell is divided according to a preset number of sub-solid angle cells to obtain a plurality of sub-solid angle cells; each cell boundary is divided according to a preset number of cell boundary solid angles to obtain a plurality of cell boundary solid angle cells; each cell boundary solid angle is divided according to a preset number of cell boundary sub-solid angles to obtain a plurality of cell boundary sub-solid angle cells; the method comprises:

[0007] Obtain the temperature of each sub-solid corner cell and the temperature of each cell boundary sub-solid corner cell;

[0008] The initial value of the spectral radiation intensity of the unit boundary solid corner unit is obtained by calculation according to the temperature of the unit boundary sub-solid corner unit;

[0009] Calculating an initial value of the spectral radiation intensity of the solid corner element according to the temperature of the sub-solid corner element;

[0010] If the unit boundary is a wall unit boundary or a far-field unit boundary, the unit boundary flux is calculated according to the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit;

[0011] If the unit boundary is a symmetric unit boundary, the unit boundary flux is calculated according to the initial value of the spectral radiation intensity of the solid corner unit;

[0012] Obtaining the spectral radiation intensity of the wall unit according to the unit boundary flux;

[0013] The wall radiation heat flux value is calculated according to the spectral radiation intensity of the wall unit, and the radiation heat of the aircraft to be tested is evaluated according to the wall radiation heat flux value.

[0014] Preferably, the solid corner element comprises a first solid corner element and a second solid corner element; the sub-solid corner element comprises a first sub-solid corner element and a second sub-solid corner element; each first solid corner element and each second solid corner element are symmetrically distributed in every two adjacent symmetric elements about the symmetric element boundary;

[0015] The step of calculating an initial value of the spectral radiation intensity of the solid corner element according to the temperature of the sub-solid corner element comprises:

[0016] obtaining a direction of each first sub-solid corner element;

[0017] Each calculated direction is calculated based on the direction of each first sub-solid corner element;

[0018] Obtain each direction angle formed by each calculated direction and the direction of each first sub-solid corner element;

[0019] Comparing each direction angle with each other to obtain the direction of the second sub-solid corner element; wherein the direction of the second sub-solid corner element is the calculated direction corresponding to the direction angle with the smallest angle;

[0020] An initial value of the spectral radiation intensity of the first solid corner element is calculated according to the temperature of the first sub-solid corner element;

[0021] The initial value of the spectral radiation intensity of the second sub-cube corner element corresponding to the direction of the second sub-cube corner element is determined by the initial value of the spectral radiation intensity of the first cube corner element.

[0022] Preferably, the unit boundary sub-solid angles include wall unit boundary sub-solid angle units and far-field unit boundary sub-solid angle units; the unit boundary solid angle units include wall unit boundary solid angle units and far-field unit boundary solid angle units;

[0023] The step of calculating the initial value of the spectral radiation intensity of the unit boundary solid corner element according to the temperature of the unit boundary sub-solid corner element comprises:

[0024] If the unit boundary sub-solid angle is the wall unit boundary sub-solid angle, then the initial value of the spectral radiation intensity of the wall unit boundary solid angle unit is calculated according to the temperature of the wall unit boundary sub-solid angle;

[0025] The calculation formula for the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit is:

[0026]

[0027] in, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit, is the wall emissivity, is the Boltzmann constant, is the temperature of the sub-solid angle of the wall unit boundary, is the spatial direction of the wall unit, is the set of directions of the solid corner elements of all wall elements, is the spectral radiance in the direction of the solid corner unit of one wall unit in the jth wall unit, is the normal vector of the wall unit boundary of the wall unit, is the steradian of the solid angle unit;

[0028] If the unit boundary sub-solid angle is the far-field unit boundary sub-solid angle, then calculating the initial value of the spectral radiation intensity of the far-field unit boundary solid angle unit according to the temperature of the far-field unit boundary sub-solid angle;

[0029] The calculation formula for the initial value of the spectral radiation intensity of the far-field unit boundary solid corner unit is:

[0030]

[0031] in, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the far-field unit, is the Boltzmann constant, is the temperature of the far-field unit boundary sub-solid angle.

[0032] Preferably, the step of obtaining each calculated direction according to the direction of each first sub-solid corner element comprises:

[0033] The calculation formula for the calculation direction is:

[0034]

[0035] in, is the calculation direction, is the direction of the first sub-cube corner element, is the normal vector of the symmetry cell boundary of the symmetry cell in which the first sub-solid corner element is located.

[0036] Preferably, the solid corner unit comprises a third solid corner unit and a fourth solid corner unit, wherein the third solid corner unit is located at a first side of the boundary of the wall unit, and the fourth solid corner unit is located at a second side of the boundary of the wall unit; the solid corner unit further comprises a fifth solid corner unit and a sixth solid corner unit, wherein the fifth solid corner unit is located at a first side of the boundary of the far field unit, and the sixth solid corner unit is located at a second side of the boundary of the far field unit; the unit boundary flux comprises: a wall unit boundary flux and a far field unit boundary flux;

[0037] The step of calculating the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit comprises:

[0038] The initial value of the spectral radiation intensity of the fourth solid corner element is calculated according to the initial value of the spectral radiation intensity of the solid corner element at the boundary of the wall element and the initial value of the spectral radiation intensity of the third solid corner element;

[0039] The calculation formula for the initial value of the spectral radiation intensity of the fourth solid corner element is:

[0040]

[0041] in, is the initial value of the spectral radiation intensity of the fourth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit, is the initial value of the spectral radiation intensity of the third solid corner element;

[0042] The calculation formula for the initial value of the spectral radiation intensity of the third solid corner element is:

[0043]

[0044] in, is the initial value of the spectral radiation intensity of the third solid corner element, is the temperature of the third sub-solid corner element, is the Boltzmann constant;

[0045] The initial value of the spectral radiation intensity of the sixth solid corner element is calculated according to the initial value of the spectral radiation intensity of the far-field element boundary solid corner element and the initial value of the spectral radiation intensity of the fifth solid corner element;

[0046] The calculation formula for the initial value of the spectral radiation intensity of the sixth solid corner element is:

[0047]

[0048] in, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the far-field unit, is the initial value of the spectral radiation intensity of the fifth solid corner element;

[0049] The calculation formula for the initial value of the spectral radiation intensity of the fifth solid corner element is:

[0050]

[0051] in, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the temperature of the fifth sub-solid corner element, is the Boltzmann constant;

[0052] The wall unit boundary flux is calculated according to the initial value of the spectral radiation intensity of the fourth solid corner unit and the initial value of the spectral radiation intensity of the third solid corner unit;

[0053] The calculation formula of the wall unit boundary flux is:

[0054]

[0055] in, is the wall unit boundary flux, is the initial value of the spectral radiation intensity of the third solid corner element, is the initial value of the spectral radiation intensity of the fourth solid corner element, is the direction weight of the first side of the wall unit boundary, The direction weight for the second side of the wall cell boundary, is the number of the sub-solid angle;

[0056] The far-field unit boundary flux is calculated based on the initial value of the spectral radiation intensity of the sixth solid corner unit and the initial value of the spectral radiation intensity of the fifth solid corner unit;

[0057] The calculation formula of the far-field unit boundary flux is:

[0058]

[0059] in, is the far-field unit boundary flux, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the directional weight for the first side of the far-field cell boundary, is the directional weight for the second side of the far-field cell boundary, is the number of the sub-solid angle.

