Cabin thermal sealing and thermal management integrated design method, device, equipment and medium

Abstract

The embodiments of the present application provide a method, device, equipment and medium for integrated design of cabin thermal sealing and thermal management, the method comprising: performing boundary constraints on the initial input conditions of the cabin to obtain boundary conditions; based on the boundary conditions, coupling the thermal sealing module and the thermal management module through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management; inputting the integrated design scheme for cabin thermal sealing and thermal management into a three-dimensional model for verification; coupling the interface influencing factors between multiple modules in the design, thereby solving the problem of using simple idealized boundaries when designing sub-modules separately, and each module participating in the design most of the time, thereby solving the problem of high structural weight cost and low efficiency caused by modules being in a waiting state for a long time in the traditional process.

Description

Technical Field

[0001] The present application relates to the field of thermal design technology, and more specifically, to a method, device, equipment and medium for integrated design of cabin thermal sealing and thermal management. Background Art

[0002] At present, the status of thermal sealing, thermal management design and thermal simulation of hypersonic aircraft cabins is that most of the work is still in the stage of single technical research or single-point problem simulation. The common characteristics of existing cabin designs are that they mostly adopt passive thermal design solutions that rely on the temperature resistance of materials, and mainly focus on one-time, short-time flight, ablative thermal protection technologies such as hypersonic missiles, space shuttles, and spacecraft. The cabin wall structure design is highly redundant, resulting in the aircraft's structural weight for thermal protection accounting for more than 30%, and after adding the weight of the load-bearing cold structure, the proportion is close to 50%; there are problems such as high structural weight cost, serious space volume occupation (the thickness of the insulation layer can reach 10~25mm), poor impact resistance, low thermal design efficiency and limited service life. At the same time, the thermal sealing design of the switch cover on the cabin surface is less considered, and simulation analysis is mostly carried out according to independent closed cabins, which makes it impossible to finely analyze the dynamic thermal boundary of the cabin heat source, and the cabin thermal management system is inefficient, and more weight costs are also paid. Summary of the invention

[0003] The purpose of the embodiments of the present application is to provide a method, device, equipment and medium for integrated design of cabin thermal sealing and thermal management, so as to solve the problems of high structural weight cost and low thermal design efficiency in existing thermal sealing and thermal management simulation analysis methods.

[0004] In a first aspect, an embodiment of the present application provides a method for integrated design of cabin thermal sealing and thermal management, including:

[0005] Apply boundary constraints to the initial input conditions of the cabin to obtain boundary conditions;

[0006] Based on boundary conditions, the thermal sealing module and thermal management module are coupled through one-dimensional design tools to construct an integrated design scheme for cabin thermal sealing and thermal management;

[0007] The integrated design of cabin thermal sealing and thermal management is input into the three-dimensional model for verification.

[0008] In the above implementation process, boundary constraints are imposed on the initial input conditions of the cabin to obtain boundary conditions; based on the boundary conditions, the thermal sealing module and the thermal management module are coupled through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management; the integrated design scheme for cabin thermal sealing and thermal management is input into the three-dimensional model for verification; the interface influencing factors between multiple modules in the design are coupled, which solves the problem of using simple idealized boundaries when designing individual modules separately. Each module participates in the design most of the time, which solves the problem of high structural weight cost and low efficiency caused by long-term waiting state of modules in the traditional process.

[0009] Furthermore, the initial input conditions include: flight profile, cabin geometry model, aerodynamic heat, equipment heat, cabin pressure requirement, cabin temperature requirement, internal flow inlet condition and internal flow outlet condition.

[0010] In the above implementation process, the initial input conditions are confirmed to ensure the accuracy and efficiency of the generation of the integrated design scheme of cabin thermal sealing and thermal management.

[0011] Furthermore, coupling the thermal sealing module and the thermal management module by using a one-dimensional design tool includes:

[0012] The heat sealing module and the thermal management module are coupled through the boundary loading module, the heat sealing thermal management parameter matching module, the heat sealing thermal management scheme design module, the flow heat transfer calculation module, the efficiency and compensation evaluation module, and the scheme output module.

[0013] In the above implementation process, by coupling the thermal sealing module and the thermal management module, an integrated design scheme of cabin thermal sealing and thermal management is constructed, which improves the simulation accuracy without repeated iterations.

[0014] Furthermore, based on the boundary conditions, the thermal sealing module and the thermal management module are coupled by a one-dimensional design tool to construct an integrated design scheme of cabin thermal sealing and thermal management, including:

[0015] The three-dimensional boundary condition data is converted into one-dimensional boundary condition data through the boundary loading module;

[0016] Provide basic physical property parameters based on heat sealing thermal management parameter matching module;

[0017] Based on the boundary conditions, the initial design scheme is designed through the heat seal thermal management scheme design module combined with the parameter influence mechanism;

[0018] The various modules of thermal sealing and thermal management are coupled through the flow and heat transfer calculation module;

[0019] Based on the performance and compensation evaluation module, the initial design scheme is evaluated for performance, compensation and parameter optimization;

[0020] The integrated design scheme of cabin thermal sealing and thermal management is output through the scheme output module.

[0021] In the above implementation process, a one-dimensional design tool is used to couple the cabin thermal sealing and thermal management. The one-dimensional design tool reduces the complex cabin thermal comprehensive design problem to one dimension through methods such as averaging and reasonable partitioning. While ensuring a certain calculation accuracy, the coupling design of thermal sealing and thermal management solutions can be quickly performed.

