Method for calculating surface temperature of high-speed target

Abstract

The embodiment of the invention relates to the technical field of temperature calculation, in particular to a method for calculating the surface temperature of a high-speed target. The invention provides a method for calculating the surface temperature of a high-speed target, and the method comprises the steps: building a physical model of the high-speed target, carrying out the structural grid discretization of a solid domain and a fluid domain of the physical model, and obtaining a plurality of space control volumes of the solid domain and a plurality of space control volumes of the fluid domain; fine modeling is carried out according to the multiple space control volumes of the fluid domain, and cold wall heat flow libraries of the high-speed target at different moments are obtained through calculation; according to the conversion function and the cold-wall heat flow library, converting the cold-wall heat flow into hot-wall heat flow to obtain hot-wall heat flow libraries of the high-speed target at different moments; and inputting the hot wall heat flow in the hot wall heat flow library as a pneumatic heat flow, coupling a radiation heat dissipation boundary condition, solving a solid transient heat conduction differential equation, and obtaining the surface temperature of the high-speed target. The calculation method provided by the invention can be used for calculating the surface temperature of the high-speed target.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of temperature calculation, and in particular to a method for high-speed target surface temperature calculation. Background Art

[0002] At present, there are two algorithms for calculating the surface temperature of high-speed targets. One is the refined numerical modeling of commercial software, which simultaneously meshes the fluid domain and the solid domain and solves the NS equations in a coupled manner. The other is a pure engineering algorithm, which does not perform finite element numerical solutions to the aerodynamic heat in the fluid domain, but uses empirical formulas to determine the airflow convection heat transfer coefficient and recovery temperature on the outer surface of the solid domain, determines the boundary conditions of the aerodynamic heat, and only solves the solid thermal conductivity differential equation. Both have advantages and disadvantages. Refined modeling requires consideration of transient disturbance changes in the fluid domain due to the simultaneous coupling of the fluid domain and the solid domain. The calculation time step needs to be set very small, resulting in low calculation efficiency and slow speed, but high accuracy. The engineering algorithm only solves the heat conduction equation in the solid domain and does not consider the solution of the NS equation in the fluid domain. Therefore, it has high efficiency and fast speed, but low calculation accuracy. Summary of the invention

[0003] The embodiments of the present invention provide a method, a device, an electronic device and a storage medium for high-speed target surface temperature calculation, which can be used for high-speed target surface temperature calculation.

[0004] In a first aspect, an embodiment of the present invention provides a method for high-speed target surface temperature calculation, comprising:

[0005] A physical model of a high-speed target is established, and a solid domain and a fluid domain of the physical model are discretized into structural grids to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively; wherein the solid domain is the space where the shell of the high-speed target is located, and the fluid domain is the space where the fluid wrapped outside the high-speed target is located;

[0006] Refined modeling is performed based on multiple spatial control volumes of the fluid domain to calculate the cold wall heat flux reservoir of the high-speed target at different times; wherein the cold wall is the area consisting of the part of the spatial control volume of the fluid domain that contacts the solid domain;

[0007] According to the conversion function and the cold wall heat flux library, the cold wall heat flux is converted into the hot wall heat flux to obtain the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is the area consisting of the part in contact with the fluid domain in the spatial control volume of the solid domain;

[0008] The hot wall heat flux in the hot wall heat flux library is used as the aerodynamic heat flux input, coupled with the radiation heat dissipation boundary condition, and the solid transient heat conduction differential equation is solved to obtain the surface temperature of the high-speed target.