[0060] Preferably, the step of calculating an initial value of the spectral radiation intensity of the first solid corner element according to the temperature of the first sub-solid corner element comprises:

[0061] The calculation formula for the initial value of the spectral radiation intensity of the first solid corner element is:

[0062]

[0063] in, is the initial value of the spectral radiation intensity of the first solid corner element, is the temperature of the first sub-solid corner element, is the Boltzmann constant.

[0064] Preferably, the step of calculating the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit comprises:

[0065] The calculation formula of the symmetric unit boundary flux is:

[0066]

[0067] in, is the symmetry unit boundary flux, is the initial value of the spectral radiation intensity of the first solid corner element, is the initial value of the spectral radiation intensity of the second solid corner element, is the direction weight for the first side of the symmetry unit boundary, is the direction weight for the second side of the symmetry cell boundary, is the number of the sub-solid angle.

[0068] The aircraft radiation heat assessment method provided in this application brings the following beneficial effects:

[0069] The present application provides a method for evaluating radiation heat of an aircraft, which divides a grid unit created on the aircraft to obtain a plurality of solid angle units, divides a unit boundary to obtain a plurality of unit boundary solid angle units, divides each solid angle unit boundary to obtain a plurality of unit boundary sub-solid angle units, and divides each solid angle unit to obtain a plurality of sub-solid angle units, so as to improve the resolution of each grid unit and each unit boundary, so as to improve the accuracy of the wall radiation heat flux value obtained by subsequent calculation.

[0070] In a second aspect, the present application further provides an aircraft radiation heat evaluation device, wherein the simulation device pre-creates an unstructured grid based on the aircraft to be tested, wherein the unstructured grid has a plurality of grid cells, and a cell boundary is set between every two adjacent grid cells; each grid cell is divided according to a preset number of solid angle cells to obtain a plurality of solid angle cells; each solid angle cell is divided according to a preset number of sub-solid angle cells to obtain a plurality of sub-solid angle cells; each cell boundary is divided according to a preset number of cell boundary solid angles to obtain a plurality of cell boundary solid angle cells; each cell boundary solid angle is divided according to a preset number of cell boundary sub-solid angles to obtain a plurality of cell boundary sub-solid angle cells; the device comprises:

[0071] An acquisition module, used for acquiring the temperature of each sub-solid corner unit and the temperature of each unit boundary sub-solid corner unit;

[0072] A data processing module, configured to calculate an initial value of the spectral radiation intensity of the unit boundary solid corner unit according to the temperature of the unit boundary sub-solid corner unit;

[0073] The data processing module is further used to calculate the initial value of the spectral radiation intensity of the solid corner unit according to the temperature of the sub-solid corner unit;

[0074] The data processing module is further configured to calculate the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit if the unit boundary is a wall unit boundary or a far-field unit boundary;

[0075] The data processing module is further configured to calculate the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit if the unit boundary is a symmetric unit boundary;

[0076] The data processing module is further used to obtain the spectral radiation intensity of the wall unit according to the unit boundary flux;

[0077] The data processing module is also used to calculate the wall radiation heat flux value according to the spectral radiation intensity of the wall unit, and evaluate the radiation heat of the aircraft to be tested according to the wall radiation heat flux value.

[0078] The aircraft radiation heat evaluation device provided in the embodiment of the present application has the same technical features as the aircraft radiation heat evaluation method provided in the above embodiment, so it can also solve the same technical problems and achieve the same technical effects.

[0079] In a third aspect, the present application provides a computing device, including a memory and a processor;

[0080] One or more computer programs are stored in the memory, and the one or more computer programs include instructions; when the instructions are executed by the processor, the computing device executes the method as described in any one of the first aspects.

[0081] In a fourth aspect, the present application provides a computer-readable storage medium, wherein the computer-readable storage medium is used to store a computer program, and the computer program is used to execute the method as described in any one of the first aspects.

[0082] Other features and advantages of the present application will be described in the following description, and partly become apparent from the description, or understood by practicing the present application. The purpose and other advantages of the present application are realized and obtained by the structures particularly pointed out in the description and the drawings.

[0083] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are specifically cited below and described in detail with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0084] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0085] Figure 1 A schematic diagram of a method for evaluating radiation heat of an aircraft provided in an embodiment of the present application;

[0086] Figure 2 Cloud diagram of the wall radiation heat flux value of the cylindrical aircraft provided in this application;

[0087] Figure 3 A comparative schematic diagram provided for an embodiment of the present application;

[0088] Figure 4 A schematic diagram of the structure of an aircraft radiation heat assessment device provided in an embodiment of the present application;

[0089] Figure 5 A schematic diagram of a computing device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0090] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution of the present application will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present application.

[0091] To facilitate understanding of this embodiment, the embodiments of the present application are described in detail below.

[0092] The embodiment of the present application provides a method for evaluating the radiant heat of an aircraft, which is applied to a simulation device. The simulation device pre-creates an unstructured grid based on the aircraft to be tested, wherein the unstructured grid has a plurality of grid cells, and a cell boundary is set between every two adjacent grid cells; each grid cell is divided according to a preset number of solid angle cells to obtain a plurality of solid angle cells; each solid angle cell is divided according to a preset number of sub-solid angle cells to obtain a plurality of sub-solid angle cells; each cell boundary is divided according to a preset number of cell boundary solid angles to obtain a plurality of cell boundary solid angle cells; each cell boundary solid angle is divided according to a preset number of cell boundary sub-solid angles to obtain a plurality of cell boundary sub-solid angle cells; Figure 1 As shown, Figure 1 A schematic flow chart of a method for evaluating radiation heat of an aircraft provided in an embodiment of the present application. The method comprises the following steps:

[0093] S101, a simulation device obtains the temperature of each sub-solid corner element and the temperature of each element boundary sub-solid corner element.

[0094] Specifically, taking a cylindrical aircraft as an example, the number of solid angle units divided in the zenith angle (longitude) direction is 5, and the number of solid angle units divided in the circular angle (latitude) direction is 10; the number of sub-solid angle units divided in the zenith angle (longitude) direction is 3, and the number of sub-solid angle units divided in the circular angle (latitude) direction is 3. The temperature of each sub-solid angle unit and the temperature of each unit boundary sub-solid angle unit are assigned to 1200K and input into the simulation device for calculation.

[0095] S102, the simulation device calculates the initial value of the spectral radiation intensity of the unit boundary solid corner unit according to the temperature of the unit boundary sub-solid corner unit.

[0096] Specifically, spectral radiation intensity is an important physical quantity that describes the radiation energy of a radiation source within a specific wavelength or frequency range. The initial value of spectral radiation intensity is calculated based on the temperature pre-assigned to the sub-solid angle unit at the unit boundary, so that the unit boundary flux can be calculated later.

