CN108304595B - Structural temperature analysis method for hypersonic aircraft semi-closed area - Google Patents
Structural temperature analysis method for hypersonic aircraft semi-closed area Download PDFInfo
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Abstract
The embodiment of the invention discloses a structural temperature analysis method for a hypersonic aircraft semi-closed area, relates to a structural temperature analysis technology for the hypersonic aircraft semi-closed area, and can solve the problem that the precision and the efficiency of a semi-closed complex interference area pneumatic heating/multi-component radiation interference/three-dimensional heat transfer analysis result cannot be considered at the same time. The method comprises the steps of firstly generating a pneumatic heating grid of a concerned part, then utilizing the pneumatic heating grid to carry out pneumatic heating analysis, carrying out convection heat flow analysis at different wall temperatures, obtaining a convection heat flow database at a high wall temperature, generating a three-dimensional heat transfer analysis grid considering high wall temperature convection heat exchange and multi-component radiation interference, and finally utilizing the three-dimensional heat transfer analysis grid to carry out three-dimensional heat transfer calculation considering high wall temperature convection heat exchange and multi-component radiation interference.
Description
Technical Field
The invention relates to the technical field of structural temperature analysis of a hypersonic aircraft semi-closed area, in particular to a three-dimensional heat transfer analysis method for the hypersonic aircraft semi-closed area by considering high wall temperature convective heat transfer and multi-component radiation interference.
Background
Along with the increasingly complex appearance of hypersonic aircraft, flight mach number is increasingly high, and the thermal environment on aircraft surface is harsher, and semi-closed complicated interference zone high temperature part surface not only has pneumatic heating, and still radiation/reflection/absorption energy each other between the high temperature part, and the physical process is very complicated. Because the temperatures of a plurality of components in the current complex interference area are all on the allowable boundary of materials, the determination of a structural thermal protection scheme and a flight test ballistic scheme is restricted, and therefore the structural temperature of high-temperature components in the complex interference area of the aircraft needs to be finely analyzed.
Conventional analysis of aircraft structure temperature typically utilizes cold wall heat flow and recovery enthalpy, and cannot account for convective heat transfer coefficient changes with wall temperature, so the analyzed structure temperature is typically high. The conventional analysis of 'convection/radiation/heat transfer' usually adopts a fluid-solid coupling method, but the method has extremely low calculation efficiency, and heating heat sources (convection heat flow, radiation heat flow and heat conduction heat flow) can only adopt original calculation results, cannot be corrected, and cannot ensure the calculation accuracy.
Therefore, a structural temperature analysis technology for coupling high wall temperature convective heat transfer, multi-component radiation interference and three-dimensional heat transfer is urgently needed to be broken through.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, provides a structural temperature analysis method for a hypersonic aircraft semi-closed area, and can solve the problem that the precision and the efficiency of a pneumatic heating/multi-component radiation interference/three-dimensional heat transfer analysis result cannot be considered at the same time.
The technical solution of the invention is as follows:
a structural temperature analysis method for a hypersonic aircraft semi-enclosed area, which considers high wall temperature convective heat transfer and multi-component radiation interference, comprises the following steps:
generating a pneumatic heating grid of the concerned part, wherein the size of a first layer of grid in a wall surface boundary layer is 0.01 mm;
carrying out pneumatic heating analysis by using a pneumatic heating grid, carrying out convective heat flow analysis at different wall temperatures, and obtaining a convective heat flow database at a high wall temperature, wherein the database comprises node coordinates, and corresponding relations between the wall temperatures and the convective heat flows;
generating a three-dimensional heat transfer analysis grid considering high wall temperature convective heat transfer and multi-component radiation interference, wherein the grid comprises air grids and structural heat transfer grids, and the size difference between the adjacent air grids and the structural heat transfer grids is less than 1.5-3 times;
three-dimensional heat transfer calculation considering high wall temperature convective heat transfer and multi-component radiation interference is carried out by utilizing a three-dimensional heat transfer analysis grid, and a wall surface subjected to pneumatic heating is a guide with a certain thicknessThermal thin shell, shell thickness<1e-6m, loading the high-wall-temperature convection heat flow into the heat-conducting thin shell in the form of heat generation rate, wherein the relationship between the heat generation rate library and the high-wall-temperature convection heat flow library is
Meanwhile, the radiation model is used for analyzing the radiation heat flow of other high-temperature walls to the pneumatic heating wall, the heat transfer model is used for analyzing the temperature rise and three-dimensional heat transfer of the pneumatic heating wall under the combined action of the high-wall-temperature convection heat flow and the radiation heat flow, during calculation, each node on the pneumatic heating wall extracts the temperature of each node in real time at each time step, then corresponding convection heat flow is extracted from the convection heat flow database, the convection heat flow is loaded on the node, an energy equation and a radiation equation are solved, and the radiation heat flow is automatically loaded.
