High-speed aircraft equipment cabin thermal analysis modeling method, device, system and equipment

Abstract

The embodiments of the present application provide a method, device, system and equipment for thermal analysis modeling of a high-speed aircraft equipment cabin, the method comprising: dividing different heat transfer processes of cabin thermal analysis into several modules according to the heat transfer process and thermal control scheme and establishing models of each module respectively; determining model parameters of each module according to the module division, wherein the model parameters include two types: fixed parameters and interface parameters; completing modeling according to the different divided modules and the determined model parameters, and configuring and correcting the model; connecting and coupling the various models to obtain an overall modular simulation model for analysis and verification; local debugging and testing can be performed when the design of other modules is not clear, and other modules can be avoided from being changed at the same time when adjustments are made later, thereby improving the versatility and debuggability of the constructed model and improving the efficiency of thermal analysis design.

Description

Technical Field

[0001] The present application relates to the field of modeling technology, and in particular to a method, device, system and equipment for thermal analysis modeling of a high-speed aircraft equipment cabin. Background Art

[0002] Hypersonic vehicles fly at high speeds. On the one hand, the surface of the vehicle is subjected to huge heat loads, and the structure must be protected by a high-performance thermal protection system to keep the temperature of the body structure within the temperature range that the material can tolerate. On the other hand, the bleed air can no longer be used for cooling during high-speed flight, and cabin thermal management requires finding new heat sinks, and the application effects of technologies such as consumable cooling need to be further explored. In addition, gaps at the joints of the aircraft skin will leak external hot air into the cabin, further increasing the difficulty of cabin thermal management. The traditional decoupled design method of calculating the structure first and then using the internal structure temperature as the boundary of the thermal analysis calculation can no longer meet the design needs of hypersonic aircraft cabin thermal management, and is prone to adjustments to all calculation contents due to local adjustments, resulting in a large workload for modification and improvement. Summary of the invention

[0003] The purpose of the embodiments of the present application is to provide a method, device, system and equipment for thermal analysis modeling of a high-speed aircraft equipment cabin, so as to solve the problem that the existing thermal analysis methods can no longer meet the design requirements of thermal management of hypersonic aircraft cabins, and are prone to the problem of adjustment of all calculation contents due to local adjustments.

[0004] In a first aspect, an embodiment of the present application provides a method for thermal analysis modeling of a high-speed aircraft equipment cabin, comprising:

[0005] According to the heat transfer process and thermal control scheme, the different heat transfer processes of cabin thermal analysis are divided into several modules and the models of each module are established respectively;

[0006] According to the module division, the model parameters of each module are determined, wherein the model parameters include two types: fixed parameters and interface parameters;

[0007] Complete modeling according to the different modules and determined model parameters, and configure and calibrate the model;

[0008] The various models are connected and coupled to obtain an overall modular simulation model for analysis and verification.

[0009] In the above implementation process, according to the heat transfer process and thermal control scheme, the different heat transfer processes of the cabin thermal analysis are divided into several modules and the models of each module are established respectively; according to the module division, the model parameters of each module are determined, wherein the model parameters include two types: fixed parameters and interface parameters; the modeling is completed according to the different divided modules and the determined model parameters, and the model is configured and corrected; the various models are connected and coupled to obtain an overall modular simulation model for analysis and verification; local debugging and testing can be carried out when the design of other modules is not clear, and it can avoid the need to change other modules at the same time when making adjustments in the later stage, thereby improving the versatility and debuggability of the constructed model, and at the same time improving the efficiency of thermal analysis design.

[0010] Furthermore, the heat transfer process includes the heat exchange process between aerodynamic heat and the cabin structure, the heat conduction process of heat in the cabin structure, and the heat exchange process of gas in the cabin caused by leakage of electronic equipment, cabin structure, and gaps.

[0011] In the above implementation process, from the analysis of the heat flow process, the surfaces of the equipment and structures can be used as the dividing boundaries of the thermal problem. The cabin thermal problem can be mainly divided into three processes, namely, the heat exchange process between aerodynamic heat and structure, the heat conduction process in the structure, and the heat exchange process of the gas in the cabin caused by leakage of equipment, structure, and gaps. Therefore, thermal analysis and modeling are carried out from these three processes to ensure the accuracy of the analysis results.

[0012] Furthermore, the model of the module includes an aerodynamic heat calculation model, a structural heat conduction calculation model, a cabin gas heat exchange calculation model, a thermal sealing calculation model, an equipment heat exchange calculation model, and an efficiency evaluation model.

[0013] In the above implementation process, modeling is achieved by setting multiple models.

[0014] Furthermore, when establishing the aerodynamic heat calculation model, the following method is used:

[0015] Interpolation method for solving aerodynamic thermal loads in arbitrary states using typical state points;

[0016] Aerothermal engineering calculation methods using typical structural characteristics.

[0017] In the above implementation process, the aerodynamic thermal calculation model mainly provides parameters for the thermal conductivity calculation of the cabin structure and the calculation of the thermal sealing structure. Its main function is to convert the current flight state into input for thermal sealing and structural thermal conductivity calculation.

[0018] Furthermore, the structural heat conduction calculation model includes a material database of cabin structure heat transfer, and the structural heat conduction calculation model describes the one-dimensional heat transfer process along the normal direction within the structure, which is used to calculate the temperature state of the structure as a calculation boundary for gas heat exchange within the cabin.

[0019] In the above implementation process, the structural heat conduction calculation model is mainly used to calculate the temperature state of the cabin structure as the calculation boundary of the gas heat exchange in the cabin, which mainly involves the thermal load loading of the aerodynamic thermal boundary, the surface radiation heat transfer calculation, and the heat conduction calculation in the structure.

[0020] Furthermore, establishing the cabin gas heat exchange calculation model includes the following steps:

[0021] Determine the heat transfer object and heat transfer process of the gas in the cabin;

[0022] Determine the calculation method of heat transfer coefficient between cabin and equipment surface, cabin and fuselage structure;

[0023] Determine cabin cooling and pressure relief control plan;

[0024] Based on the above results, a calculation model for cabin gas heat exchange is established to calculate the cabin gas heat exchange.

[0025] Furthermore, the heat sealing calculation model is used to calculate the heat leakage caused by the inconsistent gas state between the internal and external environments through the heat sealing structure, and calculate the leakage amount and temperature of the output gas.

