CN114781075B - Method for determining equivalent model for simulating aerodynamic thermal environment of aerospace plane shell - Google Patents

Method for determining equivalent model for simulating aerodynamic thermal environment of aerospace plane shell Download PDF

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CN114781075B
CN114781075B CN202210700974.5A CN202210700974A CN114781075B CN 114781075 B CN114781075 B CN 114781075B CN 202210700974 A CN202210700974 A CN 202210700974A CN 114781075 B CN114781075 B CN 114781075B
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CN114781075A (en
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田敏
王彬文
秦强
刘宁夫
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AVIC Aircraft Strength Research Institute
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Abstract

The invention discloses a method for determining an equivalent model for simulating the aerodynamic thermal environment of a plane shell of an aerospace plane, which comprises the following steps: firstly, determining a heating distance between a plane to be heated of a plane shell of the plane of the airplane and a heating element; dividing a plane to be heated and a heating element; thirdly, determining the installation position of the light screen; and fourthly, determining an equivalent model. According to the invention, a plane to be heated is equivalent to a two-dimensional plane, and a novel element is not required to be designed by controlling a single variable under the existing test condition through analyzing the installation position of the light shielding plate; by utilizing the similar triangle law, the value range of the vertical distance between the bottom of the light screen and the bottom surface of the mounting area between any two adjacent plane units to be heated can be obtained, and the influence of a heat flow field between two adjacent heating adjacent areas in the plane shell of the airplane is effectively reduced.

Description

Method for determining equivalent model for simulating aerodynamic thermal environment of aerospace plane shell
Technical Field
The invention belongs to the technical field of aerospace plane aerodynamic thermal environment simulation, and particularly relates to an equivalent model determination method for aerospace plane shell aerodynamic thermal environment simulation.
Background
The aerospace plane, called aerospace plane for short, is more and more important in the current and future aviation development, and with the continuous development of aerospace planes, in order to adapt to higher flight Mach number, part of the shell of the aerospace plane is a smooth plane, when the shell is subjected to aerodynamic thermal environment simulation of ground test, radiation elements need to be arranged into units as small as possible and are attached to a plane shell of the aerospace plane at equal intervals, and due to the mutual influence of unit boundaries, the conventional thermal flow field partitioning mode has the factors that the heat flow at the junction of a temperature zone is uncontrollable, the control and feedback of the thermal flow field of the temperature zone are influenced by an adjacent temperature zone, and the simulation of the aerodynamic thermal environment of the ground test is not facilitated. In order to reduce the mutual influence between two adjacent temperature zones in a simulation test, a light screen can be arranged between the two adjacent temperature zones to play a role in shielding, and a thermal flow field model of the plane shell of the airplane is obtained through pneumatic thermal environment simulation; theoretically, the lower edge of the light screen needs to be tightly attached to the plane shell of the airplane, temperature areas on two sides cannot interfere with each other, but the plane shell of the airplane in the test is deformed and can be displaced in multiple directions, the light screen can be extruded, and the light screen cannot play the original shading effect after displacement, so that the lower edge of the light screen cannot be tightly attached to the plane shell of the airplane, and the installation position of the light screen needs to be analyzed so as to obtain a more accurate thermal flow field model of the plane shell of the airplane.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an equivalent model determination method for the aerodynamic thermal environment simulation of the plane shell of the aerospace plane aiming at the defects in the prior art, wherein a plane to be heated is equivalent to a two-dimensional plane, and a novel element is not required to be designed by controlling a single variable under the existing test condition by analyzing the installation position of a light screen; by utilizing the similar triangle law, the value range of the vertical distance between the bottom of the shading plate between any two adjacent plane units to be heated and the bottom surface of the mounting area can be obtained, and the influence of a heat flow field between two adjacent heating adjacent areas in the plane shell of the airplane is effectively reduced.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows: the method for determining the equivalent model for simulating the aerodynamic thermal environment of the plane shell of the aerospace plane is characterized by comprising the following steps of: the method comprises the following steps:
step one, determining a heating distance between a plane to be heated of an aircraft plane shell and a heating element: performing heat flow field analysis on a plane to be heated according to a thermal module of Ansys, and obtaining a heating distance H between the plane to be heated and a heating element according to the heat flow density and the heat flow temperature requirement of the plane to be heated; proportionally extracting a plane to be heated and a heating element into a two-dimensional plane; wherein the vertical distance between the bottom surface of the heating element in the two-dimensional plane and the surface of the plane to be heated is H;
