CN114722543A - Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft - Google Patents

Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft Download PDF

Info

Publication number
CN114722543A
CN114722543A CN202210644177.XA CN202210644177A CN114722543A CN 114722543 A CN114722543 A CN 114722543A CN 202210644177 A CN202210644177 A CN 202210644177A CN 114722543 A CN114722543 A CN 114722543A
Authority
CN
China
Prior art keywords
heat
test piece
top surface
rectangular
screen
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202210644177.XA
Other languages
Chinese (zh)
Other versions
CN114722543B (en
Inventor
王彬文
姚港
秦强
丛琳华
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AVIC Aircraft Strength Research Institute
Original Assignee
AVIC Aircraft Strength Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AVIC Aircraft Strength Research Institute filed Critical AVIC Aircraft Strength Research Institute
Priority to CN202210644177.XA priority Critical patent/CN114722543B/en
Publication of CN114722543A publication Critical patent/CN114722543A/en
Application granted granted Critical
Publication of CN114722543B publication Critical patent/CN114722543B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/27—Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/06—Multi-objective optimisation, e.g. Pareto optimisation using simulated annealing [SA], ant colony algorithms or genetic algorithms [GA]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Evolutionary Computation (AREA)
  • Computer Hardware Design (AREA)
  • General Engineering & Computer Science (AREA)
  • Mathematical Analysis (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Computational Mathematics (AREA)
  • Artificial Intelligence (AREA)
  • Computer Vision & Pattern Recognition (AREA)
  • Medical Informatics (AREA)
  • Software Systems (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)

Abstract

The invention discloses a design method of a heat reflecting screen in a structural heat intensity test of a hypersonic aircraft, which comprises the following steps: firstly, building a thermal strength test of a hypersonic aircraft structure; secondly, establishing coordinates; thirdly, acquiring the total heat flow of the radiation of the rectangular test piece; and fourthly, optimizing the parameter design of the heat reflecting screen. The method has reasonable design, realizes the design optimization of the structural parameters of the heat reflecting screen in the structural heat intensity test of the hypersonic aerocraft, and improves the uniformity of the heat flow field borne by the surface of the structural test piece of the hypersonic aerocraft, so that the surface temperature field of the structural test piece of the hypersonic aerocraft is uniform, thereby increasing the accuracy of the subsequent structural heat intensity test of the hypersonic aerocraft.

