CN114528645A - Design method of hypersonic velocity aerodynamic thermal standard model for simulating three-dimensional complex flow - Google Patents

Design method of hypersonic velocity aerodynamic thermal standard model for simulating three-dimensional complex flow Download PDF

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CN114528645A
CN114528645A CN202210432717.8A CN202210432717A CN114528645A CN 114528645 A CN114528645 A CN 114528645A CN 202210432717 A CN202210432717 A CN 202210432717A CN 114528645 A CN114528645 A CN 114528645A
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blunt
rudder
configuration
basic
wedge
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CN114528645B (en
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胡守超
李贤�
庄宇
吕明磊
陈苏宇
田润雨
张扣立
黄成扬
屈涛
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Ultra High Speed Aerodynamics Institute China Aerodynamics Research and Development Center
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Ultra High Speed Aerodynamics Institute China Aerodynamics Research and Development Center
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F16/00—Information retrieval; Database structures therefor; File system structures therefor
    • G06F16/20—Information retrieval; Database structures therefor; File system structures therefor of structured data, e.g. relational data
    • G06F16/21—Design, administration or maintenance of databases
    • G06F16/211—Schema design and management
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • 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
    • 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
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract

The invention belongs to the field of hypersonic aerodynamic, and discloses a design method of a hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow. The design method of the aerodynamic thermal standard model comprises the following steps: establishing a basic model according to the characteristics of a plane-symmetric high-lift high-supersonic pneumatic profile; on the basis of basic model, build modification
Figure 100004_DEST_PATH_IMAGE002
(ii) a On the basis of basic model, build modification
Figure 100004_DEST_PATH_IMAGE004
(ii) a Design and processing basic model and modification
Figure 783093DEST_PATH_IMAGE002
Modification of the same
Figure 700233DEST_PATH_IMAGE004
The test model of (1); carrying out basic model and modification
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Modification of the same
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The hypersonic wind tunnel aerodynamic heat test; basic type and modified type of release
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Modification of the same
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The pneumatic calibration model database. Basic model, modification
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And modifications
Figure 571423DEST_PATH_IMAGE004
The method has the common characteristic of the current hypersonic aircraft, and a reliable pneumatic calibration model database can be established through numerical calculation and wind tunnel tests. The design method of the aerodynamic heat standard model has the characteristics of simplicity and practicability, and is suitable for designing the hypersonic aerodynamic heat standard model for wind tunnel tests, numerical simulation and flight tests.

Description

Design method of hypersonic velocity aerodynamic thermal standard model for simulating three-dimensional complex flow
Technical Field
The invention belongs to the field of hypersonic aerodynamic, and particularly relates to a design method of a hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow.
Background
Hypersonic flight is the leading edge and focus of current aerospace research, and the violent motion of air and aircraft surface under hypersonic flight produces heat energy, forms "thermal barrier". The accuracy of the pneumatic thermal environment is directly related to the thermal protection design, the structural weight and the overall performance index of the aircraft, and is one of key technologies for restricting the development of the hypersonic aircraft.
In recent years, the hypersonic aerocraft is developed from a traditional axisymmetric simple appearance to a plane-symmetric high-lift complex configuration, and the surface flow of the aerocraft is more complex. Meanwhile, due to the presence of additional devices such as an air inlet channel and a control rudder, the prediction of the aerodynamic thermal environment with local complex interference flow faces a great challenge. At present, problems of low test precision (10% -15%), difficulty in effective verification of CFD numerical simulation results, difference between a wind tunnel simulation environment and a real flight environment and the like exist in pneumatic thermal environment prediction, and urgent solutions are needed.
The aerodynamic thermal standard model is a basic model providing "standard data" of an aerodynamic thermal environment. The standard model data can be used for evaluating the simulation capability/test technology of the test equipment, verifying the CFD algorithm/program, developing the heaven-earth correlation analysis and the like, and is basic data for supporting the hypersonic pneumatic problem research and improving the prediction accuracy of the pneumatic thermal environment. The rapid development of the hypersonic aircraft has urgent need for the construction of a hypersonic aerodynamic standard model, and particularly, an aerodynamic thermal standard model which is concerned with the problem of thermal barrier still has obvious defects at present. The existing pneumatic thermal standard model mainly has two types: background standard models with application development as background, and simple standard models such as ball head/double cone with test equipment/test technology verification as background. The former often has the background characteristics too strong to play the basic functions of the standard model; the latter has the single flow phenomenon, and is difficult to completely reflect the typical characteristics of hypersonic flow. Under the background, a hypersonic aerodynamic thermal standard model which can simulate typical hypersonic flow characteristics and is widely applicable to wind tunnel tests, numerical simulation and flight tests is urgently required to be developed.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the development characteristics of a hypersonic aircraft and the high-precision prediction requirement of a pneumatic thermal environment, a hypersonic pneumatic thermal standard model design method for simulating three-dimensional complex flow is provided.
The invention discloses a design method of a hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow, which comprises the following steps of:
s10, establishing a basic model according to the characteristics of a plane-symmetric high-lift high-supersonic pneumatic appearance;
s20, establishing a modification on the basis of the basic model
Figure 100002_DEST_PATH_IMAGE002
；
S30, establishing a modification on the basis of the basic model
Figure 100002_DEST_PATH_IMAGE004
；
S40, designing and processing basic model and modifying
Figure 445675DEST_PATH_IMAGE002
Modification of the same
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The test model of (1);
s50, carrying out basic model and modification
Figure 752340DEST_PATH_IMAGE002
Modification of the same
Figure 616390DEST_PATH_IMAGE004
The hypersonic wind tunnel aerodynamic heat test;
s60, issuing basic model and modification
Figure 601402DEST_PATH_IMAGE002
Modification of the same
Figure 955023DEST_PATH_IMAGE004
The pneumatic calibration model database.
