A method for high-speed target surface temperature calculation

Abstract

The embodiments of the present invention relate to the field of temperature calculation technology, and in particular to a method for calculating the surface temperature of a high-speed target. The present invention provides a method for calculating the surface temperature of a high-speed target, comprising: establishing a physical model of the high-speed target, and discretizing the solid domain and the fluid domain of the physical model by structural grid, respectively obtaining multiple spatial control volumes of the solid domain and multiple spatial control volumes of the fluid domain; performing refined modeling based on the multiple spatial control volumes of the fluid domain, and calculating the cold wall heat flux reservoir of the high-speed target at different times; converting the cold wall heat flux into the hot wall heat flux based on the conversion function and the cold wall heat flux reservoir, and obtaining the hot wall heat flux reservoir of the high-speed target at different times; using the hot wall heat flux in the hot wall heat flux reservoir as the 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. The calculation method provided by the present invention can be used for calculating the surface temperature of a 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] Currently, there are two algorithms for calculating the surface temperature of high-speed targets. One is commercial software-based refined numerical modeling, which simultaneously meshes the fluid and solid domains and solves the coupled NS equations. The other is a pure engineering algorithm, which does not perform finite element numerical solutions for the aerodynamic heat in the fluid domain. Instead, it uses empirical formulas to determine the airflow convection heat transfer coefficient and recovery temperature on the outer surface of the solid domain, establishes the aerodynamic heat boundary conditions, and solves only the solid thermal conductivity differential equation. Both have advantages and disadvantages. Refined modeling, because it simultaneously couples the fluid and solid domains, must account for transient perturbations in the fluid domain, requiring a very small calculation time step. This results in low computational efficiency and speed, but high accuracy. On the other hand, the engineering algorithm only solves the heat conduction equation in the solid domain and does not consider the NS equations in the fluid domain. Therefore, it is efficient and fast, but has low computational accuracy. Summary of the Invention

[0003] Embodiments of the present invention provide a method, device, electronic device, and 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 by structural meshes 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 outer 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] Based on the multiple spatial control volumes of the fluid domain, refined modeling is performed 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 portion 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 portion of the spatial control volume of the solid domain that contacts the fluid 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 preceding claims, the device comprising:

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

[0011] a cold wall heat flux reservoir establishment unit, configured to perform refined modeling based on multiple 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 the area consisting of the portion of the spatial control volume of the fluid domain that contacts the solid domain;

[0012] a conversion unit, configured to convert the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, thereby obtaining the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is a region consisting of a portion of the spatial control volume of the solid domain that contacts the fluid domain;

[0013] The calculation unit is used to input the hot wall heat flux in the hot wall heat flux library as the aerodynamic heat flux, couple the radiation heat dissipation boundary condition, 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, comprising 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 combines the advantages of both methods and mitigates their disadvantages. First, 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, to address the problem of low calculation efficiency of fine-tune 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, thereby improving 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 following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 any creative work.

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

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

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

[0021] Figure 3 This is a cold wall heat flow reservoir provided by 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 This 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 one 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, not all the embodiments. Based on the embodiments of 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: Establish a physical model of a high-speed target and discretize the solid domain and fluid domain of the physical model into a structural grid to obtain a plurality of spatial control volumes of the solid domain and a plurality of spatial control volumes of the fluid domain, respectively. The solid domain is the space where the high-speed target shell is located, and the fluid domain is the space where the fluid surrounding the high-speed target is located.

[0029] Step 102: performing refined modeling 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 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, 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 portion of the spatial control volume of the solid domain that contacts the fluid domain;

[0031] Step 106 : Using the hot wall heat flux in the hot wall heat flux library as the 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] This paper proposes a fast surface dynamic temperature algorithm suitable for high-speed targets, combining the advantages of both methods while mitigating their shortcomings. First, to address the low computational accuracy of engineering algorithms, commercial software is used to fine-tune the modeling of the fluid domain, determining the cold wall heat flux at each moment and improving computational accuracy. Second, to address the low computational efficiency of this refined modeling, the fluid and solid domains are decoupled, and the cold wall heat flux is converted into a hot wall heat flux as the boundary condition for the solid heat conduction equation, ignoring the solution of the NS equations and improving computational 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 and solid domains 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 detailed modeling and calculations on the fluid domain. The solid wall temperature of the fluid domain is set to a preset temperature, which can be room temperature. Then, the flight altitude and speed at different times are input. The kw turbulence model is used to solve the NS equations and output the wall heat flux, thereby establishing a cold wall heat flux library at different times along the flight path, such as Figure 3 shown.

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

[0041] q or =q 300K (h r -h w ) / (h r -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 based on the flight speed, altitude and cold wall heat flux of the high-speed target at the current moment;

[0047] Substituting the current wall heat flux into the solid transient heat conduction equations and coupling with the radiation heat dissipation boundary conditions, the high-speed target surface temperature is obtained.