[0022] Furthermore, the three-dimensional boundary condition data is converted into one-dimensional boundary condition data by using the boundary loading module, including:

[0023] The aerodynamic heat loading module reads the three-dimensional aerodynamic heat flow data and pressure data of typical state points output by the simulation software, converts the calculation results of the three-dimensional aerodynamic heat flow data into surface average heat flow and surface average pressure, and calculates the aerodynamic heat flow value and pressure value under the corresponding state according to the height, Mach number and wall temperature;

[0024] The cabin structure characteristic data is extracted through the cabin structure loading module, and the three-dimensional structure is characterized in one dimension;

[0025] The electronic equipment heat source module calculates the temperature change value of the equipment and dissipates heat to the environment according to the properties and operating conditions of the equipment.

[0026] In the above implementation process, each boundary data and boundary conditions are loaded into the one-dimensional design tool through the boundary loading module to facilitate the construction of subsequent design solutions.

[0027] Furthermore, the coupling of the thermal sealing and thermal management modules through the flow heat transfer calculation module includes:

[0028] The thermal sealing interface module calculates the change of structural temperature and boundary heat flow according to the thickness of the thermal insulation layer, aerodynamic heat conditions and cabin gas temperature conditions, and calculates the gas leakage and boundary heat flow according to the thermal sealing form, seal deformation, aerodynamic heat conditions and cabin airflow conditions;

[0029] The cabin flow module is used to calculate the cabin flow heat transfer according to the initial conditions and boundary conditions. The cabin flow heat transfer is calculated based on the boundary conditions of cabin structure, inner wall temperature and leakage to obtain the cabin temperature, pressure distribution and heat sink utilization.

[0030] The cabin radiation heat transfer module is used to calculate the radiation heat transfer between cabin walls according to given conditions;

[0031] The electronic equipment heat source module calculates the temperature change of the equipment and dissipates heat to the environment according to the properties and operating conditions of the equipment.

[0032] In the above implementation process, the flow and heat transfer calculation module is the core calculation part of the one-dimensional design tool. Some parameters are coupled between various modules to complete the coupled solution of thermal sealing and thermal management, thereby improving the simulation accuracy and efficiency.

[0033] Furthermore, the performance evaluation, compensation evaluation and parameter optimization of the initial design scheme based on the performance and compensation evaluation module include:

[0034] Based on the performance evaluation module, the cabin leakage, heat sink utilization, average cabin temperature, and pressure changes along with the flight profile are calculated;

[0035] The compensation evaluation module is used to calculate the mass compensation of the cabin thermal integrated design system, including thermal sealing structure compensation, thermal management system compensation and total compensation;

[0036] Through the parameter optimization module, the thermal management and thermal sealing parameters are optimized with the goal of minimum mass compensation. Based on the influence mechanism of each parameter on the flow and heat transfer in the cabin, an optimization objective function is established.

[0037] In the above implementation process, it is used to evaluate and optimize the cabin thermal design scheme, and the performance and compensation evaluation module is used to evaluate the performance and compensation of the result scheme and provide suggestions for scheme improvement.

[0038] Furthermore, the integrated design scheme of cabin thermal sealing and thermal management is input into the three-dimensional model for verification, including:

[0039] According to the thermal sealing design scheme of the integrated thermal sealing and thermal management design scheme of the cabin, the wall temperature of the cabin structure and the heat and mass transfer of the sealing structure are calculated to obtain the first data in the cabin; wherein the first data includes: leakage, wall temperature, and cabin temperature;

[0040] Based on the simulation boundary of the thermal management data, the second data in the cabin is calculated according to the thermal management design scheme of the cabin thermal sealing and thermal management integrated design scheme; wherein the second data includes flow heat transfer, mass compensation, and heat sink utilization;

[0041] It is determined whether the cabin temperature is within the set cabin temperature range. If so, the three-dimensional model is verified. If not, feedback is given to the one-dimensional design tool to instruct the one-dimensional design tool to optimize parameters.

[0042] During the above implementation process, the integrated design scheme of cabin thermal sealing and thermal management is subjected to three-dimensional inspection to optimize the design scheme and improve the simulation accuracy.

[0043] In a second aspect, an embodiment of the present application provides a cabin thermal sealing and thermal management integrated design device, comprising:

[0044] A boundary constraint module is used to perform boundary constraints on the initial input conditions of the cabin to obtain boundary conditions;

[0045] The scheme design module is used to couple the thermal sealing module and the thermal management module based on boundary conditions through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management;

[0046] The scheme verification module is used to input the cabin thermal sealing and thermal management integrated design scheme into the three-dimensional model for verification.

[0047] In a third aspect, an embodiment of the present application provides an electronic device, including:

[0048] 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 integrated design method for cabin thermal sealing and thermal management as described above.

[0049] In a fourth 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 integrated design method for cabin thermal sealing and thermal management as described above.

[0050] In a fifth 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 integrated design method for cabin thermal sealing and thermal management as described above. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] 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.

[0052] Figure 1 A schematic diagram of a process flow of a cabin thermal sealing and thermal management integrated design method provided in an embodiment of the present application;

[0053] Figure 2 A flow chart for inputting the cabin thermal sealing and thermal management integrated design scheme into a three-dimensional model for verification provided in an embodiment of the present application;

[0054] Figure 3 It is a structural schematic diagram of a cabin thermal sealing and thermal management integrated design device provided in an embodiment of the present application;

[0055] Figure 4 It is a structural schematic diagram of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0056] 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.

[0057] 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.

[0058] Based on the current status of background technologies, the following challenges are faced:

[0059] a. Existing research on thermal seal structures is mainly based on verification tests. There are few theoretical and simulation studies on their thermal gas response laws and thermal seal effectiveness. There is a lack of systematic quantitative research on thermal seal leakage performance and heat transfer characteristics. It is unable to support the design of hypersonic aircraft thermal seals and thermal seal effectiveness analysis. It is urgent to further establish corresponding evaluation models and simulation methods, and use typical tests to verify and correct the corresponding evaluation models.