Description

Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft
Technical Field
The invention belongs to the technical field of structural heat intensity tests of hypersonic flight vehicles, and particularly relates to a design method of a heat reflecting screen in the structural heat intensity tests of the hypersonic flight vehicles.
Background
The test of the thermal strength of the hypersonic aircraft structure is a test for verifying and evaluating the strength of the hypersonic aircraft structure under the environment of ground simulated aerodynamic heat and the like. When the hypersonic aerocraft flies at a higher speed in the atmosphere, the outer surface of the hypersonic aerocraft needs to bear severe pneumatic heating, so that the hypersonic aerocraft structure is in an extremely high-temperature environment (namely a high-temperature environment of 1200-1600 ℃). The influence of pneumatic heating on the structure of the hypersonic aerocraft is mainly reflected in the following aspects: the strength limit and the elastic modulus of the material are reduced under the extremely high temperature environment, so that the bearing capacity of the structure is reduced; additional thermal stress is generated and is superposed with mechanical stress generated by other force loads to influence the bearing capacity of the structure; under the combined action of extreme high temperature and thermal stress, the structure may deform, destroy the aerodynamic appearance of the component and reduce the natural frequency of the structure, and in severe cases, dangerous resonance phenomenon, namely aeroelasticity problem, is easily caused to cause flight accidents. Ground verification and evaluation of hypersonic aircraft must therefore be performed through structural heat intensity tests. One of the cores of the heat intensity test is the extreme high-temperature thermal environment caused by accurate simulation pneumatic heating under the ground environment, therefore, the radiation heating device is generally adopted for simulating the extreme high-temperature thermal environment caused by pneumatic heating at present, but the heat reflection screen in the radiation heating device is mostly a flat plate type heat reflection screen, the radiation heat flow received at the center of the hypersonic aircraft structure test piece can be caused to be large, and the direction is gradually reduced all around, and then the surface temperature distribution of the test piece is uneven, the uniform extreme high-temperature environment required by the hypersonic aircraft structure heat intensity test can not be accurately simulated.
Disclosure of Invention
The invention aims to solve the technical problem that the defects in the prior art are overcome, and provides a design method of a heat reflecting screen in a hypersonic aircraft structure heat intensity test.
In order to solve the technical problems, the invention adopts the technical scheme that: a design method for a heat reflecting screen in a structural heat intensity test of a hypersonic aircraft is characterized by comprising the following steps:
step one, building a thermal strength test of a hypersonic aircraft structure:
step 101, building a hypersonic aircraft structure heat strength test device in an airplane test room; the hypersonic aircraft structure heat intensity test device comprises a radiation heating device and a hypersonic aircraft structure test piece arranged below the radiation heating device, wherein the hypersonic aircraft structure test piece is marked as a rectangular test piece (3), and the radiation heating device comprises a radiation heating element array and a heat reflecting screen (1);
102, setting a radiation heating element array to comprise a plurality of radiation heating parts (2) which are uniformly distributed in parallel, wherein the radiation heating parts (2) are cylindrical, and the plurality of radiation heating parts (2) are sequentially marked as the 1 st radiation heating part according to the length direction of the heat reflecting screen (1)
Figure 615450DEST_PATH_IMAGE001
A radiant heating element, the first
Figure 634222DEST_PATH_IMAGE002
A radiant heating element; wherein the content of the first and second substances,
Figure 46748DEST_PATH_IMAGE001
and
Figure 137064DEST_PATH_IMAGE003
are all positive integers, and
Figure 318647DEST_PATH_IMAGE004
，
Figure 773899DEST_PATH_IMAGE002
representing radiation plusThe total number of the heating elements, the length direction of any one radiation heating element is arranged along the width direction of the heat reflecting screen (1);
103, setting the cross section of the heat reflection screen (1) to be a rectangular heat reflection screen, wherein a rectangular opening part (1-1) is arranged at the center of the heat reflection screen (1), the center of the rectangular opening part (1-1) is superposed with the center projection of the rectangular test piece (3), the length direction of the rectangular opening part (1-1) is arranged along the length directions of the rectangular test piece (3) and the heat reflection screen (1), the width direction of the rectangular opening part (1-1) is arranged along the width directions of the rectangular test piece (3) and the heat reflection screen (1), and the projection area of the heat reflection screen (1) is larger than the surface area of the rectangular test piece (3);
step 104, setting the vertical distance between the axes of the plurality of radiant heating elements (2) and the top surface of the rectangular test piece (3) to be
Figure 408143DEST_PATH_IMAGE005
The axes of the plurality of radiation heating members (2) are vertically spaced from the bottom surface of the heat reflecting screen (1)
Figure 974253DEST_PATH_IMAGE006
；
Step two, coordinate establishment:
step 201, using the top surface center of the rectangular test piece (3) as an origin
Figure 88971DEST_PATH_IMAGE007
Passing through the origin
Figure 715124DEST_PATH_IMAGE007
And the length direction of the top surface of the rectangular test piece (3) is
Figure 836664DEST_PATH_IMAGE008
Axis, passing through origin
Figure 206465DEST_PATH_IMAGE009
And the width direction of the top surface of the rectangular test piece (3) is
Figure 362640DEST_PATH_IMAGE010
Shaft, establishment
Figure 222012DEST_PATH_IMAGE011
A coordinate system;
step 202, taking the center of the top surface of the heat reflecting screen (1) as an origin
Figure 830848DEST_PATH_IMAGE012
Passing through the origin
Figure 738761DEST_PATH_IMAGE012
And along the length direction of the top surface of the heat reflection screen (1) is
Figure 749442DEST_PATH_IMAGE013
Axis, passing through origin
Figure 717398DEST_PATH_IMAGE012
And along the width direction of the top surface of the heat reflection screen (1) is
Figure 813530DEST_PATH_IMAGE014
Shaft, building
Figure 836719DEST_PATH_IMAGE015
A coordinate system;
step three, obtaining the total heat flow of the radiation of the rectangular test piece:
step 301, setting any point on the top surface of the rectangular test piece (3) to be at
Figure 701907DEST_PATH_IMAGE016
Seat marking in coordinate system
Figure 840764DEST_PATH_IMAGE017
(ii) a Wherein the content of the first and second substances,
Figure 424192DEST_PATH_IMAGE018
represent
Figure 939487DEST_PATH_IMAGE019
The axis abscissa;
Figure 721498DEST_PATH_IMAGE020
to represent
Figure 31257DEST_PATH_IMAGE021
An axis ordinate;
step 302, setting the first
Figure 101981DEST_PATH_IMAGE022
The axial length direction of the radiation heating element is at any point
Figure 155388DEST_PATH_IMAGE023
The abscissa in the coordinate system is
Figure 995168DEST_PATH_IMAGE024
(ii) a Wherein the content of the first and second substances,
Figure 288877DEST_PATH_IMAGE025
has a value range of
Figure 846897DEST_PATH_IMAGE026
，
Figure 438416DEST_PATH_IMAGE027
Represents the length of the heat reflection screen (1);
step 303, establishing a dimensionless radiation function
Figure 132702DEST_PATH_IMAGE028
As follows:
Figure 49842DEST_PATH_IMAGE029
(ii) a Wherein the content of the first and second substances,
Figure 829580DEST_PATH_IMAGE030
represents a dimensionless first parameter, an
Figure 287106DEST_PATH_IMAGE031
；
Figure 101478DEST_PATH_IMAGE032
Represents a dimensionless second parameter, an
Figure 923941DEST_PATH_IMAGE033
；
Figure 190974DEST_PATH_IMAGE034
Represents a dimensionless third parameter, an
Figure 389874DEST_PATH_IMAGE035
；
Figure 370337DEST_PATH_IMAGE036
Represents the width of the heat reflection screen (1);
step 304, according to the formula
Figure 363701DEST_PATH_IMAGE037
To obtain the first
Figure 118030DEST_PATH_IMAGE038
The radiation heating element directly radiates to the top surface of the rectangular test piece (3)
Figure 855042DEST_PATH_IMAGE039
Heat flow at a point
Figure 378427DEST_PATH_IMAGE040
(ii) a Wherein the content of the first and second substances,
Figure 870589DEST_PATH_IMAGE041
represents the radiation power of the radiation heating element (2);
305, according to the formula
Figure 112214DEST_PATH_IMAGE042
To obtain the first
Figure 387338DEST_PATH_IMAGE038
A radiation heating member directly radiates to the surface of the test piece