The structural temperature analysis method for the hypersonic aircraft semi-closed area establishes corresponding operation specifications, ensures the precision and efficiency of pneumatic heating/multi-component radiation interference/three-dimensional heat transfer analysis results, can quickly and accurately obtain the structural temperature of pneumatic heating/multi-component radiation interference/three-dimensional heat transfer coupling by using the method, and is used for designing and evaluating a structural thermal protection system of a hypersonic aircraft complex interference area. The method has the advantages that the temperature of the high-temperature component in the complex interference area of the aircraft is finely analyzed, and the more accurate structural thermal protection design, evaluation and determination of the flight test ballistic scheme can be realized.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic flow chart of a structural temperature analysis method for a semi-closed region of a hypersonic aircraft according to an embodiment of the present invention.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the scheme according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted.
The embodiment of the invention provides a structural temperature analysis method for a hypersonic aircraft semi-closed area, which considers high wall temperature convective heat transfer and multi-component radiation interference and is not a simple three-dimensional heat transfer analysis method. Simple three-dimensional heat transfer analysis does not need to consider high wall temperature convective heat transfer and calculate multi-component radiation interference by using a radiation model.
The method comprises the following steps:
101. generating a pneumatic heating grid of the concerned part, wherein the size of a first layer of grid in a wall surface boundary layer is 0.01 mm;
102. carrying out pneumatic heating analysis by using a pneumatic heating grid, carrying out convective heat flow analysis at different wall temperatures, and obtaining a convective heat flow database at a high wall temperature, wherein the database comprises node coordinates, and corresponding relations between the wall temperatures and the convective heat flows;
103. generating a three-dimensional heat transfer analysis grid considering high wall temperature convective heat transfer and multi-component radiation interference, wherein the grid comprises air grids and structural heat transfer grids, and the size difference between the adjacent air grids and the structural heat transfer grids is less than 1.5-3 times;
104. three-dimensional heat transfer calculation considering high wall temperature convective heat transfer and multi-component radiation interference is carried out by utilizing a three-dimensional heat transfer analysis grid, a pneumatically-heated wall surface is a heat-conducting thin shell with a certain thickness, and the shell is thick<1e-6m, loading the high-wall-temperature convection heat flow into the heat-conducting thin shell in the form of heat generation rate, wherein the relationship between the heat generation rate library and the high-wall-temperature convection heat flow library is
Meanwhile, the radiation model is used for analyzing the radiation heat flow of other high-temperature walls to the pneumatic heating wall, the heat transfer model is used for analyzing the temperature rise and three-dimensional heat transfer of the pneumatic heating wall under the combined action of the high-wall-temperature convection heat flow and the radiation heat flow, during calculation, each node on the pneumatic heating wall extracts the temperature of each node in real time at each time step, then corresponding convection heat flow is extracted from the convection heat flow database, the convection heat flow is loaded on the node, an energy equation and a radiation equation are solved, and the radiation heat flow is automatically loaded.