[0060] b. Research and simulation technologies based on single-point thermal management technologies such as spray cooling and water heat exchangers are relatively mature, but there is a lack of evaluation of the overall heat dissipation characteristics under the coupling of multiple heat sources in low-pressure and variable-pressure cabins; in terms of research methods, experimental research is the main method, the optimization cycle is long, there are few reference materials for model-based simulation research, the correctness and accuracy are not fully verified, and there is a lack of systematic research on coupled thermal sealing and flow and heat transfer in the cabin.

[0061] c. Traditional cabin thermal design methods have the characteristics of weak coupling, strong repetition, and low precision, and are not suitable for the actual cabin temperature control problems of hypersonic aircraft. It is urgent to develop an integrated agile design process and method.

[0062] Hypersonic aircraft emphasize reusability (more than 100 takeoffs and landings) and long-term cruising (about 0.5 to 1 hour), requiring the total weight of thermal protection structures and load-bearing cold structures to be limited to less than 30%. At the same time, the overall requirements for structural load, structural life, anti-oxidation ability, vibration resistance and thermal protection effect are stringent. The overall goal is difficult to achieve, and new thermal design technologies must be developed. At the same time, in order to ensure repeated inspection and maintenance of airborne equipment and adaptability to wide-range environments, equipment cabins generally use non-sealed designs. The changes in internal and external pressure differences under wide-range flight and variable working conditions bring complex comprehensive thermal effects to the cabin environment. The factors affecting thermal design are many and complex. For the comprehensive thermal effect problems faced by its cabin design, an efficient thermal design process and simulation method have not yet been formed.

[0063] Hypersonic aircraft are affected by aerodynamic heat, propulsion system heat, and equipment heat. There are many types of heat sources, complex heat exchange forms, and different forms of heat and characteristics in each part. They mainly include external heat sources and internal heat sources. External heat sources include heat generated by aerodynamic heating, radiation heating, and leakage of the fuselage structure. Internal heat sources mainly come from electronic equipment such as radars and computers on board, mechanical equipment such as generators and steering gears, and heat generated by the propulsion system. As the part with the most influencing factors on the onboard heat source and the most obvious coupling characteristics of thermal sealing and thermal management, the thermal environment of the typical equipment compartment of hypersonic aircraft is difficult to solve through the cabin design concept based on traditional one-way serial.

[0064] Low Mach number aircraft do not need to adopt thermal protection design, and the fuselage skin is in a constant temperature and hot state for a long time. It is reasonable and feasible to adopt steady-state design based on severe state points in the traditional design process. However, as the Mach number of hypersonic aircraft increases, the appearance of thermal insulation will cause the structural temperature to continue to change during the entire flight process. If the traditional steady-state boundary design is still used, the design margin will be over-considered, which is very likely to lead to the non-closure of the technical solution.

[0065] In addition, since the total temperature of the incoming air is low for low Mach number aircraft, if there is gas backflow, the low-temperature air will enter the cabin, which will only have a positive impact on the cabin thermal environment. Therefore, the equipment cabin is often designed to be open, and no additional pressure requirements are made. As for the cabin of a hypersonic aircraft, as analyzed in the previous article, reasonable control of its pressure will significantly improve the thermal environment in the cabin, and its demand for thermal sealing design is much higher than that of a low Mach number aircraft.

[0066] The traditional design process is based on the idea of ​​one-way serial and professional decoupling design to design the thermal seal thermal management scheme of the cabin. The traditional design process can be divided into four parts: aerodynamic thermal calculation, thermal protection and thermal seal design, thermal management design, and performance evaluation. This process has the following main problems.

[0067] Problem 1: Decoupling design of each discipline leads to low simulation accuracy

[0068] In the traditional design process, each discipline conducts decoupled design separately, and there are a lot of simple idealized processing in simulation, which leads to low accuracy. Taking thermal protection calculation as an example, the gas temperature and flow conditions in the cabin cannot be determined during calculation, so the precise boundary conditions of the cabin inner wall cannot be set. Usually, the inner wall is set as an adiabatic boundary, which is quite different from the heat transfer process in real scenes.

[0069] Problem 2: Serial design, low efficiency

[0070] Traditional cabin design has a clear professional process, which is to first perform aerodynamic thermal calculations, then complete thermal protection and thermal sealing calculations, and finally carry out thermal management design. Each part needs to use the output results of the previous process as the boundary, and specific work cannot be carried out before the previous process is completed. Although cabin thermal designers will divide the work according to their profession, usually only one professional will be involved in the work at the same time, while other professionals are in a waiting state, resulting in low design efficiency.

[0071] Problem 3: Initial design relies on experience

[0072] The work in each discipline can be summarized as two parts: scheme design and simulation calculation. When designing a scheme, there are no relevant references, instruction manuals, etc., especially when designing the initial scheme, there are no simulation calculation results of the previous round of schemes, and the initial scheme design can only be carried out based on experience. If there is insufficient experience, the initial scheme and the final scheme will deviate greatly, which will increase the number of iterations and thus increase the time required for cabin thermal seal thermal management design.

[0073] Problem 4: Repeated iterations are required

[0074] As mentioned in question 3, the initial schemes are mostly designed based on experience, which inevitably requires multiple rounds of iterative optimization. When returning to iteration, since there is no mechanism for influencing relevant parameters, each discipline can only make qualitative improvements based on the original scheme, which greatly increases the number of iterations. In addition, each iteration requires three-dimensional simulation calculations for the new scheme, which consumes a lot of time.

[0075] Problem 5: Evaluation is only done at the end of the process

[0076] The evaluation process is only carried out after a round of iterations is completed and all data is obtained, in order to judge the pros and cons of the scheme and whether the process is completed. Each iterative calculation takes a lot of energy and time from the designers. If the evaluation fails, the data results of this iteration become the process quantity in the cabin thermal design and can only provide a reference for the subsequent optimization of the scheme. A lot of time is wasted on the scheme calculation in the iterative process. If there is a fast evaluation method, it can greatly speed up the pace of cabin thermal comprehensive design.