Figure 30809DEST_PATH_IMAGE039
The radiation reflected by the heat reflecting screen is reflected on the surface of the test piece
Figure 365975DEST_PATH_IMAGE039
Sum of heat flows at points
Figure 94897DEST_PATH_IMAGE043
(ii) a Wherein the content of the first and second substances,
Figure 986760DEST_PATH_IMAGE044
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 484738DEST_PATH_IMAGE039
The heat flow at the point of the heat transfer,
Figure 256385DEST_PATH_IMAGE045
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 207023DEST_PATH_IMAGE039
Heat flow at the point;
step 306, according to the formula
Figure 89529DEST_PATH_IMAGE046
To obtain the top surface of the test piece
Figure 504329DEST_PATH_IMAGE039
Total heat flow of radiation at a point
Figure 446878DEST_PATH_IMAGE047
；
Step four, optimizing the parameter design of the heat reflecting screen:
step 401, giving the length of the rectangular opening (1-1) in the heat reflection screen
Figure 884812DEST_PATH_IMAGE048
An initial value is given to the width of the rectangular opening (1-1) in the heat reflection screen
Figure 305429DEST_PATH_IMAGE049
Assigning an initial value;
step 402, adopting a multi-island genetic algorithm to determine the length of the rectangular opening (1-1)
Figure 777999DEST_PATH_IMAGE048
And the width of the rectangular opening (1-1)
Figure 226470DEST_PATH_IMAGE049
Performing iterative optimization to obtain
Figure 151701DEST_PATH_IMAGE051
Length after sub-iteration optimization
Figure 376009DEST_PATH_IMAGE052
And width
Figure 437506DEST_PATH_IMAGE053
；
Step 403, judge
Figure 721857DEST_PATH_IMAGE054
Length after sub-iteration optimization
Figure 196700DEST_PATH_IMAGE052
And width
Figure 224699DEST_PATH_IMAGE053
Whether the set convergence condition is met or not is judged, if the set convergence condition is not met, the next iteration optimization is executed; if the set convergence condition is satisfied, the first step
Figure 406282DEST_PATH_IMAGE054
Length after sub-iteration optimization
Figure 595955DEST_PATH_IMAGE055
And width
Figure 495778DEST_PATH_IMAGE053
Is heatDesigning optimized structural parameters of the reflecting screen; wherein the content of the first and second substances,
Figure 874938DEST_PATH_IMAGE056
is a positive integer;
Figure 176606DEST_PATH_IMAGE057
。
the design method of the heat reflecting screen in the structural heat intensity test of the hypersonic aircraft is characterized by comprising the following steps: in step 305
Figure 537180DEST_PATH_IMAGE058
And
Figure 924299DEST_PATH_IMAGE059
the specific process of obtaining is as follows:
3051, according to a formula
Figure 294101DEST_PATH_IMAGE060
To obtain the top surface of the rectangular test piece (3) reflected by the heat reflection screen (1)
Figure 184696DEST_PATH_IMAGE061
Heat flow at a point
Figure 44068DEST_PATH_IMAGE062
Wherein, the water-soluble polymer is a polymer,
Figure 652904DEST_PATH_IMAGE063
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 826396DEST_PATH_IMAGE061
Reflects heat flow specularly, and
Figure 837077DEST_PATH_IMAGE064
；
Figure 805033DEST_PATH_IMAGE065
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 212750DEST_PATH_IMAGE066
Diffusely reflects heat flow thereto, and
Figure 924354DEST_PATH_IMAGE067
，
Figure 789542DEST_PATH_IMAGE068
indicates that any point on the bottom surface of the heat reflection screen (1) is at
Figure 928399DEST_PATH_IMAGE069
The coordinates of the object under the coordinate system,
Figure 511827DEST_PATH_IMAGE070
which represents the double differential of the light beam,
Figure 823860DEST_PATH_IMAGE071
representing the specular reflection coefficient of the heat reflecting screen (1),
Figure 809133DEST_PATH_IMAGE072
represents the diffuse reflection coefficient of the heat reflection screen (1);
3052, according to the formula
Figure 118892DEST_PATH_IMAGE073
Obtaining the area of a rectangular opening part (1-1) in the heat reflecting screen (1) to be reflected to the top surface of the rectangular test piece (3)
Figure 189616DEST_PATH_IMAGE074
Heat flow at a point
Figure 243023DEST_PATH_IMAGE075
Wherein, the water-soluble polymer is a polymer,
Figure 895852DEST_PATH_IMAGE076
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 376512DEST_PATH_IMAGE074
Reflects heat flow specularly, and
Figure 668953DEST_PATH_IMAGE077
;
Figure 526051DEST_PATH_IMAGE078
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 220337DEST_PATH_IMAGE074
Diffusely reflects heat flow thereto, and
Figure 871898DEST_PATH_IMAGE079
;
Figure 979532DEST_PATH_IMAGE080
is shown as
Figure 374741DEST_PATH_IMAGE081
The axial length direction of the radiation heating element is at any point
Figure 923534DEST_PATH_IMAGE082
An abscissa in the coordinate system and located in the region of the rectangular opening (1-1);
Figure 11576DEST_PATH_IMAGE083
has a value range of
Figure 278609DEST_PATH_IMAGE084
，
Figure 789093DEST_PATH_IMAGE085
The length of a rectangular opening (1-1) in a heat reflection screen (1) is shown.
The design method of the heat reflecting screen in the hypersonic aircraft structure heat strength test is characterized by comprising the following steps: step 401 gives the length of the rectangular opening (1-1) in the heat reflection screen
Figure 192393DEST_PATH_IMAGE086
Giving an initial value of
Figure 451336DEST_PATH_IMAGE087
Giving the width of the rectangular opening (1-1) in the heat reflection screen
Figure 205665DEST_PATH_IMAGE088
Giving an initial value of
Figure 942677DEST_PATH_IMAGE089
；
The convergence condition set in step 403 specifically includes the following steps:
step 4031, get
Figure 528379DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 958224DEST_PATH_IMAGE091
And width
Figure 934270DEST_PATH_IMAGE092
Substitute step 306 to obtain the second
Figure 474973DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 118444DEST_PATH_IMAGE091
And width
Figure 266659DEST_PATH_IMAGE092
Corresponding test piece top surface
Figure 995581DEST_PATH_IMAGE093
Total heat flow of radiation at a point
Figure 74395DEST_PATH_IMAGE094
；
4032, repeating 4031 for multiple times to obtain total radiant heat flow at all points of the top surface of the test piece, and acquiring total radiant heat flow at all points of the top surface of the test piece
Figure 572373DEST_PATH_IMAGE095
And
Figure 78441DEST_PATH_IMAGE096
(ii) a Wherein the content of the first and second substances,
Figure 294658DEST_PATH_IMAGE097
is shown as
Figure 239480DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 591964DEST_PATH_IMAGE091
And width
Figure 534513DEST_PATH_IMAGE092
The maximum value of the total heat flow of the radiation at all points of the top surface of the corresponding test piece,
Figure 972447DEST_PATH_IMAGE096
is shown as
Figure 393064DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 177218DEST_PATH_IMAGE098
And width
Figure 25089DEST_PATH_IMAGE099
The minimum value of the total radiant heat flow at all points of the top surface of the corresponding test piece;
step 4033, the convergence conditions are set as follows:
Figure 950319DEST_PATH_IMAGE100
。
the design method of the heat reflecting screen in the structural heat intensity test of the hypersonic aircraft is characterized by comprising the following steps: the parameters of the multi-island genetic algorithm in step 402 are set as: the number and size of each island were set to 10, and the crossover rate, the variation rate, and the mobility were 1.00, 0.01, and 0.01, respectively.
Compared with the prior art, the invention has the following advantages:
1. the design method of the heat reflecting screen in the structural heat strength test of the hypersonic aircraft has simple steps and is convenient to realize, so that the structural size parameters of the heat reflecting screen in the structural heat strength test of the hypersonic aircraft are obtained, and the design optimization of the heat reflecting screen is completed.
2. The design method of the heat reflecting screen in the hypersonic speed aircraft structure heat intensity test is reasonable in design, firstly, the construction of the hypersonic speed aircraft structure heat intensity test is carried out, secondly, the coordinate establishment is carried out, secondly, the rectangular test piece radiation total heat flow is obtained, and finally, the parameter design optimization of the heat reflecting screen is carried out by adopting a multi-island genetic algorithm, so that the structural parameters after the heat reflecting screen is designed and optimized are obtained.
3. The invention can avoid the phenomenon that the nonuniformity of a radiation heat flow field is aggravated due to the indiscriminate reflection energy of the whole area of the heat reflection screen, the heat reflection screen with the rectangular opening part after the size optimization can selectively reflect, the uniformity and the accuracy of the heat flow field in a heating area are ensured, and further, the surface temperature field of the test piece of the structure of the hypersonic aerocraft is uniform, so that the accuracy of the subsequent structural heat intensity test of the hypersonic aerocraft is improved.