[0009] In a second aspect, an embodiment of the present invention further provides a device for high-speed target surface temperature calculation, for implementing any of the methods described in the above claims, the device comprising:

[0010] A grid discretization unit is used to establish a physical model of a high-speed target, and to perform structural grid discretization on a solid domain and a fluid domain of the physical model, to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively; wherein the solid domain is a space where the shell of the high-speed target is located, and the fluid domain is a space where the fluid wrapped outside the high-speed target is located;

[0011] A cold wall heat flux reservoir establishment unit is used to perform refined modeling according to a plurality of spatial control volumes of the fluid domain, and calculate the cold wall heat flux reservoir of the high-speed target at different times; wherein the cold wall is a region composed of a portion of the spatial control volume of the fluid domain that contacts the solid domain;

[0012] A conversion unit, used for converting the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, so as to obtain the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is a region composed of a portion of the spatial control volume of the solid domain that contacts the fluid domain;

[0013] The calculation unit is used to use the hot wall heat flux in the hot wall heat flux library as the aerodynamic heat flux input, couple the radiation heat dissipation boundary conditions, solve the solid transient heat conduction differential equation, and obtain the surface temperature of the high-speed target.

[0014] In a third aspect, an embodiment of the present invention further provides an electronic device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method described in any embodiment of this specification is implemented.

[0015] In a fourth aspect, an embodiment of the present invention further provides a computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, enables the computer to execute the method described in any embodiment of this specification.

[0016] The embodiments of the present invention provide a method, device, electronic device and storage medium for calculating the surface temperature of a high-speed target. The present invention proposes a fast algorithm for the dynamic surface temperature of a high-speed target, which takes into account the advantages of both and weakens the disadvantages of both. First, in order to address the problem of low calculation accuracy of engineering algorithms, commercial software is used to fine-tune the modeling of the fluid domain separately, determine the cold wall heat flux at each moment, and improve the calculation accuracy; second, in order to address the problem of low calculation efficiency of refined modeling, the fluid domain and the solid domain are decoupled, and the cold wall heat flux is converted into the hot wall heat flux as the boundary condition of the solid heat conduction equation, and the solution of the NS equation is ignored to improve the calculation speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 is a schematic diagram of a high-speed target physical model provided by an embodiment of the present invention;

[0019] Figure 2a is a schematic diagram of a solid domain grid provided by an embodiment of the present invention;

[0020] Figure 2b is a schematic diagram of a fluid domain grid provided by an embodiment of the present invention;

[0021] Figure 3 A cold wall heat flux reservoir is provided in one embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of a cold wall to hot wall conversion result provided by an embodiment of the present invention;

[0023] Figure 5 is a result comparison curve diagram provided by an embodiment of the present invention;

[0024] Figure 6 This is a hardware architecture diagram of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0026] The specific implementation of the above concept is described below.

[0027] An embodiment of the present invention provides a method for calculating the surface temperature of a high-speed target, the method comprising:

[0028] Step 100, establishing a physical model of a high-speed target, and performing structural grid discretization on a solid domain and a fluid domain of the physical model, to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively; wherein the solid domain is a space where the outer shell of the high-speed target is located, and the fluid domain is a space where the fluid wrapped outside the high-speed target is located;

[0029] Step 102, performing refined modeling according to a plurality of spatial control volumes of the fluid domain, and calculating the cold wall heat flux reservoir of the high-speed target at different times; wherein the cold wall is a region consisting of a portion of the spatial control volume of the fluid domain that contacts the solid domain;

[0030] Step 104, converting the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, and obtaining the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is the area consisting of the part in contact with the fluid domain in the spatial control volume of the solid domain;

[0031] Step 106, using the hot wall heat flux in the hot wall heat flux library as aerodynamic heat flux input, coupling the radiation heat dissipation boundary condition, solving the solid transient heat conduction differential equation, and obtaining the surface temperature of the high-speed target.

[0032] The present invention proposes a fast algorithm for surface dynamic temperature of high-speed targets, which takes into account the advantages of both and weakens their disadvantages. First, in order to solve the problem of low calculation accuracy of engineering algorithms, commercial software is used to finely model the fluid domain separately, determine the cold wall heat flux at each moment, and improve the calculation accuracy; second, in order to solve the problem of low calculation efficiency of fine modeling, the fluid domain and the solid domain are decoupled, and the cold wall heat flux is converted into the hot wall heat flux as the boundary condition of the solid heat conduction equation, ignoring the solution of the NS equation, and improving the calculation speed.

[0033] The following describes how each step is performed.