[0097] S103, the simulation device calculates the initial value of the spectral radiation intensity of the solid corner element according to the temperature of the sub-solid corner element.

[0098] Specifically, the initial value of the spectral radiation intensity is calculated based on the temperature pre-assigned to the sub-solid corner unit, so that the unit boundary flux can be calculated subsequently.

[0099] S104, if the cell boundary is a wall cell boundary or a far-field cell boundary, the simulation device calculates the cell boundary flux according to the initial value of the spectral radiation intensity of the solid corner cell and the initial value of the spectral radiation intensity of the cell boundary solid corner cell.

[0100] Specifically, the cell boundary flux is a physical quantity passing through the cell boundary between two adjacent grid cells per unit time, and the calculated cell boundary flux is used to update the physical quantity state inside the two adjacent grid cells, for example, the temperature state.

[0101] S105: If the cell boundary is a symmetrical cell boundary, the simulation device calculates the cell boundary flux according to the initial value of the spectral radiation intensity of the solid corner cell.

[0102] Specifically, since the cell boundary condition of the symmetric cell boundary between two adjacent symmetric cells cannot be determined, it is necessary to calculate the cell boundary flux according to the initial value of the spectral radiation intensity of the solid corner cell.

[0103] S106, the simulation device obtains the spectral radiation intensity of the wall unit according to the unit boundary flux.

[0104] Specifically, the calculation formula of the radiation transfer equation is:

[0105]

[0106] Where R is the radiation transfer equation, is the cell boundary flux, is the area of ​​the cell boundary, is the volume of the grid unit, a is the absorption coefficient, a=0.1, is the scattering coefficient, is the temperature of the solid corner element, is the spectral radiation intensity of the mth wall unit, is the spectral radiation intensity of the nth wall unit, is the direction of the mth solid corner element, is the direction of the nth solid corner element, is the (size) steradian of the nth solid angle unit, is the (size) steradian of the mth solid angle unit, is the Boltzmann constant.

[0107] Let R = 0 and use Newton's method to solve the radiation transfer equation. The iterative formula is as follows:

[0108]

[0109] Where N is the number of iterations, R is the radiation transfer equation, and I is the solution of the radiation transfer equation (the spectral radiation intensity of the wall unit).

[0110] The above iterative formula is iteratively solved using GMRES (Generalized Minimal Residual) to obtain the spectral radiation intensity of the wall unit. When the residual of two iterations of the radiation transfer equation is less than the preset threshold, the solution of the radiation transfer equation is converged, and the solution of the radiation transfer equation obtained at this time is the spectral radiation intensity of the wall unit.

[0111] S107, the simulation device calculates the wall radiation heat flux value according to the spectral radiation intensity of the wall unit, and evaluates the radiation heat of the aircraft to be tested according to the wall radiation heat flux value.

[0112] Specifically, the calculation formula of the wall radiation heat flux value is:

[0113]

[0114] in, is the wall radiation heat flux, is the number of spectral generations, =1, is the wall emissivity, =0.9, is the Boltzmann constant, is the temperature of the sub-solid angle of the wall unit boundary, =273k, is the number of solid angles divided by the circular angle (latitude) direction, =10, is the spectral radiation intensity of the mth wall unit, is the direction weight of the mth solid corner element of the wall element, It is the spectral sequence number.

[0115] The wall radiation heat flux value calculated above has high accuracy and can accurately reflect the radiation heat environment of the aircraft surface. Therefore, the radiation heat of the aircraft can be evaluated based on the more accurate radiation heat flux value. The wall radiation heat flux value can cover multiple areas of the aircraft surface, thereby providing comprehensive radiation heat information, which can more comprehensively evaluate the radiation heat of the aircraft, help to comprehensively evaluate the radiation heat protection performance of the aircraft, and provide a comprehensive reference for the design optimization of the aircraft.

[0116] like Figure 2 As shown, Figure 2 This is a cloud diagram of the wall radiation heat flux value of a cylindrical aircraft provided in this application. Due to the limited number of solid corner units, the wall radiation heat flux value shows a fluctuating change, and the peak heat flux value is about 105.5kW / m 2 The trough heat flow value is about 101.5kW / m 2 .like Figure 3 As shown, Figure 3 A comparative schematic diagram provided in an embodiment of the present application. The peak heat flux value of the wall radiation heat flux value calculated in an aircraft radiation heat evaluation method provided in an embodiment of the present application is about 105.5kW / m 2 The trough heat flow value is about 101.5kW / m 2 The peak heat flux value of the wall radiation heat flux calculated in the prior art is about 105.kW / m 2 , the trough heat flow value is about 100.8kW / m 2 The wall radiation heat flux value calculated in an aircraft radiation heat evaluation method provided in an embodiment of the present application has a small fluctuation amplitude, which verifies that the method can effectively improve the resolution of the calculation results and the simulation accuracy of the radiation heat flux, reduce the volatility of the calculation results caused by the limited number of solid angle unit divisions due to the limitation of the calculation memory, and realize the high-precision simulation of the wall radiation heat flux value of the high-temperature medium.

[0117] The embodiment of the present application provides a method for evaluating radiation heat of an aircraft, wherein the method divides a grid unit created on the aircraft to obtain a plurality of solid angle units, divides a unit boundary to obtain a plurality of unit boundary solid angle units, divides each solid angle unit boundary to obtain a plurality of unit boundary sub-solid angle units, and divides each solid angle unit to obtain a plurality of sub-solid angle units, so as to improve the resolution of each grid unit and each unit boundary, so as to improve the accuracy of the wall radiation heat flux value obtained by subsequent calculation. In the prior art, only each grid unit is divided to obtain a plurality of solid angle units. Due to the limitation of computer memory, the number of divided solid angle units should not be too large, resulting in that the resolution of the grid unit cannot be further improved, and thus the accuracy of the wall radiation heat flux value obtained by subsequent calculation cannot be further improved. Compared with the prior art, in the method, each solid angle unit is divided into a plurality of sub-solid angle units, which greatly improves the resolution of the grid unit, and the iterative solution process of the radiation transfer equation and the calculation process of the wall radiation heat flux value only need to calculate the various parameters of the solid angle unit, and only the various parameters of each solid angle unit occupy the computer memory. This method improves the resolution of the grid cells, thereby improving the accuracy of the wall radiation heat flux values ​​obtained in subsequent calculations, and does not take up too much computer memory.