[0077] Based on the above problems, the embodiment of the present application proposes an integrated design method for cabin thermal sealing and thermal management. For problem 1, a multi-discipline coupling design method is adopted to solve it. However, directly performing the coupled design of thermal seal thermal management will bring difficulties to the simulation calculation, such as cross-scale modeling of cabin-gap, multi-physics field coupling of thermal deformation of sealing structure and gas flow, and cross-time scale, which greatly increases the difficulty and time of simulation. Therefore, based on the starting point of multi-discipline coupling design without excessively increasing the difficulty of simulation, an integrated design method is proposed, which uses a one-dimensional model to couple the design and iterative optimization of the thermal seal thermal management solution, and then uses three-dimensional simulation for fine verification; the interface influencing factors between multiple disciplines in the design are coupled, which solves the problem of using simple idealized boundaries when designing separately for each discipline.

[0078] For problem 2, a coupled design method was adopted. Through repeated iterative design and optimization of a one-dimensional coupling model, a cabin thermal design scheme was formed, and then three-dimensional simulation was used for detailed verification. In this process, all disciplines participated in the design most of the time, which solved the problem of inefficiency caused by long waiting times for various disciplines in the traditional process.

[0079] For questions 3 and 4, the one-dimensional coupling design model has the characteristics of fast design calculation, and the time for one round of iterative design is much shorter than the traditional design process. The quality of the initial solution will only increase the rapid iteration process a few times, and will no longer have a great impact on the overall design time, solving the problem of the dependence of the scheme design on experience. In addition, a method of adding a parameter optimization function module to the one-dimensional coupling design model is proposed to solve the problem of a large number of iterations. Through core parameter optimization research, sensitivity analysis and other means, a key parameter group is established, and the mathematical relationship between the parameters is further established. Based on this, optimization suggestions for the scheme design parameters are proposed after the evaluation process, which can effectively reduce the number of scheme iterations.

[0080] In response to question 5, an efficiency and compensation evaluation module is added to the one-dimensional design for rapid evaluation. At the same time, based on the fast calculation characteristics of the one-dimensional model and the parameter optimization module, the speed of the cabin thermal design integration process is greatly accelerated.

[0081] Figure 1 A schematic flow chart of a cabin thermal sealing and thermal management integrated design method provided in an embodiment of the present application. The cabin thermal sealing and thermal management integrated design method includes:

[0082] 100. Apply boundary constraints to the initial input conditions of the cabin to obtain boundary conditions.

[0083] Optionally, the initial input conditions include: flight profile, cabin geometry model, aerodynamic heat, equipment heat, cabin pressure requirements, cabin temperature requirements, internal flow inlet conditions, and internal flow outlet conditions; specifically, the initial input conditions are confirmed to ensure the accuracy and efficiency of generating the integrated design scheme of cabin thermal sealing and thermal management.

[0084] Optionally, in addition to the above-mentioned boundary conditions, the traditional decoupled design process also has inputs and outputs between thermal sealing and thermal management, which serve as boundaries between them. In the integrated design process of the embodiment of the present application, thermal sealing and thermal management are coupled by design, and the data transfer between them is no longer a constraint boundary in the design.

[0085] Based on boundary conditions, the thermal sealing module and the thermal management module are coupled through one-dimensional design tools to construct an integrated design scheme for cabin thermal sealing and thermal management.

[0086] For details, please refer to Figure 2 , the heat sealing module and the thermal management module are coupled through the boundary loading module, the heat sealing thermal management parameter matching module, the heat sealing thermal management scheme design module, the flow heat transfer calculation module, the efficiency and compensation evaluation module, and the scheme output module; among them, by coupling the heat sealing module and the thermal management module, the integrated design scheme of cabin thermal sealing and thermal management is realized, the simulation accuracy is improved, and there is no need for repeated iterations.

[0087] Optionally, a one-dimensional design tool can be used to couple the cabin thermal sealing and thermal management. The one-dimensional design tool can reduce the complex cabin thermal comprehensive design problem to one dimension through methods such as averaging and reasonable partitioning. While ensuring a certain calculation accuracy, it can quickly couple the thermal sealing and thermal management solutions. The efficiency and compensation evaluation module can quickly evaluate the design solution and optimize the solution parameters through the parameter optimization module.

[0088] It is understandable that the one-dimensional design tool is mainly used for the preliminary design of thermal sealing thermal management solutions. Through its rapid loading, calculation and evaluation function optimization, the preliminary plan for the comprehensive thermal design of the cabin is obtained, and then the plan is verified using three-dimensional precise calculations to complete the final design.

[0089] More specifically, based on boundary conditions, the thermal sealing module and the thermal management module are coupled through a one-dimensional design tool to construct an integrated design solution for cabin thermal sealing and thermal management, including:

[0090] 210. Convert the three-dimensional boundary condition data into one-dimensional boundary condition data through the boundary loading module.

[0091] Optionally, the boundary loading module is responsible for loading various boundary data into the one-dimensional design tool, including the aerodynamic heat loading module, the cabin structure loading module and the electronic equipment heat source module. Among them, the aerodynamic heat, cabin structure, etc. are all three-dimensional, so it is necessary to design the corresponding loading module to convert the three-dimensional boundary into one dimension.

[0092] Specifically, the three-dimensional aerodynamic heat flow data and pressure data of typical state points output by the simulation software are read through the aerodynamic heat loading module, and the calculation results of the three-dimensional aerodynamic heat flow data are converted into surface average heat flow and surface average pressure, and the aerodynamic heat flow value and pressure value under the corresponding state are calculated according to the altitude, Mach number and wall temperature; wherein, the aerodynamic heat loading module is provided with an interface for reading external data, which is used to read the aerodynamic heat flow value and pressure value of the coordinate point, and its internal input data include: altitude, Mach number, wall temperature, and the internal output data include: surface average aerodynamic heat flow value and surface average pressure value.