step two, dividing a plane to be heated and a heating element: dividing a plane to be heated according to a thermal flow field analysis result in a thermal module of Ansys to obtain a plurality of plane units to be heated distributed in an array; meanwhile, according to the partition method of the plane to be heated, the heating elements are also divided to obtain a plurality of heating plane units distributed in an array, and the number of the heating plane units is equal to that of the plane units to be heated and corresponds to that of the plane units to be heated one by one;
step three, determining the installation position of the light shielding plate: inserting a light screen into each mounting area, wherein the vertical center line of the light screen is superposed with the center line of the mounting area, and the vertical distance between the bottom of the light screen inserted into the mounting area and the bottom surface of the mounting area is S; the method for determining the vertical distance between the bottom of the light shading plate inserted into each mounting area and the bottom surface of the mounting area is the same, and the process for determining the vertical distance between the bottom of the light shading plate in any mounting area and the bottom surface of the mounting area is as follows:
301, selecting two adjacent planar units to be heated, setting the two adjacent planar units to be a first planar unit to be heated and a second planar unit to be heated respectively, and determining a heating distance L1 of the first planar unit to be heated and a heating distance L2 of the second planar unit to be heated in a two-dimensional equivalent diagram;
step 302, determining the vertical distance between the bottom of the light shielding plate and the bottom surface of the mounting area under the influence of the first planar unit to be heated on the second planar unit to be heated, the process is as follows:
step 3021, heating the first to-be-heated material in the two-dimensional equivalent diagramThe heating distance L1 of the plane unit is compared with the heating distance L2 of the second plane unit to be heated when
Figure 851385DEST_PATH_IMAGE001
If so, executing step 3022, otherwise, executing step 303;
step 3022, making a connection line OA between a bottom vertex A of the light shielding plate near the first planar unit to be heated and a projection point O of the end of the first planar unit to be heated far from the light shielding plate on the heating planar unit, extending the connection line OA, wherein an intersection point with the surface of the second planar unit to be heated is a point B, a length between an end point C of the second planar unit to be heated near the light shielding plate and the intersection point B is a heating influence length L3, and Δ BAD and Δ BOK are similar according to the law of similarity of triangles, so that Δ BAD and Δ BOK are similar, and the heating effect length is equal to that of Δ BAD and Δ BOK
Figure 203869DEST_PATH_IMAGE002
Then, then
Figure 146417DEST_PATH_IMAGE003
Wherein b is the thickness of the shading plate, d is the width of the mounting area, and S1 is the vertical distance between the bottom of the shading plate and the bottom surface of the mounting area when the first plane unit to be heated affects the heating of the second plane unit to be heated;
step 3023, according to the test requirement, the first plane unit to be heated affects the heating length of the second plane unit to be heated
Figure 584351DEST_PATH_IMAGE004
The formula in step 3022 is integrated to obtain,
Figure 942652DEST_PATH_IMAGE005
Figure 415221DEST_PATH_IMAGE004
then the vertical distance S1 between the bottom of the light shielding plate and the bottom of the installation area when the first plane unit to be heated has the heating effect on the second plane unit to be heated is determined as the insertionA vertical distance S between a bottom of the visor within the mounting area and a bottom surface of the mounting area;
step 303, determining the vertical distance between the bottom of the light shielding plate and the bottom surface of the mounting area under the influence of the second planar unit to be heated on the first planar unit to be heated, the process is as follows:
step 3031, making a connecting line EF between a bottom vertex F of the light shielding plate close to the second to-be-heated plane unit and a projection point E of the end part of the second to-be-heated plane unit far away from the light shielding plate on the heating plane unit, extending the connecting line EF, wherein the intersection point of the connecting line EF and the surface of the first to-be-heated plane unit is a point G, the length between an end point I of the first to-be-heated plane unit close to the light shielding plate and the intersection point G is a heating influence length L4, and according to the law of similar triangles, Delta GFM and Delta GEN are similar, so that Delta GFM and Delta GEN are similar to each other, and therefore
Figure 528671DEST_PATH_IMAGE006
Then, then
Figure 453901DEST_PATH_IMAGE007
Wherein b is the thickness of the shading plate, d is the width of the mounting area, and S2 is the vertical distance between the bottom of the shading plate and the bottom surface of the mounting area when the second plane unit to be heated affects the heating of the first plane unit to be heated;
3032, according to the test requirement, the heating influence length of the second to-be-heated plane unit on the first to-be-heated plane unit is known
Figure 678209DEST_PATH_IMAGE008
The formula in step 3031 is integrated to obtain,
Figure 926657DEST_PATH_IMAGE009
determining that the vertical distance S2 between the bottom of the light shielding plate and the bottom surface of the installation area when the second plane unit to be heated affects the first plane unit to be heated is the vertical distance S between the bottom of the light shielding plate inserted into the installation area and the bottom surface of the installation area;
step four, determining an equivalent model: and C, inserting a light screen between two adjacent plane units to be heated according to the installation position of the light screen determined in the step III, wherein a plurality of light screens form a light screen assembly inserted in the plane to be heated, and determining an equivalent model.