[0118] The following is an introduction to the method in which the simulation device calculates the initial value of the spectral radiation intensity of the solid corner unit according to the temperature of the sub-solid corner unit. The solid corner unit includes a first solid corner unit and a second solid corner unit; the sub-solid corner unit includes a first sub-solid corner unit and a second sub-solid corner unit; each first solid corner unit and each second solid corner unit are symmetrically distributed in each two adjacent symmetrical units about the boundary of the symmetrical unit; the simulation device obtains the direction of each first sub-solid corner unit; each calculated direction is calculated according to the direction of each first sub-solid corner unit; each direction angle formed by each calculated direction and the direction of each first sub-solid corner unit is obtained; each direction angle is compared with each other to obtain the direction of the second sub-solid corner unit; wherein the direction of the second sub-solid corner unit is the calculated direction corresponding to the direction angle with the smallest angle; the initial value of the spectral radiation intensity of the first solid corner unit is calculated according to the temperature of the first sub-solid corner unit; the initial value of the spectral radiation intensity of the second sub-solid corner unit corresponding to the direction of the second sub-solid corner unit is determined by the initial value of the spectral radiation intensity of the first solid corner unit.

[0119] Among them, the calculation formula for the above calculation direction is:

[0120]

[0121] in, To calculate the direction, is the direction of the first sub-solid corner element, is the normal vector of the symmetry cell boundary of the symmetry cell in which the first sub-solid corner element is located.

[0122] Specifically, since the condition of the symmetric cell boundary cannot be determined, it is necessary to calculate the subsequent symmetric cell boundary flux by obtaining the temperature of the first sub-solid corner cell and the temperature of the second sub-solid corner cell. Since the first sub-solid corner cell and the second sub-solid corner cell are symmetrical about the symmetric cell boundary, the temperature of the first sub-solid corner cell can also be assigned to the second sub-solid corner cell. The initial value of the spectral radiation intensity of the first sub-solid corner cell and the initial value of the spectral radiation intensity of the second sub-solid corner cell calculated in this way are also equal.

[0123] In this way, the temperature of the first sub-solid corner unit can be assigned to the second sub-solid corner unit, which improves the efficiency of the assignment process and saves the time for calculating the initial value of the spectral radiation intensity of the first solid corner unit and the initial value of the spectral radiation intensity of the second sub-solid corner unit.

[0124] The following introduces the method in which the simulation device calculates the initial value of the spectral radiation intensity of the unit boundary solid angle unit according to the temperature of the unit boundary sub-solid angle. The unit boundary sub-solid angle includes the wall unit boundary sub-solid angle unit and the far-field unit boundary sub-solid angle unit; the unit boundary solid angle unit includes the wall unit boundary solid angle unit and the far-field unit boundary solid angle unit; if the unit boundary sub-solid angle is a wall unit boundary sub-solid angle, the simulation device calculates the initial value of the spectral radiation intensity of the wall unit boundary solid angle unit according to the temperature of the wall unit boundary sub-solid angle.

[0125] The calculation formula for the initial value of the spectral radiation intensity of the solid corner unit at the wall unit boundary is:

[0126]

[0127] in, is the initial value of the spectral radiation intensity of the solid corner unit at the wall unit boundary, is the wall emissivity, is the Boltzmann constant, is the temperature of the sub-solid angle of the wall unit boundary, is the spatial direction of the wall element, is the set of directions of the solid corner elements of all wall elements, is the spectral radiance in the direction of the solid corner unit of one wall unit in the jth wall unit, is the normal vector of the wall element boundary of the wall element, is the spherical degree of the solid angle unit; if the unit boundary sub-solid angle is the far-field unit boundary sub-solid angle, the simulation device calculates the initial value of the spectral radiation intensity of the far-field unit boundary solid angle unit according to the temperature of the far-field unit boundary sub-solid angle.

[0128] The calculation formula for the initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary is:

[0129]

[0130] in, is the initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary, is the Boltzmann constant, is the temperature of the far-field cell boundary sub-solid angle.

[0131] Specifically, the far-field unit boundary condition is a boundary condition artificially set during the numerical simulation process, which is used to simulate the flow field boundary far away from the object (the aircraft to be tested). In actual flow, the flow field disturbance generated by the aircraft will propagate to infinity without being reflected. However, in numerical calculations, it is impossible to take the infinite boundary of the calculation area, and the outer boundary can only be taken as the finite boundary. The initial value of the spectral radiation intensity of the far-field unit boundary solid angle unit is calculated based on the temperature of the far-field unit boundary sub-solid angle, so that the far-field unit boundary flux can be calculated based on the initial value of the spectral radiation intensity of the far-field unit boundary solid angle unit.

[0132] The wall unit boundary is a boundary condition used to simulate the interaction between a fluid, such as a mixture of carbon dioxide and water, and a solid (the aircraft under test) interface. In fluid flow, the wall unit boundary plays a role in limiting the fluid area or solid area, and is an indispensable component of fluid flow. The initial value of the spectral radiation intensity of the wall unit boundary solid angle unit is calculated based on the temperature of the wall unit boundary sub-solid angle, so that the wall unit boundary flux can be calculated based on the initial value of the spectral radiation intensity of the wall unit boundary solid angle unit.

[0133] In this way, the calculated initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary can reflect the flow field disturbance generated by the aircraft to the maximum extent, so that the subsequent far-field unit boundary flux is more in line with reality. The calculated initial value of the spectral radiation intensity of the solid corner unit at the wall unit boundary can reflect the flow field disturbance of the aircraft wall, so that the subsequent wall unit boundary flux is more in line with reality.

[0134] The following is an introduction to the method in which the simulation device calculates the unit boundary flux based on the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit. The solid corner unit also includes a third solid corner unit and a fourth solid corner unit, the third solid corner unit is on the first side of the wall unit boundary, and the third solid corner unit is on the second side of the wall unit boundary; the solid corner unit also includes a fifth solid corner unit and a sixth solid corner unit, the fifth solid corner unit is on the first side of the far field unit boundary, and the sixth solid corner unit is on the second side of the far field unit boundary; the unit boundary flux includes: the wall unit boundary flux and the far field unit boundary flux; the simulation device calculates the initial value of the spectral radiation intensity of the fourth solid corner unit based on the initial value of the spectral radiation intensity of the wall unit boundary solid corner unit and the initial value of the spectral radiation intensity of the third solid corner unit, and the calculation formula for the initial value of the spectral radiation intensity of the fourth solid corner unit is:

[0135]

[0136] in, is the initial value of the spectral radiant intensity of the fourth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the wall unit boundary, is the initial value of the spectral radiation intensity of the third solid corner element.

[0137] The calculation formula for the initial value of the spectral radiation intensity of the third solid corner element is:

[0138]

[0139] in, is the initial value of the spectral radiation intensity of the third solid corner element, is the temperature of the third sub-solid corner element, is the Boltzmann constant.

[0140] The simulation device calculates the initial value of the spectral radiation intensity of the sixth solid corner element according to the initial value of the spectral radiation intensity of the solid corner element at the far-field element boundary and the initial value of the spectral radiation intensity of the fifth solid corner element. The calculation formula of the initial value of the spectral radiation intensity of the sixth solid corner element is:

[0141]

[0142] in, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary, is the initial value of the spectral radiation intensity of the fifth solid corner element.

[0143] The calculation formula for the initial value of the spectral radiation intensity of the fifth solid corner element is:

[0144]

[0145] in, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the temperature of the fifth sub-solid corner element, is the Boltzmann constant.