[0093] Specifically, the cabin structure characteristic data is extracted through the cabin structure loading module, and the three-dimensional structure is characterized in one dimension; the cabin structure loading module is provided with an interface for reading external data, which is used to read the three-dimensional digital model of the cabin, and its internal output data includes: one-dimensional or two-dimensional models of the cabin and equipment.

[0094] Specifically, the electronic equipment heat source module calculates the temperature change value of the equipment and dissipates heat to the environment according to the properties and operating conditions of the equipment; the electronic equipment heat source module is provided with an interface for reading external data, which is used to read the equipment operating parameters (usage status, power, equivalent heat capacity, surface emissivity, equipment equivalent heat transfer coefficient and heat transfer area, equipment initial temperature). The internal input data include: cabin ambient temperature, equivalent heat transfer coefficient; the internal output data include: equipment temperature, equipment and environmental heat flow.

[0095] Specifically, each boundary data and boundary condition is loaded into the one-dimensional design tool through the boundary loading module to facilitate the construction of subsequent design solutions.

[0096] 220. Provide basic physical property parameters based on the heat sealing thermal management parameter matching module.

[0097] Optionally, the heat seal thermal management parameter matching module includes a heat seal characteristic database, a heat protection material physical property database and a cooling fluid database; these databases contain a large number of physical property parameters of heat seal structures, heat protection materials and cooling fluids, such as density, heat capacity, thermal conductivity, etc. The database module provides basic physical property parameters for the calculation of one-dimensional design tools and provides a reference basis for the design of heat seal thermal management solutions.

[0098] 230. Based on the boundary conditions, the initial design scheme is designed through the heat seal thermal management scheme design module combined with the influencing mechanism of various parameters.

[0099] Optionally, the initial design of the heat seal thermal management solution can be performed through the heat seal thermal management solution design module. During the initial design, the initial solution is designed based on the boundary conditions, based on experience and combined with the influencing mechanism of each parameter, and then the solution is optimized and improved through the one-dimensional design tool; specifically, based on the fast calculation, evaluation and optimization characteristics of the one-dimensional design tool, the quality of the initial solution no longer has too much impact on the iteration rounds and calculation time, which greatly eliminates the dependence of the design process on experience factors.

[0100] 240. The various modules of thermal sealing and thermal management are coupled through the flow heat transfer calculation module.

[0101] The optional heat transfer calculation module is the core calculation part of the one-dimensional design tool, which mainly includes the heat seal interface module, the cabin flow module, the cabin radiation heat transfer module and the electronic equipment heat source module. The heat transfer calculation module couples some parameters between the modules to complete the coupling solution of heat seal and thermal management, and improve the simulation accuracy and efficiency.

[0102] Specifically, the thermal sealing interface module calculates the change in structural temperature and boundary heat flow according to the thickness of the insulation layer, aerodynamic thermal conditions and cabin gas temperature, and calculates the gas leakage and boundary heat flow according to the thermal sealing form, seal deformation, aerodynamic thermal conditions and cabin airflow conditions; the thermal sealing interface module is provided with an interface for reading external data, which is used to read the cabin structure, initial temperature and profile information. The internal input data include: thermal sealing parameters (including insulation layer thickness, insulation layer physical properties, thermal sealing form, seal deformation), aerodynamic heat flow value, cabin ambient temperature and cabin pressure; the internal output data include: calculated temperature of each node, thermal conductivity of the insulation layer, gas leakage and gap heat leakage.

[0103] Specifically, the in-cabin flow heat exchange calculation is performed according to the initial conditions and boundary conditions through the in-cabin flow module, and the in-cabin flow heat transfer is calculated based on the boundary conditions of the cabin structure, inner wall temperature and leakage to obtain the cabin temperature, pressure distribution and heat sink utilization; the in-cabin flow module is provided with an interface for reading external data, which is used to read the cabin structure, thermal management parameters (heat sink temperature, pressure, flow), initial temperature, profile information, flow inlet and outlet conditions; the internal input data include: inner wall temperature, thermal conductivity of the insulation layer, gas leakage, heat leakage from gaps, equipment temperature, equipment and environmental heat flow; the internal output data include: cabin temperature, pressure distribution and heat sink utilization.

[0104] Specifically, the cabin radiation heat transfer module calculates the radiation heat transfer amount between the cabin walls according to given conditions; the cabin radiation heat transfer module is provided with an interface for reading external data, which is used to read the cabin structure data, and its internal input data includes: wall temperature, emissivity, area, and internal output data includes: radiation heat transfer amount.

[0105] Specifically, the electronic equipment heat source module calculates the temperature change of the equipment and the heat dissipation to the environment according to the properties and operation conditions of the equipment. The heat generated by the electronic equipment is the main heat source inside the cabin. At the same time, the layout of the equipment will affect the flow in the cabin, so the electronic equipment heat source module needs to be added to the coupling calculation.

[0106] As mentioned above, the four modules of the flow heat transfer calculation module are coupled to complete the cabin flow heat transfer calculation, and the relevant data required for the evaluation of heat sink utilization, leakage, etc. can be obtained.

[0107] 250. Based on the performance and compensation evaluation module, the initial design scheme is evaluated for performance, compensation and parameter optimization.

[0108] Optionally, the efficiency and compensation evaluation module is used to evaluate and optimize the cabin thermal design scheme, evaluate the efficiency and compensation of the scheme based on the results of the flow and heat transfer calculation part, and provide suggestions for scheme improvement. The efficiency and compensation evaluation module includes an efficiency evaluation module, a compensation evaluation module and a parameter optimization module.

