CN108304595A - A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft - Google Patents
A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft Download PDFInfo
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Abstract
A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft disclosed by the embodiments of the present invention, it is related to the structure temperature analytical technology in the semiclosed region of hypersonic aircraft, can solves the problems, such as that the precision of semi-enclosed complex jamming area Aerodynamic Heating/multi-part radiation interference/Three-dimensional Heat-transfer analysis result and efficiency cannot be taken into account.This method firstly generates the Aerodynamic Heating grid of concern position, Aerodynamic Heating grid is recycled to carry out Aerodynamic Heating analysis, carry out the convective heat flow analysis under different wall temperatures, obtain the convective heat flow database under high wall temperature, the high wall temperature heat convection of consideration is generated again, the Three-dimensional Heat-transfer of multi-part radiation interference analyzes grid, finally carry out the Three-dimensional Heat-transfer calculating for considering high wall temperature heat convection, multi-part radiation interference using the Three-dimensional Heat-transfer analysis grid, this method is mainly used for the structure temperature analysis in the semiclosed region of hypersonic aircraft.
Description
Technical field
The present invention relates to the structure temperature analysis technical fields in the semiclosed region of hypersonic aircraft, more particularly to one kind
For the semiclosed region of hypersonic aircraft consider high wall temperature heat convection, multi-part radiation interference Three-dimensional Heat-transfer analysis side
Method.
Background technology
It becomes increasingly complex with the shape of hypersonic aircraft, flight Mach number is higher and higher, the heat of aircraft surface
Environment is harsher, and there is only Aerodynamic Heatings on semi-enclosed complex jamming area high-temperature component surface, and between high-temperature component also
Mutual radiation/reflection/absorption energy, physical process are sufficiently complex.Since the very multipart temperature in current complex jamming area is all located
On the boundary allowable of material, the determination of structure thermal protection scheme and flight test trajectory scheme restrict, it is therefore desirable to flying
The structure temperature of Hang Qi complex jammings area high-temperature component carries out explication de texte.
Conventional analysis Flight Vehicle Structure temperature usually utilize cold wall hot-fluid and restore enthalpy, cannot consider convection transfer rate with
The variation of wall temperature, the structure temperature analyzed in this way are usually higher.Conventional analysis " convection current/radiation/heat transfer " generally use stream consolidates coupling
The method of conjunction, but not only computational efficiency is extremely low for this method, and also heat source (convective heat flow, radiant heat flux, heat conduction heat flux) is only
Can be using original calculation as a result, cannot correct, computational accuracy can not also ensure.
The structure temperature that therefore, it is necessary to urgently break through high wall temperature heat convection, multi-part radiation interference is coupled with Three-dimensional Heat-transfer
Spend analytical technology.
Invention content
It is an object of the invention to overcome the shortage of prior art, provide a kind of for hypersonic aircraft semi enclosed area
The structure temperature analysis method in domain, can solve Aerodynamic Heating/multi-part radiation interference/Three-dimensional Heat-transfer analysis result precision and
The problem of efficiency cannot be taken into account.
Technical solution of the invention：
A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft, this method consider high wall temperature pair
Stream heat exchange and multi-part radiation interference, include the following steps：
The Aerodynamic Heating grid of concern position is generated, first layer mesh scale is 0.01mm in wall surface boundary layer；
Carry out Aerodynamic Heating using Aerodynamic Heating grid to analyze, carries out the convective heat flow analysis under different wall temperatures, obtain high
Convective heat flow database under wall temperature, the database include the correspondence between node coordinate, wall temperature and convective heat flow；
Generation considers high wall temperature heat convection, the Three-dimensional Heat-transfer of multi-part radiation interference analyzes grid, which includes sky
Gas grid and structural thermal grid, size difference is less than 1.5~3 times between adjacent air-grid and structural thermal grid；
Utilize the high wall temperature heat convection of Three-dimensional Heat-transfer analysis grid development consideration, the Three-dimensional Heat-transfer meter of multi-part radiation interference
It calculates, the wall surface of Aerodynamic Heating is with certain thickness heat conduction thin walled shell, thickness of shell<1e-6m, high wall temperature convective heat flow with
The form of heat rate loads in heat conduction thin walled shell, and heat rate library and the relationship in high wall temperature convective heat flow library areOther high-temperature wall surfaces are analyzed to Aerodynamic Heating wall surface using radiation patterns simultaneously
Radiant heat flux utilizes the temperature of heat transfer model analysis Aerodynamic Heating wall surface under high wall temperature convective heat flow and radiant heat flux collective effect
Degree increases and Three-dimensional Heat-transfer, and when calculating, each node on Aerodynamic Heating wall surface is respective in each time step extract real-time
Temperature, then corresponding convective heat flow is extracted from the convective heat flow lane database, on this node by convective heat flow load, solve
Energy equation and radiation equation, load radiant heat flux automatically.