[0146] The simulation device calculates the wall unit boundary flux according to the initial value of the spectral radiation intensity of the fourth solid corner unit and the initial value of the spectral radiation intensity of the third solid corner unit. The calculation formula of the wall unit boundary flux is:

[0147]

[0148] in, is the wall unit boundary flux, is the initial value of the spectral radiation intensity of the third solid corner element, is the initial value of the spectral radiant intensity of the fourth solid corner element, is the direction weight of the first side of the wall element boundary, Direction weight for the second side of the wall cell boundary, is the number of the sub-solid angle.

[0149] The simulation device calculates the far-field unit boundary flux according to the initial value of the spectral radiation intensity of the sixth solid corner unit and the initial value of the spectral radiation intensity of the fifth solid corner unit. The calculation formula of the far-field unit boundary flux is:

[0150]

[0151] in, is the far-field element boundary flux, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the directional weight for the first side of the far-field cell boundary, is the directional weight for the second side of the far-field cell boundary, is the number of the sub-solid angle.

[0152] Specifically, the calculation formula of the normal vector of the first side of the wall unit boundary is:

[0153]

[0154] in, is the direction weight of the first side of the wall element boundary, is the direction of the mth solid corner element, is the direction of the wall cell on which the first side of the wall cell boundary lies, is the (size) steradian of the mth solid angle unit.

[0155] The normal vector to the second side of the wall element boundary is given by:

[0156]

[0157] in, Direction weight for the second side of the wall cell boundary, is the direction of the mth solid corner element, is the direction of the wall cell on the second side of the wall cell boundary, is the (size) steradian of the mth solid angle unit.

[0158] The normal vector to the first side of the far-field cell boundary is given by:

[0159]

[0160] in, is the directional weight for the first side of the far-field cell boundary, is the direction of the mth solid corner element, is the direction of the far-field cell at the first side of the far-field cell boundary, is the (size) steradian of the mth solid angle unit.

[0161] The normal vector to the second side of the far-field cell boundary is given by:

[0162]

[0163] in, is the directional weight for the second side of the far-field cell boundary, is the direction of the mth solid corner element, is the direction of the far-field cell on the second side of the far-field cell boundary, is the (size) steradian of the mth solid angle unit.

[0164] The (large) steradian of the mth solid corner element is calculated as:

[0165]

[0166] in, is the (size) steradian of the mth solid angle unit, is the zenith angle direction of the mth solid corner element, is the dome angle direction of the mth solid corner element, is the zenith angle direction of the solid corner unit, is the dome angle direction of the solid corner element, is the variable of the zenith angle direction of the solid angle unit, is the variable for the top angle direction of the cube corner element.

[0167] The above-mentioned wall unit boundary flux is a physical quantity passing through the wall unit boundary between two adjacent wall units per unit time, and the calculated wall unit boundary flux is used to update the physical quantity state inside the two adjacent wall units, for example, the wall temperature state. The above-mentioned far-field unit boundary flux is a physical quantity passing through the far-field unit boundary between two adjacent far-field units per unit time, and the calculated far-field unit boundary flux is used to update the physical quantity state inside the two adjacent far-field units, for example, the far-field temperature state.

[0168] In this method, the wall unit boundary flux can reflect the change of the wall temperature state of the wall unit boundary, and the wall unit boundary flux can make the subsequent iterative solution of the radiation transfer equation more accurate. The far-field unit boundary flux can reflect the change of the far-field temperature state of the far-field unit boundary, and the far-field unit boundary flux can make the subsequent iterative solution of the radiation transfer equation more accurate.

[0169] The following describes how the simulation device calculates the initial value of the spectral radiation intensity of the first solid corner element according to the temperature of the first sub-solid corner element. The calculation formula for the initial value of the spectral radiation intensity of the first solid corner element is:

[0170]

[0171] in, is the initial value of the spectral radiant intensity of the first solid corner element, is the temperature of the first sub-solid corner element, is the Boltzmann constant.

[0172] Specifically, since the first solid corner unit and the second solid corner unit are symmetrical to each other, the initial value of the spectral radiation intensity of the first solid corner unit is used to assign a value to the second solid corner unit, so that the unit boundary flux can be subsequently calculated based on the initial value of the spectral radiation intensity of the first solid corner unit and the initial value of the spectral radiation intensity of the second solid corner unit.

[0173] In this method, according to the thermal radiation theory, the radiation intensity of an object is closely related to its temperature. By accurately measuring the temperature of the first sub-solid angle unit, the initial value of the spectral radiation intensity of the symmetric unit where the first sub-solid angle unit is located is directly calculated based on the physical law (Planck radiation law), thereby improving the accuracy of the calculation.

[0174] Compared with other indirect means (measuring the radiation flux and then inferring the radiation intensity), this method can reduce the accumulation and transmission of errors and ensure the accuracy of the results.

[0175] The following is an introduction to the way in which the simulation device calculates the unit boundary flux based on the initial value of the spectral radiation intensity of the solid corner unit. The calculation formula for the symmetric unit boundary flux is:

[0176]

[0177] in, is the symmetric unit boundary flux, is the initial value of the spectral radiant intensity of the first solid corner element, is the initial value of the spectral radiant intensity of the second solid corner element, is the direction weight for the first side of the symmetry element boundary, is the direction weight for the second side of the symmetry cell boundary, is the number of the sub-solid angle.

[0178] Specifically, the above-mentioned symmetric unit boundary flux is a physical quantity passing through the symmetric unit boundary between two adjacent symmetric units in unit time, and the calculated symmetric unit boundary flux is used to update the physical quantity state inside the two adjacent symmetric units.

[0179] In this way, the symmetric unit boundary flux can reflect the change state of the symmetric temperature state of the symmetric unit boundary. The symmetric unit boundary flux can make the subsequent iterative solution results of the radiation transfer equation more accurate.

[0180] On the basis of the above method embodiment, the embodiment of the present application also provides an aircraft radiation heat evaluation device, the simulation device pre-creates an unstructured grid based on the aircraft to be tested, the unstructured grid has multiple grid units, and a unit boundary is set between every two adjacent grid units; each grid unit is divided according to a preset number of solid angle units to obtain multiple solid angle units; each solid angle unit is divided according to a preset number of sub-solid angle units to obtain multiple sub-solid angle units; each unit boundary is divided according to a preset number of unit boundary solid angles to obtain multiple unit boundary solid angle units; each unit boundary solid angle is divided according to a preset number of unit boundary sub-solid angles to obtain multiple unit boundary sub-solid angle units; the device includes: an acquisition module 41 and a data processing module 42. The functions of each module are as follows:

[0181] An acquisition module 41 is used to acquire the temperature of each sub-solid corner element and the temperature of each element boundary sub-solid corner element;

[0182] A data processing module 42 is used to calculate the initial value of the spectral radiation intensity of the unit boundary solid angle unit according to the temperature of the unit boundary sub-solid angle unit;

[0183] The data processing module 42 is further used to calculate the initial value of the spectral radiation intensity of the solid corner unit according to the temperature of the sub-solid corner unit;

[0184] The data processing module 42 is further configured to calculate the cell boundary flux according to the initial value of the spectral radiation intensity of the solid corner cell and the initial value of the spectral radiation intensity of the cell boundary solid corner cell if the cell boundary is a wall cell boundary or a far-field cell boundary;

[0185] The data processing module 42 is further configured to calculate the cell boundary flux according to the initial value of the spectral radiation intensity of the solid corner cell if the cell boundary is a symmetrical cell boundary;

[0186] The data processing module 42 is also used to obtain the spectral radiation intensity of the wall unit according to the unit boundary flux;

[0187] The data processing module 42 is further used to calculate the wall radiation heat flux value according to the spectral radiation intensity of the wall unit, and evaluate the radiation heat of the aircraft to be tested according to the wall radiation heat flux value.