Further, the step S10 includes the following steps:
s11, simplifying the appearance of the hypersonic aircraft into a configuration of a blunt wedge and a conical side surface according to the appearance characteristics of the conventional hypersonic aircraft;
s12, determining parameters of a 'blunt wedge + conical side' configuration;
the flight direction of the hypersonic aircraft is taken as the front, and the configuration of the blunt wedge and the side surface of the cone is composed of a wedge body positioned in the middle and symmetrical semi-cones positioned at the two sides of the wedge body; the vertical symmetrical surface of the 'blunt wedge + conical side' configuration is an isosceles triangle with a reversed vertex angle and a vertical bottom edge, and the vertex angle of the isosceles triangle is
Figure 100002_DEST_PATH_IMAGE006
(ii) a The horizontal symmetrical plane of the 'blunt wedge + conical side' configuration is an isosceles trapezoid with two inner angles at the upper bottom edge being rounded, and the included angle between the two sides of the isosceles trapezoid is
Figure 159739DEST_PATH_IMAGE006
The width of the lower bottom edge is
Figure 100002_DEST_PATH_IMAGE008
(ii) a The wedge body with the structure of 'blunt wedge + conical side surface' is symmetrical up and down, the upper and lower surfaces are all rectangular, the front end is rounded, and the length of the wedge body is
Figure 100002_DEST_PATH_IMAGE010
A width of
Figure 100002_DEST_PATH_IMAGE012
A height of
Figure 100002_DEST_PATH_IMAGE014
The included angle between the upper and lower surfaces of the wedge body is
Figure 141995DEST_PATH_IMAGE006
The radius of the front end is
Figure 100002_DEST_PATH_IMAGE016
(ii) a The length of the semi-cone with the configuration of 'blunt wedge + conical side surface' is also
Figure 748557DEST_PATH_IMAGE010
The radius of the bottom surface of the semi-cone is
Figure 100002_DEST_PATH_IMAGE018
(ii) a The junction of the wedge body and the semi-cone body is adopted
Figure 100002_DEST_PATH_IMAGE020
Spherical surface transition;
the wedge face compression angle defining the "blunt wedge + tapered flank" configuration is
Figure 100002_DEST_PATH_IMAGE022
The width of the model is
Figure 351708DEST_PATH_IMAGE008
The height of the model is
Figure 371616DEST_PATH_IMAGE014
The width of the wedge surface is
Figure 279267DEST_PATH_IMAGE012
The radius of the leading edge is
Figure 68232DEST_PATH_IMAGE016
、The wedge/cone length is
Figure 29234DEST_PATH_IMAGE010
Each parameter has the following constraint relationship:
Figure 100002_DEST_PATH_IMAGE024
（1）
Figure 100002_DEST_PATH_IMAGE026
（2）
Figure 100002_DEST_PATH_IMAGE028
（3）
s13, establishing a shape database of a 'blunt wedge + conical side' configuration;
by changing in steps
Figure 100002_DEST_PATH_IMAGE030
The size of one variable is changed in a step mode, and a shape database of the configuration of the blunt wedge and the conical side surface, which meets the constraint relation of the step S12, is established;
s14, establishing a pneumatic thermal calculation database with a blunt wedge and conical side configuration;
modeling each blunt wedge and conical side configuration in the shape database of the blunt wedge and conical side configuration of the step S13, calculating aerodynamic thermal characteristics of each blunt wedge and conical side configuration including boundary layer flow state change and three-dimensional turbulence intensity change by adopting computational aerodynamics, and establishing an aerodynamic thermal calculation database of the blunt wedge and conical side configuration;
s15, determining a basic model;
in an aerodynamic heat calculation database of a 'blunt wedge + conical side' configuration, a 'blunt wedge + conical side' configuration which is closest to the aerodynamic characteristics of the existing hypersonic flight vehicle or a 'blunt wedge + conical side' configuration with required aerodynamic characteristics is searched and defined as a basic type;
further, the step S20 includes the following steps:
s21, on the basis of the basic model, adding a compression corner to form a 'basic model + compression corner' configuration;
the compression corner is a wedge body with the volume smaller than that of the basic wedge body, the compression corner is defined as a small wedge body, and the small wedge body is placed on the upper surface of the basic wedge body to obtain a 'basic shape + compression corner' configuration;
s22, determining parameters of a basic type and compression corner configuration;
the upper surface and the lower surface of the small wedge body are both rectangular, and the included angle between the upper surface and the lower surface of the small wedge body is
Figure 100002_DEST_PATH_IMAGE032
The widths of the rectangle on the upper surface and the rectangle on the lower surface of the small wedge body are both
Figure 100002_DEST_PATH_IMAGE034
，
Figure 100002_DEST_PATH_IMAGE036
The length of the rectangle on the lower surface of the small wedge is
Figure 100002_DEST_PATH_IMAGE038
The horizontal distance between the front edge of the small wedge and the front edge of the basic wedge is
Figure 100002_DEST_PATH_IMAGE040
The rear bottom surface of the small wedge body is flush with the rear bottom surface of the basic wedge body and is positioned on a vertical plane; defining a compression angle of the compression corner as
Figure 126985DEST_PATH_IMAGE032
Width of
Figure 74212DEST_PATH_IMAGE034
Length of
Figure 248841DEST_PATH_IMAGE038
；
S23, establishing a shape database with a 'basic type + compression corner' configuration;
by changing in steps
Figure 223488DEST_PATH_IMAGE040
Adjusting the installation position of the compression corner; re-staging
Figure 483568DEST_PATH_IMAGE032
Adjusting the compression angle to establish compliance
Figure 968908DEST_PATH_IMAGE036
A shape database of "base + compression corner" configurations of (a);
s24, establishing an aerodynamic heat calculation database with a basic type and compression corner configuration;
modeling each basic type + compression corner configuration in the shape database of the basic type + compression corner configuration in the step S23, calculating the aerodynamic heat characteristics including air inlet channel compression of each basic type + compression corner configuration by adopting computational aerodynamics, and establishing an aerodynamic heat calculation database of the basic type + compression corner configuration;
s25, determining modification
Figure 998043DEST_PATH_IMAGE002
；
Finding the configuration of basic type and compression corner which is closest to the aerodynamic characteristics of the air inlet of the existing hypersonic aircraft or the configuration of basic type and compression corner with the required aerodynamic characteristics of the air inlet in an aerodynamic heat calculation database of the configuration of basic type and compression corner, and defining the configuration as a modification
Figure 176215DEST_PATH_IMAGE002
；
Further, the step S30 includes the following steps:
s31, adding an obtuse rudder on the basis of the basic model to form a basic model and obtuse rudder configuration;
