CN114722543B - 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 PDFInfo
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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
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 test of the hypersonic flight vehicle.
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 aircraft 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 by structural heat strength testing. 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 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)A radiant heating element, the firstA radiant heating element; wherein the content of the first and second substances,andare all positive integers, and,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 beThe axes of the plurality of radiation heating members (2) are vertically spaced from the bottom surface of the heat reflecting screen (1);
Step two, coordinate establishment:
step 201, using the top surface center of the rectangular test piece (3) as an originPassing through the originAnd the length direction of the top surface of the rectangular test piece (3) isAxis, passing through originAnd the width direction of the top surface of the rectangular test piece (3) isShaft, buildingA coordinate system;
step 202, taking the center of the top surface of the heat reflecting screen (1) as an originPassing through the originAnd along the length direction of the top surface of the heat reflection screen (1) isAxis, passing through originAnd along the width direction of the top surface of the heat reflection screen (1) isShaft, buildingA 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 atSeat marking in coordinate system(ii) a Wherein the content of the first and second substances,to representThe axis abscissa;to representAn axis ordinate;
step 302, setting the firstThe axial length direction of the radiation heating element is at any pointIn a coordinate systemOn the abscissa of(ii) a Wherein the content of the first and second substances,has a value range of,Represents the length of the heat reflection screen (1);
(ii) a Wherein the content of the first and second substances,represents a dimensionless first parameter, an;Represents a dimensionless second parameter, an;Represents a dimensionless third parameter, an;Represents the width of the heat reflection screen (1);
step 304, according to the formulaTo obtain the firstThe radiation heating element directly radiates to the top surface of the rectangular test piece (3)Heat flow at a point(ii) a Wherein the content of the first and second substances,represents the radiation power of the radiation heating element (2);
305, according to the formulaTo obtain the firstA radiation heating member directly radiates to the surface of the test pieceThe radiation reflected by the heat reflecting screen is reflected on the surface of the test pieceSum of heat flows at points(ii) a Wherein the content of the first and second substances,shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)The heat flow at the point of the heat transfer,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)Heat flow at the point;
step 306, according to the formulaTo obtain the top surface of the test pieceTotal heat flow of radiation at a point;
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 screenAn initial value is given to the width of the rectangular opening (1-1) in the heat reflection screenAssigning an initial value;
step 402, adopting a multi-island genetic algorithm to determine the length of the rectangular opening (1-1)And the width of the rectangular opening (1-1)Performing iterative optimization to obtainLength after sub-iteration optimizationAnd width;
Step 403, determine theLength after sub-iteration optimizationAnd widthWhether 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 stepLength after sub-iteration optimizationAnd widthDesigning optimized structural parameters for the heat reflecting screen; wherein the content of the first and second substances,is a positive integer;。
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 305Andthe specific process of obtaining is as follows:
3051, according to a formulaTo obtain the top surface of the rectangular test piece (3) reflected by the heat reflection screen (1)Heat flow at a pointWherein, the water-soluble polymer is a polymer,shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)Reflects heat flow specularly, and;shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)Diffusely reflects heat flow thereto, and,indicates that any point on the bottom surface of the heat reflection screen (1) is atThe coordinates of the object under the coordinate system,which represents the double differential of the light beam,representing the specular reflection coefficient of the heat reflecting screen (1),represents the diffuse reflection coefficient of the heat reflection screen (1);
3052, according to the formulaSo as to obtain the area of the rectangular opening part (1-1) in the heat reflection screen (1) to be reflected to the top surface of the rectangular test piece (3)Heat flow at a pointWherein, the water-soluble polymer is a polymer,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)Specularly reflects heat flow, and;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)Diffusely reflects heat flow thereto, and;is shown asThe axial length direction of the radiation heating element is at any pointAn abscissa in the coordinate system and located in the region of the rectangular opening (1-1);has a value range of,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 structural heat intensity test of the hypersonic aircraft is characterized by comprising the following steps: step 401 gives the length of the rectangular opening (1-1) in the heat reflection screenGiving an initial value ofGiving the width of the rectangular opening (1-1) in the heat reflection screenGiving an initial value of;
The convergence condition set in step 403 specifically includes the following steps:
step 4031, getLength after sub-iteration optimizationAnd widthSubstitute step 306 to obtain the secondLength after sub-iteration optimizationAnd widthCorresponding test piece top surfaceTotal heat flow of radiation at a point;
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 pieceAnd(ii) a Wherein the content of the first and second substances,is shown asLength after sub-iteration optimizationAnd widthThe maximum value of the total heat flow of the radiation at all points of the top surface of the corresponding test piece,is shown asLength after sub-iteration optimizationAnd widthThe 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:
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 intensity test of the hypersonic aerocraft is simple in steps and convenient to achieve, so that structural size parameters of the heat reflecting screen in the structural heat intensity test of the hypersonic aerocraft are obtained, and 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 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 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 the structural heat strength testing device of the hypersonic aircraft of the invention.