[0188] Preferably, the solid corner element comprises a first solid corner element and a second solid corner element; the sub-solid corner element comprises a first sub-solid corner element and a second sub-solid corner element; each of the first solid corner element and each of the second solid corner elements are symmetrically distributed in every two adjacent symmetric cells about the symmetric cell boundary;

[0189] An acquisition module 41 is specifically configured to acquire a direction of each first sub-solid corner unit;

[0190] A data processing module 42 is specifically configured to obtain a plurality of calculation directions according to the direction of each first sub-solid angle unit;

[0191] An acquisition module 41 is specifically used to acquire each direction angle formed by each calculation direction and the direction of each first sub-solid angle unit;

[0192] The data processing module 42 is specifically used to compare each direction angle with each other to obtain the direction of the second sub-solid corner element; wherein the direction of the second sub-solid corner element is the calculated direction corresponding to the direction angle with the smallest angle;

[0193] The data processing module 42 is specifically configured to calculate an initial value of the spectral radiation intensity of the first sub-solid corner element according to the temperature of the first sub-solid corner element;

[0194] The data processing module 42 is specifically configured to determine the initial value of the spectral radiation intensity of the second sub-solid corner element corresponding to the direction of the second sub-solid corner element according to the initial value of the spectral radiation intensity of the first solid corner element.

[0195] Preferably, the unit boundary sub-solid angles include wall unit boundary sub-solid angle units and far field unit boundary sub-solid angle units; the unit boundary solid angle units include wall unit boundary solid angle units and far field unit boundary solid angle units;

[0196] The data processing module 42 is specifically used to calculate the initial value of the spectral radiation intensity of the unit boundary solid angle unit according to the temperature of the unit boundary sub-solid angle, including:

[0197] The data processing module 42 is specifically configured to calculate the initial value of the spectral radiation intensity of the wall unit boundary solid angle unit according to the temperature of the wall unit boundary sub-solid angle if the unit boundary sub-solid angle is a wall unit boundary sub-solid angle;

[0198] The calculation formula for the initial value of the spectral radiation intensity of the solid corner unit at the wall unit boundary is:

[0199]

[0200] in, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit, is the wall emissivity, is the Boltzmann constant, is the temperature of the sub-solid angle of the wall unit boundary, is the spatial direction of the wall unit, is the set of directions of the solid corner elements of all wall elements, is the spectral radiance in the direction of the solid corner unit of one wall unit in the jth wall unit, is the normal vector of the wall unit boundary of the wall unit, is the steradian of the solid angle unit;

[0201] The data processing module 42 is specifically configured to calculate the initial value of the spectral radiation intensity of the far-field unit boundary solid angle unit according to the temperature of the far-field unit boundary sub-solid angle if the unit boundary sub-solid angle is a far-field unit boundary sub-solid angle;

[0202] The calculation formula for the initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary is:

[0203]

[0204] in, is the initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary, is the Boltzmann constant, is the temperature of the far-field cell boundary sub-solid angle.

[0205] Preferably, the data processing module 42 is specifically configured to calculate the calculation direction according to the following formula:

[0206]

[0207] in, To calculate the direction, is the direction of the first sub-solid corner element, is the normal vector of the symmetry cell boundary of the symmetry cell in which the first sub-solid corner element is located.

[0208] Preferably, the solid corner unit further comprises a third solid corner unit and a fourth solid corner unit, the third solid corner unit is located at a first side of the wall unit boundary, and the fourth solid corner unit is located at a second side of the wall unit boundary; the solid corner unit further comprises a fifth solid corner unit and a sixth solid corner unit, the fifth solid corner unit is located at a first side of the far field unit boundary, and the sixth solid corner unit is located at a second side of the far field unit boundary; the unit boundary flux comprises: a wall unit boundary flux and a far field unit boundary flux;

[0209] The data processing module 42 is specifically used to calculate the initial value of the spectral radiation intensity of the fourth solid corner unit according to the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit and the initial value of the spectral radiation intensity of the third solid corner unit;

[0210] The calculation formula for the initial value of the spectral radiation intensity of the fourth solid corner element is:

[0211]

[0212] in, is the initial value of the spectral radiant intensity of the fourth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the wall unit boundary, is the initial value of the spectral radiation intensity of the third solid corner element;

[0213] The calculation formula for the initial value of the spectral radiation intensity of the third solid corner element is:

[0214]

[0215] in, is the initial value of the spectral radiation intensity of the third solid corner element, is the temperature of the third sub-solid corner element, is the Boltzmann constant;

[0216] The data processing module 42 is specifically configured to calculate the initial value of the spectral radiation intensity of the sixth solid corner element according to the initial value of the spectral radiation intensity of the far-field element boundary solid corner element and the initial value of the spectral radiation intensity of the fifth solid corner element;

[0217] The calculation formula for the initial value of the spectral radiation intensity of the sixth solid corner element is:

[0218]

[0219] in, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the far-field unit boundary, is the initial value of the spectral radiation intensity of the fifth solid corner element;

[0220] The calculation formula for the initial value of the spectral radiation intensity of the fifth solid corner element is:

[0221]

[0222] in, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the temperature of the fifth sub-solid corner element, is the Boltzmann constant;

[0223] The data processing module 42 is specifically configured to calculate the wall unit boundary flux according to the initial value of the spectral radiation intensity of the fourth solid corner unit and the initial value of the spectral radiation intensity of the third solid corner unit;

[0224] The calculation formula of the wall unit boundary flux is:

[0225]

[0226] in, is the wall unit boundary flux, is the initial value of the spectral radiation intensity of the third solid corner element, is the initial value of the spectral radiant intensity of the fourth solid corner element, is the direction weight of the first side of the wall element boundary, Direction weight for the second side of the wall cell boundary, is the number of the sub-solid angle;

[0227] The data processing module 42 is specifically configured to calculate the far-field unit boundary flux according to the initial value of the spectral radiation intensity of the sixth solid corner unit and the initial value of the spectral radiation intensity of the fifth solid corner unit;

[0228] The calculation formula for the far-field element boundary flux is:

[0229]

[0230] in, is the far-field element boundary flux, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the directional weight for the first side of the far-field cell boundary, is the directional weight for the second side of the far-field cell boundary, is the number of the sub-solid angle.