[0109] Specifically, the cabin leakage, heat sink utilization, average cabin temperature, and pressure change process along the flight profile are calculated based on the performance evaluation module; the performance evaluation module is provided with an interface for reading external data, and its internal input data include: thermal management parameters, inner wall temperature, cabin temperature, and gap leakage heat; the internal output data include: average inner wall temperature, average cabin temperature, temperature at 75 mm on the equipment surface, total leakage, and heat sink utilization.

[0110] Specifically, the mass compensation of the cabin thermal integrated design system is calculated through the compensation evaluation module, including the thermal sealing structure compensation, the thermal management system compensation and the total compensation; the compensation evaluation module is provided with an interface for reading external data, and its internal input data include: thermal management parameters, inner wall surface temperature, cabin temperature, gap leakage heat; the internal output data include: inner wall average temperature, cabin average temperature, equipment surface temperature at 75 mm, total leakage, and heat sink utilization.

[0111] Specifically, the parameter optimization module is used to optimize the thermal management and thermal sealing parameters with the goal of minimum mass compensation, and an optimization objective function is established based on the influence mechanism of various parameters on the flow and heat transfer in the cabin. The parameter optimization module is provided with an interface for reading external data, and its internal incoming data includes: thermal management parameters, thermal sealing parameters, and its internal outgoing data includes: thermal management and thermal sealing parameters for minimum mass compensation.

[0112] 260. Output the integrated design scheme of cabin thermal sealing and thermal management through the scheme output module.

[0113] As mentioned above, the embodiment of the present application utilizes a one-dimensional design tool to perform coupled design of cabin thermal sealing and thermal management. The one-dimensional design tool reduces the complex cabin thermal comprehensive design problem to one dimension through methods such as averaging and reasonable partitioning. While ensuring a certain calculation accuracy, it can quickly perform coupled design of thermal sealing and thermal management solutions.

[0114] 300. Input the integrated design scheme of cabin thermal sealing and thermal management into the three-dimensional model for verification.

[0115] Specifically, according to the thermal sealing design scheme of the integrated design scheme of cabin thermal sealing and thermal management, the cabin structure wall temperature and the heat and mass transfer of the sealing structure are calculated to obtain the first data in the cabin; wherein the first data includes: leakage amount, wall temperature, and cabin temperature.

[0116] Based on the simulation boundary of the thermal management data, the second data in the cabin is calculated according to the thermal management design scheme of the cabin thermal sealing and thermal management integrated design scheme; wherein the second data includes flow heat transfer, mass compensation, and heat sink utilization.

[0117] It is determined whether the cabin temperature is within the set cabin temperature range. If so, the three-dimensional model is verified. If not, feedback is given to the one-dimensional design tool to instruct the one-dimensional design tool to optimize parameters.

[0118] Among them, the integrated design scheme of cabin thermal sealing and thermal management was subjected to three-dimensional inspection to optimize the design scheme and improve simulation accuracy.

[0119] As described above, the embodiment of the present application imposes boundary constraints on the initial input conditions of the cabin to obtain boundary conditions; based on the boundary conditions, the thermal sealing module and the thermal management module are coupled through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management; the integrated design scheme for cabin thermal sealing and thermal management is input into the three-dimensional model for verification; the interface influencing factors between multiple modules in the design are coupled, which solves the problem of using simple idealized boundaries when designing separate modules. Each module participates in the design most of the time, which solves the problem of high structural weight cost and low efficiency caused by modules being in a waiting state for a long time in the traditional process.

[0120] For example, the preliminary solution formed by the one-dimensional design tool is loaded into the three-dimensional model for simulation calculation. The process of three-dimensional simulation is as follows: Figure 2 As shown in the figure, the cabin structure wall temperature and the heat and mass transfer of the sealing structure are calculated based on the preliminary scheme of thermal protection / thermal sealing, and the leakage, wall temperature and other data are obtained. These data are used as the simulation boundary of thermal management, and the flow heat transfer in the cabin is calculated according to the preliminary design scheme of thermal management. The three-dimensional simulation calculation is completed to obtain the relevant data required for the evaluation of heat sink utilization, leakage, etc.

[0121] Specifically, boundary constraints are imposed on the initial input conditions (flight profile, cabin geometry model, aerodynamic heat, equipment heat, cabin temperature requirements, cabin pressure requirements, internal flow inlet conditions, and internal flow outlet conditions); the one-dimensional design tool is coupled to the heat seal thermal management module, and is processed in sequence through the boundary loading module, heat seal thermal management parameter matching module, heat seal thermal management scheme design module, flow heat transfer calculation module, and efficiency and compensation evaluation module to determine whether the cabin heat seal thermal management design scheme meets the efficiency, leakage and compensation requirements. If so, the scheme is output (including deformation, cabin pressure distribution, heat seal parameters, leakage characteristics, cabin temperature distribution, thermal management parameters and other data); if not, the parameter optimization module is used to optimize the parameters and perform three-dimensional fine verification of the design scheme.

[0122] Specifically, the design scheme is verified in three dimensions: the model corresponding to the thermal protection and thermal sealing scheme is divided into finite element networks, and the structural simulation and solution of the divided finite element networks are carried out through the aerodynamic thermal loading tool provided by the aerodynamic thermal data template to obtain the time-varying temperature field, deformation and other data of the whole machine. The time-varying temperature field of the whole machine is processed through the structural temperature loading tool provided by the structural temperature template, and the deformation is processed through the heat leakage model; the model corresponding to the thermal management scheme is divided into thermal management networks, and the thermal management simulation and solution are carried out based on the processed time-varying temperature field and deformation of the whole machine to obtain parameters such as cabin temperature distribution, deformation, cabin pressure distribution and leakage characteristics, and to judge whether the cabin temperature distribution meets the requirements. If so, the three-dimensional verification is passed. If not, the model is corrected through the parameter optimization module.