[0026] Furthermore, establishing the equipment heat exchange calculation model includes the following steps:

[0027] Determine the key parameters of cabin equipment heat exchange in the parametric simulation of cabin problems;

[0028] Determine the relationship between working status and heating power, and determine the relationship between equipment temperature and equipment heat exchange process;

[0029] An equipment heat exchange calculation model is established to calculate the heat exchange between the electronic equipment and the cabin and the temperature of the electronic equipment.

[0030] In the above implementation process, the electronic equipment is the internal heat source of the cabin thermal problem. A heat exchange calculation model for the equipment is established to exchange heat with the cabin environment through its own structure.

[0031] Furthermore, the performance evaluation model is used to calculate the utilization efficiency of the heat sink, the cooling efficiency of the cold source and the system compensation.

[0032] In the above implementation process, the performance evaluation model can effectively evaluate the performance of the cabin thermal management solution, thereby guiding the optimal design of the cabin thermal management solution.

[0033] Furthermore, when the heat transfer process is difficult to describe, a proxy model of the heat transfer process is established, including the following steps:

[0034] Select sample points and establish a sample point database based on the calculation results of three-dimensional simulation or experiment;

[0035] Establishing agent models based on computer tool parameters;

[0036] The surrogate model was validated using the set strategy and used in the overall modeling of cabin thermal analysis.

[0037] In the above implementation process, in the modular modeling process of cabin thermal problem analysis, compared with the three-dimensional heat transfer process in space, some models need to be simplified, but the accuracy problem caused by simplification needs to be solved, otherwise the calculation results of the modular model will not be accurate enough, which will lead to invalid calculation results. Therefore, when encountering the problem of difficult parameter evaluation due to simplification, it is necessary to establish a proxy model of the heat transfer process.

[0038] In a second aspect, an embodiment of the present application provides a high-speed aircraft equipment cabin thermal analysis modeling device, comprising:

[0039] Model building module, which is used to divide the different heat transfer processes of cabin thermal analysis into several modules according to the heat transfer process and thermal control scheme and build the model of each module respectively;

[0040] A parameter determination module, used to determine the model parameters of each module according to the module division situation, wherein the model parameters include two types: fixed parameters and interface parameters;

[0041] The model verification module is used to complete the modeling according to the different modules divided and the determined model parameters, and to configure and calibrate the model;

[0042] The overall simulation module is used to connect and couple various models to obtain an overall modular simulation model for analysis and verification.

[0043] In a third aspect, an embodiment of the present application provides a high-speed aircraft equipment cabin thermal analysis modeling system, comprising: an integrated model calculation module, an integrated design tool interface and a model development interface, the integrated model calculation module connecting the integrated design tool interface and the model development interface; the integrated model calculation module comprises the high-speed aircraft equipment cabin thermal analysis modeling device as described above.

[0044] In a fourth aspect, an embodiment of the present application provides an electronic device, including:

[0045] A processor, a memory and a bus, wherein the processor is connected to the memory via the bus, and the memory stores computer-readable instructions. When the computer-readable instructions are executed by the processor, they are used to implement the thermal analysis modeling method for a high-speed aircraft equipment cabin as described above.

[0046] In a fifth aspect, an embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a server, implements the thermal analysis modeling method for a high-speed aircraft equipment cabin as described above.

[0047] In a sixth aspect, an embodiment of the present application provides a computer program product, which includes instructions, and when the instructions are executed by a computer, the computer implements the high-speed aircraft equipment cabin thermal analysis modeling method as described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments of the present application will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0049] Figure 1 It is a flow analysis diagram of thermal problems in a hypersonic aircraft cabin provided in an embodiment of the present application;

[0050] Figure 2 It is a flow chart of a thermal analysis modeling method for a high-speed aircraft equipment cabin provided in an embodiment of the present application;

[0051] Figure 3 It is a one-dimensional modular simulation tool implementation form diagram of a high-speed aircraft equipment cabin thermal analysis modeling system provided by an embodiment of the present application;

[0052] Figure 4 It is a flowchart of the use of a modular tool of a high-speed aircraft equipment cabin thermal analysis modeling system provided by an embodiment of the present application;

[0053] Figure 5 It is a parameter definition and input-output relationship diagram of an aerodynamic heat calculation model of a high-speed aircraft equipment cabin thermal analysis modeling method provided in an embodiment of the present application;

[0054] Figure 6 It is a structural heat conduction calculation model parameter definition and input-output relationship diagram of a high-speed aircraft equipment cabin thermal analysis modeling method provided in an embodiment of the present application;

[0055] Figure 7It is a parameter definition and input-output relationship diagram of a gas heat exchange calculation model in a cabin of a high-speed aircraft equipment cabin thermal analysis modeling method provided in an embodiment of the present application;

[0056] Figure 8 It is a thermal sealing calculation model parameter definition and input-output relationship diagram of a high-speed aircraft equipment cabin thermal analysis modeling method provided in an embodiment of the present application;

[0057] Fig. 9 It is a parameter definition of an equipment heat exchange calculation model and its input-output relationship diagram of a high-speed aircraft equipment cabin thermal analysis modeling method provided in an embodiment of the present application;

[0058] Fig.10 It is a parameter definition of an efficiency evaluation model of a high-speed aircraft equipment cabin thermal analysis modeling method provided by an embodiment of the present application and its input-output relationship diagram;

[0059] Fig.11 It is a modular simulation model architecture diagram of a high-speed aircraft equipment cabin thermal analysis modeling method provided in an embodiment of the present application;

[0060] Fig.12 It is a structural schematic diagram of a thermal analysis modeling device for a high-speed aircraft equipment cabin provided in an embodiment of the present application;

[0061] Fig.13 It is a structural schematic diagram of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0062] The technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application.

[0063] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. At the same time, in the description of this application, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0064] The heat flow process of cabin thermal problem is as follows Figure 1As shown. The external load of the cabin heat problem comes from aerodynamic heating. After aerodynamic heating is transferred to the structure through convection heating, the structure transfers part of the heat to the cabin through the insulation and conduction of the fuselage structure and thermal protection structure. Part of the heat flows into the cabin through the gap due to the pressure difference between the gas environment inside and outside the cabin. The other part of the heat is radiated outward from the structure to the environment; the internal heat load comes from the heat generation of the equipment. The heat generated by the equipment due to work is transferred to the air in the cabin through the shell of the equipment through convection heat transfer. The radiation heat exchange between the equipment in the cabin and the internal surface of the structure is small, so this part of the heat is ignored in the heat exchange process. The cold source of the cabin comes from liquid nitrogen or cold air supplied by the thermal management system. The cold source directly acts on the gas in the cabin, mixes with the gas in the cabin, and reduces the temperature of the cabin environment. When the cabin pressure is higher than the external environment, the gas in the cabin will flow out of the cabin and take away a certain amount of heat.