A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft provided in an embodiment of the present invention,
Corresponding working specification is established, ensure that the precision and effect of Aerodynamic Heating/multi-part radiation interference/Three-dimensional Heat-transfer analysis result
Rate can fast and accurately obtain the structure of Aerodynamic Heating/multi-part radiation interference/Three-dimensional Heat-transfer coupling by using this method
Temperature is used for the design and assessment of hypersonic aircraft complex jamming plot structure thermal protection system.Realize that aircraft complexity is dry
The explication de texte of area's high-temperature component temperature is disturbed, can realize more accurate structure heat protection design, assessment and flight test bullet
The determination of road scheme.
Description of the drawings
Included attached drawing is used for providing being further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together with verbal description to illustrate the principle of the present invention.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, other drawings may also be obtained based on these drawings.
Fig. 1 is that a kind of structure temperature for the semiclosed region of hypersonic aircraft provided in an embodiment of the present invention is analyzed
Method flow schematic diagram.
Specific implementation mode
Specific embodiments of the present invention are described in detail below in conjunction with attached drawing.In the following description, for solution
Purpose and not restrictive is released, elaborates detail, to help to be apparent from the present invention.However, to people in the art
It is readily apparent that the present invention can also be put into practice in the other embodiments departing from these details for member.
It should be noted that in order to avoid having obscured the present invention because of unnecessary details, only show in the accompanying drawings
The device structure closely related with scheme according to the present invention and/or processing step are gone out, and have been omitted with relationship of the present invention not
Big other details.
The embodiment of the present invention provides a kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft, should
Method considers high wall temperature heat convection and multi-part radiation interference, this is not simple Three-dimensional Heat-transfer analysis method.Simply
Three-dimensional Heat-transfer is analyzed without the concern for high wall temperature heat convection, need not also radiation patterns be utilized to calculate multi-part radiation interference.
Include the following steps：
101, the Aerodynamic Heating grid of concern position is generated, first layer mesh scale is 0.01mm in wall surface boundary layer；
102, carry out Aerodynamic Heating using Aerodynamic Heating grid to analyze, carry out the convective heat flow analysis under different wall temperatures, obtain
It includes the corresponding pass between node coordinate, wall temperature and convective heat flow to take the convective heat flow database under high wall temperature, the database
System；
103, the high wall temperature heat convection of consideration is generated, the Three-dimensional Heat-transfer of multi-part radiation interference analyzes grid, the grid packet
Containing air-grid and structural thermal grid, size difference is less than 1.5~3 times between adjacent air-grid and structural thermal grid；
104, carried out using Three-dimensional Heat-transfer analysis grid and consider that high wall temperature heat convection, the three-dimensional of multi-part radiation interference pass
Heat calculates, and the wall surface of Aerodynamic Heating is with certain thickness heat conduction thin walled shell, thickness of shell<1e-6m, high wall temperature advection heat
In heat conduction thin walled shell, heat rate library and the relationship in high wall temperature convective heat flow library are stream for load in the form of heat rateOther high-temperature wall surfaces are analyzed to Aerodynamic Heating wall surface using radiation patterns simultaneously
Radiant heat flux utilizes the temperature of heat transfer model analysis Aerodynamic Heating wall surface under high wall temperature convective heat flow and radiant heat flux collective effect
Degree increases and Three-dimensional Heat-transfer, and when calculating, each node on Aerodynamic Heating wall surface is respective in each time step extract real-time
Temperature, then corresponding convective heat flow is extracted from the convective heat flow lane database, on this node by convective heat flow load, solve
Energy equation and radiation equation, load radiant heat flux automatically.
A kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft provided in this embodiment is established
Corresponding working specification, ensure that the precision and efficiency of Aerodynamic Heating/multi-part radiation interference/Three-dimensional Heat-transfer analysis result,
By using this method, the structure temperature of Aerodynamic Heating/multi-part radiation interference/Three-dimensional Heat-transfer coupling can be fast and accurately obtained
Degree is used for the design and assessment of hypersonic aircraft complex jamming plot structure thermal protection system.Realize aircraft complex jamming
The explication de texte of area's high-temperature component temperature can realize more accurate structure heat protection design, assessment and flight test trajectory
The determination of scheme.