[0123] The thermal sealing / thermal management scheme of the embodiment of the present application is calculated by a one-dimensional design tool based on the multi-disciplinary coupling of thermal sealing and thermal management. The three-dimensional simulation calculation is carried out on the basis of the preliminary scheme. Taking the thermal protection calculation of the cabin wall temperature as an example, the integrated process uses the one-dimensional cabin average temperature, flow heat transfer and other data as the boundary conditions of the inner wall during calculation, while the traditional process usually idealizes the inner wall as an adiabatic condition. The rationality and accuracy of the preliminary scheme are evaluated by the data obtained through three-dimensional calculations, and it is judged whether further optimization design needs to be carried out through a one-dimensional design tool: whether the cabin average temperature, pressure and other conditions meet the working conditions of electronic equipment throughout the process; whether the evaluation data such as heat sink utilization, leakage rate, mass compensation and the calculated data of the one-dimensional design tool meet a certain accuracy and are better values.

[0124] 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.

[0125] In the second aspect, based on the above embodiments, Figure 3This is a schematic diagram of the structure of a cabin thermal sealing and thermal management integrated design device provided in an embodiment of the present application. Figure 3 The cabin thermal sealing and thermal management integrated design device provided in this embodiment specifically includes: a boundary constraint module 1, a scheme design module 2 and a scheme verification module 3.

[0126] Among them, the boundary constraint module 1 is used to perform boundary constraints on the initial input conditions of the cabin to obtain boundary conditions; the scheme design module 2 is used to couple the thermal sealing module and the thermal management module through a one-dimensional design tool based on the boundary conditions to construct an integrated design scheme for cabin thermal sealing and thermal management; the scheme verification module 3 is used to input the integrated design scheme for cabin thermal sealing and thermal management into the three-dimensional model for verification.

[0127] As described above, the embodiment of the present application imposes boundary constraints on the initial input conditions of the cabin to obtain boundary conditions; based on the boundary conditions, the thermal sealing module and the thermal management module are coupled through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management; the integrated design scheme for cabin thermal sealing and thermal management is input into the three-dimensional model for verification; the interface influencing factors between multiple modules in the design are coupled, which solves the problem of using simple idealized boundaries when designing separate modules. Each module participates in the design most of the time, which solves the problem of high structural weight cost and low efficiency caused by modules being in a waiting state for a long time in the traditional process.

[0128] The cabin thermal sealing and thermal management integrated design device provided in the embodiment of the present application can be used to implement the cabin thermal sealing and thermal management integrated design method provided in the above-mentioned embodiment, and has corresponding functions and beneficial effects.

[0129] In a third aspect, an embodiment of the present application further provides an electronic device that can integrate the cabin thermal sealing and thermal management integrated design device provided in an embodiment of the present application. Figure 4 Schematic diagram of the structure of an electronic device provided by an embodiment of the present application. Figure 4 The electronic device includes: an input device 43, an output device 44, a memory 42 and one or more processors 41; the memory 42 is used to store one or more programs; when one or more programs are executed by one or more processors 41, the one or more processors 41 implement the cabin thermal sealing and thermal management integrated design method provided in the above embodiment. The input device 43, the output device 44, the memory 42 and the processor 41 can be connected by a bus or other means. Figure 4 The example of connecting through bus is taken in the following.

[0130] The processor 41 executes various functional applications and data processing of the equipment by running the software programs, instructions and modules stored in the memory 42, thereby realizing the above-mentioned integrated design method of cabin thermal sealing and thermal management.

[0131] The electronic device provided above can be used to implement the integrated design method for cabin thermal sealing and thermal management provided in the above embodiment, and has corresponding functions and beneficial effects.

[0132] In a fourth aspect, an embodiment of the present application also 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 cabin thermal sealing and thermal management integrated design method, and can achieve the same beneficial effects.

[0133] Of course, the storage medium containing computer executable instructions provided in an embodiment of the present application, whose computer executable instructions are not limited to the above-mentioned integrated design method for cabin thermal sealing and thermal management, can also execute related operations in the integrated design method for cabin thermal sealing and thermal management provided in any embodiment of the present application.

[0134] In a fifth 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 of 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.

[0135] 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.

[0136] 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.

[0137] 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.

[0138] 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.

[0139] 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.

[0140] 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.

[0141] 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 method for integrated cabin thermal sealing and thermal management design, characterized in that: include: Apply boundary constraints to the initial input conditions of the cabin to obtain boundary conditions; Based on boundary conditions, the thermal sealing module and thermal management module are coupled through one-dimensional design tools to construct an integrated design scheme for cabin thermal sealing and thermal management; Input the integrated design of cabin thermal sealing and thermal management into the 3D model for verification; The coupling of the thermal sealing module and the thermal management module by using a one-dimensional design tool comprises: The heat sealing module and the thermal management module are coupled through the boundary loading module, the heat sealing thermal management parameter matching module, the heat sealing thermal management scheme design module, the flow heat transfer calculation module, the efficiency and compensation evaluation module, and the scheme output module; Based on the boundary conditions, the thermal sealing module and the thermal management module are coupled through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management, including: The three-dimensional boundary condition data is converted into one-dimensional boundary condition data through the boundary loading module; Provide basic physical property parameters based on heat sealing thermal management parameter matching module; Based on the boundary conditions, the initial design scheme is designed through the heat seal thermal management scheme design module combined with the parameter influence mechanism; The various modules of thermal sealing and thermal management are coupled through the flow and heat transfer calculation module; Based on the performance and compensation evaluation module, the initial design scheme is evaluated for performance, compensation and parameter optimization; Output the cabin thermal sealing and thermal management integrated design solution through the solution output module; The step of converting the three-dimensional boundary condition data into one-dimensional boundary condition data by using the boundary loading module includes: The aerodynamic heat loading module reads the three-dimensional aerodynamic heat flow data and pressure data of typical state points output by the simulation software, converts the calculation results of the three-dimensional aerodynamic heat flow data into surface average heat flow and surface average pressure, and calculates the aerodynamic heat flow value and pressure value under the corresponding state according to the height, Mach number and wall temperature; The cabin structure characteristic data is extracted through the cabin structure loading module, and the three-dimensional structure is characterized in one dimension; The electronic equipment heat source module calculates the temperature change value of the equipment and dissipates heat to the environment according to the properties and operating conditions of the equipment.