According to the structural temperature analysis method for the hypersonic aircraft semi-closed area, the corresponding operation specifications are established, the precision and the efficiency of the pneumatic heating/multi-component radiation interference/three-dimensional heat transfer analysis result are guaranteed, and the structural temperature of pneumatic heating/multi-component radiation interference/three-dimensional heat transfer coupling can be rapidly and accurately obtained by using the method and is used for designing and evaluating a structural heat protection system of the hypersonic aircraft in a complex interference area. The method has the advantages that the temperature of the high-temperature component in the complex interference area of the aircraft is finely analyzed, and the more accurate structural thermal protection design, evaluation and determination of the flight test ballistic scheme can be realized.
In order to facilitate the reader to understand the technical scheme, the embodiment of the invention provides an application example of the structural temperature analysis method for the hypersonic aircraft semi-closed area, and specifically, the structural temperature analysis method is realized through the following steps:
the method comprises the following steps: and establishing a high-wall-temperature convective heat transfer database.
Step 1.1 a pneumatic heating grid is generated.
A pneumatic heating grid of the site of interest is generated. In order to ensure the calculation precision, the first layer of grid in the wall surface boundary layer is required to be 0.01mm in size. And the grids are in continuous transition, and the concerned parts are locally encrypted while the grid uniformity is ensured as much as possible.
Step 1.2 high wall temperature convection heat flow database establishment
The method comprises the steps of utilizing the pneumatic heating calculation grid generated in the step 1.1, utilizing an SST turbulence model of Fluent software, setting air material properties, different wall surface temperatures, space discrete formats of turbulence kinetic energy and specific dissipation rate and convergence standards, determining a wall surface temperature range (280-total temperature) according to an actual incoming flow state, setting different wall surface temperatures (such as 280K, 300K, 400K, 500K, 600K and 700K … … total temperature), carrying out pneumatic heating analysis under different wall temperatures, obtaining convection heat flows under different wall temperatures, specifically calculating convection heat flows by utilizing a turbulence model based on Kuran number, turbulence kinetic energy and specific dissipation rate, controlling the increase of the Garan number of a turbulence library, the space discrete format of the kinetic energy and the specific dissipation rate and the change of the discrete format of a flow equation, ensuring that the convection calculation process does not diverge and the calculation result converges, and finally adopting a flow equation in a second-order discrete format during calculation, by changing the wall temperature, convective heat flows at different wall temperatures are obtained.
And establishing a database of the high wall temperature convection heat flow, wherein the database comprises the corresponding relation among the node coordinates, the wall temperature and the convection heat flow. In order to obtain an accurate heat flow result, the increase of the number of the library and the discrete format of the flow equation need to be controlled according to a preset mode.
Step two: the three-dimensional heat transfer analysis of high wall temperature convective heat transfer and multi-component radiation interference is considered.
And 2.1, generating a three-dimensional heat transfer coupling analysis grid considering high wall temperature convective heat transfer and multi-component radiation interference.
The grid comprises grids of air domains and grids of structural heat transfer, and the size difference between the adjacent air grids and the structural heat transfer grids is smaller than 1.5-3 times.
Because the air grid is only used for calculating the angular coefficient of the radiation heat exchange, the requirement on the air grid is low, and the air grid and the grid for heat transfer of the structure are only required to be in good transition. The grid of the structural heat transfer is required to have good orthogonality and good transition.
And 2.2, developing a three-dimensional heat transfer calculation considering high wall temperature convective heat transfer and multi-component radiation interference.
The method adopts a user-defined interface provided by Fluent software, converts the whole calculation thought and calculation method into a Fluent identified language, and embeds the Fluent identified language into the software to control the whole calculation process.
And 2.2.1, loading a convection heat flow database on the wall surface.