[0034] First, for step 100, a physical model of the assumed target is established, such as Figure 1 The structured grid is used to spatially discretize the fluid domain and solid domain of the physical model to form a finite number of spatial control volumes, as shown in Figure 2.

[0035] Then, for step 102, step 102 includes:

[0036] Set the initial temperature of the cold wall to the preset temperature;

[0037] At each moment, according to the current flight altitude and speed, the kw turbulence model is used to solve the NS equations to obtain the cold wall heat flux;

[0038] Collect the cold wall heat flux at all times to obtain the cold wall heat flux library.

[0039] In this embodiment, commercial software is used to separately perform fine modeling and calculation on the fluid domain. The solid wall temperature of the fluid domain is set to a preset temperature, which can be room temperature, and then the assumed flight altitude and speed at different times are input. The kw turbulence model is used to solve the NS equation and output the wall heat flux, thereby establishing a cold wall heat flux library at different times of the flight path, such as Figure 3 shown.

[0040] Then for step 104, the conversion function in step 104 is as follows:

[0041] qor=q 300K (hr-hw) / (hr-h 300K )

[0042] Among them, q or is the wall heat flux, h r is the recovery enthalpy, h w is the wall enthalpy, q K is the cold wall heat flux at the preset temperature, h K is the enthalpy value of the preset temperature.

[0043] In this embodiment, the cold wall heat flow to hot wall heat flow function is adopted, wherein, preferably, the preset temperature is 300K, q 300K is the cold wall heat flux at a wall temperature of 300K, h r is the recovery enthalpy, h w is the wall enthalpy, which is a function of the solid wall temperature Tw and the wall pressure P and can be expressed as h w =f(p,T w ). Convert the cold wall heat flux into the hot wall heat flux and obtain the hot wall heat flux at different times along the flight path.

[0044] Regarding step 106, step 106 includes:

[0045] Set the initial hot wall heat flux temperature at the initial moment to the preset temperature;

[0046] At each time interval, the current hot wall heat flux is calculated according to the conversion function in combination with the flight speed, altitude and cold wall heat flux of the high-speed target at the current moment;

[0047] Substitute the current heat flux of the hot wall into the solid transient heat conduction equations, couple the radiation heat dissipation boundary conditions, and obtain the high-speed target surface temperature.

[0048] The hot wall heat flux is used as the aerodynamic heat flux input, coupled with the radiation heat dissipation boundary condition, and the solid transient heat conduction differential equation is solved to obtain the surface temperature of the target. The specific steps are as follows. When the time is the initial moment t0, the initial temperature of the solid is the preset temperature, 300K. At this time, the hot wall heat flux is the cold wall heat flux. During the time from t0 to t0+Δt, the external aerodynamic heat is always maintained as the hot wall heat flux at the moment t0. Substituting it into the discrete transient heat conduction equation group, the solid surface temperature Tt0+Δt at the moment t0+Δt can be solved. Combined with the target flight speed, altitude and cold wall heat flux at the moment t0+Δt, the cold wall heat flux to hot wall heat flux function is used to calculate the hot wall heat flux at t0+Δt. Substituting it into the transient heat conduction equation group, the solid surface temperature Tt0+2Δt at the moment t0+2Δt can be solved. By analogy, the dynamic temperature calculation of the target surface of the entire flight route is completed, such as Figure 4 shown.

[0049] After the calculation is completed, the temperature of the calculation result can be verified. Specifically, the calculation results of the fluid-solid coupling refined modeling of the commercial software are compared with the calculation results of the present invention to complete the accuracy verification, such as Figure 5 As shown in the figure, the maximum error between the two is 6%, the minimum error is 0.6%, and the average error is 2.8%.

[0050] In some embodiments of the present invention, the preset temperature is 300 K. The preset temperature is an initial temperature, which is close to the air temperature, preferably 300 K. Of course, other temperatures can also be selected according to specific usage conditions.

[0051] In some embodiments of the present invention, the structural grid is a hexahedron, but may also be other polyhedrons, such as a tetrahedron.