Understand that above-mentioned technical proposal, the embodiment of the present invention provide above-mentioned a kind of hypersonic aircraft half for the ease of reader
The application example of the structure temperature analysis method of closed area, specifically, being realized by following steps：
Step 1：High wall temperature heat convection Database.
Step 1.1 generates Aerodynamic Heating grid.
Generate the Aerodynamic Heating grid of concern position.To ensure computational accuracy, it is desirable that first layer grid in wall surface boundary layer
Scale is 0.01mm.Grid continuous transition carries out local cypher while ensureing grid uniformity as possible to concern position.
The high wall temperature convective heat flow Database of step 1.2
The calculation of aerodynamic heating grid generated using step 1.1, using the SST turbulence models of Fluent softwares, setting is empty
Gas material properties, different wall surface temperatures, tubulence energy and than the spatial spreading format of dissipative shock wave, convergence, according to it is practical come
Stream mode determines wall surface temperature range (280~total temperature), be arranged different wall surface temperatures (such as 280K, 300K, 400K,
500K, 600K, 700K ... total temperature), carry out the Aerodynamic Heating analysis under different wall temperatures, obtains the advection heat under different wall temperatures
Stream can specifically be based on the bright number in library, tubulence energy and than dissipative shock wave, convective heat flow is calculated using turbulence model, the control bright number in library
Increase, the variation of tubulence energy and the discrete scheme than the spatial spreading format of dissipative shock wave, flow equation, ensures that convective heat flow calculates
Process do not dissipate, numerical convergence, and flow equation is finally that Second-Order Discrete format is obtained not by changing wall temperature when calculating
With the convective heat flow under wall temperature.
The database of high wall temperature convective heat flow is established, database includes pair between node coordinate, wall temperature and convective heat flow
It should be related to.In order to achieve the purpose that obtain accurate hot-fluid result, the increasing that the bright number in library is controlled according to preset mode is needed
Long, flow equation discrete scheme.
Step 2：Consider the Three-dimensional Heat-transfer analysis of high wall temperature heat convection, multi-part radiation interference.
Step 2.1 generate it is a kind of consider high wall temperature heat convection, multi-part radiation interference Three-dimensional Heat-transfer coupling analysis net
Lattice.
The grid includes the grid of the grid and structural thermal of air-shed, adjacent air-grid and structural thermal grid it
Between size difference be less than 1.5~3 times.
Since air-grid is only used for calculating the ascent of radiation heat transfer, the requirement to air-grid is relatively low, requires nothing more than sky
The grid transition of gas grid and structural thermal is good.The grid of structural thermal requires that orthogonality is good, transition is good.
Step 2.2 carries out a kind of Three-dimensional Heat-transfer calculating considering high wall temperature heat convection, multi-part radiation interference.
This patent uses the User Defined interface that Fluent softwares provide, and will entirely calculate thinking, computational methods conversion
It is embedded into software at the Fluent language identified, controls entire calculating process.
Step 2.2.1 wall surfaces load convective heat flow database.
Using the DO radiation patterns of Fluent softwares, it sets the wall surface of Aerodynamic Heating to coupled boundary conditions, is arranged
The emissivity of wall surface and shell heat conduction；In order to ensure computational accuracy, by research, need to set wall thickness to 1e-6m；
The User Defined interface provided using Fluent, the convective heat flow database that bespoke program establishes front is according to coordinate
Load is on the corresponding node of wall surface.In order to avoid mutually conflicting with the radiant heat flux that Fluent is calculated automatically, this convective heat flow
Load mode cleverly selects Heat Generation Rate very much, and setting this to convective heat flow/wall thickness load exists
On Fluent softwares.
Step 2.2.2 radiation, heat transfer model setting
Radiation patterns：DO radiation patterns.
Air participates in radiation, and solid is not involved in radiation.
Wall boundary condition：Thermal boundary condition is selected according to actual conditions, needs that wall surface emissivity and wall surface temperature is arranged.
Step 2.2.3 settings solve equation
It due to the very difficult convergence of flow equation, solves flow equation and takes very much, in order to improve computational efficiency, when calculating not
Flow equation is solved, energy equation and radiation equation are only solved；But convective heat flow data are needed in order to solve the problems, such as to calculate, are adopted
The ingenious load in convective heat flow library for being established step 1.2 with the method for step 2.2.1, in this way can be both on wall surface
Computational efficiency is improved, while also ensureing computational accuracy.