[0065] From the analysis of the heat flow process, the surface of equipment and structure can be used as the dividing boundary of thermal problems, and the cabin thermal problem can be mainly divided into three processes, namely, the heat exchange process between aerodynamic heating and structure, the heat conduction process in the structure, and the heat exchange process of the gas in the cabin caused by leakage of equipment, structure, and gaps. These three processes are calculated with the structural temperature and cabin gas temperature as the core.

[0066] The difficulty in the thermal design of the cabin of a hypersonic aircraft lies in the fact that its heat load comes from both the heat generated by the cabin equipment and the heat leakage caused by the structural gaps and the wall heat load caused by the structural heat conduction (even if thermal protection measures are used, the heat load on the cabin cannot be ignored); at the same time, due to the lack of cold sources and weight restrictions, it is necessary to reduce the compensation caused by the thermal management system to the entire aircraft and improve the utilization efficiency of the cooling medium, which requires precise and accurate evaluation of the heat load and analysis of the flight process; in addition, since thermal problems are cumulative processes and the heat is highly coupled with the temperature of the structure and cabin, if accurate calculations are required, the structural heat exchange, seal leakage and cabin thermal problems must be coupled and calculated, and traditional design methods can no longer meet the design needs of hypersonic aircraft cabin thermal management.

[0067] To this end, the embodiment of the present application proposes a thermal analysis modeling method for a high-speed aircraft equipment cabin. Starting from the cabin thermal management problem faced by hypersonic aircraft, the heat transfer process is analyzed to illustrate the rationality of applying a modular modeling method. According to the heat transfer process and the needs of parametric modeling, the heat transfer process is divided into 6 key modules. The idea of ​​modeling around the core modules is described, and the architecture of the modeling model is established, which further verifies the rationality and feasibility of modular modeling simulation.

[0068] like Figure 2As shown, a schematic diagram of a process flow of a high-speed aircraft equipment cabin thermal analysis modeling method provided by an embodiment of the present application. The high-speed aircraft equipment cabin thermal analysis modeling method comprises:

[0069] 100. According to the heat transfer process and thermal control scheme, the different heat transfer processes of cabin thermal analysis are divided into several modules and the models of each module are established separately.

[0070] Optionally, the heat transfer process includes the heat exchange process between aerodynamic heat and the cabin structure, the heat conduction process of heat in the cabin structure, and the heat exchange process of the gas in the cabin caused by electronic equipment, cabin structure, and gap leakage; among them, from the analysis of the heat flow process, the surface of the equipment and structure can be used as the dividing boundary of the thermal problem, and the cabin thermal problem can be mainly divided into three processes, namely, the heat exchange process between aerodynamic heat and the structure, the heat conduction process of heat in the structure, and the heat exchange process of the gas in the cabin caused by equipment, structure, and gap leakage. Therefore, thermal analysis and modeling are carried out from these three processes to ensure the accuracy of the analysis results.

[0071] 200. According to the module division, determine the model parameters of each module, wherein the model parameters include two types: fixed parameters and interface parameters.

[0072] 300. Complete the modeling according to the different modules divided and the determined model parameters, and configure and calibrate the model.

[0073] 400. Connect and couple the various models to obtain an overall modular simulation model for analysis and verification.

[0074] Due to the coupling of the heat transfer process of the cabin thermal problem, and the heat transfer characteristics of each part still need further research, in order to avoid adjusting the local model and affecting the overall model, the modular modeling technology can be used to effectively avoid the adjustment of all calculation contents caused by local adjustments. For the modular modeling of cabin thermal management, each core heat transfer process is modeled separately as an independent simulation module to form a module that can be independently simulated and calculated while retaining a standardized interface. Different modules can realize the ability to carry out joint simulation using a unified interface. The modular model built in this way can be locally debugged and tested when other designs are not clear, and can avoid the need to change other modules at the same time when making adjustments in the later stage, thereby improving the versatility and debuggability of the constructed model and improving the efficiency of agile design.

[0075] Specifically, first, the module division is completed according to the heat transfer process and function definition; then, the basic model describing the different core heat transfer processes is established, and the core parameters and interface parameters are extracted; according to the individual research results of thermal protection, thermal sealing, and thermal management, the model is corrected to improve the model accuracy. Finally, by coupling the relevant parameters of each module, a thermal sealing and thermal management integrated simulation and agile design model is formed, which can be used for steady-state and transient numerical simulation calculations according to the flight mission. Among them, CFD simulation technology is used to perform multi-physics three-dimensional field non-steady-state full coupling calculations, realize the typical cabin thermal fluid-solid multi-physics field coupling three-dimensional design evaluation, and verify the model.

[0076] Optionally, the embodiment of the present application adopts the visual modeling method of MATLAB / Simulink, which provides great convenience for modular modeling. On the one hand, the parameter definition and parameter transmission process of MATLAB / Simulink matches the establishment process and interface definition process required for modular modeling. On the other hand, MATLAB's built-in calculation method and general interface can facilitate the realization of modular simulation.

[0077] Optional, see Figure 3 The embodiment of the present application uses the Simulink model as the calculation kernel, and uses the integrated design tool interface to complete data management and display interaction; the built-in Simulink model development interface is used for designers to maintain the model and load the proxy model. The thermal management solution design and model development problem interface can be separated, which is convenient for tool use and data management, while also having debuggability and scalability.

[0078] Specifically, the user interacts with the integrated agile design tool interface by using the tool. The integrated agile design tool interface can load data (including txt, excel and other formats) and manage and display data, and can export calculation results (including excel, docx, txt and other formats), and feedback the calculation structure to the user's tool; the integrated calculation model (using Simulink as the calculation core) can interact with the integrated agile design tool interface for data, specifically, output calculation results to the integrated agile design tool interface, and receive the loaded data of the integrated agile design tool interface; the model development interface (using Simulink as the calculation core) is used for calculation, function development and interface configuration, and realizes model debugging and maintenance between the integrated calculation model. Model maintenance personnel can establish a parameter library through the model development interface, realize the modification of the proxy model, send interface parameter data to the integrated agile design tool interface, and receive the switching of the integrated agile design tool interface to the debugging interface.