Setting the pneumatically heated wall surface as a couppled boundary condition by using a DO radiation model of Fluent software, and setting the emissivity of the wall surface and the shell heat conduction; in order to ensure the calculation accuracy, the wall thickness needs to be set to be 1e-6m after research; and loading the convection heat flow database established in the front on a corresponding node of the wall surface according to the coordinates by using a user-defined interface provided by Fluent. In order to avoid conflict with the radiant Heat flow automatically calculated by Fluent, the Heat Generation Rate is skillfully selected as the loading mode of the convection Heat flow, and the setting is that the convection Heat flow/wall thickness is loaded on Fluent software.
Step 2.2.2 radiation, Heat transfer model setup
Radiation model: DO radiation model.
Air participates in the radiation, and solids do not.
Wall surface boundary conditions: and selecting thermal boundary conditions according to actual conditions, and setting the wall surface emissivity and the wall surface temperature.
Step 2.2.3 set solution equations
Because the flow equation is very difficult to converge, the flow equation is very time-consuming to solve, and in order to improve the calculation efficiency, the flow equation is not solved during calculation, and only the energy equation and the radiation equation are solved; however, in order to solve the problem that the calculation needs convection heat flow data, the method of step 2.2.1 is adopted to skillfully load the convection heat flow library established in step 1.2 on the wall surface, and by adopting the method, the calculation efficiency can be improved, and meanwhile, the calculation accuracy is also ensured.
Step 2.2.4 develop the calculation
Setting proper time step length and time step, developing three-dimensional heat transfer calculation considering high wall temperature convection heat transfer and multi-component radiation interference by utilizing a three-dimensional heat transfer analysis grid, wherein the pneumatically heated wall surface is a heat conducting thin wall with certain thicknessShell, shell thickness<1e-6m, loading the high-wall-temperature convection heat flow into the heat-conducting thin shell in the form of heat generation rate, wherein the relationship between the heat generation rate library and the high-wall-temperature convection heat flow library is
Meanwhile, the radiation model is used for analyzing the radiation heat flow of other high-temperature walls to the pneumatic heating wall, the heat transfer model is used for analyzing the temperature rise and three-dimensional heat transfer of the pneumatic heating wall under the combined action of the high-wall-temperature convection heat flow and the radiation heat flow, during calculation, each node on the pneumatic heating wall extracts the temperature of each node in real time at each time step, then corresponding convection heat flow is extracted from the convection heat flow database, the convection heat flow is loaded on the node, an energy equation and a radiation equation are solved, and the radiation heat flow is automatically loaded.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The above devices and methods of the present invention can be implemented by hardware, or can be implemented by hardware and software. The present invention relates to a computer-readable program which, when executed by a logic section, enables the logic section to realize the above-described apparatus or constituent section, or to realize the above-described various methods or steps. The present invention also relates to a storage medium such as a hard disk, a magnetic disk, an optical disk, a DVD, a flash memory, or the like, for storing the above program.
The many features and advantages of these embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of these embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (2)
1. A structural temperature analysis method for a hypersonic aircraft semi-enclosed area is characterized in that the method considers high wall temperature convective heat transfer and multi-component radiation interference and comprises the following steps:
generating a pneumatic heating grid of the concerned part, wherein the size of a first layer of grid in a wall surface boundary layer is 0.01 mm;
carrying out pneumatic heating analysis by using a pneumatic heating grid, carrying out convective heat flow analysis at different wall temperatures, and obtaining a convective heat flow database at a high wall temperature, wherein the database comprises node coordinates, and corresponding relations between the wall temperatures and the convective heat flows;
generating a three-dimensional heat transfer analysis grid considering high wall temperature convective heat transfer and multi-component radiation interference, wherein the grid comprises an air grid and a structural heat transfer grid, and the size difference between the adjacent air grid and the structural heat transfer grid is less than 3 times;
three-dimensional heat transfer calculation considering high wall temperature convective heat transfer and multi-component radiation interference is carried out by utilizing the three-dimensional heat transfer analysis grid, the pneumatically heated wall surface is a heat-conducting thin shell with certain thickness, and the shell is thick<1e-6m, loading the high-wall-temperature convection heat flow into the heat-conducting thin shell in the form of heat generation rate, wherein the relationship between the heat generation rate library and the high-wall-temperature convection heat flow library is
Meanwhile, the radiation model is used for analyzing the radiation heat flow of other high-temperature walls to the pneumatic heating wall, the heat transfer model is used for analyzing the temperature rise and three-dimensional heat transfer of the pneumatic heating wall under the combined action of the high-wall temperature convection heat flow and the radiation heat flow, during calculation, each node on the pneumatic heating wall extracts the respective temperature at each time step in real time, and then the pair of nodes extracts the respective temperature from the temperature rise and three-dimensional heat transfer of the pneumatic heating wallAnd extracting corresponding convection heat flow from the heat flow database, loading the convection heat flow on the node, solving an energy equation and a radiation equation, and automatically loading the radiation heat flow.