2. The integrated design method for cabin thermal sealing and thermal management according to claim 1, characterized in that: The initial input conditions include: flight profile, cabin geometry model, aerodynamic heat, equipment heat, cabin pressure requirement, cabin temperature requirement, internal flow inlet condition and internal flow outlet condition.

3. The integrated design method for cabin thermal sealing and thermal management according to claim 1, characterized in that: The heat transfer calculation module is used to couple the various modules of thermal sealing and thermal management, including: The thermal sealing interface module calculates the change of structural temperature and boundary heat flow according to the thickness of the thermal insulation layer, aerodynamic heat conditions and cabin gas temperature conditions, and calculates the gas leakage and boundary heat flow according to the thermal sealing form, seal deformation, aerodynamic heat conditions and cabin airflow conditions; The cabin flow module is used to calculate the cabin flow heat transfer according to the initial conditions and boundary conditions. The cabin flow heat transfer is calculated based on the boundary conditions of cabin structure, inner wall temperature and leakage to obtain the cabin temperature, pressure distribution and heat sink utilization. The cabin radiation heat transfer module is used to calculate the radiation heat transfer between cabin walls according to given conditions; The electronic equipment heat source module calculates the temperature change of the equipment and dissipates heat to the environment according to the properties and operating conditions of the equipment.

4. The integrated design method for cabin thermal sealing and thermal management according to claim 1, characterized in that: The performance evaluation, compensation evaluation and parameter optimization of the initial design scheme based on the performance and compensation evaluation module include: Based on the performance evaluation module, the cabin leakage, heat sink utilization, average cabin temperature, and pressure changes along with the flight profile are calculated; The compensation evaluation module is used to calculate the mass compensation of the cabin thermal integrated design system, including thermal sealing structure compensation, thermal management system compensation and total compensation; Through the parameter optimization module, the thermal management and thermal sealing parameters are optimized with the goal of minimum mass compensation. Based on the influence mechanism of each parameter on the flow and heat transfer in the cabin, an optimization objective function is established.

5. The integrated design method for cabin thermal sealing and thermal management according to claim 1, characterized in that: The step of inputting the cabin thermal sealing and thermal management integrated design scheme into the three-dimensional model for verification includes: According to the thermal sealing design scheme of the integrated thermal sealing and thermal management design scheme of the cabin, the wall temperature of the cabin structure and the heat and mass transfer of the sealing structure are calculated to obtain the first data in the cabin; wherein the first data includes: leakage, wall temperature, and cabin temperature; Based on the simulation boundary of the thermal management data, the second data in the cabin is calculated according to the thermal management design scheme of the cabin thermal sealing and thermal management integrated design scheme; wherein the second data includes flow heat transfer, mass compensation, and heat sink utilization; It is determined whether the cabin temperature is within the set cabin temperature range. If so, the three-dimensional model is verified. If not, feedback is given to the one-dimensional design tool to instruct the one-dimensional design tool to optimize parameters.

6. A cabin thermal sealing and thermal management integrated design device, characterized in that: include: A boundary constraint module is used to perform boundary constraints on the initial input conditions of the cabin to obtain boundary conditions; The scheme design module is used to couple the thermal sealing module and the thermal management module based on boundary conditions through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management; The scheme verification module is used to input the cabin thermal sealing and thermal management integrated design scheme into the 3D model for verification; The coupling of the thermal sealing module and the thermal management module by using a one-dimensional design tool comprises: The heat sealing module and the thermal management module are coupled through the boundary loading module, the heat sealing thermal management parameter matching module, the heat sealing thermal management scheme design module, the flow heat transfer calculation module, the efficiency and compensation evaluation module, and the scheme output module; Based on the boundary conditions, the thermal sealing module and the thermal management module are coupled through a one-dimensional design tool to construct an integrated design scheme for cabin thermal sealing and thermal management, including: The three-dimensional boundary condition data is converted into one-dimensional boundary condition data through the boundary loading module; Provide basic physical property parameters based on heat sealing thermal management parameter matching module; Based on the boundary conditions, the initial design scheme is designed through the heat seal thermal management scheme design module combined with the parameter influence mechanism; The various modules of thermal sealing and thermal management are coupled through the flow and heat transfer calculation module; Based on the performance and compensation evaluation module, the initial design scheme is evaluated for performance, compensation and parameter optimization; Output the cabin thermal sealing and thermal management integrated design solution through the solution output module; The step of converting the three-dimensional boundary condition data into one-dimensional boundary condition data by using the boundary loading module includes: The aerodynamic heat loading module reads the three-dimensional aerodynamic heat flow data and pressure data of typical state points output by the simulation software, converts the calculation results of the three-dimensional aerodynamic heat flow data into surface average heat flow and surface average pressure, and calculates the aerodynamic heat flow value and pressure value under the corresponding state according to the height, Mach number and wall temperature; The cabin structure characteristic data is extracted through the cabin structure loading module, and the three-dimensional structure is characterized in one dimension; The electronic equipment heat source module calculates the temperature change value of the equipment and dissipates heat to the environment according to the properties and operating conditions of the equipment.

7. 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 integrated design method for cabin thermal sealing and thermal management as described in any one of claims 1 to 5.

8. 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 integrated design method for cabin thermal sealing and thermal management as described in any one of claims 1-5.

9. A computer program product, characterized in that The computer program product includes instructions, which, when executed by a computer, enable the computer to implement the integrated design method for cabin thermal sealing and thermal management according to any one of claims 1-5.

Images