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)A radiant heating element, the firstA radiant heating element; wherein, the first and the second end of the pipe are connected with each other,andare all positive integers, and,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 beThe axes of the plurality of radiation heating members (2) are vertically spaced from the bottom surface of the heat reflecting screen (1);
Step two, coordinate establishment:
step 201, using the top surface center of the rectangular test piece (3) as an originPassing through the originAnd the length direction of the top surface of the rectangular test piece (3) isAxis, passing through originAnd the width direction of the top surface of the rectangular test piece (3) isShaft, buildingA coordinate system;
step 202, taking the center of the top surface of the heat reflecting screen (1) as an originPassing through the originAnd along the length direction of the top surface of the heat reflection screen (1) isAxis, passing through originAnd along the width direction of the top surface of the heat reflection screen (1) isShaft, buildingA 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 atSeat marking in coordinate system(ii) a Wherein the content of the first and second substances,to representThe axis abscissa;to representAn axis ordinate;
step 302, setting the firstThe axial length direction of each radiation heating element is at any pointThe abscissa in the coordinate system is(ii) a Wherein the content of the first and second substances,has a value range of,Represents the length of the heat reflection screen (1);
(ii) a Wherein the content of the first and second substances,represents a dimensionless first parameter, an;Represents a dimensionless second parameter, an;Represents a dimensionless third parameter, an;Represents the width of the heat reflection screen (1);
step 304, according to the formulaTo obtain the firstThe radiation heating element directly radiates to the top surface of the rectangular test piece (3)Heat flow at a point(ii) a Wherein the content of the first and second substances,represents the radiation power of the radiation heating element (2);
305, according to the formulaTo obtain the firstA radiation heating member directly radiates to the surface of the test pieceThe radiation reflected by the heat reflecting screen is reflected on the surface of the test pieceSum of heat flows at points(ii) a Wherein the content of the first and second substances,shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)The heat flow at the point of the heat transfer,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)Heat flow at the point;
step 306, according to the formulaTo obtain the top surface of the test pieceTotal heat flow of radiation at a point;
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 screenAn initial value is given to the width of the rectangular opening (1-1) in the heat reflection screenAssigning an initial value;
step (ii) of402. Using a multi-island genetic algorithm to measure the length of the rectangular opening (1-1)And the width of the rectangular opening (1-1)Performing iterative optimization to obtainLength after sub-iteration optimizationAnd width;
Step 403, judgeLength after sub-iteration optimizationAnd widthWhether 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 stepLength after sub-iteration optimizationAnd widthDesigning optimized structural parameters for the heat reflecting screen; wherein the content of the first and second substances,is a positive integer;。
3051, according to a formulaTo obtain the top surface of the rectangular test piece (3) reflected by the heat reflection screen (1)Heat flow at a pointWherein, the water-soluble polymer is a polymer,shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)Reflects heat flow specularly, and;showing the reflection of the heat reflection screen (1) to the top surface of the rectangular test piece (3)Diffusely reflects heat flow thereto, and,indicates that any point on the bottom surface of the heat reflection screen (1) is onThe coordinates of the object under the coordinate system,which represents the double differential of the light beam,representing the specular reflection coefficient of the heat reflecting screen (1),represents the diffuse reflection coefficient of the heat reflection screen (1);
3052, according to the formulaObtaining 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)Heat flow at a pointWherein, the water-soluble polymer is a polymer,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)Reflects heat flow specularly, and;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)Diffusely reflects heat flow thereto, and;is shown asThe axial length direction of the radiation heating element is at any pointAn abscissa in the coordinate system and located in the region of the rectangular opening (1-1);has a value range of,The length of a rectangular opening (1-1) in a heat reflection screen (1) is shown.