2. The method of claim 1, wherein the performing convective heat flow analysis at different wall temperatures comprises: based on the Kurong number, the turbulent energy and the specific dissipation rate, the convection heat flow is calculated by using a turbulence model, the increase of the Kurong number, the space discrete format of the turbulent energy and the specific dissipation rate and the change of the discrete format of a flow equation are controlled, the non-divergence of the calculation process of the convection heat flow and the convergence of the calculation result are ensured, the flow equation is finally in a second-order discrete format during calculation, and the convection heat flow at different wall temperatures is obtained by changing the wall temperature.
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| CN109726432B (en) * | 2018-11-26 | 2023-05-16 | 北京空天技术研究所 | Aircraft bottom structure temperature calculation method |
| CN109800488B (en) * | 2019-01-02 | 2022-09-20 | 南京理工大学 | Numerical calculation method for bottom thermal environment of liquid rocket in high-altitude environment |
| CN113065201B (en) * | 2021-05-08 | 2022-03-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Radiation balance temperature calculation method considering slip correction |
| CN117963157A (en) * | 2024-03-28 | 2024-05-03 | 南京工业大学 | Thermal test method and system for multi-temperature-zone structure of full-size hypersonic aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2107481A1 (en) * | 2006-11-29 | 2009-10-07 | Airbus España, S.L. | Thermal simulation methods and systems for analysing fire in objects |
| CN104461677A (en) * | 2014-10-30 | 2015-03-25 | 中国运载火箭技术研究院 | Virtual thermal test method based on CFD and FEM |
| CN105095603A (en) * | 2015-09-09 | 2015-11-25 | 哈尔滨工业大学 | Multi-field coupling transient numerical method for hypersonic flow-heat transfer and structural response |
| CN105354354A (en) * | 2015-09-28 | 2016-02-24 | 沈阳航空航天大学 | Method for calculating temperature field of main driving motor of electric aircraft |
-
2017
- 2017-05-04 CN CN201710306477.6A patent/CN108304595B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2107481A1 (en) * | 2006-11-29 | 2009-10-07 | Airbus España, S.L. | Thermal simulation methods and systems for analysing fire in objects |
| CN104461677A (en) * | 2014-10-30 | 2015-03-25 | 中国运载火箭技术研究院 | Virtual thermal test method based on CFD and FEM |
| CN105095603A (en) * | 2015-09-09 | 2015-11-25 | 哈尔滨工业大学 | Multi-field coupling transient numerical method for hypersonic flow-heat transfer and structural response |
| CN105354354A (en) * | 2015-09-28 | 2016-02-24 | 沈阳航空航天大学 | Method for calculating temperature field of main driving motor of electric aircraft |
Non-Patent Citations (2)
| Title |
|---|
| 基于代理模型的高超声速气动热模型降阶研究;陈鑫等;《北京理工大学学报》;20160430;第36卷(第4期);第340-347页 * |
| 高超声速飞行器翼面气动加热、辐射换热与瞬态;陈鑫等;《弹道学报》;20140630;第26卷(第2期);第1-5页 * |
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