The method for determining the equivalent model for simulating the aerodynamic thermal environment of the plane shell of the aerospace plane is characterized by comprising the following steps of: in the first step, the heating distance H ranges from 50mm to 80 mm.
The method for determining the equivalent model for simulating the aerodynamic thermal environment of the plane shell of the aerospace plane is characterized by comprising the following steps of: in the third step, in two adjacent planar units to be heated, the rectangular area between the top surface of one planar unit to be heated and the bottom surface of the heating planar unit is set as a first transition area, the rectangular area between the top surface of the other planar unit to be heated and the bottom surface of the heating planar unit is set as a second transition area, and the rectangular area between the first transition area and the second transition area is set as a mounting area.
The method for determining the equivalent model for simulating the aerodynamic thermal environment of the plane shell of the aerospace plane is characterized by comprising the following steps of: in the third step, the thickness of the shading plate is less than 1 mm.
Compared with the prior art, the invention has the following advantages:
1. according to the plane heating device, the plane to be heated is equivalent to a two-dimensional plane, the installation position of the light screen is analyzed, a novel element is not required to be designed by controlling a single variable under the existing test condition, the influence of a heat flow field between two adjacent plane units to be heated of the plane shell of the airplane is reduced, the processing period is short, the processing difficulty is low, and the installation is convenient.
2. The invention divides the temperature zone of the plane to be heated, analyzes the influence of the heat flow field between two adjacent plane units to be heated respectively, obtains the installation position of the light screen under the condition of reducing the influence of the heat flow field between two adjacent plane units to be heated, has simple steps and obvious effect of reducing the influence of the heat flow field.
3. According to the invention, the position of the light screen arranged between two adjacent plane units to be heated is analyzed and determined, so that the installation position of the light screen can be accurately determined in the plane to be heated, and the light screen is arranged between all the two adjacent plane units to be heated in the plane to be heated to form an equivalent model, thereby facilitating subsequent tests.
4. According to the invention, the value range of the vertical distance between the bottom of the light screen and the bottom surface of the mounting area between any two adjacent plane units to be heated can be obtained by using the similar triangle law, and the influence of a heat flow field between two adjacent heating adjacent areas in the plane shell of the airplane is effectively reduced.
In conclusion, the plane to be heated is equivalent to the two-dimensional plane, and by analyzing the installation position of the light shielding plate, a novel element is not required to be designed by controlling a single variable under the existing test condition; by utilizing the similar triangle law, the value range of the vertical distance between the bottom of the light screen and the bottom surface of the mounting area between any two adjacent plane units to be heated can be obtained, and the influence of a heat flow field between two adjacent heating adjacent areas in the plane shell of the airplane is effectively reduced.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic view of the relationship between the plane to be heated and the heating element according to the present invention.
Fig. 2 is a schematic diagram of the positional relationship between the light shielding plate and the two temperature zones when the heating influence of the first planar unit to be heated on the second planar unit to be heated is determined according to the present invention.
Fig. 3 is a schematic diagram of the positional relationship between the light shielding plate and the two temperature zones when the heating influence of the second planar unit to be heated on the first planar unit to be heated is determined.