the blunt rudder is a trapezoidal rudder sheet, and a rudder shaft is positioned on a vertical symmetrical plane of the basic model and is vertical to the upper surface of the wedge body of the basic model; fixing the trapezoidal rudder sheet on the upper surface of the basic wedge through a rudder shaft to obtain a basic + blunt rudder configuration;
s32, determining parameters of a basic type and an obtuse rudder configuration;
the upper surface and the lower surface of the blunt rudder are both parallel to the upper surface of the basic type wedge body, and the gap height between the lower surface of the blunt rudder and the upper surface of the basic type wedge body is
Figure 100002_DEST_PATH_IMAGE042
(ii) a The sweep angle of the blunt rudder is
Figure 100002_DEST_PATH_IMAGE044
A thickness of
Figure 100002_DEST_PATH_IMAGE046
Has a length of
Figure 100002_DEST_PATH_IMAGE048
The front edge of the blunt rudder is rounded off
Figure 100002_DEST_PATH_IMAGE050
(ii) a The diameter of the rudder shaft of the blunt rudder is
Figure 100002_DEST_PATH_IMAGE052
The length of the central line of the rudder shaft from the tail end of the blunt rudder is
Figure 100002_DEST_PATH_IMAGE054
(ii) a The blunt rudder rotates around a rudder shaft, and after the blunt rudder rotates, the included angle between the vertical symmetrical plane of the blunt rudder and the flight direction is a rudder deflection angle
Figure 100002_DEST_PATH_IMAGE056
(ii) a The horizontal distance between the front edge of the blunt rudder and the sharp point of the basic wedge body is
Figure 100002_DEST_PATH_IMAGE058
；
S33, establishing a database of a basic type and blunt rudder configuration state;
first, a step change is made
Figure 175788DEST_PATH_IMAGE058
Adjusting the installation position of the blunt rudder; second stepChange of
Figure 464818DEST_PATH_IMAGE044
Adjusting the sweepback angle of the blunt rudder; step change again
Figure 348461DEST_PATH_IMAGE042
Adjusting the gap height of the blunt rudder to obtain a basic type and blunt rudder configuration; last step change
Figure 196069DEST_PATH_IMAGE056
Adjusting the rudder deflection angle of the blunt rudder, and establishing a database of a 'basic type + blunt rudder' configuration state;
s34, establishing an aerodynamic heat calculation database in a basic type and blunt rudder configuration state;
modeling each basic type and blunt rudder configuration state in the database of the basic type and blunt rudder configuration state of the step S33, calculating aerodynamic heat characteristics of each basic type and blunt rudder configuration state including wing/body interference, rudder/body interference and rudder gap flow by adopting computational aerodynamics, and establishing an aerodynamic heat calculation database of the basic type and blunt rudder configuration state;
s35, determining modification
Figure 165162DEST_PATH_IMAGE004
；
In an aerodynamic heat calculation database of the 'basic type + blunt rudder' configuration state, the 'basic type + blunt rudder' configuration closest to the interference aerodynamic characteristics of the rudder pieces of the existing hypersonic aircraft or the 'basic type + blunt rudder' configuration with the required interference aerodynamic characteristics of the rudder pieces is searched and defined as modification
Figure 726724DEST_PATH_IMAGE004
；
Further, the step S40 includes the following steps:
the method is characterized in that a hypersonic wind tunnel is inspected, and a special basic model and a special modification are designed and processed for the selected hypersonic wind tunnel
Figure 730452DEST_PATH_IMAGE002
Modification of the same
Figure 250427DEST_PATH_IMAGE004
The test model is provided with a heat flow sensor or a pressure sensor;
further, the step S50 includes the following steps:
in the selected hypersonic wind tunnel, according to the predetermined test outline, the basic model and the modification are carried out
Figure 706816DEST_PATH_IMAGE002
Modification of the same
Figure 337648DEST_PATH_IMAGE004
The hypersonic wind tunnel pneumatic heat test of the test model comprises the steps of respectively obtaining temperature data or pressure data through a heat flow sensor or a pressure sensor, and establishing a basic model and a modification
Figure 930304DEST_PATH_IMAGE002
Modification of the same
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The pneumatic standard model database;
further, the step S60 includes the following steps:
basic model and modification
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Modification of the same
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The pneumatic standard model database is released to the society as a basic model and a modification in the future
Figure 473314DEST_PATH_IMAGE002
Modification of the same
Figure 335091DEST_PATH_IMAGE004
Or reference data of a wind tunnel test.
The model designed by the hypersonic aerodynamic thermal standard model design method for simulating three-dimensional complex flow can embody typical characteristics of lift body layout, complex wing/body interference, wing/rudder interference and the like of the current hypersonic aircraft, and can realize typical flow simulation of large-attack-angle streaming, shock wave/shock wave interference, shock wave/boundary layer interference, rudder gap flow and the like through reasonable test design; meanwhile, the method has the advantages of simplicity, universality and the like, and is favorable for developing tests and obtaining high-precision test data.
The designed hypersonic pneumatic thermal standard model comprises a basic model and a modified model
Figure 907017DEST_PATH_IMAGE002
And modifications
Figure 4286DEST_PATH_IMAGE004
。
(1) The basic model has the following design principles:
a. the plane symmetry configuration has the layout characteristics of a lifting body;
the requirements of concise model appearance, practicability and high fault tolerance in the data acquisition process of the hypersonic pneumatic thermal standard model can be met.
b. The structure is simple, and the surface is smooth;
in the extremely short test time of the pulse wind tunnel, the flow field can be quickly established and the stable state is achieved, and the sensor is convenient to install and beneficial to the development of the wind tunnel test.
c. The parameters are adjustable;
basic type wedge surface compression angle
Figure 211014DEST_PATH_IMAGE022
Width of wedge surface
Figure 102747DEST_PATH_IMAGE012
Radius of leading edge
Figure 896391DEST_PATH_IMAGE016
、Tip wedge/cone lengthLEach parameter is adjustable, and the design can be flexibly carried out as required, so that the state simulation of boundary layer flow state change, three-dimensional turbulence intensity change and the like can be realized.
d. The expansibility is strong;
the plane symmetry configuration has a smooth wedge surface, so that the compression corner and the rudder can be conveniently installed, and the complicated interference flow simulation can be realized.
(2) Modifications of the type
Figure 797351DEST_PATH_IMAGE002
The design principle is as follows:
by adjusting the horizontal distance between the front edge of the small wedge and the front edge of the basic wedge
Figure 94471DEST_PATH_IMAGE040
Adjusting the installation position of the compression corner; by adjusting the compression angle
Figure 422684DEST_PATH_IMAGE032
And carrying out different compression angle influence analysis.