[0079] Optionally, based on the implementation form of the integrated agile design tool and the design process, define the process for users to use the tool, such as Figure 4 As shown in the figure, the tool usage process can be roughly divided into three stages: parameter setting, loading and calculation, and result recording. The optimization function can be achieved by adjusting parameters and comparing results. The versatility of the software is reflected in the parameter setting stage, and the accuracy of the model depends on the feasibility of the modeling in the calculation.

[0080] Specifically, establish a design file (available for loading, review, and calculation results), set / load the overall plan (including cabin conditions, structural conditions, equipment quantity, thermal sealing conditions, and cooling plans), set detailed parameters for each structure, set detailed equipment parameters, set detailed thermal sealing plans, set detailed thermal management plans, select loading data, select output results, load the model, configure the model and perform calculations, display output results and evaluation results, and export calculation results and calculation reports.

[0081] In the above implementation process, according to the heat transfer process and thermal control scheme, the different heat transfer processes of the cabin thermal analysis are divided into several modules and the models of each module are established respectively; according to the module division, the model parameters of each module are determined, wherein the model parameters include two types: fixed parameters and interface parameters; according to the different divided modules and the determined model parameters, the modeling is completed, and the model is configured and corrected; the various models are connected and coupled to obtain an overall modular simulation model for analysis and verification; local debugging and testing can be carried out when the design of other modules is not clear, and other modules can be avoided from being changed at the same time when making adjustments in the later stage, thereby improving the versatility and debuggability of the constructed model, and at the same time improving the efficiency of thermal analysis design.

[0082] On the basis of the above-mentioned embodiment, the thermal analysis modeling method for the equipment cabin of a high-speed aircraft can also be embodied as follows: establishing an aerodynamic heat calculation model.

[0083] Specifically, the aerodynamic heat calculation model mainly provides parameters for the calculation of structural heat conduction and thermal sealing structure. Its main function is to convert the current flight state into input for thermal sealing and structural heat calculation. The input-output relationship of the aerodynamic heat calculation model is as follows: Figure 5 shown.

[0084] It should be noted that the modeling of the aerodynamic heat calculation model requires the integration of the calculation function of atmospheric data and the function of using typical state points to calculate the thermal load at the current altitude and flight speed. To achieve the above functions, it is also necessary to establish a connection between the aerodynamic heat parameters of the typical state points and the module as input. The specific modeling process is as follows:

[0085] 111. An interpolation method for solving aerodynamic thermal loads in arbitrary states using typical state points.

[0086] It can be understood that since the aerodynamic thermal data provided by the aerodynamic thermal professional are data of typical state points, the calculation of cabin thermal problems requires aerodynamic thermal data at any time and in any flight state. Therefore, it is necessary to establish a method for calculating the aerodynamic thermal data at the current moment based on the typical state points; specifically, the embodiment of the present application adopts a method of linear interpolation of data of adjacent Mach number state points to obtain the equivalent adiabatic temperature and convective heat transfer coefficient of the required calculation state, and after correction using the flight altitude, the aerodynamic thermal load calculation of the current state is completed in combination with the temperature of the outer surface of the structure in the current state.

[0087] 112. Aerothermal engineering calculation method using typical structural characteristics.

[0088] It can be understood that the calculation of the aerodynamic thermal calculation model needs to be based on the aerodynamic thermal data of typical state points; the aerodynamic thermal data required by the module is a list of average adiabatic temperature and convective heat transfer coefficient on a certain area. Due to the existence of certain regularity, it is planned to complete the loading of typical state point data in the form of input arrays on the setting interface of the module; and the required input array needs to be calculated and generated using a three-dimensional to one-dimensional aerodynamic thermal conversion tool.

[0089] Specifically, a simulation calculation model is established and debugged to obtain an aerodynamic thermal calculation model, which is used to provide parameters for the thermal conductivity calculation of the cabin structure and the calculation of the cabin thermal sealing structure. According to the required defined interfaces and functions, a simulation calculation model is established through Simulink, and the model is debugged using steady-state boundary conditions.

[0090] Optionally, the calculation of the aerodynamic thermal calculation model requires an aerodynamic thermal parameter table of typical state points as input, and a three-dimensional aerodynamic thermal parameter processing module is set to convert the aerodynamic thermal load file of the aerodynamic profession into the aerodynamic thermal parameter table required by the aerodynamic thermal calculation model; specifically, the main function of the model of the three-dimensional aerodynamic thermal parameter processing module is to screen the selected state points according to the defined structural surface size, and further, to perform weighted averaging based on the calculation results of the grid points to calculate the average adiabatic temperature and heat flow value of the structural surface, so as to provide an aerodynamic thermal parameter table for the aerodynamic thermal calculation model.

[0091] On the basis of the above-mentioned embodiments, the thermal analysis modeling method for the cabin of high-speed aircraft equipment can also be concretized as follows: the structural heat conduction calculation model includes a material database for cabin structure heat transfer, and the structural heat conduction calculation model describes the one-dimensional heat transfer process along the normal direction in the structure, which is used to calculate the temperature state of the structure as the calculation boundary of the gas heat exchange in the cabin.

[0092] Specifically, the structural heat conduction calculation model is used to calculate the temperature state of the structure as the calculation boundary of the gas heat exchange in the cabin; it mainly involves the heat load loading of the aerodynamic thermal boundary, the surface radiation heat transfer calculation, and the heat conduction calculation in the structure. Its input and output relationship is as follows: Figure 6 shown.

[0093] It should be noted that the heat transfer process of cabin structure design is relatively complex, so many parameters need to be defined; in addition, the heat transfer of the cabin structure may involve metal structures and non-metallic thermal protection structures, and the relationship between the module and the structural physical parameters needs to be established. The specific modeling process is as follows:

[0094] 121. Obtain the material database of cabin structure heat transfer and establish a structural heat conduction calculation model to calculate the temperature state of the structure as the calculation boundary of the gas heat exchange in the cabin.