In this embodiment, the length of the rectangular opening (1-1) in the heat reflection screen is given in step 401Giving an initial value ofGiving the width of the rectangular opening (1-1) in the heat reflection screenGiving an initial value of;
The convergence condition set in step 403 specifically includes the following steps:
step 4031, getLength after sub-iteration optimizationAnd widthSubstitute step 306 to obtain the firstLength after sub-iteration optimizationAnd widthCorresponding test piece top surfaceTotal heat flow of radiation at a point;
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 pieceAnd(ii) a Wherein the content of the first and second substances,is shown asLength after sub-iteration optimizationAnd widthThe maximum value of the total heat flow of the radiation at all points of the top surface of the corresponding test piece,is shown asLength after sub-iteration optimizationAnd widthThe 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:
in this embodiment, 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.
In this embodiment, it should be noted that,when the heat reflecting screen (1) is not provided with the rectangular opening part (1-1), the whole body is reflected to the top surface of the rectangular test piece (3)Heat flow at the point.
In this embodiment, it should be noted thatIs assigned a value ofSubstituting into dimensionless radiation functionTo obtain a first radiation function;
Will be provided withIs assigned a value of,Is assigned a value of,Is assigned a value ofSubstituting into dimensionless radiation functionTo obtain a second radiation function;
Will be provided withIs assigned a value of,Is assigned a value ofSubstituting into dimensionless radiation functionTo obtain a third radiation function;
Will be provided withIs assigned a value of,Is assigned a value of,Is assigned a value of,Is assigned a value ofSubstitution of dimensionless radiationFunction(s)To obtain a fourth radiation function。
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 reflection screen (1) is 500mm × 310mm, the thickness of the heat reflection screen (1) is 3mm to 6mm, and the heat reflection 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)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 distanceThe value range of (1) is 20 cm-30 cm, and the upper vertical distanceThe 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 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 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 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 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)A radiant heating element, the firstA radiant heating element; wherein the content of the first and second substances,andare all positive integers, and,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 beThe axes of the plurality of radiation heating members (2) are vertically spaced from the bottom surface of the heat reflecting screen (1);
Step two, coordinate establishment:
step 201, using the top surface center of the rectangular test piece (3) as an originPassing through the originAnd the length direction of the top surface of the rectangular test piece (3) isAxis, passing through originAnd the width direction of the top surface of the rectangular test piece (3) isShaft, buildingA coordinate system;
step 202, taking the center of the top surface of the heat reflecting screen (1) as an originPassing through the originAnd along the length direction of the top surface of the heat reflection screen (1) isAxis, passing through originAnd along the width direction of the top surface of the heat reflection screen (1) isShaft, buildingA coordinate system;
step three, obtaining the total heat flux of the radiation of the rectangular test piece:
step 301, setting a rectangular bodyAny point on the top surface of the test piece (3) isSeat marking in coordinate system(ii) a Wherein the content of the first and second substances,to representThe axis abscissa;to representAn axis ordinate;
step 302, setting the firstThe axial length direction of each radiation heating element is at any pointThe abscissa in the coordinate system is(ii) a Wherein the content of the first and second substances,has a value range of,Showing a heat reflecting screen (1) Length of (d);
(ii) a Wherein the content of the first and second substances,represents a dimensionless first parameter, an;Represents a dimensionless second parameter, an;Represents a dimensionless third parameter, an;Represents the width of the heat reflection screen (1);