FIG. 4 is a block diagram of a method flow of the present invention.
Description of reference numerals:
1-a first planar unit to be heated; 2-a second planar unit to be heated; 3-installation area;
4-a light screen; 5 — a first transition zone; 6-a second transition zone;
7-a heating element; 8, a plane to be heated; 9-heating the planar unit.
Detailed Description
The method for determining the equivalent model for the aerospace plane housing aerodynamic thermal environment simulation shown in fig. 1 to 4 comprises the following steps:
step one, determining a heating distance between a plane to be heated of an aircraft plane shell and a heating element: performing heat flow field analysis on the plane to be heated 8 according to a thermal module of Ansys, and obtaining a heating distance H between the plane to be heated 8 and the heating element 7 according to the heat flow density and the heat flow temperature requirement of the plane to be heated 8; proportionally extracting a plane to be heated 8 and a heating element 7 into a two-dimensional plane; wherein the vertical distance between the bottom surface of the heating element 7 and the surface of the plane to be heated 8 in the two-dimensional plane is H;
step two, dividing a plane to be heated and a heating element: dividing a plane to be heated 8 according to a thermal flow field analysis result in a thermal module of Ansys to obtain a plurality of plane units to be heated distributed in an array; meanwhile, according to the partition method of the plane to be heated 8, the heating elements 7 are also divided to obtain a plurality of heating plane units 9 arranged in an array, and the number of the heating plane units 9 is equal to that of the plane units to be heated and corresponds to that of the plane units to be heated one by one;
step three, determining the installation position of the shading plate: a light screen 4 is inserted in each mounting area 3, the vertical center line of the light screen 4 is superposed with the center line of the mounting area 3, and the vertical distance between the bottom of the light screen 4 inserted in the mounting area 3 and the bottom surface of the mounting area 3 is S; the method for determining the vertical distance between the bottom of the light screen 4 inserted into each installation area 3 and the bottom surface of the installation area 3 is the same, and the process for determining the vertical distance between the bottom of the light screen 4 in any installation area 3 and the bottom surface of the installation area 3 is as follows:
step 301, selecting two adjacent planar units to be heated, setting the two adjacent planar units to be a first planar unit to be heated 1 and a second planar unit to be heated 2, and determining a heating distance L1 of the first planar unit to be heated 1 and a heating distance L2 of the second planar unit to be heated 2 in a two-dimensional equivalent diagram;
step 302, determining the vertical distance between the bottom of the light shielding plate and the bottom surface of the mounting area under the influence of the first planar unit to be heated on the second planar unit to be heated, the process is as follows:
step 3021, comparing the heating distance L1 of the first planar unit to be heated 1 and the heating distance L2 of the second planar unit to be heated 2 in the two-dimensional equivalent diagram, when
Figure 211008DEST_PATH_IMAGE010
If so, executing step 3022, otherwise, executing step 303;
step 3022, making a connection line OA between a bottom vertex A of the light shielding plate 4 close to the first planar unit to be heated 1 and a projection point O of an end of the first planar unit to be heated 1 far from the light shielding plate 4 on the heating planar unit 9, extending the connection line OA, making an intersection point with the surface of the second planar unit to be heated 2 a point B, making a length between an end point C of the second planar unit to be heated 2 close to the light shielding plate 4 and the intersection point B a heating influence length L3, and obtaining Δ BAD and Δ BOK similar according to the law of similar triangles, so that Δ BAD and Δ BOK are similar, and therefore
Figure 623535DEST_PATH_IMAGE011
Then, then
Figure 651533DEST_PATH_IMAGE012
Wherein b is the thickness of the light shielding plate 4, d is the width of the mounting area 3, and S1 is the vertical distance between the bottom of the light shielding plate 4 and the bottom surface of the mounting area 3 when the first planar unit to be heated 1 affects the heating of the second planar unit to be heated 2;
step 3023, according to the test requirement, the heating influence length of the first plane unit to be heated 1 on the second plane unit to be heated 2
Figure 833116DEST_PATH_IMAGE013
The formula in step 3022 is integrated to obtain,
Figure 22789DEST_PATH_IMAGE014
then, it is determined that a vertical distance S1 between the bottom of the light shielding plate 4 and the bottom surface of the installation area 3 when the first planar unit to be heated 1 affects the heating of the second planar unit to be heated 2 is a vertical distance S between the bottom of the light shielding plate 4 inserted in the installation area 3 and the bottom surface of the installation area 3;