[0231] Preferably, the data processing module 42 is specifically configured to calculate an initial value of the spectral radiation intensity of the first solid corner element according to the following formula:

[0232]

[0233] in, is the initial value of the spectral radiant intensity of the first solid corner element, is the temperature of the first sub-solid corner element, is the Boltzmann constant.

[0234] Preferably, the data processing module 42 is specifically used to calculate the symmetric unit boundary flux according to the following formula:

[0235]

[0236] in, is the symmetric unit boundary flux, is the initial value of the spectral radiant intensity of the first solid corner element, is the initial value of the spectral radiant intensity of the second solid corner element, is the direction weight for the first side of the symmetry element boundary, is the direction weight for the second side of the symmetry cell boundary, is the number of the sub-solid angle.

[0237] The aircraft radiation heat evaluation device provided in the embodiment of the present application has the same technical features as the aircraft radiation heat evaluation method provided in the above embodiment, so it can also solve the same technical problems and achieve the same technical effects.

[0238] The present application also provides a computing device. Figure 5As shown, this figure is a schematic diagram of a computing device provided in an embodiment of the present application, and the computing device 400 includes a bus 401, a processor 402, a communication interface 403 and a memory 404. The processor 402, the memory 404 and the communication interface 403 communicate with each other through the bus 401.

[0239] The bus 401 may be a peripheral component interconnect (PCI) bus or an extended industry standard architecture (EISA) bus. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 5 Only one thick line is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0240] The processor 402 may be any one or more of a central processing unit (CPU), a graphics processing unit (GPU), a microprocessor (MP), or a digital signal processor (DSP).

[0241] The communication interface 403 is used for communicating with the outside. The memory 404 may include a volatile memory, such as a random access memory (RAM). The memory 404 may also include a non-volatile memory, such as a read-only memory (ROM), a flash memory, a hard disk drive (HDD) or a solid state drive (SSD).

[0242] The memory 404 stores executable codes, and the processor 402 executes the executable codes to perform the aforementioned aircraft radiation heat assessment method.

[0243] The embodiment of the present application also provides a computer-readable storage medium. The computer-readable storage medium may be any available medium that can be stored by a computing device or a data storage device such as a data center that contains one or more available media. The available medium may be a magnetic medium (such as a floppy disk, a hard disk, a tape), an optical medium (such as a DVD), or a semiconductor medium (such as a solid-state hard disk). The computer-readable storage medium includes instructions that instruct the computing device to execute the above-mentioned aircraft radiation heat assessment method.

[0244] The embodiment of the present application further provides a computer program product, which includes one or more computer instructions. When the computer instructions are loaded and executed on a computing device, the process or function described in the embodiment of the present application is generated in whole or in part.

[0245] The computer instructions may be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium. For example, the computer instructions may be transmitted from one website, computer or data center to another website, computer or data center via wired (e.g., coaxial cable, optical fiber) or wireless (e.g., infrared, wireless, microwave, etc.) means.

[0246] When the computer program product is executed by a computer, the computer executes any of the aforementioned aircraft radiation heat assessment methods. The computer program product may be a software installation package, and when any of the aforementioned aircraft radiation heat assessment methods is needed, the computer program product may be downloaded and executed on a computer.

[0247] The descriptions of the processes or structures corresponding to the above-mentioned figures have different emphases. For parts that are not described in detail in a certain process or structure, please refer to the relevant descriptions of other processes or structures.

[0248] The above description is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present application should be included in the protection scope of the present application.

Claims

1. A method for evaluating aircraft radiation heat, characterized in that: The method is applied to a simulation device, wherein the simulation device preliminarily creates an unstructured grid based on an aircraft to be tested, wherein the unstructured grid has a plurality of grid cells, and a cell boundary is set between every two adjacent grid cells; each grid cell is divided according to a preset number of solid angle cells to obtain a plurality of solid angle cells; each solid angle cell is divided according to a preset number of sub-solid angle cells to obtain a plurality of sub-solid angle cells; each cell boundary is divided according to a preset number of cell boundary solid angles to obtain a plurality of cell boundary solid angle cells; Dividing each unit boundary solid angle according to a preset number of unit boundary sub-solid angles to obtain a plurality of unit boundary sub-solid angle units; the method comprises: Obtain the temperature of each sub-solid corner cell and the temperature of each cell boundary sub-solid corner cell; The initial value of the spectral radiation intensity of the unit boundary solid corner unit is obtained by calculation according to the temperature of the unit boundary sub-solid corner unit; Calculating an initial value of the spectral radiation intensity of the solid corner element according to the temperature of the sub-solid corner element; If the unit boundary is a wall unit boundary or a far-field unit boundary, the unit boundary flux is calculated according to the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit; If the unit boundary is a symmetric unit boundary, the unit boundary flux is calculated according to the initial value of the spectral radiation intensity of the solid corner unit; Obtaining the spectral radiation intensity of the wall unit according to the unit boundary flux; The wall radiation heat flux value is calculated according to the spectral radiation intensity of the wall unit, and the radiation heat of the aircraft to be tested is evaluated according to the wall radiation heat flux value.

2. The aircraft radiation heat assessment method according to claim 1, characterized in that: The solid corner element comprises a first solid corner element and a second solid corner element; the sub-solid corner element comprises a first sub-solid corner element and a second sub-solid corner element; each first solid corner element and each second solid corner element are symmetrically distributed in every two adjacent symmetric cells about the symmetric cell boundary; The step of calculating an initial value of the spectral radiation intensity of the solid corner element according to the temperature of the sub-solid corner element comprises: obtaining a direction of each first sub-solid corner element; Each calculated direction is calculated based on the direction of each first sub-solid corner element; Obtain each direction angle formed by each calculated direction and the direction of each first sub-solid corner element; Comparing each direction angle with each other to obtain the direction of the second sub-solid corner element; wherein the direction of the second sub-solid corner element is the calculated direction corresponding to the direction angle with the smallest angle; An initial value of the spectral radiation intensity of the first solid corner element is calculated according to the temperature of the first sub-solid corner element; The initial value of the spectral radiation intensity of the second sub-cube corner element corresponding to the direction of the second sub-cube corner element is determined by the initial value of the spectral radiation intensity of the first cube corner element.