[0052] like Figure 6 As shown, an embodiment of the present invention provides a device for high-speed target surface temperature calculation. The device embodiment can be implemented by software, or by hardware or a combination of software and hardware. From the hardware level, Figure 6 As shown, it is a hardware architecture diagram of an electronic device for high-speed target surface temperature calculation device provided by an embodiment of the present invention, except Figure 6In addition to the processor, memory, network interface, and non-volatile memory shown, the electronic device in the embodiment may also generally include other hardware, such as a forwarding chip responsible for processing messages, etc. Taking software implementation as an example, as a device in a logical sense, it is formed by the CPU of the electronic device in which it is located reading the corresponding computer program in the non-volatile memory into the memory and running it. This embodiment provides a device for high-speed target surface temperature calculation, including:

[0053] A grid discretization unit is used to establish a physical model of a high-speed target, and to perform structural grid discretization on a solid domain and a fluid domain of the physical model, to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively; wherein the solid domain is a space where the shell of the high-speed target is located, and the fluid domain is a space where the fluid wrapped outside the high-speed target is located;

[0054] A cold wall heat flux reservoir establishment unit is used to perform refined modeling according to a plurality of spatial control volumes of the fluid domain, and calculate the cold wall heat flux reservoir of the high-speed target at different times; wherein the cold wall is a region composed of a portion of the spatial control volume of the fluid domain that contacts the solid domain;

[0055] A conversion unit, used for converting the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, so as to obtain the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is a region composed of a portion of the spatial control volume of the solid domain that contacts the fluid domain;

[0056] The calculation unit is used to use the hot wall heat flux in the hot wall heat flux library as the aerodynamic heat flux input, couple the radiation heat dissipation boundary conditions, solve the solid transient heat conduction differential equation, and obtain the surface temperature of the high-speed target.

[0057] It is to be understood that the structure illustrated in the embodiment of the present invention does not constitute a specific limitation on a device for high-speed target surface temperature calculation. In other embodiments of the present invention, a device for high-speed target surface temperature calculation may include more or fewer components than shown in the figure, or combine some components, or split some components, or arrange the components differently. The components shown in the figure may be implemented in hardware, software, or a combination of software and hardware.

[0058] The information interaction, execution process and other contents between the modules in the above-mentioned device are based on the same concept as the embodiment of the method of the present invention. For the specific contents, please refer to the description in the embodiment of the method of the present invention, and no further description is given here.

[0059] An embodiment of the present invention further provides an electronic device, including a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, a method for calculating a high-speed target surface temperature in any embodiment of the present invention is implemented.

[0060] An embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the processor executes a method for calculating a high-speed target surface temperature in any embodiment of the present invention.

[0061] Specifically, a system or device equipped with a storage medium can be provided, on which software program code that implements the functions of any of the above-mentioned embodiments is stored, and a computer (or CPU or MPU) of the system or device can be enabled to read and execute the program code stored in the storage medium.

[0062] In this case, the program code itself read from the storage medium can realize the function of any one of the above-mentioned embodiments, and thus the program code and the storage medium storing the program code constitute a part of the present invention.

[0063] The storage medium embodiments for providing the program code include a floppy disk, a hard disk, a magneto-optical disk, an optical disk (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), a magnetic tape, a non-volatile memory card, and a ROM. Alternatively, the program code can be downloaded from a server computer by a communication network.

[0064] In addition, it should be clear that the functions of any of the above embodiments can be implemented not only by executing the program code read by the computer, but also by enabling an operating system operating on the computer to complete part or all of the actual operations based on instructions from the program code.

[0065] In addition, it can be understood that the program code read from the storage medium is written to a memory provided in an expansion board inserted into the computer or to a memory provided in an expansion module connected to the computer, and then based on the instructions of the program code, a CPU installed on the expansion board or expansion module is enabled to perform part or all of the actual operations, thereby realizing the functions of any of the above-mentioned embodiments.

[0066] It should be noted that, in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical factors in the process, method, article or device including the elements.

[0067] A person of ordinary skill in the art can understand that all or part of the steps of implementing the above method embodiments can be completed by hardware related to program instructions, and the aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it executes the steps of the above method embodiments; and the aforementioned storage medium includes: ROM, RAM, magnetic disk or optical disk, etc., various media that can store program codes.