[0095] Optionally, the structure of a hypersonic aircraft includes a skin and a thermal protection structure, which involves a variety of materials, that is, the calculation of the heat transfer process of non-uniform physical properties, and has high requirements for computational convergence. Therefore, the embodiment of the present application uses the Simscape heat transfer toolbox under MATLAB / Simulink to establish a computational model of the structural heat transfer process. The toolbox includes heat conduction, convection and radiation heat transfer processes, and can use an independent solver to meet the requirements of modular simulation.

[0096] In addition, in terms of node division, in order to achieve the universality of the module, it is planned to increase the number of structural division nodes to achieve the calculation universality of adjusting the design thickness of the thermal protection structure; due to the large difference between the structure and the thermal protection thickness, the number of nodes is set to be relatively matched.

[0097] Among them, since a variety of materials may be used for structure and thermal protection, it is necessary to establish the relationship between the calculation module and the material properties. According to specific needs, the physical property parameters can be established inside the model, and the user can select them using the menu as needed.

[0098] As described above, according to the required defined interfaces and functions, a simulation model of the structural heat conduction calculation model is established through Simulink, and the model is debugged using steady-state boundary conditions.

[0099] On the basis of the above-mentioned embodiments, the thermal analysis modeling method for the equipment cabin of a high-speed aircraft can also be embodied as follows: establishing a calculation model for the heat exchange of gases in the cabin.

[0100] Specifically, the main function of the cabin gas heat exchange calculation model is to calculate the cabin gas heat exchange. The cabin gas heat exchange is interconnected with thermal management forms such as liquid nitrogen, structural thermal protection, thermal sealing, and equipment heat exchange. The input-output relationship is relatively complex. The input-output relationship of the calculation module is as follows: Figure 7 shown.

[0101] It should be noted that the flow process in the cabin is a comprehensive process of heat transfer and mass transfer. The heat transfer process is relatively complex. Compared with the heat transfer problem of the structure, the heat transfer of the gas involves pressure changes, and the process description is more difficult. The calculation of the cabin thermal management model needs to be coupled to this model. The specific modeling process is as follows:

[0102] 131. Determine the heat exchange object and heat exchange process of the gas in the cabin.

[0103] Optionally, in the modular model, the physical properties of nitrogen are used to calculate the changes in the gas in the cabin according to the state equation of an ideal gas.

[0104] On the other hand, in order to simplify the calculation and improve the calculation efficiency, the cabin gas state is proposed to adopt the lumped parameter method, that is, the gas in the cabin is considered to have the same physical properties at the same time, and further evaluation is required based on the three-dimensional simulation results.

[0105] 132. Determine the calculation method of the heat transfer coefficient between the cabin and the equipment surface, and between the cabin and the body structure.

[0106] Specifically, there is a heat exchange process between the cabin and the equipment surface, and between the cabin and the inner surface of the body structure. The amount of heat exchange depends on the temperature difference on the one hand, and on the flow state of the gas in the cabin on the other hand. In the modular calculation process, the description of the gas in the cabin is simplified in order to increase the calculation speed. The embodiment of the present application establishes a proxy model of the relationship between the gas inflow / outflow process and the convective heat transfer coefficient, and then uses the proxy model to establish a method for calculating the heat transfer coefficient.

[0107] Specifically, the liquid nitrogen cooling process involves a phase change process, which will rapidly change the state of the gas in the cabin. Therefore, liquid nitrogen cooling can be defined as instantaneous vaporization cooling in the modular model, and there is no need to consider the time scale of the liquid nitrogen vaporization process. Among them, according to the design results of the thermal management solution, if the vaporization process does not occur in the equipment cabin, it will be treated as cold air.

[0108] 133. Determine cabin cooling and pressure relief control plan.

[0109] Specifically, the cabin cooling and pressure relief control plan is determined according to specific needs.

[0110] 134. Based on the above results, a calculation model for cabin gas heat exchange is established to calculate the cabin gas heat exchange.

[0111] Specifically, once the modeling scheme is determined, the simulation model of the cabin gas heat exchange calculation model can be established using Simulink software according to the required defined interfaces and functions, and the model can be debugged using the set boundary conditions.

[0112] Based on the above embodiments, the thermal analysis modeling method for high-speed aircraft equipment cabins can also be concretized as follows: the thermal sealing calculation model is used to calculate the heat leakage caused by the inconsistent gas state between the internal and external environments through the thermal sealing structure, and calculate the leakage amount and temperature of the output gas.

[0113] Specifically, the heat seal calculation model is used to calculate the heat leakage caused by the internal and external environmental gas state and the heat seal structure. Its output parameters are the gas leakage and temperature, and the definition parameters are the form of the heat seal structure. The input and output relationship of the module is as follows: Figure 8 shown.

[0114] It should be noted that it is necessary to calculate the thermal sealing structural performance under different working conditions, different structural forms, different materials and geometric dimensions, the possible degree of thermal sealing failure and the corresponding changes in cabin heat load, and realize rapid prediction of thermal sealing performance.

[0115] In the embodiment of the present application, the selected heat sealing structure is mainly composed of two parts, one is the possible leakage at the seam of the skin, and the other is the leakage at the fuselage cover. At present, corresponding CFD simulation models have been established for these two potential leakage situations. It is planned to carry out simulation calculations and use the three-dimensional calculation results to determine the specific modeling method of the module.

[0116] On the basis of the above-mentioned embodiments, the thermal analysis modeling method for the equipment cabin of a high-speed aircraft can also be embodied as follows: establishing an equipment heat exchange calculation model.

[0117] Specifically, electronic equipment is the internal heat source of cabin heat problems. It mainly exchanges heat with the cabin environment through its own structure. The heat exchange power and its own temperature change are the parameters that the model focuses on. The input-output relationship is as follows: Fig. 9 As shown. Among them, the process of modeling the equipment heat exchange calculation model is:

[0118] 151. Determine the key parameters of cabin equipment heat exchange in the parametric simulation of cabin problems.

[0119] Specifically, the heat dissipation problem has been considered in the design of electronic equipment, and the heat dissipation path planned inside it affects the heat dissipation power of different surfaces. Therefore, the key parameters of cabin electronic equipment in the parametric simulation of cabin problems are determined according to specific needs.

[0120] 152. Determine the relationship between the working state and the heating power, and determine the relationship between the equipment temperature and the equipment heat exchange process.