(3) Modifications of the type
Figure 172465DEST_PATH_IMAGE004
The method has the following design principles:
by adjusting the horizontal distance between the front edge of the blunt rudder and the sharp point of the basic wedge
Figure 877116DEST_PATH_IMAGE058
Adjusting the installation position of the blunt rudder; by adjusting the sweep angle
Figure 795787DEST_PATH_IMAGE044
Analyzing the influence of different sweepback angles; by adjusting the gap height
Figure 560481DEST_PATH_IMAGE042
Researching the height influence of different gaps; by adjusting the rudder deflection angle to
Figure 797558DEST_PATH_IMAGE056
Study rudderThe declination angle.
The design method of the hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow, the designed basic model and the designed modification
Figure 305900DEST_PATH_IMAGE002
And modifications
Figure 577612DEST_PATH_IMAGE004
The following flow characteristics can be simulated:
(1) simple standard model flow simulation such as a cylinder, a hemispherical head, a two-dimensional flat plate, a conical surface and the like;
(2) simulating three-dimensional turbulence under the layout and large attack angle of a lifting body;
(3) two-stage compression and shock wave/shock wave interference and shock wave/boundary layer interference flow simulation;
(4) and the dynamic simulation is disturbed due to the complex rudder gap and rudder/body interference.
According to the hypersonic aerodynamic thermal standard model design method for simulating three-dimensional complex flow, the designed basic model of 'blunt wedge + conical side surface' can simulate the basic characteristics of a lifting body aircraft, and the 'basic model + compression corner' modification
Figure 247628DEST_PATH_IMAGE002
Can simulate the modification of the "basic model + blunt rudder" of the air intake compression
Figure 237581DEST_PATH_IMAGE004
Typical complex flows such as wing/body disturbances, rudder gap flows, etc. can be simulated. Basic model, modification
Figure 752876DEST_PATH_IMAGE002
And modifications
Figure 643209DEST_PATH_IMAGE004
The method has the common characteristic of the current hypersonic aircraft, and a reliable pneumatic heat calculation database can be established through numerical calculation and wind tunnel tests.
The design method of the hypersonic pneumatic thermal standard model for simulating three-dimensional complex flow adopts a parametric design method, has the characteristics of simplicity and practicability, and is suitable for designing the hypersonic pneumatic thermal standard model for wind tunnel tests, numerical simulation and flight tests.
Drawings
FIG. 1 is a flow chart of a hypersonic aerodynamic thermal standard model design method for simulating three-dimensional complex flow according to the invention;
FIG. 2 is a basic model designed by the design method of the hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow;
FIG. 3a is a design parameter of a basic model (front view);
FIG. 3b is a design parameter of the basic model (top view);
FIG. 4 is a modification of the design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to the invention
Figure 484126DEST_PATH_IMAGE002
；
FIG. 5a is a modification
Figure 961375DEST_PATH_IMAGE002
Design parameters (front view);
FIG. 5b is a modification
Figure 545940DEST_PATH_IMAGE002
Design parameters (top view);
FIG. 6 is a modification of the design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to the invention
Figure 792245DEST_PATH_IMAGE004
；
FIG. 7a is a modification
Figure 804063DEST_PATH_IMAGE004
Design parameters (front view);
FIG. 7b is a modification
Figure 362083DEST_PATH_IMAGE004
Design parameters (top view);
FIG. 8 is a modification
Figure 625706DEST_PATH_IMAGE004
Surface and space pressure contour maps (0 ° angle of attack) flowing under Ma 12;
FIG. 9 is a modification
Figure 851151DEST_PATH_IMAGE004
Surface and space pressure contour plot (7 ° angle of attack) flowing down Ma 12.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
As shown in fig. 1, the design method of the hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow of the invention comprises the following steps:
s10, establishing a basic model according to the characteristics of a plane-symmetric high-lift high-supersonic pneumatic appearance;
s20, establishing a modification on the basis of the basic model
Figure 404842DEST_PATH_IMAGE002
；
S30, establishing a modification on the basis of the basic model
Figure 981317DEST_PATH_IMAGE004
；
S40, designing and processing basic model and modifying
Figure 783051DEST_PATH_IMAGE002
Modification of the same
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The test model of (1);
s50, carrying out basic model and modification
Figure 888727DEST_PATH_IMAGE002
Modification of the same
Figure 562285DEST_PATH_IMAGE004
The hypersonic wind tunnel aerodynamic heat test;
s60, issuing basic model and modification
Figure 292344DEST_PATH_IMAGE002
Modification of the same
Figure 600703DEST_PATH_IMAGE004
The pneumatic calibration model database.