step 303, determining the vertical distance between the bottom of the light shielding plate and the bottom surface of the mounting area under the influence of the second planar unit to be heated on the first planar unit to be heated, the process is as follows:
step 3031, a connecting line EF is formed between a bottom vertex F of the light shielding plate 4 close to the second to-be-heated plane unit 2 and a projection point E of the end part of the second to-be-heated plane unit 2 far away from the light shielding plate 4 on the heating plane unit 9, the connecting line EF is extended, an intersection point of the connecting line EF and the surface of the first to-be-heated plane unit 1 is a point G, a length between an end point I of the first to-be-heated plane unit 1 close to the light shielding plate 4 and the intersection point G is a heating influence length L4, and Δ GFM and Δ GEN are similar according to a similar triangle law, so that Δ GFM and Δ GEN are similar to each other, and therefore, the connecting line EF is a connecting the surface of the first to-be-heated plane unit 1 and the connecting line EF is a point G connecting the end point of the light shielding plate 4 and the end point G connecting the light shielding plate 4 and the light shielding plate
Figure 860295DEST_PATH_IMAGE015
Then, then
Figure 426405DEST_PATH_IMAGE016
Wherein b is the thickness of the light shielding plate 4, d is the width of the mounting area 3, and S2 is the vertical distance between the bottom of the light shielding plate 4 and the bottom surface of the mounting area 3 when the second to-be-heated plane unit 2 is affected by heating the first to-be-heated plane unit 1;
3032, according to the test requirement, the heating influence length of the second to-be-heated plane unit 2 on the first to-be-heated plane unit 1 is known
Figure 728074DEST_PATH_IMAGE017
The formula in step 3031 is integrated to obtain,
Figure 88648DEST_PATH_IMAGE018
then, it is determined that a vertical distance S2 between the bottom of the light-shielding plate 4 and the bottom surface of the installation area 3 when the second planar unit to be heated 2 affects the heating of the first planar unit to be heated 1 is a vertical distance S between the bottom of the light-shielding plate 4 inserted in the installation area 3 and the bottom surface of the installation area 3;
step four, determining an equivalent model: according to the installation position of the light shielding plates 4 determined in the third step, the light shielding plates 4 are inserted between two adjacent plane units to be heated, the plurality of light shielding plates 4 form a light shielding plate assembly inserted in the plane 8 to be heated, and an equivalent model is determined.
According to the invention, the plane 8 to be heated is equivalent to a two-dimensional plane, and the installation position of the light screen 4 is analyzed, so that under the existing test condition, by controlling a single variable, a novel element is not required to be designed, the influence of a heat flow field between two adjacent plane units to be heated of the plane shell of the airplane is reduced, the processing period is short, the processing difficulty is low, and the installation is convenient.
According to the invention, the temperature zone division is carried out on the plane 8 to be heated, the influence of the heat flow field between two adjacent plane units to be heated is respectively analyzed, and the installation position of the light screen 4 is obtained under the condition of reducing the influence of the heat flow field between two adjacent plane units to be heated.
According to the invention, the position of the light screen 4 arranged between two adjacent planar units to be heated is analyzed and determined, so that the installation position of the light screen 4 can be accurately determined in the planar unit to be heated 8, and the light screen 4 is arranged between all two adjacent planar units to be heated in the planar unit to be heated 8, thereby forming an equivalent model and facilitating subsequent tests.
According to the invention, the value range of the vertical distance between the bottom of the light screen 4 and the bottom surface of the mounting area 3 between any two adjacent plane units to be heated can be obtained by using the similar triangle law, and the influence of a heat flow field between two adjacent heating adjacent areas in the plane shell of the airplane is effectively reduced.
In actual use, the vertical distance between the bottom of the light shielding plate 4 and the bottom surface of the installation area 3 under the influence of the second planar unit to be heated 2 on the first planar unit to be heated 1 is determined, or the vertical distance between the bottom of the light shielding plate 4 and the bottom surface of the installation area 3 under the influence of the first planar unit to be heated 1 on the second planar unit to be heated 2 is determined to be greater than zero, excluding the direct contact between the bottom of the light shielding plate 4 and the bottom surface of the installation area 3.