[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. From t0 to t0+Δt, the external aerodynamic heat remains the hot wall heat flux at time t0. Substituting it into the discretized transient heat conduction equation group, the solid surface temperature Tt0+Δt at time t0+Δt can be solved. Combined with the target flight speed, altitude and cold wall heat flux at time 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 time t0+2Δt can be solved. By analogy, the dynamic temperature calculation of the target surface along the entire flight path is completed, as shown in the following example. Figure 4 shown.

[0049] After the calculation is completed, the temperature of the calculation results 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 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, 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 structured 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, hardware, or a combination of software and hardware. From the hardware level, as Figure 6As shown in FIG. 1 , a hardware architecture diagram of an electronic device for a high-speed target surface temperature calculation device provided by an embodiment of the present invention is shown. Figure 6 In 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. Taking software implementation as an example, as a logical device, the CPU of the electronic device in which it is located reads the corresponding computer program in the non-volatile memory into the memory and runs 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 the high-speed target and perform structural grid discretization on the solid domain and fluid domain of the physical model to obtain multiple spatial control volumes of the solid domain and multiple spatial control volumes of the fluid domain, respectively; wherein the solid domain is the space where the high-speed target shell is located, and the fluid domain is the space where the fluid wrapped outside the high-speed target is located;

[0054] a cold wall heat flux reservoir establishment unit, configured to perform refined modeling based on multiple 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 the area consisting of the portion of the spatial control volume of the fluid domain that contacts the solid domain;

[0055] a conversion unit, configured to convert the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, thereby obtaining the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is a region consisting of a portion of the spatial control volume of the solid domain that contacts the fluid domain;

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

[0057] It should be understood that the structures illustrated in the embodiments of the present invention do not constitute specific limitations on the apparatus for high-speed target surface temperature calculation. In other embodiments of the present invention, the apparatus for high-speed target surface temperature calculation may include more or fewer components than illustrated, or may combine or separate certain components, or employ different component arrangements. The illustrated components may be implemented in hardware, software, or a combination of software and hardware.

[0058] The information interaction, execution process, etc. 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 specific contents, please refer to the description in the embodiment of the method of the present invention and will not be repeated 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 having a computer program stored thereon. When the computer program is executed by a processor, the processor executes a method for calculating a high-speed target surface temperature according to any embodiment of the present invention.

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

[0063] Examples of storage media for providing program code include floppy disks, hard disks, magneto-optical disks, optical disks (such as CD-ROM, CD-R, CD-RW, DVD-ROM, DVD-RAM, DVD-RW, DVD+RW), magnetic tapes, non-volatile memory cards, and ROMs. Alternatively, the program code can be downloaded from a server computer via a communication network.

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

[0065] In addition, it can be understood that the program code read from the storage medium is written into a memory provided in an expansion board inserted into the computer or into 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 embodiments.

[0066] It should be noted that, in this article, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply the existence of any such actual relationship or order between these entities or operations. Moreover, the terms "comprises", "comprising" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising 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 sentence "comprising a ..." do not exclude the presence of other identical factors in the process, method, article or device comprising the elements.

[0067] Those skilled in the art will understand that all or part of the steps of implementing the above-mentioned method embodiment 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-mentioned method embodiment; and the aforementioned storage medium includes: ROM, RAM, 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 various 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 by structural meshes 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 outer 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; Based on the multiple spatial control volumes of the fluid domain, refined modeling is performed 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 portion 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 portion of the spatial control volume of the solid domain that contacts the fluid 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: q or =q K (h r -h w ) / (h r -h K ) 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, wherein 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 based on the flight speed, altitude and cold wall heat flux of the high-speed target at the current moment; Substituting the current wall heat flux into the solid transient heat conduction equations and coupling with the radiation heat dissipation boundary conditions, the high-speed target surface temperature is obtained.

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 according to any one of claims 1 to 6, the device comprises: A grid discretization unit is used to establish a physical model of the high-speed target and perform structural grid discretization on the solid domain and fluid domain of the physical model to obtain multiple spatial control volumes of the solid domain and multiple spatial control volumes of the fluid domain, respectively; wherein the solid domain is the space where the high-speed target shell is located, and the fluid domain is the space where the fluid wrapped outside the high-speed target is located; a cold wall heat flux reservoir establishment unit, configured to perform refined modeling based on multiple 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 the area consisting of the portion of the spatial control volume of the fluid domain that contacts the solid domain; a conversion unit, configured to convert the cold wall heat flux into the hot wall heat flux according to the conversion function and the cold wall heat flux library, thereby obtaining the hot wall heat flux library at different times of the high-speed target; wherein the hot wall is a region consisting of a portion of the spatial control volume of the solid domain that contacts the fluid domain; The calculation unit is used to input the hot wall heat flux in the hot wall heat flux library as the aerodynamic heat flux, couple the radiation heat dissipation boundary condition, 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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