Further, the step S10 includes the following steps:
s11, simplifying the appearance of the hypersonic aircraft into a configuration of 'blunt wedge + conical side' as shown in figure 2 according to the appearance characteristics of the existing hypersonic aircraft;
s12, determining parameters of a 'blunt wedge + conical side' configuration;
as shown in fig. 3a and 3b, the flight direction of the hypersonic flight vehicle is taken as the front, and the configuration of the "blunt wedge + conical side surface" is composed of a wedge body positioned in the middle and symmetrical semi-cones positioned at both sides of the wedge body; the vertical symmetrical surface of the 'blunt wedge + conical side' configuration is an isosceles triangle with a reversed vertex angle and a vertical bottom edge, and the vertex angle of the isosceles triangle is
Figure 390804DEST_PATH_IMAGE006
(ii) a The horizontal symmetrical plane of the 'blunt wedge + conical side' configuration is an isosceles trapezoid with two inner angles at the upper bottom edge being rounded, and the included angle between the two sides of the isosceles trapezoid is
Figure 551658DEST_PATH_IMAGE006
The width of the lower bottom edge is
Figure 819829DEST_PATH_IMAGE008
(ii) a The wedge body with the structure of 'blunt wedge + conical side surface' is symmetrical up and down, the upper and lower surfaces are all rectangular, the front end is rounded, and the length of the wedge body is
Figure 484159DEST_PATH_IMAGE010
With a width of
Figure 445162DEST_PATH_IMAGE012
A height of
Figure 827733DEST_PATH_IMAGE014
The included angle between the upper surface and the lower surface of the wedge body is
Figure 899594DEST_PATH_IMAGE006
The radius of the front end is
Figure 451055DEST_PATH_IMAGE016
(ii) a The length of the semi-cone with the configuration of 'blunt wedge + conical side surface' is also
Figure 317380DEST_PATH_IMAGE010
The radius of the bottom surface of the semi-cone is
Figure 452826DEST_PATH_IMAGE018
(ii) a The junction of wedge and semi-cone adopts
Figure 62799DEST_PATH_IMAGE020
Spherical surface transition;
the wedge face compression angle defining the "blunt wedge + tapered flank" configuration is
Figure 967301DEST_PATH_IMAGE022
The width of the model is
Figure 738948DEST_PATH_IMAGE008
The height of the model is
Figure 627269DEST_PATH_IMAGE014
The width of the wedge surface is
Figure 775354DEST_PATH_IMAGE012
The radius of the leading edge is
Figure 298477DEST_PATH_IMAGE016
、The wedge/cone length is
Figure 772184DEST_PATH_IMAGE010
Each parameter has the following constraint relationship:
Figure 616643DEST_PATH_IMAGE024
（1）
Figure 568418DEST_PATH_IMAGE026
（2）
Figure 447513DEST_PATH_IMAGE028
（3）
s13, establishing a shape database of a 'blunt wedge + conical side' configuration;
by changing in steps
Figure 826541DEST_PATH_IMAGE030
The size of one variable is changed in a step mode, and a shape database of the configuration of the blunt wedge and the conical side surface, which meets the constraint relation of the step S12, is established;
s14, establishing a pneumatic thermal calculation database with a blunt wedge and conical side configuration;
modeling each blunt wedge and conical side configuration in the shape database of the blunt wedge and conical side configuration of the step S13, calculating aerodynamic thermal characteristics of each blunt wedge and conical side configuration including boundary layer flow state change and three-dimensional turbulence intensity change by adopting computational aerodynamics, and establishing an aerodynamic thermal calculation database of the blunt wedge and conical side configuration;
s15, determining a basic model;
in an aerodynamic heat calculation database of a 'blunt wedge + conical side' configuration, a 'blunt wedge + conical side' configuration which is closest to the aerodynamic characteristics of the existing hypersonic flight vehicle or a 'blunt wedge + conical side' configuration with required aerodynamic characteristics is searched and defined as a basic type;
further, the step S20 includes the following steps:
s21, on the basis of the basic model, adding a compression corner to form a 'basic model + compression corner' configuration;
the compression corner is a wedge body with the volume smaller than that of the basic wedge body, and is defined as a small wedge body, and the small wedge body is placed on the upper surface of the basic wedge body to obtain the configuration of 'basic type + compression corner' shown in figure 4;
s22, determining parameters of a basic type and compression corner configuration;
as shown in fig. 5a and 5b, the upper surface and the lower surface of the small wedge are both rectangular, and the included angle between the upper surface and the lower surface of the small wedge is
Figure 158297DEST_PATH_IMAGE032
The widths of the rectangle on the upper surface and the rectangle on the lower surface of the small wedge body are both
Figure 913763DEST_PATH_IMAGE034
，
Figure 431986DEST_PATH_IMAGE036
The length of the rectangle on the lower surface of the small wedge is
Figure 654020DEST_PATH_IMAGE038
The horizontal distance between the front edge of the small wedge and the front edge of the basic wedge is
Figure 738651DEST_PATH_IMAGE040
The rear bottom surface of the small wedge body is flush with the rear bottom surface of the basic wedge body and is positioned on a vertical plane; defining a compression angle of the compression corner as
Figure 438753DEST_PATH_IMAGE032
Width of
Figure 417074DEST_PATH_IMAGE034
Length of
Figure 308544DEST_PATH_IMAGE038
；
S23, establishing a shape database with a 'basic type + compression corner' configuration;
by changing in steps
Figure 880471DEST_PATH_IMAGE040
Adjusting the installation position of the compression corner; re-staging
Figure 118685DEST_PATH_IMAGE032
Adjusting the compression angle to establish coincidence
Figure 685933DEST_PATH_IMAGE036
A shape database of "base + compression corner" configurations of (a);
s24, establishing an aerodynamic heat calculation database with a basic type and compression corner configuration;
modeling each basic type + compression corner configuration in the shape database of the basic type + compression corner configuration in the step S23, calculating the aerodynamic heat characteristics including air inlet channel compression of each basic type + compression corner configuration by adopting computational aerodynamics, and establishing an aerodynamic heat calculation database of the basic type + compression corner configuration;
s25, determining modification
Figure 249769DEST_PATH_IMAGE002
；
In an aerodynamic heat calculation database of the basic type + compression corner configuration, the basic type + compression corner configuration which is closest to the aerodynamic characteristics of the air inlet of the existing hypersonic aircraft or the basic type + compression corner configuration with the required aerodynamic characteristics of the air inlet is searched and defined as the modification
Figure 544878DEST_PATH_IMAGE002
；
Further, the step S30 includes the following steps:
s31, adding an obtuse rudder on the basis of the basic model to form a basic model and obtuse rudder configuration;
the blunt rudder is a trapezoidal rudder sheet, and a rudder shaft is positioned on a vertical symmetrical plane of the basic model and is vertical to the upper surface of the wedge body of the basic model; fixing the trapezoidal rudder sheet on the upper surface of the basic wedge through a rudder shaft to obtain a basic type + blunt rudder configuration shown in figure 6;
s32, determining parameters of a basic type and an obtuse rudder configuration;