In practical use, when the plane shell of the airplane is subjected to temperature division, the plane shell of the airplane can be divided into a plurality of plane units to be heated which are arranged in an array manner, so that a light screen 4 needs to be installed between two adjacent plane units to be heated along the length direction of the plane shell of the airplane, and the light screen 4 also needs to be installed between two adjacent plane units to be heated along the width direction of the plane shell of the airplane; in determining the position of the light screen 4 between two adjacent planar units to be heated in the length direction of the aircraft planar housing, the heating distance L1 of the first planar unit to be heated 1 and the heating distance L2 of the second planar unit to be heated 2 are both the heating length of the planar unit to be heated; when determining the position of the light screen 4 between two adjacent planar units to be heated in the width direction of the aircraft planar housing, the heating distance L1 of the first planar unit to be heated 1 and the heating distance L2 of the second planar unit to be heated 2 are both the heating width of the planar unit to be heated.
In the embodiment, in the first step, the heating distance H ranges from 50mm to 80 mm.
In the third step of the present embodiment, in two adjacent planar units to be heated, a rectangular area between the top surface of one planar unit to be heated and the bottom surface of the heating planar unit 9 is set as the first transition area 5, a rectangular area between the top surface of the other planar unit to be heated and the bottom surface of the heating planar unit 9 is set as the second transition area 6, and a rectangular area between the first transition area 5 and the second transition area 6 is set as the installation area 3.
In the third step, the thickness of the light shielding plate 4 is smaller than 1 mm.
It should be noted that the light shielding plate 4 is a silicon nitride heat insulation light shielding plate, and in order to facilitate installation of the light shielding plate 4 under the condition of considering the self weight of the light shielding plate 4, the thickness of the light shielding plate 4 should be less than 1 mm.
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. The method for determining the equivalent model for simulating the aerodynamic thermal environment of the plane shell of the aerospace plane is characterized by comprising the following steps of:
step one, determining a heating distance between a plane to be heated of a plane shell of an airplane and a heating element: performing heat flow field analysis on the plane to be heated (8) according to a thermal module of Ansys, and obtaining a heating distance H between the plane to be heated (8) and the heating element (7) according to the heat flow density and the heat flow temperature requirement of the plane to be heated (8); proportionally extracting a plane (8) to be heated and a heating element (7) into a two-dimensional plane; wherein the vertical distance between the bottom surface of the heating element (7) and the surface of the plane (8) to be heated in the two-dimensional plane is H;
step two, dividing a plane to be heated and a heating element: dividing a plane (8) to be heated according to a thermal flow field analysis result in a thermal module of Ansys to obtain a plurality of plane units to be heated distributed in an array; meanwhile, according to the partition method of the plane (8) to be heated, the heating elements (7) are also divided to obtain a plurality of heating plane units (9) which are arranged in an array, and the number of the heating plane units (9) is equal to that of the plane units to be heated and corresponds to that of the plane units to be heated one by one;
step three, determining the installation position of the shading plate: a light screen (4) is inserted into each mounting area (3), the vertical center line of the light screen (4) is superposed with the center line of the mounting area (3), and the vertical distance between the bottom of the light screen (4) inserted into the mounting area (3) and the bottom surface of the mounting area (3) is S; the method for determining the vertical distance between the bottom of the light screen (4) inserted into each mounting area (3) and the bottom surface of the mounting area (3) is the same, and the process for determining the vertical distance between the bottom of the light screen (4) in any mounting area (3) and the bottom surface of the mounting area (3) is as follows:
301, selecting two adjacent planar units to be heated, setting the two adjacent planar units to be a first planar unit to be heated (1) and a second planar unit to be heated (2), and determining a heating distance L1 of the first planar unit to be heated (1) and a heating distance L2 of the second planar unit to be heated (2) in a two-dimensional equivalent diagram;