[0121] Optionally, in modular simulation, the heating power of the electronic device is set to be constant, that is, if the electronic device is working, the heat generation is constant, that is, a constant coefficient is set; if there are other requirements for the device, it is modeled separately.

[0122] 153. Establish an equipment heat exchange calculation model to calculate the heat exchange between the electronic equipment and the cabin and the temperature of the electronic equipment.

[0123] On the basis of the above-mentioned embodiments, the thermal analysis modeling method for the equipment cabin of a high-speed aircraft can also be embodied as follows: the performance evaluation model is used to calculate the utilization efficiency of the heat sink, the cooling efficiency of the cold source and the system compensation.

[0124] Optionally, the performance evaluation model includes a performance evaluation module and a compensation evaluation module, which can perform effective performance evaluation / compensation evaluation on the cabin thermal management solution, thereby guiding the optimal design of the cabin thermal management solution.

[0125] The heat sink utilization efficiency E is comprehensively defined from two aspects: liquid nitrogen cooling efficiency η and system compensation δ:

[0126] E = η·δ;

[0127] The liquid nitrogen cooling efficiency η is the ratio of the heat removed from the equipment cabin to the theoretical maximum cooling capacity, as shown in the following formula:

[0128] ;

[0129] Among them, Qc is the heat taken away by liquid nitrogen from the equipment cabin; m is the liquid nitrogen consumption; γ is the latent heat of vaporization of liquid nitrogen; is the specific heat of nitrogen; It is the target of cabin temperature control; is the phase transition temperature of liquid nitrogen.

[0130] The system compensation δ is the ratio of the weight of liquid nitrogen to the total weight of the system, as shown in the following formula.

[0131] ;

[0132] Among them, My is the weight of liquid nitrogen and Ms is the total weight of the system.

[0133] Therefore, according to the requirements of efficiency and compensation evaluation, the main input parameters of the performance evaluation model are the heat of the equipment cabin taken away by liquid nitrogen and the flow demand of liquid nitrogen. Therefore, the input-output relationship of this module is as follows: Fig.10 shown.

[0134] Establish an efficiency evaluation model to calculate the heat sink utilization efficiency, liquid nitrogen cooling efficiency and system compensation. Optionally, after confirming the evaluation parameters, the main task of the efficiency evaluation module modeling is to complete the establishment of the MATLAB / Simulink simulation model according to the defined parameters.

[0135] On the basis of the above-mentioned embodiments, the thermal analysis modeling method for the high-speed aircraft equipment cabin can also be concretized as follows: when the heat transfer process is difficult to describe, a proxy model of the heat transfer process is established, including the following steps.

[0136] 171. Select sample points and establish a sample point database based on the calculation results of three-dimensional simulation or experiment.

[0137] 172. Establish an agent model based on computer tool parameters.

[0138] 173. The proxy model is validated using the set strategy and used in the overall modeling of cabin thermal analysis.

[0139] Specifically, in the modular modeling process of cabin thermal problem analysis, compared with the three-dimensional heat transfer process in space, some models need to be simplified, but the accuracy problem caused by simplification needs to be solved, otherwise the calculation results of the modular model are not accurate enough, which will lead to invalid calculation results. Therefore, when encountering the problem that the parameters are difficult to evaluate due to simplification, it is necessary to establish a proxy model based on computer tool parameters. The specific modeling process is as follows:

[0140] Optionally, random sampling data is obtained through random sampling space, and the experimental design method is used to randomly and uniformly select points. The response value of each sampling point is obtained by simulation. The sampling point and the response value are established with the corresponding approximate mathematical relationship through the corresponding algorithm, and this mathematical relationship is used to replace the actual complex relationship. From the construction process of the surrogate model, it can be seen that the surrogate model is a comprehensive modeling technology that includes experimental design and approximate methods, among which the approximate method is its main body and the main content of the surrogate model research. Experimental design is an important branch of mathematical statistics. It studies how to arrange the experimental plan, improve the rationality of the distribution of experimental samples, reduce the influence of experimental errors, and make the experimental results reasonably statistically analyzed. Common experimental design methods include full factorial design method, orthogonal experimental design method, Latin square experimental design method, etc. The most important technologies of the surrogate model are response surface model (RSM) based on polynomial equations, radial basis function (RBF), artificial neural network (ANN), Kriging, etc.

[0141] As described above, according to the modular modeling method and basic modeling conditions formed in the embodiment of the present application, the architecture of the modular model is established as follows: Fig.11 As shown in the figure, after modular modeling, each aerodynamic heat calculation model, structural heat conduction calculation model, and equipment heat exchange calculation model can be modeled through a single standardized module by adjusting parameters. Each module in the system can perform calculations on its own, without the need to form a whole according to the above architecture before performing calculations, which can reduce the initial modeling cost and reduce the debugging workload. It should be noted that the middle part of the above architecture contains parameter settings and model definition content.

[0142] The above steps are not to be performed in a strict order as described in the numbers, but should be understood as an overall solution.

[0143] In the second aspect, based on the above embodiments, Fig.12 This is a schematic diagram of the structure of a high-speed aircraft equipment cabin thermal analysis modeling device provided in an embodiment of the present application. Fig.12 The high-speed aircraft equipment cabin thermal analysis modeling device provided in this embodiment specifically includes: a model building module 601, a parameter determination module 602, a model verification module 603 and an overall simulation module 604.

[0144] Among them, the model building module 601 is used to divide the different heat transfer processes of cabin thermal analysis into several modules according to the heat transfer process and thermal control scheme, and to establish the model of each module respectively; the parameter determination module 602 is used to determine the model parameters of each module according to the module division, wherein the model parameters include two types: fixed parameters and interface parameters; the model verification module 603 is used to complete the modeling according to the different divided modules and the determined model parameters, and to configure and calibrate the model; the overall simulation module 604 is used to connect and couple the various models to obtain an overall modular simulation model for analysis and verification.

[0145] As described above, the embodiment of the present application divides the different heat transfer processes of cabin thermal analysis into several modules according to the heat transfer process and thermal control scheme, and establishes the model of each module respectively; determines the model parameters of each module according to the module division, wherein the model parameters include two types: fixed parameters and interface parameters; completes the modeling according to the different divided modules and the determined model parameters, and configures and corrects the model; connects and couples the models to obtain an overall modular simulation model for analysis and verification; can perform local debugging and testing when the design of other modules is not clear, and can avoid the need to change other modules at the same time when making adjustments in the later stage, thereby improving the versatility and debuggability of the constructed model, and at the same time improving the efficiency of thermal analysis design.