3. The aircraft radiation heat assessment method according to claim 1, characterized in that: The unit boundary sub-solid angles include wall unit boundary sub-solid angle units and far-field unit boundary sub-solid angle units; the unit boundary solid angle units include wall unit boundary solid angle units and far-field unit boundary solid angle units; The step of calculating the initial value of the spectral radiation intensity of the unit boundary solid corner element according to the temperature of the unit boundary sub-solid corner element comprises: If the unit boundary sub-solid angle is the wall unit boundary sub-solid angle, then the initial value of the spectral radiation intensity of the wall unit boundary solid angle unit is calculated according to the temperature of the wall unit boundary sub-solid angle; The calculation formula for the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit is: in, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit, is the wall emissivity, is the Boltzmann constant, is the temperature of the sub-solid angle of the wall unit boundary, is the spatial direction of the wall unit, is the set of directions of the solid corner elements of all wall elements, is the spectral radiance in the direction of the solid corner unit of one wall unit in the jth wall unit, is the normal vector of the wall unit boundary of the wall unit, is the steradian of the solid angle unit; If the unit boundary sub-solid angle is the far-field unit boundary sub-solid angle, then calculating the initial value of the spectral radiation intensity of the far-field unit boundary solid angle unit according to the temperature of the far-field unit boundary sub-solid angle; The calculation formula for the initial value of the spectral radiation intensity of the far-field unit boundary solid corner unit is: in, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the far-field unit, is the Boltzmann constant, is the temperature of the far-field unit boundary sub-solid angle.

4. The aircraft radiation heat assessment method according to claim 2, characterized in that: The step of obtaining each calculated direction according to the direction of each first sub-solid corner element comprises: The calculation formula for the calculation direction is: in, is the calculation direction, is the direction of the first sub-cube corner element, is the normal vector of the symmetry cell boundary of the symmetry cell in which the first sub-solid corner element is located.

5. The aircraft radiation heat assessment method according to claim 3, characterized in that: The solid corner unit comprises a third solid corner unit and a fourth solid corner unit, wherein the third solid corner unit is located at a first side of the boundary of the wall unit, and the fourth solid corner unit is located at a second side of the boundary of the wall unit; the solid corner unit further comprises a fifth solid corner unit and a sixth solid corner unit, wherein the fifth solid corner unit is located at a first side of the boundary of the far field unit, and the sixth solid corner unit is located at a second side of the boundary of the far field unit; the unit boundary flux comprises: a wall unit boundary flux and a far field unit boundary flux; The step of calculating the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit comprises: The initial value of the spectral radiation intensity of the fourth solid corner element is calculated according to the initial value of the spectral radiation intensity of the solid corner element at the boundary of the wall element and the initial value of the spectral radiation intensity of the third solid corner element; The calculation formula for the initial value of the spectral radiation intensity of the fourth solid corner element is: in, is the initial value of the spectral radiation intensity of the fourth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the wall unit, is the initial value of the spectral radiation intensity of the third solid corner element; The calculation formula for the initial value of the spectral radiation intensity of the third solid corner element is: in, is the initial value of the spectral radiation intensity of the third solid corner element, is the temperature of the third sub-solid corner element, is the Boltzmann constant; The initial value of the spectral radiation intensity of the sixth solid corner element is calculated according to the initial value of the spectral radiation intensity of the far-field element boundary solid corner element and the initial value of the spectral radiation intensity of the fifth solid corner element; The calculation formula for the initial value of the spectral radiation intensity of the sixth solid corner element is: in, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the initial value of the spectral radiation intensity of the solid corner unit at the boundary of the far-field unit, is the initial value of the spectral radiation intensity of the fifth solid corner element; The calculation formula for the initial value of the spectral radiation intensity of the fifth solid corner element is: in, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the temperature of the fifth sub-solid corner element, is the Boltzmann constant; The wall unit boundary flux is calculated according to the initial value of the spectral radiation intensity of the fourth solid corner unit and the initial value of the spectral radiation intensity of the third solid corner unit; The calculation formula of the wall unit boundary flux is: in, is the wall unit boundary flux, is the initial value of the spectral radiation intensity of the third solid corner element, is the initial value of the spectral radiation intensity of the fourth solid corner element, is the direction weight of the first side of the wall unit boundary, The direction weight for the second side of the wall cell boundary, is the number of the sub-solid angle; The far-field unit boundary flux is calculated based on the initial value of the spectral radiation intensity of the sixth solid corner unit and the initial value of the spectral radiation intensity of the fifth solid corner unit; The calculation formula of the far-field unit boundary flux is: in, is the far-field unit boundary flux, is the initial value of the spectral radiation intensity of the fifth solid corner element, is the initial value of the spectral radiation intensity of the sixth solid corner element, is the directional weight for the first side of the far-field cell boundary, is the directional weight for the second side of the far-field cell boundary, is the number of the sub-solid angle.

6. The aircraft radiation heat assessment method according to claim 2, characterized in that: The step of calculating an initial value of the spectral radiation intensity of the first solid corner element according to the temperature of the first sub-solid corner element comprises: The calculation formula for the initial value of the spectral radiation intensity of the first solid corner element is: in, is the initial value of the spectral radiation intensity of the first solid corner element, is the temperature of the first sub-solid corner element, is the Boltzmann constant.

7. The aircraft radiation heat assessment method according to claim 2, characterized in that: The step of calculating the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit comprises: The calculation formula of the symmetric unit boundary flux is: in, is the symmetry unit boundary flux, is the initial value of the spectral radiation intensity of the first solid corner element, is the initial value of the spectral radiation intensity of the second solid corner element, is the direction weight for the first side of the symmetry unit boundary, is the direction weight for the second side of the symmetry cell boundary, is the number of the sub-solid angle.

8. An aircraft radiation heat evaluation device, characterized in that: The simulation device pre-creates an unstructured grid based on the aircraft to be tested, wherein the unstructured grid has a plurality of grid cells, and a cell boundary is set between every two adjacent grid cells; each grid cell is divided according to a preset number of solid angle cells to obtain a plurality of solid angle cells; each solid angle cell is divided according to a preset number of sub-solid angle cells to obtain a plurality of sub-solid angle cells; each cell boundary is divided according to a preset number of cell boundary solid angles to obtain a plurality of cell boundary solid angle cells; Each unit boundary solid angle is divided according to a preset number of unit boundary sub-solid angles to obtain a plurality of unit boundary sub-solid angle units; the device comprises: An acquisition module, used for acquiring the temperature of each sub-solid corner unit and the temperature of each unit boundary sub-solid corner unit; A data processing module, configured to calculate an initial value of the spectral radiation intensity of the unit boundary solid corner unit according to the temperature of the unit boundary sub-solid corner unit; The data processing module is further used to calculate the initial value of the spectral radiation intensity of the solid corner unit according to the temperature of the sub-solid corner unit; The data processing module is further configured to calculate the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit and the initial value of the spectral radiation intensity of the unit boundary solid corner unit if the unit boundary is a wall unit boundary or a far-field unit boundary; The data processing module is further configured to calculate the unit boundary flux according to the initial value of the spectral radiation intensity of the solid corner unit if the unit boundary is a symmetric unit boundary; The data processing module is further used to obtain the spectral radiation intensity of the wall unit according to the unit boundary flux; The data processing module is also used to calculate the wall radiation heat flux value according to the spectral radiation intensity of the wall unit, and evaluate the radiation heat of the aircraft to be tested according to the wall radiation heat flux value.

9. A computing device, characterized in that including memory and processor; One or more computer programs are stored in the memory, and the one or more computer programs include instructions; when the instructions are executed by the processor, the computing device executes the method as claimed in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium is used to store a computer program, and the computer program is used to execute the method according to any one of claims 1 to 7.

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