step 302, determining the vertical distance between the bottom of the light shielding plate and the bottom surface of the mounting area under the influence of the first planar unit to be heated on the second planar unit to be heated, the process is as follows:
step 3021, comparing the heating distance L1 of the first planar unit to be heated (1) and the heating distance L2 of the second planar unit to be heated (2) in the two-dimensional equivalent diagram, when
Figure 909226DEST_PATH_IMAGE001
If so, executing step 3022, otherwise, executing step 303;
step 3022, a connecting line OA between a bottom vertex A of the light shielding plate (4) close to the first planar unit to be heated (1) and a projection point O of the end of the first planar unit to be heated (1) far away from the light shielding plate (4) on the heating planar unit (9) is made, the connecting line OA is extended, an intersection point with the surface of the second planar unit to be heated (2) is a point B, a length between an end point C of the second planar unit to be heated (2) close to the light shielding plate (4) and the intersection point B is a heating influence length L3, and according to the law of similarity of triangles, Delta BAD and Delta BOK are similar, so that Delta BAD and Delta BOK are similar, and Delta BOK is obtained
Figure 184350DEST_PATH_IMAGE002
Then, then
Figure 827821DEST_PATH_IMAGE003
Wherein b is the thickness of the light screen (4), d is the width of the mounting area (3), and S1 is the vertical distance between the bottom of the light screen (4) and the bottom surface of the mounting area (3) when the first planar unit to be heated (1) has heating influence on the second planar unit to be heated (2);
step 3023, according to the test requirement, the heating influence length of the first plane unit to be heated (1) on the second plane unit to be heated (2)
Figure 162987DEST_PATH_IMAGE004
The formula in step 3022 is integrated to obtain,
Figure 891909DEST_PATH_IMAGE005
determining that the vertical distance S1 between the bottom of the shading plate (4) and the bottom surface of the mounting area (3) when the first planar unit to be heated (1) has heating influence on the second planar unit to be heated (2) is the vertical distance S between the bottom of the shading plate (4) inserted into the mounting area (3) and the bottom surface of the mounting area (3);
step 303, determining the vertical distance between the bottom of the light shielding plate and the bottom surface of the mounting area under the influence of the second planar unit to be heated on the first planar unit to be heated, the process is as follows:
3031, a connecting line EF between a bottom vertex F of the light shielding plate (4) close to the second plane unit to be heated (2) and a projection point E of the end part of the second plane unit to be heated (2) far away from the light shielding plate (4) on the heating plane unit (9) is made, the connecting line EF is extended, an intersection point with the surface of the first plane unit to be heated (1) is a point G, the length between an end point I of the first plane unit to be heated (1) close to the light shielding plate (4) and the intersection point G is a heating influence length L4, and according to the law of similarity of triangles, Delta GFM and Delta GEN are similar, so that the Delta GFM and the Delta GEN are similar
Figure 970723DEST_PATH_IMAGE006
Then, then
Figure 661511DEST_PATH_IMAGE007
Wherein b is the thickness of the light screen (4), d is the width of the mounting area (3), and S2 is the vertical distance between the bottom of the light screen (4) and the bottom surface of the mounting area (3) when the second planar unit to be heated (2) has heating influence on the first planar unit to be heated (1);
3032, according to the test requirement, the heating influence length of the second plane unit to be heated (2) on the first plane unit to be heated (1)
Figure 433158DEST_PATH_IMAGE008
The formula in step 3031 is integrated to obtain,
Figure 383796DEST_PATH_IMAGE009
determining that the vertical distance S2 between the bottom of the light shielding plate (4) and the bottom surface of the mounting area (3) when the second planar unit to be heated (2) has heating influence on the first planar unit to be heated (1) is the vertical distance S between the bottom of the light shielding plate (4) inserted into the mounting area (3) and the bottom surface of the mounting area (3);
step four, determining an equivalent model: according to the installation position of the light shielding plates (4) determined in the third step, the light shielding plates (4) are inserted between two adjacent plane units to be heated, the plurality of light shielding plates (4) form a light shielding plate assembly inserted in the plane (8) to be heated, and an equivalent model is determined.
2. The equivalent model determination method for aerospace plane housing aerodynamic thermal environment simulation of claim 1, wherein: in the first step, the heating distance H is 50-80 mm.