step 304, according to the formulaTo obtain the firstThe radiation heating element directly radiates to the top surface of the rectangular test piece (3)Heat flow at a point(ii) a Wherein the content of the first and second substances,represents the radiation power of the radiation heating element (2);
305, according to the formulaTo obtain the firstA radiation heating member directly radiates to the surface of the test pieceThe radiation reflected by the heat reflecting screen is reflected on the surface of the test pieceSum of heat flows at points(ii) a Wherein the content of the first and second substances,shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)The heat flow at the point of the heat transfer,showing the reflection of the rectangular opening (1-1) area in the heat reflection screen (1) to the rectangular test piece (3)The top surfaceHeat flow at the point;
step 306, according to the formulaTo obtain the top surface of the test pieceTotal heat flow of radiation at a point;
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 screenAn initial value is given to the width of the rectangular opening (1-1) in the heat reflection screenAssigning an initial value;
step 402, adopting a multi-island genetic algorithm to determine the length of the rectangular opening (1-1)And the width of the rectangular opening (1-1)Performing iterative optimization to obtainLength after sub-iteration optimizationAnd width;
Step 403, judgeLength after sub-iteration optimizationAnd widthIf the set convergence condition is not met, executing the next iterative optimization; if the set convergence condition is satisfied, the first stepLength after sub-iteration optimizationAnd widthDesigning optimized structural parameters for the heat reflecting screen; wherein the content of the first and second substances,is a positive integer;。
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 305Andthe specific process of obtaining is as follows:
3051, according to a formulaTo obtain the top surface of the rectangular test piece (3) reflected by the heat reflection screen (1)Heat flow at a pointWherein, the water-soluble polymer is a polymer,shows that the heat reflection screen (1) reflects to the top surface of the rectangular test piece (3)Reflects heat flow specularly, and;showing the reflection of the heat reflection screen (1) to the top surface of the rectangular test piece (3)Diffusely reflects heat flow thereto, and,indicates that any point on the bottom surface of the heat reflection screen (1) is atThe coordinates of the object under the coordinate system,which represents the double differential of the light beam,representing the specular reflection coefficient of the heat reflecting screen (1),represents the diffuse reflection coefficient of the heat reflection screen (1);
3052, according to the formulaObtaining 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)Heat flow at a pointWherein, the water-soluble polymer is a polymer,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)Reflects heat flow specularly, and;representing a rectangle in the heat-reflecting screen (1)The area of the opening part (1-1) is reflected to the top surface of the rectangular test piece (3)Diffusely reflects heat flow thereto, and;is shown asThe axial length direction of the radiation heating element is at any pointAn abscissa in the coordinate system and located in the region of the rectangular opening (1-1);has a value range of,The length of a rectangular opening (1-1) in a heat reflection screen (1) is shown.
3. The method for designing the heat reflecting screen in the structural heat intensity test of the hypersonic aerocraft according to claim 1, characterized in that: step 401 gives the length of the rectangular opening (1-1) in the heat reflection screenGiving an initial value ofGiving the width of the rectangular opening (1-1) in the heat reflection screenGiving an initial value of;
The convergence condition set in step 403 specifically includes the following steps:
step 4031, getLength after sub-iteration optimizationAnd widthSubstitute step 306 to obtain the secondLength after sub-iteration optimizationAnd widthCorresponding test piece top surfaceTotal heat flow of radiation at a point;
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 pieceAnd(ii) a Wherein the content of the first and second substances,is shown asLength after sub-iteration optimizationAnd widthThe maximum value of the total heat flow of the radiation at all points of the top surface of the corresponding test piece,is shown asLength after sub-iteration optimizationAnd widthThe 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:
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.
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