[0146] The high-speed aircraft equipment cabin thermal analysis modeling device provided in the embodiment of the present application can be used to execute the high-speed aircraft equipment cabin thermal analysis modeling method provided in the above-mentioned embodiment, and has corresponding functions and beneficial effects.

[0147] On the third aspect, an embodiment of the present application provides a high-speed aircraft equipment cabin thermal analysis modeling system, including: an integrated model calculation module, an integrated design tool interface and a model development interface, the integrated model calculation module is connected to the integrated design tool interface and the model development interface; the integrated model calculation module includes the high-speed aircraft equipment cabin thermal analysis modeling device as described above.

[0148] Optionally, the embodiment of the present application uses the Simulink model as the calculation kernel, and uses the integrated design tool interface to complete data management and display interaction; the built-in Simulink model development interface is called for designers to perform model maintenance and proxy model loading. The thermal management solution design and model development problem interface can be separated to facilitate tool use and data management, while also being debuggable and scalable.

[0149] In a fourth aspect, an embodiment of the present application further provides an electronic device that can integrate the high-speed aircraft equipment cabin thermal analysis modeling device provided in an embodiment of the present application. Fig.13 Schematic diagram of the structure of an electronic device provided by an embodiment of the present application. Fig.13 The electronic device includes: an input device 73, an output device 74, a memory 72 and one or more processors 71; the memory 72 is used to store one or more programs; when one or more programs are executed by one or more processors 71, the one or more processors 71 implement the high-speed aircraft equipment cabin thermal analysis modeling method provided in the above embodiment. The input device 73, the output device 74, the memory 72 and the processor 71 can be connected by a bus or other means. Fig.13 The example of connecting through bus is taken in the following.

[0150] The processor 71 executes various functional applications and data processing of the device by running the software programs, instructions and modules stored in the memory 72, that is, realizes the above-mentioned high-speed aircraft equipment cabin thermal analysis modeling method.

[0151] The electronic device provided above can be used to execute the thermal analysis modeling method for the high-speed aircraft equipment cabin provided in the above embodiment, and has corresponding functions and beneficial effects.

[0152] In a fifth aspect, an embodiment of the present application further provides a computer-readable storage medium, the computer-readable storage medium including a stored computer program; wherein, when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute the above-mentioned high-speed aircraft equipment cabin thermal analysis modeling method, and can achieve the same beneficial effects.

[0153] Of course, the storage medium containing computer executable instructions provided in the embodiment of the present application is not limited to the above-mentioned thermal analysis modeling method for the cabin of high-speed aircraft equipment, and the computer executable instructions can also execute the relevant operations in the thermal analysis modeling method for the cabin of high-speed aircraft equipment provided in any embodiment of the present application.

[0154] In a sixth aspect, the embodiments of the present application also provide a computer program product, and the methods of the various embodiments of the present application can be implemented in whole or in part by software, hardware, firmware, or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer programs or instructions. When a computer program or instruction is loaded and executed on a computer, the processes or functions described in the various embodiments of the present application are executed in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, a network device, a user device, a core network device, an OAM (Open Application Model) or other programmable device.

[0155] A computer program or instruction 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, a computer program or instruction may be transmitted from one website, computer, server or data center to another website, computer, server or data center by wired or wireless means. A computer-readable storage medium may be any available medium that a computer can access or a data storage device such as a server or data center that integrates one or more available media. Available media may be magnetic media, such as a floppy disk, hard disk, or magnetic tape; may also be optical media, such as a digital video disk; or may be semiconductor media, such as a solid-state drive. The computer-readable storage medium may be a volatile or non-volatile storage medium, or may include both volatile and non-volatile types of storage media.

[0156] In several embodiments provided in the present application, it should be understood that the disclosed devices and methods can also be implemented in other ways. The device embodiments described above are merely schematic. For example, the flowcharts and block diagrams in the accompanying drawings show the possible architecture, functions and operations of the devices, methods and computer program products according to multiple embodiments of the present application. In this regard, each box in the flowchart or block diagram can represent a module, a program segment or a part of the code, and a part of the module, program segment or code contains one or more executable instructions for implementing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order from the order marked in the accompanying drawings. For example, two consecutive boxes can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram and / or flowchart, and the combination of boxes in the block diagram and / or flowchart can be implemented with a dedicated hardware-based system that performs a specified function or action, or can be implemented with a combination of dedicated hardware and computer instructions.

[0157] In addition, the functional modules in the various embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.

[0158] If the function is implemented in the form of a software function module and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including a number of instructions to enable an electronic device (which can be a personal computer, server, or network device, etc.) to perform all or part of the steps of the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, and other media that can store program codes.

[0159] The above description is only an embodiment of the present application and is not intended to limit the scope of protection of the present application. For those skilled in the art, the present application may have various changes and variations. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the scope of protection of the present application. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings.

[0160] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

[0161] It should be noted that, in this article, relational terms such as first and second, etc. 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 sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

Claims

1. A thermal analysis modeling method for a high-speed aircraft equipment cabin, characterized in that: The following steps are involved: According to the heat transfer process and thermal control scheme, the different heat transfer processes of cabin thermal analysis are divided into several modules and the models of each module are established respectively; According to the module division, the model parameters of each module are determined, wherein the model parameters include two types: fixed parameters and interface parameters; Complete modeling according to the different modules and determined model parameters, and configure and calibrate the model; Connect and couple the various models to obtain an overall modular simulation model for analysis and verification; The heat transfer process includes the heat exchange process between aerodynamic heat and cabin structure, the heat conduction process of heat in the cabin structure, and the heat exchange process of gas in the cabin caused by leakage of electronic equipment, cabin structure and gaps; The models of the module include aerodynamic heat calculation model, structural heat conduction calculation model, cabin gas heat exchange calculation model, thermal sealing calculation model, equipment heat exchange calculation model, and efficiency evaluation model; The performance evaluation model is used to calculate the heat sink utilization efficiency, the cooling efficiency of the cold source and the system compensation, wherein: The heat sink utilization efficiency E is comprehensively defined from two aspects: liquid nitrogen cooling efficiency η and system compensation δ: E = η·δ; The liquid nitrogen cooling efficiency η is the ratio of the heat removed from the equipment cabin to the theoretical maximum cooling capacity, as shown in the following formula: η = Q c / m [ γ + c p ( T c - T γ )]； in, Q c is the heat removed from the equipment cabin by liquid nitrogen; m is the liquid nitrogen consumption; γ is the latent heat of vaporization of liquid nitrogen; c p is the specific heat of nitrogen; T c It is the target of cabin temperature control; T γ is the phase transition temperature of liquid nitrogen; The system compensation δ is the ratio of the weight of liquid nitrogen to the total weight of the system, as shown in the following formula; δ = M and / M s; Among them, My is the weight of liquid nitrogen, Ms is the total weight of the system; When the heat transfer process is difficult to describe, a proxy model of the heat transfer process is established, including the following steps: Select sample points and establish a sample point database based on the calculation results of three-dimensional simulation or experiment; Establishing agent models based on computer tool parameters; The surrogate model was validated using the set strategy and used in the overall modeling of cabin thermal analysis.