4. The invention can optimize the heat reflection performance of the heat reflection screen only by changing the rectangular opening part, namely two hollow-out sizes, in the heat reflection screen, and has the advantages of simple principle, simple and convenient processing, easy implementation and good universality.
In conclusion, the method has reasonable design, realizes the design optimization of the structural parameters of the heat reflecting screen in the structural heat intensity test of the hypersonic aerocraft, improves the uniformity of the heat flow field borne by the surface of the structural test piece of the hypersonic aerocraft, so that the surface temperature field of the structural test piece of the hypersonic aerocraft is uniform, and the accuracy of the subsequent structural heat intensity test of the hypersonic aerocraft is improved.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic structural diagram of a structural heat strength testing device of a hypersonic aerocraft.
Fig. 2 is a front view of fig. 1.
FIG. 3 is a flow chart of a design method of a heat reflecting screen in a structural heat intensity test of a hypersonic aircraft according to the invention.
Description of reference numerals:
1-heat reflecting screen; 1-a rectangular opening; 2-a radiant heating element;
and 3, a rectangular test piece.
Detailed Description
As shown in fig. 1 to 3, the present invention includes the steps of:
step one, building a thermal strength test of a hypersonic aircraft structure:
step 101, building a hypersonic aircraft structure heat strength test device in an airplane test room; the test device for the structural heat intensity of the hypersonic aerocraft comprises a radiation heating device and a hypersonic aerocraft structural test piece arranged below the radiation heating device, wherein the hypersonic aerocraft structural test piece is marked as a rectangular test piece (3), and the radiation heating device comprises a radiation heating element array and a heat reflecting screen (1);
102, setting a radiation heating element array to comprise a plurality of radiation heating parts (2) which are uniformly distributed in parallel, wherein the radiation heating parts (2) are cylindrical, and the plurality of radiation heating parts (2) are sequentially marked as the 1 st radiation heating part according to the length direction of the heat reflecting screen (1)
Figure 174627DEST_PATH_IMAGE101
A radiant heating element, the first
Figure 501703DEST_PATH_IMAGE102
A radiant heating element; wherein the content of the first and second substances,
Figure 848371DEST_PATH_IMAGE101
and
Figure 260898DEST_PATH_IMAGE103
are all positive integers, and
Figure 23318DEST_PATH_IMAGE104
，
Figure 204900DEST_PATH_IMAGE102
represents the total number of radiation heating elements, the length direction of any one radiation heating element is arranged along the width direction of the heat reflection screen (1);
103, setting the cross section of the heat reflection screen (1) to be a rectangular heat reflection screen, wherein a rectangular opening part (1-1) is arranged at the center of the heat reflection screen (1), the center of the rectangular opening part (1-1) is superposed with the center projection of the rectangular test piece (3), the length direction of the rectangular opening part (1-1) is arranged along the length directions of the rectangular test piece (3) and the heat reflection screen (1), the width direction of the rectangular opening part (1-1) is arranged along the width directions of the rectangular test piece (3) and the heat reflection screen (1), and the projection area of the heat reflection screen (1) is larger than the surface area of the rectangular test piece (3);
step 104, setting the vertical distance between the axes of the plurality of radiation heating elements (2) and the top surface of the rectangular test piece (3) to be lower than that of the rectangular test piece
Figure 660152DEST_PATH_IMAGE105
The axes of the plurality of radiation heating members (2) are vertically spaced from the bottom surface of the heat reflecting screen (1)
Figure 373025DEST_PATH_IMAGE106
；
Step two, coordinate establishment:
step 201, using the top surface center of the rectangular test piece (3) as an origin
Figure 939135DEST_PATH_IMAGE107
Passing through the origin
Figure 975224DEST_PATH_IMAGE107
And the length direction of the top surface of the rectangular test piece (3) is
Figure 601378DEST_PATH_IMAGE108
Axis, passing through origin
Figure 988497DEST_PATH_IMAGE109
And the width direction of the top surface of the rectangular test piece (3) is
Figure 155036DEST_PATH_IMAGE110
Shaft, building
Figure 311211DEST_PATH_IMAGE111
A coordinate system;
step 202, taking the center of the top surface of the heat reflecting screen (1) as an origin
Figure 108265DEST_PATH_IMAGE112
Passing through the origin
Figure 717101DEST_PATH_IMAGE112
And along the length direction of the top surface of the heat reflection screen (1) is
Figure 890594DEST_PATH_IMAGE113
Axis, passing through origin
Figure 901275DEST_PATH_IMAGE112
And along the width direction of the top surface of the heat reflection screen (1) is
Figure 180815DEST_PATH_IMAGE114
Shaft, building
Figure 276947DEST_PATH_IMAGE115
A coordinate system;
step three, obtaining the total heat flow of the radiation of the rectangular test piece:
step 301, setting any point on the top surface of the rectangular test piece (3) to be at
Figure 722972DEST_PATH_IMAGE116
Seat marking in coordinate system
Figure 853739DEST_PATH_IMAGE117
(ii) a Wherein the content of the first and second substances,
Figure 992597DEST_PATH_IMAGE118
to represent
Figure 638341DEST_PATH_IMAGE119
The axis abscissa;
Figure 888057DEST_PATH_IMAGE120
to represent
Figure 873331DEST_PATH_IMAGE121
An axis ordinate;
step 302, setting the first
Figure 183089DEST_PATH_IMAGE122
The axial length direction of the radiation heating element is at any point
Figure 253814DEST_PATH_IMAGE123
The abscissa in the coordinate system is
Figure 120270DEST_PATH_IMAGE124
(ii) a Wherein the content of the first and second substances,
Figure 960050DEST_PATH_IMAGE125
has a value range of
Figure 440709DEST_PATH_IMAGE126
，
Figure 733151DEST_PATH_IMAGE127
Represents the length of the heat reflection screen (1);
step 303, establishing a dimensionless radial function
Figure 590248DEST_PATH_IMAGE128
As follows:
Figure 284535DEST_PATH_IMAGE129
(ii) a Wherein the content of the first and second substances,
Figure 998413DEST_PATH_IMAGE130
represents a dimensionless first parameter, an
Figure 43729DEST_PATH_IMAGE131
；
Figure 438938DEST_PATH_IMAGE132
Represents a dimensionless second parameter, an
Figure 987731DEST_PATH_IMAGE133
；
Figure 75773DEST_PATH_IMAGE134
Represents a dimensionless third parameter, an
Figure 654391DEST_PATH_IMAGE135
；
Figure 587712DEST_PATH_IMAGE136
Represents the width of the heat reflection screen (1);
step 304, according to the formula
Figure 256591DEST_PATH_IMAGE137
To obtain the first
Figure 515534DEST_PATH_IMAGE138
The radiation heating element directly radiates to the top surface of the rectangular test piece (3)
Figure 4284DEST_PATH_IMAGE139
Heat flow at a point
Figure 69192DEST_PATH_IMAGE140
(ii) a Wherein, the first and the second end of the pipe are connected with each other,
Figure 592577DEST_PATH_IMAGE141
represents the radiation power of the radiation heating element (2);
305, according to the formula
Figure 756842DEST_PATH_IMAGE142
To obtain the first
Figure 998468DEST_PATH_IMAGE138
A radiation heating member directly radiates to the surface of the test piece
Figure 539170DEST_PATH_IMAGE139
The radiation reflected by the heat reflecting screen is reflected on the surface of the test piece
Figure 730111DEST_PATH_IMAGE139
Sum of heat flows at points
Figure 330857DEST_PATH_IMAGE143
(ii) a Wherein the content of the first and second substances,
Figure 794199DEST_PATH_IMAGE144
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 138593DEST_PATH_IMAGE139
The heat flow at the point of the heat transfer,
Figure 636570DEST_PATH_IMAGE145
the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 142638DEST_PATH_IMAGE139
Heat flow at the point;
step 306, according to the formula
Figure 421173DEST_PATH_IMAGE146
To obtain the top surface of the test piece
Figure 303678DEST_PATH_IMAGE139
Total heat flow of radiation at a point
Figure 656162DEST_PATH_IMAGE147
；
Step four, optimizing the parameter design of the heat reflecting screen:
step 401, giving the length of the rectangular opening (1-1) in the heat reflection screen
Figure 333131DEST_PATH_IMAGE148
An initial value is given to the width of the rectangular opening (1-1) in the heat reflection screen
Figure 771066DEST_PATH_IMAGE149
Assigning an initial value;
step 402, adopting a multi-island genetic algorithm to determine the length of the rectangular opening (1-1)
Figure 768846DEST_PATH_IMAGE148
And the width of the rectangular opening (1-1)
Figure 975837DEST_PATH_IMAGE149
Performing iterative optimization to obtain the first
Figure 89286DEST_PATH_IMAGE051
Length after sub-iteration optimization
Figure 14517DEST_PATH_IMAGE052
And width
Figure 238825DEST_PATH_IMAGE053
；
Step 403, judge
Figure 628218DEST_PATH_IMAGE054
Length after sub-iteration optimization
Figure 912569DEST_PATH_IMAGE052
And width