as shown in fig. 7a and 7b, the upper surface and the lower surface of the blunt rudder are parallel to the upper surface of the basic type wedge body, and the gap between the lower surface of the blunt rudder and the upper surface of the basic type wedge body has the height of
Figure 180259DEST_PATH_IMAGE042
(ii) a The sweep angle of the blunt rudder is
Figure 742958DEST_PATH_IMAGE044
A thickness of
Figure 71171DEST_PATH_IMAGE046
Has a length of
Figure 86532DEST_PATH_IMAGE048
The front edge of the blunt rudder is rounded off
Figure 791183DEST_PATH_IMAGE050
(ii) a The diameter of the rudder shaft of the blunt rudder is
Figure 208389DEST_PATH_IMAGE052
The length of the central line of the rudder shaft from the tail end of the blunt rudder is
Figure 707503DEST_PATH_IMAGE054
(ii) a The blunt rudder rotates around a rudder shaft, and after the rotation, the included angle between the vertical symmetrical plane of the blunt rudder and the flight direction is the rudder deflection angle
Figure 708695DEST_PATH_IMAGE056
(ii) a The horizontal distance between the front edge of the blunt rudder and the sharp point of the basic wedge body is
Figure 685878DEST_PATH_IMAGE058
；
S33, establishing a database of a basic type and blunt rudder configuration state;
first, a step change is made
Figure 223170DEST_PATH_IMAGE058
Adjusting the installation position of the blunt rudder; second step change
Figure 893185DEST_PATH_IMAGE044
Adjusting the sweepback angle of the blunt rudder; step change again
Figure 883138DEST_PATH_IMAGE042
Adjusting the gap height of the blunt rudder to obtain a basic type and blunt rudder configuration; last step change
Figure 664012DEST_PATH_IMAGE056
Adjusting the rudder deflection angle of the blunt rudder, and establishing a database of the configuration state of 'basic type + blunt rudder';
s34, establishing an aerodynamic heat calculation database in a basic type and blunt rudder configuration state;
modeling each basic type and blunt rudder configuration state in the database of the basic type and blunt rudder configuration state of the step S33, calculating aerodynamic heat characteristics of each basic type and blunt rudder configuration state including wing/body interference, rudder/body interference and rudder gap flow by adopting computational aerodynamics, and establishing an aerodynamic heat calculation database of the basic type and blunt rudder configuration state;
s35, determining modification
Figure 55811DEST_PATH_IMAGE004
；
In an aerodynamic heat calculation database of a basic type and blunt rudder configuration state, a rudder of the existing hypersonic aircraft is searchedThe configuration of 'basic type + blunt rudder' with the closest aerodynamic characteristics of blade interference or the configuration of 'basic type + blunt rudder' with the required aerodynamic characteristics of blade interference is defined as a modification
Figure 896728DEST_PATH_IMAGE004
；
Further, the step S40 includes the following steps:
the method is characterized in that a hypersonic wind tunnel is inspected, and a special basic model and a special modification are designed and processed for the selected hypersonic wind tunnel
Figure 869582DEST_PATH_IMAGE002
Modification of the same
Figure 454147DEST_PATH_IMAGE004
The test model is provided with a heat flow sensor or a pressure sensor;
further, the step S50 includes the following steps:
in the selected hypersonic wind tunnel, according to the predetermined test outline, the basic model and the modification are carried out
Figure 700452DEST_PATH_IMAGE002
Modification of the same
Figure 712270DEST_PATH_IMAGE004
The hypersonic wind tunnel pneumatic heat test of the test model comprises the steps of respectively obtaining temperature data or pressure data through a heat flow sensor or a pressure sensor, and establishing a basic model and a modification
Figure 676815DEST_PATH_IMAGE002
Modification of the same
Figure 471596DEST_PATH_IMAGE004
The pneumatic standard model database;
further, the step S60 includes the following steps:
basic model and modification
Figure 336521DEST_PATH_IMAGE002
Modification of the same
Figure 660186DEST_PATH_IMAGE004
The pneumatic standard model database is released to the society as a basic model and a modification in the future
Figure 502240DEST_PATH_IMAGE002
Modification of the same
Figure 303974DEST_PATH_IMAGE004
Or reference data of a wind tunnel test.
Example 1
The hypersonic standard model example design is developed according to the design requirements, and comprises a basic model, a modification I design and a modification II design, wherein the basic dimensions are as follows:
a. basic type:
Figure DEST_PATH_IMAGE060
the compression angle of the wedge surface and the half cone angle of the cone surface are 7 degrees, and the length of the pointed wedge/cone is
Figure DEST_PATH_IMAGE062
The width of the model is
Figure DEST_PATH_IMAGE064
The width of the wedge surface is
Figure DEST_PATH_IMAGE066
The height of the model is
Figure DEST_PATH_IMAGE068
The radius of the leading edge is
Figure 901702DEST_PATH_IMAGE016
1mm, 5mm and 20mm respectively;
b. modification I: on the basis of the basic model, a compression corner is added to form a 'basic model + compression corner' configuration, and the compression angle is
Figure DEST_PATH_IMAGE070
Compressing corner width
Figure DEST_PATH_IMAGE072
Length of
Figure DEST_PATH_IMAGE074
The horizontal distance between the front edge of the small wedge at the compression corner and the front edge of the basic wedge is
Figure DEST_PATH_IMAGE076
；
c. Modification II: on the basis of the basic model, an obtuse rudder is added to form a basic model and obtuse rudder configuration; sweepback angle of blunt rudder
Figure DEST_PATH_IMAGE078
Length, length of
Figure DEST_PATH_IMAGE080
Thickness of the film
Figure DEST_PATH_IMAGE082
Blunt rudder with rounded front edge
Figure DEST_PATH_IMAGE084
Diameter of rudder shaft
Figure DEST_PATH_IMAGE086
The length of the central line of the rudder shaft from the tail end of the blunt rudder is
Figure DEST_PATH_IMAGE088
(ii) a The height of the gap between the lower surface of the blunt rudder and the upper surface of the basic wedge
Figure 707853DEST_PATH_IMAGE042
Respectively 2mm, 5mm and 8 mm; rudder deflection angle of
Figure 381411DEST_PATH_IMAGE056
Respectively 0 degree and 10 degrees.
Through numerical simulation, the modification at the attack angle of 0 degrees shown in FIG. 8 is obtained
Figure 845891DEST_PATH_IMAGE004
Surface and space pressure contour map with Ma12 coming down, modification at 7 deg. angle of attack as shown in FIG. 9
Figure 416899DEST_PATH_IMAGE004
Surface and space pressure contour map flowing down Ma 12.

Claims (7)

1. The design method of the hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow is characterized by comprising the following steps of:
s10, establishing a basic model according to the characteristics of a plane-symmetric high-lift high-supersonic pneumatic appearance;
s20, establishing a modification on the basis of the basic model
Figure DEST_PATH_IMAGE002
；
S30, establishing a modification on the basis of the basic model
Figure DEST_PATH_IMAGE004
；
S40, designing and processing basic model and modifying
Figure 720577DEST_PATH_IMAGE002
Modification of the same
Figure 903297DEST_PATH_IMAGE004
The test model of (1);
s50, carrying out basic model and modification
Figure 948613DEST_PATH_IMAGE002
Modification of the same
Figure 107937DEST_PATH_IMAGE004
The hypersonic wind tunnel aerodynamic heat test;
s60, issuing basic model and modification
Figure 187889DEST_PATH_IMAGE002
Modification of the same
Figure 275930DEST_PATH_IMAGE004
The pneumatic calibration model database.