3. The method for determining the equivalent model for aerospace plane housing aerodynamic thermal environment simulation according to claim 1, wherein: in the third step, in two adjacent planar units to be heated, the rectangular area between the top surface of one planar unit to be heated and the bottom surface of the heating planar unit (9) is set as a first transition area (5), the rectangular area between the top surface of the other planar unit to be heated and the bottom surface of the heating planar unit (9) is set as a second transition area (6), and the rectangular area between the first transition area (5) and the second transition area (6) is set as a mounting area (3).
4. The equivalent model determination method for aerospace plane housing aerodynamic thermal environment simulation of claim 1, wherein: in the third step, the thickness of the light shielding plate (4) is less than 1 mm.
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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106796305A (en) * 2014-09-29 2017-05-31 唯景公司 Sunlight intensity or cloud detection with variable range sensing
CN107844631A (en) * 2017-09-29 2018-03-27 北京空间机电研究所 A kind of remote sensor life cycle management orbit external thermal flux extreme operating condition accurate determination method
CN110688791A (en) * 2019-08-30 2020-01-14 中国航天空气动力技术研究院 Method for generating blunt body flow field laser adaptive structure grid
CN112415046A (en) * 2020-10-30 2021-02-26 同济大学 System and method for measuring longitudinal thermal diffusion coefficient of film based on medium detector
CN113642267A (en) * 2021-07-15 2021-11-12 中国空气动力研究与发展中心空天技术研究所 Aircraft surface front edge attachment line region extraction method
CN113901594A (en) * 2021-12-09 2022-01-07 中国空气动力研究与发展中心计算空气动力研究所 Intelligent prediction method for aerodynamic thermal environment on surface of aircraft
CN114527519A (en) * 2022-02-15 2022-05-24 上海华铭智能终端设备股份有限公司 Optical path deviation rectifying method of correlation type sensor and gate device
CN114528645A (en) * 2022-04-24 2022-05-24 中国空气动力研究与发展中心超高速空气动力研究所 Design method of hypersonic velocity aerodynamic thermal standard model for simulating three-dimensional complex flow

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11244095B2 (en) * 2019-05-31 2022-02-08 Livermore Software Technology Corporation Numerically estimating a pre-stamped shape of a workpiece used for manufacturing a product/part with deep draw metal stamping

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106796305A (en) * 2014-09-29 2017-05-31 唯景公司 Sunlight intensity or cloud detection with variable range sensing
CN107844631A (en) * 2017-09-29 2018-03-27 北京空间机电研究所 A kind of remote sensor life cycle management orbit external thermal flux extreme operating condition accurate determination method
CN110688791A (en) * 2019-08-30 2020-01-14 中国航天空气动力技术研究院 Method for generating blunt body flow field laser adaptive structure grid
CN112415046A (en) * 2020-10-30 2021-02-26 同济大学 System and method for measuring longitudinal thermal diffusion coefficient of film based on medium detector
CN113642267A (en) * 2021-07-15 2021-11-12 中国空气动力研究与发展中心空天技术研究所 Aircraft surface front edge attachment line region extraction method
CN113901594A (en) * 2021-12-09 2022-01-07 中国空气动力研究与发展中心计算空气动力研究所 Intelligent prediction method for aerodynamic thermal environment on surface of aircraft
CN114527519A (en) * 2022-02-15 2022-05-24 上海华铭智能终端设备股份有限公司 Optical path deviation rectifying method of correlation type sensor and gate device
CN114528645A (en) * 2022-04-24 2022-05-24 中国空气动力研究与发展中心超高速空气动力研究所 Design method of hypersonic velocity aerodynamic thermal standard model for simulating three-dimensional complex flow

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
Simulation calculation of thermal environment for hypersonic blunt cone;Zhang Chao;《Journal of Projectiles,Rocket,Missiles and Guidance》;20181231;全文 *
Stability Analysis of Different Stiffened Plates in Thermal-Mechanical Coupling Environment;Ma Liang;《Journey of Northwestern Polytechnical University》;20200201;全文 *
地球静止轨道太阳X-EUV成像仪探测器组件热控技术研究;吴愉华;《中国优秀硕士论文全文库 工程科技Ⅱ辑》;20190815;全文 *
基于数值仿真的接触式加热器优化设计;田敏;《工程与试验》;20220315;全文 *

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