Figure 59516DEST_PATH_IMAGE053
If the set convergence condition is not met, executing the next iterative optimization; if the set convergence condition is satisfied, the first step
Figure 87515DEST_PATH_IMAGE054
Length after sub-iteration optimization
Figure 269098DEST_PATH_IMAGE055
And width
Figure 724350DEST_PATH_IMAGE053
Designing optimized structural parameters for the heat reflecting screen; wherein the content of the first and second substances,
Figure 437222DEST_PATH_IMAGE056
is a positive integer;
Figure 3333DEST_PATH_IMAGE057
。
in this embodiment, in step 305
Figure 39422DEST_PATH_IMAGE058
And
Figure 665575DEST_PATH_IMAGE059
the specific process of acquisition is as follows:
3051, according to a formula
Figure 787115DEST_PATH_IMAGE060
To obtain the top surface of the rectangular test piece (3) reflected by the heat reflection screen (1)
Figure 219233DEST_PATH_IMAGE061
Heat flow at a point
Figure 375408DEST_PATH_IMAGE062
Wherein the content of the active ingredients in the composition,
Figure 172463DEST_PATH_IMAGE063
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 781299DEST_PATH_IMAGE061
Reflects heat flow specularly, and
Figure 689212DEST_PATH_IMAGE064
；
Figure 11478DEST_PATH_IMAGE065
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 979434DEST_PATH_IMAGE066
Diffusely reflects heat flow thereto, and
Figure 75566DEST_PATH_IMAGE067
，
Figure 787170DEST_PATH_IMAGE068
indicates that any point on the bottom surface of the heat reflection screen (1) is on
Figure 917937DEST_PATH_IMAGE069
The coordinates of the object under the coordinate system,
Figure 119111DEST_PATH_IMAGE070
which represents the double differential of the light beam,
Figure 436960DEST_PATH_IMAGE071
representing the specular reflection coefficient of the heat reflecting screen (1),
Figure 952255DEST_PATH_IMAGE072
represents the diffuse reflection coefficient of the heat reflection screen (1);
3052, according to the formula
Figure 937528DEST_PATH_IMAGE073
Obtaining the area of a rectangular opening part (1-1) in the heat reflecting screen (1) to be reflected to the top surface of the rectangular test piece (3)
Figure 247287DEST_PATH_IMAGE074
Heat flow at a point
Figure 52432DEST_PATH_IMAGE075
Wherein, the water-soluble polymer is a polymer,
Figure 918888DEST_PATH_IMAGE076
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 758668DEST_PATH_IMAGE074
Reflects heat flow specularly, and
Figure 239328DEST_PATH_IMAGE077
;
Figure 797348DEST_PATH_IMAGE078
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 388866DEST_PATH_IMAGE074
Diffusely reflects heat flow thereto, and
Figure 411049DEST_PATH_IMAGE079
;
Figure 62610DEST_PATH_IMAGE080
is shown as
Figure 842347DEST_PATH_IMAGE081
The axial length direction of the radiation heating element is at any point
Figure 237557DEST_PATH_IMAGE082
An abscissa in the coordinate system and located in the region of the rectangular opening (1-1);
Figure 51929DEST_PATH_IMAGE083
has a value range of
Figure 185976DEST_PATH_IMAGE084
，
Figure 453009DEST_PATH_IMAGE085
The length of a rectangular opening (1-1) in a heat reflection screen (1) is shown.
In this embodiment, heat is supplied in step 401The length of the rectangular opening (1-1) in the reflecting screen
Figure 651909DEST_PATH_IMAGE150
Giving an initial value of
Figure 320788DEST_PATH_IMAGE087
Giving the width of the rectangular opening (1-1) in the heat reflection screen
Figure 314152DEST_PATH_IMAGE088
Giving an initial value of
Figure 68481DEST_PATH_IMAGE151
；
The convergence condition set in step 403 specifically includes the following steps:
step 4031, get
Figure 133389DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 656774DEST_PATH_IMAGE091
And width
Figure 821040DEST_PATH_IMAGE092
Substitute step 306 to obtain the second
Figure 62665DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 603368DEST_PATH_IMAGE091
And width
Figure 794309DEST_PATH_IMAGE092
Corresponding test piece top surface
Figure 395054DEST_PATH_IMAGE093
Total heat flow of radiation at a point
Figure 858397DEST_PATH_IMAGE094
；
4032, repeating 4031 for multiple times to obtain the total radiant heat flow of all points on the top surface of the test piece, and acquiring the total radiant heat flow of all points on the top surface of the test piece
Figure 202790DEST_PATH_IMAGE095
And
Figure 435189DEST_PATH_IMAGE096
(ii) a Wherein the content of the first and second substances,
Figure 269153DEST_PATH_IMAGE097
is shown as
Figure 219791DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 102296DEST_PATH_IMAGE091
And width
Figure 454780DEST_PATH_IMAGE092
The maximum value of the total heat flow of the radiation at all points of the top surface of the corresponding test piece,
Figure 397328DEST_PATH_IMAGE096
is shown as
Figure 835263DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 833044DEST_PATH_IMAGE098
And width
Figure 40034DEST_PATH_IMAGE099
The minimum value of the total radiant heat flow at all points of the top surface of the corresponding test piece;
step 4033, the convergence conditions are set as follows:
Figure 153484DEST_PATH_IMAGE100
。
in this embodiment, the parameters of the multi-island genetic algorithm in step 402 are set as follows: the number and size of each island were set to 10, and the crossover rate, the variation rate, and the mobility were 1.00, 0.01, and 0.01, respectively.
In this embodiment, it should be noted that,
Figure 78714DEST_PATH_IMAGE152
the heat reflection screen (1) is integrally reflected to the top surface of the rectangular test piece (3) when the rectangular opening part (1-1) is not arranged
Figure 303022DEST_PATH_IMAGE153
Heat flow at the point.
In this embodiment, it should be noted that
Figure 692415DEST_PATH_IMAGE154
Is assigned a value of
Figure 711187DEST_PATH_IMAGE155
Substituting into dimensionless radiation function
Figure 123714DEST_PATH_IMAGE156
To obtain a first radiation function
Figure 151713DEST_PATH_IMAGE157
；
Will be provided with
Figure 333295DEST_PATH_IMAGE158
Is assigned a value of
Figure 601597DEST_PATH_IMAGE159
，
Figure 235840DEST_PATH_IMAGE160
Is assigned a value of
Figure 801951DEST_PATH_IMAGE161
，
Figure 103619DEST_PATH_IMAGE162
Is assigned a value of
Figure 729773DEST_PATH_IMAGE163
Substituting into dimensionless radiation function
Figure 913629DEST_PATH_IMAGE156
To obtain a second radiation function
Figure 283431DEST_PATH_IMAGE164
；
Will be provided with
Figure 439606DEST_PATH_IMAGE165
Is assigned a value of
Figure 236660DEST_PATH_IMAGE166
，
Figure 845496DEST_PATH_IMAGE154
Is assigned a value of
Figure 753409DEST_PATH_IMAGE155
Substituting into dimensionless radiation function
Figure 75675DEST_PATH_IMAGE156
To obtain a third radiation function
Figure 43631DEST_PATH_IMAGE167
；
Will be provided with
Figure 139763DEST_PATH_IMAGE158
Is assigned a value of
Figure 851367DEST_PATH_IMAGE159
，
Figure 716555DEST_PATH_IMAGE160
Is assigned a value of
Figure 917729DEST_PATH_IMAGE161
，
Figure 501157DEST_PATH_IMAGE165
Is assigned a value of
Figure 16452DEST_PATH_IMAGE166
，
Figure 736147DEST_PATH_IMAGE162
Is assigned a value of
Figure 45905DEST_PATH_IMAGE163
Substituting into the dimensionless radiation function
Figure 929679DEST_PATH_IMAGE156
To obtain a fourth radiation function
Figure 983085DEST_PATH_IMAGE168
。
In this embodiment, the length × the width of the rectangular test piece (3) is 300mm × 200mm, the thickness of the rectangular test piece (3) is 30mm, and the material of the rectangular test piece (3) is the same as that of the airplane to be tested.
In this embodiment, the length × width of the heat reflecting screen (1) is 500mm × 310mm, the thickness of the heat reflecting screen (1) is 3mm to 6mm, and the heat reflecting screen (1) is made of aluminum or stainless steel.
In this embodiment, the radiation heating members (2) are graphite rods or quartz lamps, and the number of the radiation heating members (2)
Figure 822865DEST_PATH_IMAGE169
The length of the radiation heating element (2) and the width of the heat reflection screen (1) are equal to 25.
In this embodiment, the vertical distance
Figure 303525DEST_PATH_IMAGE170
The value range of (1) is 20 cm-30 cm, and the upper vertical distance
Figure 861546DEST_PATH_IMAGE171
The value range of (A) is 8-15 cm.
In the embodiment, during actual test, the heat insulation felt can be arranged around the hypersonic aircraft structure heat strength test device; a channel for introducing cooling water is arranged in the heat reflecting screen (1) to cool by water, so that the heat reflecting screen (1) is prevented from being damaged by high temperature.
In conclusion, the method provided by the invention has the advantages that the steps are reasonable in design, the design optimization of the structural parameters of the heat reflecting screen in the structural heat intensity test of the hypersonic flight vehicle is realized, the uniformity of the heat flow field borne by the surface of the structural test piece of the hypersonic flight vehicle is improved, the surface temperature field of the structural test piece of the hypersonic flight vehicle is uniform, and the accuracy of the subsequent structural heat intensity test of the hypersonic flight vehicle is improved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims (4)