2. The design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to claim 1, wherein said step S10 includes the following steps:
s11, simplifying the appearance of the hypersonic aircraft into a configuration of a blunt wedge and a conical side surface according to the appearance characteristics of the conventional hypersonic aircraft;
s12, determining parameters of a 'blunt wedge + conical side' configuration;
the flight direction of the hypersonic aircraft is taken as the front, and the configuration of the blunt wedge and the side surface of the cone is composed of a wedge body positioned in the middle and symmetrical semi-cones positioned at the two sides of the wedge body; the vertical symmetrical surface of the 'blunt wedge + conical side' configuration is an isosceles triangle with a reversed vertex angle and a vertical bottom edge, and the vertex angle of the isosceles triangle is
Figure DEST_PATH_IMAGE006
(ii) a The horizontal symmetrical plane of the 'blunt wedge + conical side' configuration is an isosceles trapezoid with two inner angles at the upper bottom edge being rounded, and the included angle between the two sides of the isosceles trapezoid is
Figure 74122DEST_PATH_IMAGE006
The width of the lower bottom edge is
Figure DEST_PATH_IMAGE008
(ii) a The wedge body with the structure of 'blunt wedge + conical side surface' is symmetrical up and down, the upper and lower surfaces are all rectangular, the front end is rounded, and the length of the wedge body is
Figure DEST_PATH_IMAGE010
With a width of
Figure DEST_PATH_IMAGE012
A height of
Figure DEST_PATH_IMAGE014
The included angle between the upper surface and the lower surface of the wedge body is
Figure 600918DEST_PATH_IMAGE006
The radius of the front end is
Figure DEST_PATH_IMAGE016
(ii) a The length of the semi-cone with the configuration of 'blunt wedge + conical side surface' is also
Figure 800955DEST_PATH_IMAGE010
The radius of the bottom surface of the semi-cone is
Figure DEST_PATH_IMAGE018
(ii) a The junction of the wedge body and the semi-cone body is adopted
Figure DEST_PATH_IMAGE020
Spherical surface transition;
the wedge face compression angle defining the "blunt wedge + tapered flank" configuration is
Figure DEST_PATH_IMAGE022
The width of the model is
Figure 591057DEST_PATH_IMAGE008
The height of the model is
Figure 610966DEST_PATH_IMAGE014
The width of the wedge surface is
Figure 115021DEST_PATH_IMAGE012
The radius of the leading edge is
Figure 903986DEST_PATH_IMAGE016
、The wedge/cone length is
Figure 599409DEST_PATH_IMAGE010
Each parameter has the following constraint relationship:
Figure DEST_PATH_IMAGE024
（1）
Figure DEST_PATH_IMAGE026
（2）
Figure DEST_PATH_IMAGE028
（3）
s13, establishing a shape database of a 'blunt wedge + conical side' configuration;
by changing in steps
Figure DEST_PATH_IMAGE030
The size of one variable is changed in a step mode, and a shape database of the configuration of the blunt wedge and the conical side surface, which meets the constraint relation of the step S12, is established;
s14, establishing a pneumatic thermal calculation database with a blunt wedge and conical side configuration;
modeling each blunt wedge and conical side configuration in the shape database of the blunt wedge and conical side configuration of the step S13, calculating aerodynamic thermal characteristics of each blunt wedge and conical side configuration including boundary layer flow state change and three-dimensional turbulence intensity change by adopting computational aerodynamics, and establishing an aerodynamic thermal calculation database of the blunt wedge and conical side configuration;
s15, determining a basic model;
in an aerodynamic heat calculation database of a 'blunt wedge + conical side' configuration, the 'blunt wedge + conical side' configuration which is closest to the aerodynamic characteristics of the existing hypersonic flight vehicle or the 'blunt wedge + conical side' configuration with the required aerodynamic characteristics is searched and defined as a basic type.
3. The design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to claim 1, wherein said step S20 includes the following steps:
s21, on the basis of the basic model, adding a compression corner to form a 'basic model + compression corner' configuration;
the compression corner is a wedge body with the volume smaller than that of the basic wedge body, the compression corner is defined as a small wedge body, and the small wedge body is placed on the upper surface of the basic wedge body to obtain a 'basic shape + compression corner' configuration;
s22, determining parameters of a basic type and compression corner configuration;
the upper surface and the lower surface of the small wedge body are both rectangular, and the included angle between the upper surface and the lower surface of the small wedge body is
Figure DEST_PATH_IMAGE032
The widths of the rectangle on the upper surface and the rectangle on the lower surface of the small wedge body are both
Figure DEST_PATH_IMAGE034
，
Figure DEST_PATH_IMAGE036
The length of the rectangle on the lower surface of the small wedge is
Figure DEST_PATH_IMAGE038
The horizontal distance between the front edge of the small wedge and the front edge of the basic wedge is
Figure DEST_PATH_IMAGE040
The rear bottom surface of the small wedge body is flush with the rear bottom surface of the basic wedge body and is positioned on a vertical plane; defining a compression angle of the compression corner as
Figure 965669DEST_PATH_IMAGE032
Width of
Figure 506371DEST_PATH_IMAGE034
Length of
Figure 415422DEST_PATH_IMAGE038
；
S23, establishing a shape database with a 'basic type + compression corner' configuration;
by changing in steps
Figure 16167DEST_PATH_IMAGE040
Adjusting the installation position of the compression corner; re-staging
Figure 10668DEST_PATH_IMAGE032
Adjusting the compression angle to establish compliance
Figure 355062DEST_PATH_IMAGE036
A shape database of "base + compression corner" configurations of (a);
s24, establishing an aerodynamic heat calculation database with a basic type and compression corner configuration;
modeling each basic type + compression corner configuration in the shape database of the basic type + compression corner configuration in the step S23, calculating the aerodynamic heat characteristics including air inlet channel compression of each basic type + compression corner configuration by adopting computational aerodynamics, and establishing an aerodynamic heat calculation database of the basic type + compression corner configuration;
s25, determining modification
Figure 617154DEST_PATH_IMAGE002
；