Step 2.2.4, which carries out, to be calculated
Suitable time step and time step are set, is carried out using Three-dimensional Heat-transfer analysis grid and considers that high wall temperature convection current is changed
Heat, the Three-dimensional Heat-transfer of multi-part radiation interference calculate, and the wall surface of Aerodynamic Heating is with certain thickness heat conduction thin walled shell, shell
Thickness<1e-6m loads high wall temperature convective heat flow in heat conduction thin walled shell in the form of heat rate, heat rate library and height
The relationship in wall temperature convective heat flow library isIt is analyzed simultaneously using radiation patterns other high
Warm wall surface analyzes common in high wall temperature convective heat flow and radiant heat flux the radiant heat flux of Aerodynamic Heating wall surface using heat transfer model
The temperature of the lower Aerodynamic Heating wall surface of effect increases and Three-dimensional Heat-transfer, and when calculating, each node on Aerodynamic Heating wall surface is each
The respective temperature of time step all extract real-times, then corresponding convective heat flow is extracted from the convective heat flow lane database, by convection current
Hot-fluid loads on this node, solves energy equation and radiation equation, loads radiant heat flux automatically.
As above it is directed to that a kind of embodiment describes and/or the feature that shows can be in a manner of same or similar at one or more
It is used in a number of other embodiments, and/or the feature in other embodiments is combined or substitutes with the feature in other embodiments
It uses.
It should be emphasized that term "comprises/comprising" refers to the presence of feature, one integral piece, step or component when being used herein, but simultaneously
It is not excluded for the presence or additional of one or more other features, one integral piece, step, component or combinations thereof.
The device and method more than present invention can be by hardware realization, can also be by combination of hardware software realization.The present invention
It is related to such computer-readable program, when the program is performed by logical block, the logical block can be made to realize above
The device or component parts, or the logical block is made to realize various method or steps described above.The invention further relates to
Storage medium for storing procedure above, such as hard disk, disk, CD, DVD, flash memory.
The many features and advantage of these embodiments are clear according to the detailed description, therefore appended claims are intended to
Cover all these feature and advantage of these embodiments fallen into its true spirit and range.Further, since this field
Technical staff is readily apparent that many modifications and changes, therefore is not meant to the embodiment of the present invention being limited to illustrated and description essence
Really structurally and operationally, but all suitable modifications and the equivalent fallen within the scope of its can be covered.
Unspecified part of the present invention is known to the skilled person technology.
Claims (2)
1. a kind of structure temperature analysis method for the semiclosed region of hypersonic aircraft, which is characterized in that this method is examined
Consider high wall temperature heat convection and multi-part radiation interference, includes the following steps：
The Aerodynamic Heating grid of concern position is generated, first layer mesh scale is 0.01mm in wall surface boundary layer；
Carry out Aerodynamic Heating using Aerodynamic Heating grid to analyze, carries out the convective heat flow analysis under different wall temperatures, obtain high wall temperature
Under convective heat flow database, the database includes correspondence between node coordinate, wall temperature and convective heat flow；
Generation considers high wall temperature heat convection, the Three-dimensional Heat-transfer of multi-part radiation interference analyzes grid, which includes air net
Lattice and structural thermal grid, size difference is less than 1.5~3 times between adjacent air-grid and structural thermal grid；
Utilize the high wall temperature heat convection of Three-dimensional Heat-transfer analysis grid development consideration, the Three-dimensional Heat-transfer of multi-part radiation interference
It calculates, the wall surface of Aerodynamic Heating is with certain thickness heat conduction thin walled shell, thickness of shell<1e-6m, high wall temperature convective heat flow
In heat conduction thin walled shell, heat rate library and the relationship in high wall temperature convective heat flow library are for load in the form of heat rateOther high-temperature wall surfaces are analyzed to Aerodynamic Heating wall surface using radiation patterns simultaneously
Radiant heat flux utilizes the temperature of heat transfer model analysis Aerodynamic Heating wall surface under high wall temperature convective heat flow and radiant heat flux collective effect
Degree increases and Three-dimensional Heat-transfer, and when calculating, each node on Aerodynamic Heating wall surface is respective in each time step extract real-time
Temperature, then corresponding convective heat flow is extracted from the convective heat flow lane database, on this node by convective heat flow load, solve
Energy equation and radiation equation, load radiant heat flux automatically.
2. according to the method described in claim 1, it is characterized in that, the convective heat flow analysis bag carried out under different wall temperatures
It includes：Based on the bright number in library, tubulence energy and than dissipative shock wave, convective heat flow is calculated using turbulence model, controls growth, the turbulence of the bright number in library
Can and discrete scheme than the spatial spreading format of dissipative shock wave, flow equation variation, ensure that convective heat flow calculating process is not sent out
It dissipates, numerical convergence, flow equation is finally that Second-Order Discrete format is obtained by changing wall temperature under different wall temperatures when calculating
Convective heat flow.
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