[0068] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for high-speed target surface temperature calculation, characterized in that: include: A physical model of a high-speed target is established, and a solid domain and a fluid domain of the physical model are discretized into structural grids to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively; wherein the solid domain is the space where the shell of the high-speed target is located, and the fluid domain is the space where the fluid wrapped outside the high-speed target is located; Refined modeling is performed based on multiple spatial control volumes of the fluid domain to calculate the cold wall heat flux reservoir of the high-speed target at different times; wherein the cold wall is the area consisting of the part of the spatial control volume of the fluid domain that contacts the solid domain; According to the conversion function and the cold wall heat flux library, the cold wall heat flux is converted into the hot wall heat flux to obtain the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is the area consisting of the part in contact with the fluid domain in the spatial control volume of the solid domain; The hot wall heat flux in the hot wall heat flux library is used as the aerodynamic heat flux input, coupled with the radiation heat dissipation boundary condition, and the solid transient heat conduction differential equation is solved to obtain the surface temperature of the high-speed target.

2. The method according to claim 1, characterized in that The method of performing refined modeling based on multiple spatial control volumes of the fluid domain and calculating the cold wall heat flux reservoir of the high-speed target at different times includes: Set the initial temperature of the cold wall to the preset temperature; At each moment, according to the current flight altitude and speed, the kw turbulence model is used to solve the NS equations to obtain the cold wall heat flux; The cold wall heat flux at all times is collected to obtain the cold wall heat flux library.

3. The method according to claim 1, characterized in that The conversion function is as follows: qor=q K (hr-hw) / (hr-hK) Among them, q or is the wall heat flux, h r is the recovery enthalpy, h w is the wall enthalpy, q K is the cold wall heat flux at the preset temperature, h K is the enthalpy value of the preset temperature.

4. The method according to claim 1, characterized in that: The method uses the hot wall heat flux in the hot wall heat flux reservoir as the aerodynamic heat flux input, couples the radiation heat dissipation boundary condition, solves the solid transient heat conduction differential equation, and obtains the surface temperature of the high-speed target, including: Set the initial hot wall heat flux temperature at the initial moment to the preset temperature; At each time interval, the current hot wall heat flux is calculated according to the conversion function in combination with the flight speed, altitude and cold wall heat flux of the high-speed target at the current moment; Substitute the current heat flux of the hot wall into the solid transient heat conduction equations, couple the radiation heat dissipation boundary conditions, and obtain the high-speed target surface temperature.

5. The method according to claim 2 or 4, characterized in that: The preset temperature is 300K.

6. The method according to claim 1, characterized in that The structural grid is a hexahedron.

7. A device for high-speed target surface temperature calculation, characterized in that: For implementing the method described in any one of claims 1 to 6, the device comprises: A grid discretization unit is used to establish a physical model of a high-speed target, and to perform structural grid discretization on a solid domain and a fluid domain of the physical model, to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively; wherein the solid domain is a space where the shell of the high-speed target is located, and the fluid domain is a space where the fluid wrapped outside the high-speed target is located; A cold wall heat flux reservoir establishment unit is used to perform refined modeling according to a plurality of spatial control volumes of the fluid domain, and calculate the cold wall heat flux reservoir of the high-speed target at different times; wherein the cold wall is a region composed of a portion of the spatial control volume of the fluid domain that contacts the solid domain; A conversion unit, used for converting the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, so as to obtain the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is a region composed of a portion of the spatial control volume of the solid domain that contacts the fluid domain; The calculation unit is used to use the hot wall heat flux in the hot wall heat flux library as the aerodynamic heat flux input, couple the radiation heat dissipation boundary conditions, solve the solid transient heat conduction differential equation, and obtain the surface temperature of the high-speed target.

8. An electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and when the processor executes the computer program, the method according to any one of claims 1 to 6 is implemented.

9. A computer-readable storage medium having a computer program stored thereon, which, when executed in a computer, causes the computer to execute the method according to any one of claims 1 to 6.

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