In an aerodynamic heat calculation database of the basic type + compression corner configuration, the basic type + compression corner configuration which is closest to the aerodynamic characteristics of the air inlet of the existing hypersonic aircraft or the basic type + compression corner configuration with the required aerodynamic characteristics of the air inlet is searched and definedFor retrofitting
Figure 654380DEST_PATH_IMAGE002
。
4. The design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to claim 1, wherein said step S30 includes the following steps:
s31, adding an obtuse rudder on the basis of the basic model to form a basic model and obtuse rudder configuration;
the blunt rudder is a trapezoidal rudder sheet, and a rudder shaft is positioned on a vertical symmetrical plane of the basic model and is vertical to the upper surface of the wedge body of the basic model; fixing a trapezoidal rudder sheet on the upper surface of a basic wedge through a rudder shaft to obtain a basic + blunt rudder configuration;
s32, determining parameters of a basic type and an obtuse rudder configuration;
the upper surface and the lower surface of the blunt rudder are both parallel to the upper surface of the basic type wedge body, and the gap height between the lower surface of the blunt rudder and the upper surface of the basic type wedge body is
Figure DEST_PATH_IMAGE042
(ii) a The sweep angle of the blunt rudder is
Figure DEST_PATH_IMAGE044
A thickness of
Figure DEST_PATH_IMAGE046
Has a length of
Figure DEST_PATH_IMAGE048
The front edge of the blunt rudder is rounded off
Figure DEST_PATH_IMAGE050
(ii) a The diameter of the rudder shaft of the blunt rudder is
Figure DEST_PATH_IMAGE052
The length of the central line of the rudder shaft from the tail end of the blunt rudder is
Figure DEST_PATH_IMAGE054
(ii) a The blunt rudder rotates around a rudder shaft, and after the blunt rudder rotates, the included angle between the vertical symmetrical plane of the blunt rudder and the flight direction is a rudder deflection angle
Figure DEST_PATH_IMAGE056
(ii) a The horizontal distance between the front edge of the blunt rudder and the sharp point of the basic wedge body is
Figure DEST_PATH_IMAGE058
；
S33, establishing a database of a basic type and blunt rudder configuration state;
first, a step change is made
Figure 995231DEST_PATH_IMAGE058
Adjusting the installation position of the blunt rudder; second step change
Figure 143316DEST_PATH_IMAGE044
Adjusting the sweepback angle of the blunt rudder; step change again
Figure 761379DEST_PATH_IMAGE042
Adjusting the gap height of the blunt rudder to obtain a basic type and blunt rudder configuration; last step change
Figure 969506DEST_PATH_IMAGE056
Adjusting the rudder deflection angle of the blunt rudder, and establishing a database of the configuration state of 'basic type + blunt rudder';
s34, establishing an aerodynamic heat calculation database in a basic type and blunt rudder configuration state;
modeling each basic type and blunt rudder configuration state in the database of the basic type and blunt rudder configuration state of the step S33, calculating aerodynamic heat characteristics of each basic type and blunt rudder configuration state including wing/body interference, rudder/body interference and rudder gap flow by adopting computational aerodynamics, and establishing an aerodynamic heat calculation database of the basic type and blunt rudder configuration state;
s35, determining modification
Figure 673020DEST_PATH_IMAGE004
；
In an aerodynamic heat calculation database of the 'basic type + blunt rudder' configuration state, the 'basic type + blunt rudder' configuration closest to the interference aerodynamic characteristics of the rudder pieces of the existing hypersonic aircraft or the 'basic type + blunt rudder' configuration with the required interference aerodynamic characteristics of the rudder pieces is searched and defined as modification
Figure 359216DEST_PATH_IMAGE004
。
5. The design method of the hypersonic aerodynamic thermal standard model for simulating the three-dimensional complex flow as claimed in claim 1, wherein said step S40 includes the following steps:
the hypersonic wind tunnel is inspected, and a special basic model and a special modification are designed and processed aiming at the selected hypersonic wind tunnel
Figure 864409DEST_PATH_IMAGE002
Modification of the same
Figure 243438DEST_PATH_IMAGE004
The heat flow sensor or the pressure sensor is mounted on the test model.
6. The design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to claim 1, wherein said step S50 includes the following steps:
in the selected hypersonic wind tunnel, according to the predetermined test outline, the basic model and the modification are carried out
Figure 434248DEST_PATH_IMAGE002
Modification of the same
Figure 924135DEST_PATH_IMAGE004
The hypersonic wind tunnel pneumatic heat test of the test model comprises the steps of respectively obtaining temperature data or pressure data through a heat flow sensor or a pressure sensor, and establishing a basic model and a modification
Figure 985632DEST_PATH_IMAGE002
Modification of the same
Figure 535562DEST_PATH_IMAGE004
The pneumatic calibration model database.
7. The design method of hypersonic aerodynamic thermal standard model for simulating three-dimensional complex flow according to claim 1, wherein said step S60 includes the following steps:
basic model, modification
Figure 213668DEST_PATH_IMAGE002
Modification of the same
Figure 507246DEST_PATH_IMAGE004
The pneumatic standard model database is released to the society as a basic model and a modification in the future
Figure 954408DEST_PATH_IMAGE002
Modification of the same
Figure 409660DEST_PATH_IMAGE004
Or reference data of a wind tunnel test.
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CN114781075A (en) * 2022-06-21 2022-07-22 中国飞机强度研究所 Method for determining equivalent model for simulating aerodynamic thermal environment of aerospace plane shell
CN114781076A (en) * 2022-06-21 2022-07-22 中国飞机强度研究所 Equivalent model determination method for simulation of aerodynamic thermal environment of cambered surface shell of aerospace plane
CN114781076B (en) * 2022-06-21 2022-09-02 中国飞机强度研究所 Equivalent model determination method for simulation of aerodynamic thermal environment of cambered surface shell of aerospace plane
CN114781075B (en) * 2022-06-21 2022-09-02 中国飞机强度研究所 Method for determining equivalent model for simulating aerodynamic thermal environment of aerospace plane shell
CN116596824A (en) * 2023-07-17 2023-08-15 中国空气动力研究与发展中心高速空气动力研究所 Multi-camera three-dimensional surface model fusion method
CN116596824B (en) * 2023-07-17 2023-09-12 中国空气动力研究与发展中心高速空气动力研究所 Multi-camera three-dimensional surface model fusion method

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