2. The high-speed aircraft equipment cabin thermal analysis modeling method according to claim 1 is characterized in that: When establishing the aerodynamic heat calculation model, the following method is used: Interpolation method for solving aerodynamic thermal loads in arbitrary states using typical state points; Aerothermal engineering calculation methods using typical structural characteristics.

3. The high-speed aircraft equipment cabin thermal analysis modeling method according to claim 1, characterized in that: The structural heat conduction calculation model includes a material database for cabin structure heat transfer, and the structural heat conduction calculation model describes the one-dimensional heat transfer process along the normal direction in the structure, which is used to calculate the temperature state of the structure as a calculation boundary for gas heat exchange in the cabin.

4. The high-speed aircraft equipment cabin thermal analysis modeling method according to claim 1, characterized in that: Establishing the cabin gas heat exchange calculation model includes the following steps: Determine the heat transfer object and heat transfer process of the gas in the cabin; Determine the calculation method of heat transfer coefficient between cabin and equipment surface, cabin and fuselage structure; Determine cabin cooling and pressure relief control plan; Based on the above results, a calculation model for cabin gas heat exchange is established to calculate the cabin gas heat exchange.

5. The high-speed aircraft equipment cabin thermal analysis modeling method according to claim 1, characterized in that: The heat sealing calculation model is used to calculate the heat leakage caused by the inconsistent gas state of the internal and external environments through the heat sealing structure, and calculate the leakage amount and temperature of the output gas.

6. The high-speed aircraft equipment cabin thermal analysis modeling method according to claim 1, characterized in that: Establishing the equipment heat exchange calculation model includes the following steps: Determine the key parameters of cabin equipment heat exchange in the parametric simulation of cabin problems; Determine the relationship between working status and heating power, and determine the relationship between equipment temperature and equipment heat exchange process; An equipment heat exchange calculation model is established to calculate the heat exchange between the electronic equipment and the cabin and the temperature of the electronic equipment.

7. A thermal analysis modeling device for a high-speed aircraft equipment cabin, characterized in that: include: Model building module, which is used to divide the different heat transfer processes of cabin thermal analysis into several modules according to the heat transfer process and thermal control scheme and build the model of each module respectively; A parameter determination module, used to determine the model parameters of each module according to the module division situation, wherein the model parameters include two types: fixed parameters and interface parameters; The model verification module is used to complete the modeling according to the different modules divided and the determined model parameters, and to configure and calibrate the model; The overall simulation module is used to connect and couple the various models to obtain an overall modular simulation model for analysis and verification; The heat transfer process includes the heat exchange process between aerodynamic heat and cabin structure, the heat conduction process of heat in the cabin structure, and the heat exchange process of gas in the cabin caused by leakage of electronic equipment, cabin structure and gaps; The models of the module include aerodynamic heat calculation model, structural heat conduction calculation model, cabin gas heat exchange calculation model, thermal sealing calculation model, equipment heat exchange calculation model, and efficiency evaluation model; The performance evaluation model is used to calculate the heat sink utilization efficiency, the cooling efficiency of the cold source and the system compensation, wherein: The heat sink utilization efficiency E is comprehensively defined from two aspects: liquid nitrogen cooling efficiency η and system compensation δ: E = η·δ; The liquid nitrogen cooling efficiency η is the ratio of the heat removed from the equipment cabin to the theoretical maximum cooling capacity, as shown in the following formula: η = Q c / m [ γ + c p ( T c - T γ )]； in, Q c is the heat removed from the equipment cabin by liquid nitrogen; m is the liquid nitrogen consumption; γ is the latent heat of vaporization of liquid nitrogen; c p is the specific heat of nitrogen; T c It is the target of cabin temperature control; T γ is the phase transition temperature of liquid nitrogen; The system compensation δ is the ratio of the weight of liquid nitrogen to the total weight of the system, as shown in the following formula; δ = M and / M s; Among them, My is the weight of liquid nitrogen, Ms is the total weight of the system; When the heat transfer process is difficult to describe, a proxy model of the heat transfer process is established, including the following steps: Select sample points and establish a sample point database based on the calculation results of three-dimensional simulation or experiment; Establishing agent models based on computer tool parameters; The surrogate model was validated using the set strategy and used in the overall modeling of cabin thermal analysis.

8. A high-speed aircraft equipment cabin thermal analysis modeling system, characterized in that: include: An integrated model calculation module, an integrated design tool interface and a model development interface, wherein the integrated model calculation module is connected to the integrated design tool interface and the model development interface; The integrated model calculation module includes the high-speed aircraft equipment cabin thermal analysis modeling device as described in claim 7.

9. An electronic device, characterized in that: include: A processor, a memory and a bus, wherein the processor is connected to the memory via the bus, and the memory stores computer-readable instructions. When the computer-readable instructions are executed by the processor, they are used to implement the thermal analysis modeling method for a high-speed aircraft equipment cabin as described in any one of claims 1 to 6.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, which, when executed by a server, implements the high-speed aircraft equipment cabin thermal analysis modeling method as described in any one of claims 1-6.

11. A computer program product, characterized in that The computer program product comprises instructions, which, when executed by a computer, enable the computer to implement the high-speed aircraft equipment compartment thermal analysis modeling method according to any one of claims 1-6.

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