1. A design method for a heat reflecting screen in a structural heat intensity test of a hypersonic aerocraft is characterized by comprising the following steps:
step one, building a thermal strength test of a hypersonic aircraft structure:
step 101, building a hypersonic aircraft structure heat strength test device in an airplane test room; the test device for the structural heat intensity of the hypersonic aerocraft comprises a radiation heating device and a hypersonic aerocraft structural test piece arranged below the radiation heating device, wherein the hypersonic aerocraft structural test piece is marked as a rectangular test piece (3), and the radiation heating device comprises a radiation heating element array and a heat reflecting screen (1);
102, setting a radiation heating element array to comprise a plurality of radiation heating elements (2) which are uniformly distributed in parallel, wherein the radiation heating elements (2) are cylindrical, and the plurality of radiation heating elements (2) are sequentially marked as the 1 st radiation heating element according to the length direction of a heat reflecting screen (1)
Figure 825117DEST_PATH_IMAGE001
A radiant heating element, the first
Figure 237644DEST_PATH_IMAGE002
A radiant heating element; wherein the content of the first and second substances,
Figure 63DEST_PATH_IMAGE001
and
Figure 181646DEST_PATH_IMAGE002
are all positive integers, and
Figure 636898DEST_PATH_IMAGE003
，
Figure 599038DEST_PATH_IMAGE002
represents the total number of the radiation heating members, the length direction of any one of the radiation heating members is arranged along the width direction of the heat reflecting screen (1);
103, setting the cross section of the heat reflection screen (1) to be a rectangular heat reflection screen, wherein a rectangular opening part (1-1) is arranged at the center of the heat reflection screen (1), the center of the rectangular opening part (1-1) is superposed with the center projection of the rectangular test piece (3), the length direction of the rectangular opening part (1-1) is arranged along the length directions of the rectangular test piece (3) and the heat reflection screen (1), the width direction of the rectangular opening part (1-1) is arranged along the width directions of the rectangular test piece (3) and the heat reflection screen (1), and the projection area of the heat reflection screen (1) is larger than the surface area of the rectangular test piece (3);
step 104, setting the vertical distance between the axes of the plurality of radiant heating elements (2) and the top surface of the rectangular test piece (3) to be
Figure 165148DEST_PATH_IMAGE004
The axes of the plurality of radiation heating members (2) are vertically spaced from the bottom surface of the heat reflecting screen (1)
Figure 201237DEST_PATH_IMAGE005
；
Step two, coordinate establishment:
step 201, using the top surface center of the rectangular test piece (3) as an origin
Figure 827391DEST_PATH_IMAGE006
Passing through the origin
Figure 214510DEST_PATH_IMAGE006
And the length direction of the top surface of the rectangular test piece (3) is
Figure 131781DEST_PATH_IMAGE007
Axis, passing through origin
Figure 287956DEST_PATH_IMAGE008
And the width direction of the top surface of the rectangular test piece (3) is
Figure 85011DEST_PATH_IMAGE009
Shaft, building
Figure 693847DEST_PATH_IMAGE010
A coordinate system;
step 202, taking the center of the top surface of the heat reflecting screen (1) as an origin
Figure 867339DEST_PATH_IMAGE011
Passing through the origin
Figure 940337DEST_PATH_IMAGE011
And along the length direction of the top surface of the heat reflection screen (1) is
Figure 908293DEST_PATH_IMAGE012
Axis, passing through origin
Figure 4425DEST_PATH_IMAGE011
And along the top of the heat reflecting screen (1)The width direction of the surface is
Figure 450450DEST_PATH_IMAGE013
Shaft, building
Figure 581217DEST_PATH_IMAGE014
A coordinate system;
step three, obtaining the total heat flow of the radiation of the rectangular test piece:
step 301, setting any point on the top surface of the rectangular test piece (3) to be at
Figure 31659DEST_PATH_IMAGE015
Seat marking in coordinate system
Figure 615087DEST_PATH_IMAGE016
(ii) a Wherein, the first and the second end of the pipe are connected with each other,
Figure 864803DEST_PATH_IMAGE017
to represent
Figure 850076DEST_PATH_IMAGE018
The axis abscissa;
Figure 159835DEST_PATH_IMAGE019
to represent
Figure 230559DEST_PATH_IMAGE020
An axis ordinate;
step 302, set up
Figure 346283DEST_PATH_IMAGE021
The axial length direction of the radiation heating element is at any point
Figure 186063DEST_PATH_IMAGE022
The abscissa in the coordinate system is
Figure 666723DEST_PATH_IMAGE023
(ii) a Wherein the content of the first and second substances,
Figure 959164DEST_PATH_IMAGE024
has a value range of
Figure 816261DEST_PATH_IMAGE025
，
Figure 323597DEST_PATH_IMAGE026
Represents the length of the heat reflection screen (1);
step 303, establishing a dimensionless radiation function
Figure 975158DEST_PATH_IMAGE027
As follows:
Figure 20475DEST_PATH_IMAGE028
(ii) a Wherein the content of the first and second substances,
Figure 415684DEST_PATH_IMAGE029
represents a dimensionless first parameter, an
Figure 964477DEST_PATH_IMAGE030
；
Figure 114836DEST_PATH_IMAGE031
Represents a dimensionless second parameter, an
Figure 381869DEST_PATH_IMAGE032
；
Figure 315190DEST_PATH_IMAGE033
Represents a dimensionless third parameter, an
Figure 984069DEST_PATH_IMAGE034
；
Figure 243012DEST_PATH_IMAGE035
Represents the width of the heat reflection screen (1);
step 304, according to the formula
Figure 43346DEST_PATH_IMAGE036
To obtain the first
Figure 45937DEST_PATH_IMAGE037
The radiation heating element directly radiates to the top surface of the rectangular test piece (3)
Figure 569323DEST_PATH_IMAGE038
Heat flow at a point
Figure 733588DEST_PATH_IMAGE039
(ii) a Wherein the content of the first and second substances,
Figure 975213DEST_PATH_IMAGE040
represents the radiation power of the radiation heating element (2);
305, according to the formula
Figure 578233DEST_PATH_IMAGE041
To obtain the first
Figure 956124DEST_PATH_IMAGE037
A radiation heating member directly radiates to the surface of the test piece
Figure 556870DEST_PATH_IMAGE038
The radiation reflected by the heat reflecting screen is reflected on the surface of the test piece
Figure 20212DEST_PATH_IMAGE038
Sum of heat flows at points
Figure 364606DEST_PATH_IMAGE042
(ii) a Wherein the content of the first and second substances,
Figure 675633DEST_PATH_IMAGE043
showing the reflection of the heat reflection screen (1) to the top surface of the rectangular test piece (3)
Figure 181701DEST_PATH_IMAGE038
The heat flow at the point of the heat transfer,
Figure 397918DEST_PATH_IMAGE044
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 280424DEST_PATH_IMAGE038
Heat flow at the point;
step 306, according to the formula
Figure 632908DEST_PATH_IMAGE045
To obtain the top surface of the test piece
Figure 309877DEST_PATH_IMAGE038
Total heat flow of radiation at a point
Figure 810128DEST_PATH_IMAGE046
；
Step four, optimizing the parameter design of the heat reflecting screen:
step 401, giving the length of the rectangular opening (1-1) in the heat reflection screen
Figure 496324DEST_PATH_IMAGE047
An initial value is given to the width of the rectangular opening (1-1) in the heat reflection screen
Figure 703315DEST_PATH_IMAGE048
Assigning an initial value;
step 402, adopting a multi-island genetic algorithm to determine the length of the rectangular opening (1-1)
Figure 816764DEST_PATH_IMAGE047
And the width of the rectangular opening (1-1)
Figure 741995DEST_PATH_IMAGE049
Performing iterative optimization to obtain
Figure 277887DEST_PATH_IMAGE051
Length after sub-iteration optimization
Figure 604963DEST_PATH_IMAGE052
And width
Figure 889314DEST_PATH_IMAGE053
；
Step 403, determine the
Figure 36262DEST_PATH_IMAGE054
Length after sub-iteration optimization
Figure 64261DEST_PATH_IMAGE052
And width
Figure 308160DEST_PATH_IMAGE053
Whether the set convergence condition is met or not is judged, if the set convergence condition is not met, the next iteration optimization is executed; if the set convergence condition is satisfied, the first step
Figure 763412DEST_PATH_IMAGE054
Length after sub-iteration optimization
Figure 663235DEST_PATH_IMAGE055
And width
Figure 229346DEST_PATH_IMAGE053
Designing optimized structural parameters for the heat reflecting screen; wherein the content of the first and second substances,
Figure 265435DEST_PATH_IMAGE056
is a positive integer;
Figure 891588DEST_PATH_IMAGE057
。
2. the design method of the heat reflecting screen in the structural heat intensity test of the hypersonic aircraft according to claim 1, characterized in that: in step 305
Figure 826177DEST_PATH_IMAGE058
And
Figure 195979DEST_PATH_IMAGE059
the specific process of obtaining is as follows:
3051, according to a formula
Figure 352154DEST_PATH_IMAGE060
To obtain the top surface of the rectangular test piece (3) reflected by the heat reflection screen (1)
Figure 149208DEST_PATH_IMAGE061
Heat flow at a point
Figure 758044DEST_PATH_IMAGE062
Wherein, the water-soluble polymer is a polymer,
Figure 728274DEST_PATH_IMAGE063
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 738956DEST_PATH_IMAGE061
Specularly reflects heat flow, and
Figure 706912DEST_PATH_IMAGE064
；
Figure 803044DEST_PATH_IMAGE065
shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)
Figure 514648DEST_PATH_IMAGE066
Diffusely reflects heat flow thereto, and
Figure 956999DEST_PATH_IMAGE067
，
Figure 95857DEST_PATH_IMAGE068
indicates that any point on the bottom surface of the heat reflection screen (1) is on
Figure 413705DEST_PATH_IMAGE069
The coordinates of the object under the coordinate system,
Figure 929000DEST_PATH_IMAGE070
which represents the double differential of the light beam,
Figure 914274DEST_PATH_IMAGE071
representing the specular reflection coefficient of the heat reflecting screen (1),
Figure 286349DEST_PATH_IMAGE072
represents the diffuse reflection coefficient of the heat reflection screen (1);
3052, according to the formula
Figure 91494DEST_PATH_IMAGE073
Obtaining the area of a rectangular opening part (1-1) in the heat reflecting screen (1) to be reflected to the top surface of the rectangular test piece (3)
Figure 144901DEST_PATH_IMAGE074
Heat flow at a point
Figure 984681DEST_PATH_IMAGE075
Wherein, the water-soluble polymer is a polymer,
Figure 465341DEST_PATH_IMAGE076
the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 23361DEST_PATH_IMAGE074
Reflects heat flow specularly, and
Figure 427929DEST_PATH_IMAGE077
;
Figure 387795DEST_PATH_IMAGE078
showing that the area of a rectangular opening part (1-1) in the heat reflecting screen (1) is reflected to the top surface of a rectangular test piece (3)
Figure 39356DEST_PATH_IMAGE074
Diffusely reflects heat flow thereto, and
Figure 819093DEST_PATH_IMAGE079
;
Figure 214302DEST_PATH_IMAGE080
is shown as
Figure 90991DEST_PATH_IMAGE081
The axial length direction of each radiation heating element is at any point
Figure 913454DEST_PATH_IMAGE082
An abscissa in the coordinate system and located in the region of the rectangular opening (1-1);
Figure 180487DEST_PATH_IMAGE083
has a value range of
Figure 379387DEST_PATH_IMAGE084
，
Figure 48266DEST_PATH_IMAGE085
The length of a rectangular opening (1-1) in a heat reflection screen (1) is shown.
3. According to claimThe design method of the heat reflecting screen in the structural heat intensity test of the hypersonic aircraft, which is characterized by comprising the following steps: step 401 gives the length of the rectangular opening (1-1) in the heat reflection screen
Figure 353214DEST_PATH_IMAGE086
Giving an initial value of
Figure 107544DEST_PATH_IMAGE087
The width of the rectangular opening (1-1) in the heat reflection screen is given
Figure 110135DEST_PATH_IMAGE088
Giving an initial value of
Figure 633520DEST_PATH_IMAGE089
；
The convergence condition set in step 403 specifically includes the following steps:
step 4031, get
Figure 797785DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 39411DEST_PATH_IMAGE091
And width
Figure 642430DEST_PATH_IMAGE092
Substitute step 306 to obtain the second
Figure 20322DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 621068DEST_PATH_IMAGE091
And width
Figure 84410DEST_PATH_IMAGE092
Corresponding test piece top surface
Figure 428804DEST_PATH_IMAGE093
Total heat flow of radiation at a point
Figure 474251DEST_PATH_IMAGE094
；
4032, repeating 4031 for multiple times to obtain total radiant heat flow at all points of the top surface of the test piece, and acquiring total radiant heat flow at all points of the top surface of the test piece
Figure 245898DEST_PATH_IMAGE095
And
Figure 196537DEST_PATH_IMAGE096
(ii) a Wherein the content of the first and second substances,
Figure 79042DEST_PATH_IMAGE097
denotes the first
Figure 431526DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 436391DEST_PATH_IMAGE091
And width
Figure 874326DEST_PATH_IMAGE092
The maximum value of the total heat flow of the radiation at all points of the top surface of the corresponding test piece,
Figure 560522DEST_PATH_IMAGE096
is shown as
Figure 767512DEST_PATH_IMAGE090
Length after sub-iteration optimization
Figure 880962DEST_PATH_IMAGE091
And width
Figure 806192DEST_PATH_IMAGE092
The minimum value of the total radiant heat flow at all points of the top surface of the corresponding test piece;
step 4033, the convergence conditions are set as follows:
Figure 342085DEST_PATH_IMAGE098
。
4. the design method of the heat reflecting screen in the structural heat intensity test of the hypersonic aircraft according to claim 1, characterized in that: the parameters of the multi-island genetic algorithm in step 402 are set as: the number and size of each island were set to 10, and the crossover rate, the variation rate, and the mobility were 1.00, 0.01, and 0.01, respectively.
CN202210644177.XA 2022-06-09 2022-06-09 Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft Active CN114722543B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210644177.XA CN114722543B (en) 2022-06-09 2022-06-09 Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210644177.XA CN114722543B (en) 2022-06-09 2022-06-09 Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft

Publications (2)

Publication Number Publication Date
CN114722543A true CN114722543A (en) 2022-07-08
CN114722543B CN114722543B (en) 2022-08-12

Family

ID=82232348

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210644177.XA Active CN114722543B (en) 2022-06-09 2022-06-09 Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft

Country Status (1)

Country Link
CN (1) CN114722543B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114852369A (en) * 2022-07-11 2022-08-05 中国飞机强度研究所 Heating adjustment control method for high-temperature heat strength test of aircraft nose cone structure

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101907422A (en) * 2010-06-02 2010-12-08 北京航空航天大学 Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile
CN102183312A (en) * 2011-03-16 2011-09-14 北京航空航天大学 Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft
CN202002747U (en) * 2011-03-16 2011-10-05 北京航空航天大学 High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts
CN102262099A (en) * 2011-04-15 2011-11-30 北京航空航天大学 1400-DEG C high-temperature thermal-mechanical coupling test device for aerofoil structure of hypersonic vehicle
CN102539099A (en) * 2012-02-02 2012-07-04 北京航空航天大学 Measuring device for 1400 DEG C high-temperature modal test of wing helm structure of hypersonic aircraft
CN104198332A (en) * 2014-05-22 2014-12-10 西北工业大学 Device and method for measuring viscosity of supercritical aviation kerosene
CN104267062A (en) * 2014-10-22 2015-01-07 北京航空航天大学 Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test
CN107843405A (en) * 2016-09-21 2018-03-27 北京空天技术研究所 The acquisition methods of testpieces and engine gas to aircraft bottom radiant heat flux
US20180266395A1 (en) * 2016-01-20 2018-09-20 Soliton Holdings Corporation, Delaware Corporation Generalized Jet-Effect and Shaped Tunnel
CN108918582A (en) * 2018-07-05 2018-11-30 北京强度环境研究所 A kind of hot external pressure test system and method for aircraft cargo tank structure
CN109883660A (en) * 2017-12-01 2019-06-14 中国飞机强度研究所 A kind of thermal modeling test control method
CN112193401A (en) * 2020-04-07 2021-01-08 北京空天技术研究所 Thermal protection method for front edge of hypersonic aircraft
CN113155885A (en) * 2021-03-30 2021-07-23 中国飞机强度研究所 Heat loss calibration method and calibration device for quartz lamp radiation heating test
CN114252232A (en) * 2021-12-28 2022-03-29 中国航天空气动力技术研究院 Optimal arrangement method for pulse pressure test sensors of hypersonic aircraft

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101907422A (en) * 2010-06-02 2010-12-08 北京航空航天大学 Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile
CN102183312A (en) * 2011-03-16 2011-09-14 北京航空航天大学 Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft
CN202002747U (en) * 2011-03-16 2011-10-05 北京航空航天大学 High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts
CN102262099A (en) * 2011-04-15 2011-11-30 北京航空航天大学 1400-DEG C high-temperature thermal-mechanical coupling test device for aerofoil structure of hypersonic vehicle
CN102539099A (en) * 2012-02-02 2012-07-04 北京航空航天大学 Measuring device for 1400 DEG C high-temperature modal test of wing helm structure of hypersonic aircraft
CN104198332A (en) * 2014-05-22 2014-12-10 西北工业大学 Device and method for measuring viscosity of supercritical aviation kerosene
CN104267062A (en) * 2014-10-22 2015-01-07 北京航空航天大学 Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test
US20180266395A1 (en) * 2016-01-20 2018-09-20 Soliton Holdings Corporation, Delaware Corporation Generalized Jet-Effect and Shaped Tunnel
CN107843405A (en) * 2016-09-21 2018-03-27 北京空天技术研究所 The acquisition methods of testpieces and engine gas to aircraft bottom radiant heat flux
CN109883660A (en) * 2017-12-01 2019-06-14 中国飞机强度研究所 A kind of thermal modeling test control method
CN108918582A (en) * 2018-07-05 2018-11-30 北京强度环境研究所 A kind of hot external pressure test system and method for aircraft cargo tank structure
CN112193401A (en) * 2020-04-07 2021-01-08 北京空天技术研究所 Thermal protection method for front edge of hypersonic aircraft
CN113155885A (en) * 2021-03-30 2021-07-23 中国飞机强度研究所 Heat loss calibration method and calibration device for quartz lamp radiation heating test
CN114252232A (en) * 2021-12-28 2022-03-29 中国航天空气动力技术研究院 Optimal arrangement method for pulse pressure test sensors of hypersonic aircraft

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114852369A (en) * 2022-07-11 2022-08-05 中国飞机强度研究所 Heating adjustment control method for high-temperature heat strength test of aircraft nose cone structure
CN114852369B (en) * 2022-07-11 2022-09-06 中国飞机强度研究所 Heating adjustment control method for high-temperature thermal strength test of aircraft nose cone structure

Also Published As

Publication number Publication date
CN114722543B (en) 2022-08-12

Similar Documents

Publication Publication Date Title
CN114722543B (en) Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft
CN108120613B (en) Carrier rocket upper-stage transient thermal balance test device and method
US10260953B2 (en) Applique and method for thermographic inspection
CN113155885A (en) Heat loss calibration method and calibration device for quartz lamp radiation heating test
CN110570478B (en) Thermal stability calibration method for reflector of space optical remote sensing camera
TW201243974A (en) Methods and apparatus for optimization of inspection speed by generation of stage speed profile and selection of care areas for automated wafer inspection
CN109583147A (en) A kind of centrifugal impeller Top spindle gradient-norm of prewhirling intends part design method
CN109738141A (en) A kind of device and method measuring high aspect ratio aerofoil Static stiffness
CN107092724A (en) One kind considers probabilistic thermal protection system model modification method
CN107992709B (en) Thermal structure model correction method based on intermediate function
McVetta et al. Aerodynamic investigation of incidence angle effects in a large scale transonic turbine cascade
CN107451377A (en) A kind of crystallite dimension modification method of Aviation turbine engine disk structural life-time analysis
CN113884538A (en) Infrared thermal image detection method for micro defects in large wind turbine blade
Yao et al. Influence of flat endwall simplification in gas turbines on cooling performance
CN108303378B (en) Device and method for measuring and testing high-temperature emissivity of heat-proof tile
CN113884536A (en) Invisible coating layered damage detection method based on infrared thermal wave detection technology
CN115203840A (en) Turbine disk reliability verification method based on Bayesian sequential test
CN111177884A (en) Irradiation-high temperature-strong wind coupling subsection experimental method based on temperature field similarity
CN113901690A (en) Satellite-borne reflector antenna on-orbit thermal deformation performance evaluation method
CN112881208A (en) Equivalent initial defect size determination and evaluation method
CN114662369B (en) Method for evaluating large-gradient extremely-high-temperature thermal strength of complex curved surface structure of aerospace plane
CN114647959B (en) Method for constructing test piece heat flow density distribution calculation model in airplane test and application
Samiudin et al. Development of solar simulator for indoor testing of solar collector
Kitamura et al. Variable nozzles for aerodynamic testing of scramjet engines
Bugaj et al. Can PVT bend?: The elaboration of flexible hybrid photovoltaic thermal solar collector structure and testing methodology

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant