Method for vacuum thermal test of super-large caliber antenna with whole satellite

Abstract

The application provides a method for vacuum thermal test of a super-large caliber antenna with a whole satellite, which comprises the following steps: arranging the satellite and the antenna in a vacuum tank, arranging the antenna on both sides of the satellite after being folded, arranging heating components at the heat dissipation surface of the satellite and the antenna to simulate external heat flow, adjusting the folding angle of the antenna according to the thermal radiation level of the surface of the satellite and the antenna, and performing vacuum thermal test on the satellite and the antenna after the adjustment. The method for vacuum thermal test of the super-large caliber antenna with the whole satellite can avoid batch test of the vacuum thermal test due to the size of the antenna, and can greatly shorten the test time and personnel arrangement by placing the antenna and the whole satellite in the tank, so that the purpose of shortening the development cycle and reducing the development cost is achieved.

Description

Technical Field

[0001] This invention relates to the field of satellite antenna vacuum thermal testing technology, specifically, to a method for conducting vacuum thermal testing of an ultra-large aperture antenna along with the entire satellite. Background Technology

[0002] Currently, one of the development trends for radar antennas is to increase the aperture to pursue performance. This is characterized by a uniform arrangement of components on the antenna. The antenna consists of multiple sub-boards with identical or similar configurations, and the aperture often reaches tens or even hundreds of meters, far exceeding the size of current vacuum tanks.

[0003] In current vacuum thermal tests of radar satellites, the satellite platform is typically placed in a seated position within a vacuum chamber, while the radar antenna is laid flat in an extended state, mirroring the satellite's actual on-orbit condition and simulating the temperature boundary between the two. However, when the radar antenna aperture exceeds the size of the vacuum chamber, it cannot be placed, requiring multiple tests. This significantly impacts the development process and cycle time, and is also costly, hindering the development needs of modern satellites.

[0004] To address the aforementioned issues, it is necessary to develop a simple and low-cost vacuum thermal testing method.

[0005] According to research, a method for thermal balance testing of multiple satellites in a single vacuum container is disclosed in Chinese patent document CN106275496B. The method proposes to install multiple satellites in a vacuum container and conduct thermal balance tests simultaneously. This method is based on the premise that the satellites are relatively small and two or more satellites can be placed side by side in the container. However, it has no practical guiding significance for the method of conducting vacuum thermal tests on ultra-large aperture antennas along with the entire satellite.

[0006] Chinese patent document CN111605742B discloses a method and system for multi-satellite vacuum thermal testing, which includes conducting vacuum thermal tests on multiple satellites simultaneously. It focuses on evaluating the thermal balance of each satellite with the inner cladding of the space environment model equipment. Two or more satellites can be placed inside the container. However, it has no practical guiding significance for the vacuum thermal testing method of ultra-large aperture antennas with the whole satellite.

[0007] Chinese patent document CN110171584B discloses a method for mass production of satellite constellation systems for vacuum thermal testing. This method involves placing multiple satellites simultaneously into a space environment simulation device and selecting thermal balance satellites and thermal vacuum satellites respectively. It can be widely used for vacuum thermal testing of multiple satellites simultaneously or in batches. However, it has no practical guiding significance for vacuum thermal testing of ultra-large aperture antennas along with the entire satellite.

[0008] Chinese patent document CN113665853A discloses a vacuum thermal testing method for satellite systems, including a feasibility theoretical analysis of conducting multi-satellite tests to explore the influencing factors of satellite temperature inside a vacuum chamber. However, the theoretical analysis is not instructive for thermal testing of antennas with apertures exceeding the size of the vacuum chamber. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method for conducting vacuum thermal tests on ultra-large aperture antennas along with the entire satellite.

[0010] According to the present invention, a method for vacuum thermal testing of an ultra-large aperture antenna with a satellite includes: arranging the satellite and the antenna in a vacuum container, with the antenna folded and arranged on both sides of the satellite, setting heating components to simulate external heat flow around the satellite and on the heat dissipation surface of the antenna, adjusting the folding angle of the antenna according to the heat radiation level of the satellite and the antenna surface, and then conducting a vacuum thermal test on the satellite and the antenna.

[0011] Preferably, the antenna includes two antenna sub-assemblies respectively disposed on both sides of the satellite. Each antenna sub-assembly is composed of multiple sub-unit boards spliced ​​sequentially. The two sub-unit boards closest to the satellite are placed horizontally above the satellite, and the remaining sub-unit boards are arranged in a "W" shape on both sides of the satellite. The antenna is supported by an antenna fixture disposed in a vacuum container.

[0012] Preferably, an aluminum plate is provided on the back of the antenna, and the aluminum plate is used to mount the load connecting the T / R assembly.

[0013] Preferably, the heating assembly includes an infrared heating cage and a heating substrate. The infrared heating cage is used around the satellite to simulate external heat flow, and the heating substrate is used at the heat dissipation surface of the antenna to simulate external heat flow.

[0014] Preferably, the method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 1 is characterized in that the back of the antenna is covered with a multi-layer heat insulation component by an aluminum plate.

[0015] Preferably, the sub-unit plate radiates heat to the vacuum tank. The angle between adjacent sub-unit plates is calculated based on the formula for calculating the radiative heat dissipation of each sub-unit plate's heat dissipation surface and the actual radiative heat dissipation obtained from simulation calculations.

[0016] Preferably, in the non-edge sub-unit plates of the antenna sub-assembly, the radiative heat dissipation of any two adjacent sub-unit plates is calculated in the following manner:

[0017] Step S1: Calculate the angle coefficient between the first sub-unit plate and the second sub-unit plate. In the formula, A1 is the area of ​​the first sub-unit plate, A2 is the area of ​​the second sub-unit plate, θ1 is the normal of the first sub-unit plate 101 micro-element, θ2 is the normal of the second sub-unit plate 102 micro-element, and r is the distance between the first sub-unit plate 101 micro-element and the second sub-unit plate 102 micro-element.

[0018] Step S2: Based on the fact that the areas of the first sub-unit plate and the second sub-unit plate are equal and interchangeable, we obtain A1 = A2, X 1,2 =X 2,1 The angular coefficient X of the first and second sub-unit plates with respect to the vacuum tank. 1,3 =X 2,3 =1-X 1,2 ;

[0019] Step S3: Use the network method for radiative heat transfer to solve for the effective radiation of the first and second sub-unit plates by solving the system of equations:

[0020]

[0021] in,

[0022] In the formula, J1 is the effective radiation of the first sub-unit plate, J2 is the effective radiation of the second sub-unit plate, ε1 is the infrared emissivity of the surface of the first sub-unit plate facing the second sub-unit plate, ε2 is the infrared emissivity of the surface of the second sub-unit plate facing the first sub-unit plate, and ε1=ε2, T1 is the temperature of the first sub-unit plate, T2 is the temperature of the second sub-unit plate, T3 is the temperature of the heat sink of the vacuum tank, and C0 is the blackbody radiation coefficient;

[0023] Since the temperatures of the first and second sub-unit plates are in the form of temperature fields, the integral method is used to solve the problem.

[0024] Step S4: Radiative heat transfer of the first sub-unit plate Radiative heat transfer of the second table unit panel

[0025] Preferably, the radiative heat dissipation of the outermost sub-unit plate in the antenna sub-assembly is calculated in the following manner:

[0026]

[0027] Where C0 is the blackbody radiation coefficient, and A 21 ε is the area of ​​the outermost sub-unit plate. 21 T represents the infrared emissivity of the outermost sub-unit plate. 21 This refers to the temperature of the outermost sub-unit plate.

[0028] Preferably, the two sub-unit boards closest to the satellite in the antenna sub-assembly, the satellite side, and the surface of the vacuum tank radiate heat to each other, and the radiated heat dissipation of each surface is calculated as follows:

[0029] Step A1: Calculate the angle coefficient X between every two adjacent faces. i,j , where X i,j Let represent the angle coefficient of the i-th face to the j-th face, and X i,i =0;

[0030] Step A2: Calculate the effective radiation J1 to J4 of each surface:

[0031]

[0032] Among them, J i Let A represent the effective radiation of the i-th surface. i Let be the area of ​​surface i, σ be the blackbody radiation constant, and T be the surface area of ​​surface i. i Let ε be the temperature of surface i. i Let i be the infrared emissivity of surface i;

[0033] Step A3: Calculate the radiative heat transfer on each surface.

[0034] Preferably, the radiative heat dissipation of the sub-unit board heat dissipation surface near the satellite in the antenna sub-assembly is calculated in the following manner:

[0035]

[0036] Where C0 is the blackbody radiation coefficient, and A 28 ε is the area of ​​the sub-unit plate closest to the satellite. 21 For the infrared emissivity of the heat dissipation surface of the sub-unit board near the satellite, T 21 This refers to the temperature of the sub-unit board closest to the satellite.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. This invention employs a method for vacuum thermal testing of an ultra-large aperture antenna along with the entire satellite, which avoids having to conduct the vacuum thermal test in batches due to the antenna size. By placing the antenna and the entire satellite in one container, the testing time and personnel allocation can be greatly reduced, thereby shortening the development cycle and reducing development costs.

[0039] 2. This invention employs a vacuum thermal test method for ultra-large aperture antennas carried by the entire satellite. By theoretically calculating the mutual thermal radiation effects between antenna sub-unit boards and between the satellite body and the antenna sub-unit boards, the folding angle of each sub-unit board is determined, ensuring the effectiveness of the vacuum thermal test.

[0040] 3. This invention employs a method for vacuum thermal testing of an ultra-large aperture antenna along with the entire satellite, providing a new approach to solving the problem of vacuum thermal testing methods for satellites and antennas that are too large to be fully deployed and would exceed the size envelope of the vacuum container.

[0041] 4. This invention meets the design requirements of simple design and fast development cycle, and has good reliability and flexible design.

[0042] Other beneficial effects of the present invention will be explained in detail through the introduction of specific technical features and technical solutions in specific embodiments. Those skilled in the art should be able to understand the beneficial technical effects brought about by these technical features and technical solutions through the introduction of these technical features and technical solutions. Attached Figure Description

[0043] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0044] Figure 1 This is a schematic diagram showing the placement of the satellite and antenna in the vacuum chamber during the vacuum thermal test of this invention;

[0045] Figure 2 This is a schematic diagram showing the angles of the first sub-unit plate and the second sub-unit plate in this invention.

[0046] Explanation of reference numerals in the attached figures:

[0047] Satellite 1 Second Subunit Board 22

[0048] Antenna 2 Third Subunit Board 23

[0049] Vacuum tank 3, fourth sub-unit plate 24

[0050] Infrared heating cage 4, fifth sub-unit board 25

[0051] Satellite tooling 5, sixth sub-unit board 26

[0052] Antenna fixture 6, seventh sub-unit board 27

[0053] Heating substrate 7 Eighth sub-unit board 28

[0054] Aluminum plate 8, first sub-unit plate 101

[0055] First sub-unit board 21 Second unit board 102 Detailed Implementation

[0056] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0057] This invention provides a method for vacuum thermal testing of ultra-large aperture antennas along with the entire satellite, referring to... Figure 1 As shown, the setup includes: arranging satellite 1 and antenna 2 in a vacuum chamber 3, with satellite 1 placed in a seated position within the chamber 3, and antenna 2 folded and arranged on either side of satellite 1. Heating components are installed around satellite 1 and at the heat dissipation surface of antenna 2 to simulate external heat flow. These heating components include an infrared heating cage 4 and a heating substrate 7. The infrared heating cage 4 simulates external heat flow around satellite 1, and the heating substrate 7 simulates external heat flow at the heat dissipation surface of antenna 2. This installation layout reduces mutual interference between satellite 1 and antenna 2. Satellite 1 is placed on a satellite fixture 5, and heating elements are attached to the fixture 5 to ensure temperature boundaries. The folding angle of antenna 2 is adjusted according to the heat radiation levels on the surfaces of satellite 1 and antenna 2. After adjustment, a vacuum thermal test is performed on satellite 1 and antenna 2.

[0058] The antenna 2 includes two antenna sub-assemblies respectively located on both sides of the satellite. Each antenna sub-assembly is composed of multiple sub-unit boards spliced ​​together in sequence. The two sub-unit boards closest to the satellite are placed horizontally above the satellite 1, and the remaining sub-unit boards are arranged in a "W" shape on both sides of the satellite. The antenna 2 is supported by the antenna fixture 6 located inside the vacuum tank.

[0059] Each antenna sub-assembly is composed of eight sub-unit boards assembled sequentially, starting from the outermost side: the first sub-unit board 21, the second sub-unit board 22, the third sub-unit board 23, the fourth sub-unit board 24, the fifth sub-unit board 25, the sixth sub-unit board 26, the seventh sub-unit board 27, and the eighth sub-unit board 28. The eighth sub-unit board 28 is placed horizontally on top of the satellite, and the second and seventh sub-unit boards (22 to 27) are folded at the same angle. The first sub-unit board 21 is located on the outermost side of the antenna 2.

[0060] An aluminum plate 8 is provided on the back of the antenna 2. The aluminum plate 8 is used to install the load connecting the T / R assembly and to prevent the heat sink from occupying space inside the tank. The back of the antenna 2 is covered with a multi-layer heat insulation assembly through the aluminum plate.

[0061] The folding angle of antenna 2 has a significant impact on its heat dissipation capability. The smaller the folding angle of antenna 2, the greater the heat dissipation obstruction between two adjacent antennas 2. When the angle is less than a certain value, the heat of antenna 2 cannot be dissipated in time, affecting the performance of antenna 2. The sub-unit board of this invention radiates heat to the vacuum tank. Based on the calculation formula of the radiated heat dissipation amount of each sub-unit board's heat dissipation surface, combined with the actual radiated heat dissipation amount obtained from simulation calculations, the included angle between adjacent sub-unit boards is calculated.

[0062] In the second to seventh sub-unit boards (22-27) of the antenna sub-assembly, any two adjacent sub-unit boards are designated as the first sub-unit board 101 and the second sub-unit board 102, respectively, referring to... Figure 2 As shown, the radiative heat dissipation of the two sub-unit boards is calculated as follows:

[0063] Step S1: Calculate the angle coefficient between the first sub-unit plate 101 and the second sub-unit plate 102. In the formula, A1 is the area of ​​the first sub-unit plate 101, A2 is the area of ​​the second sub-unit plate 102, θ1 is the normal of the micro-element of the first sub-unit plate 101, θ2 is the normal of the micro-element of the second sub-unit plate 102, and r is the distance between the micro-element of the first sub-unit plate 101 and the micro-element of the second sub-unit plate 102, or the Monte Carlo method can be used for calculation.

[0064] Step S2: Based on the fact that the areas of the first sub-unit plate 101 and the second sub-unit plate 102 are equal and interchangeable, we obtain A1 = A2, X 1,2 =X 2,1 The angular coefficient X of the first sub-unit plate 101 and the second sub-unit plate 102 with respect to the vacuum tank 1,3 =X 2,3 =1-X 1,2 ;

[0065] Step S3: Use the network method for radiative heat transfer to solve for the effective radiation of the first sub-unit plate 101 and the second sub-unit plate 102 by solving the system of simultaneous equations:

[0066]

[0067] in,

[0068] In the formula, J1 is the effective radiation of the first sub-unit plate 101, J2 is the effective radiation of the second sub-unit plate 102, ε1 is the infrared emissivity of the surface of the first sub-unit plate 101 facing the second sub-unit plate 102, ε2 is the infrared emissivity of the surface of the second sub-unit plate 102 facing the first sub-unit plate 101, and ε1=ε2, T1 is the temperature of the first sub-unit plate 101, T2 is the temperature of the second sub-unit plate 102, T3 is the temperature of the heat sink of the vacuum tank, generally ≤100K, and C0 is the blackbody radiation coefficient, with a value of 5.67W / (m²). 2 ·K 4 );

[0069] Since the temperatures of the first sub-unit plate 101 and the second sub-unit plate 102 are in the form of temperature fields, the integral method is used to solve the problem.

[0070] Step S4: Radiative heat transfer of the first sub-unit plate 101 The radiative heat transfer of the second unit panel 102

[0071] In its original state, antenna 2 is fully extended and laid flat, consistent with or similar to the simulation and on-orbit state, and the vacuum thermal experiment can represent the real state. The method proposed in this invention, however, suffers from the "W"-shaped arrangement of antenna 2, where the two antenna sub-plates obstruct each other due to their angular coefficients, making it unrepresentative of the real state and posing a risk of insufficient heat dissipation. Calculating the radiated heat dissipation is significant because it reveals the actual heat dissipation capacity of each antenna plate when the antenna is arranged in a "W" shape; the heat dissipation capacity varies at different angles. In step S3, T1, T2, T3, and in step S4, the radiated heat transfer φ1, φ2 are known conditions (which can be obtained through simulation calculations when the antenna is laid flat). By solving the system of equations, the angular coefficients are obtained, and the calculation returns to step S1 to calculate the angle θ between the surfaces.

[0072] In a specific implementation case, the temperature of a single antenna sub-unit board is -10 to 30℃. If the temperature exceeds 30℃, the antenna risks failing to dissipate heat. Therefore, in step S3, T1 and T2 are both taken as the average temperature of -10 to 30℃, which is 10℃, or 283.15K (E can also be obtained by integrating the temperature field from the squared result). b1 and E b2 T3 = 100K, therefore E b3 φ1 and φ2 represent the radiative heat dissipation in the flat position, which can be calculated using temperature, emissivity, and area. Returning to step S2, we obtain X. 1,2 =X 2,1=0.74, returning to step S1, we obtain an angle ≥15°. Clearly, the larger the angle, the stronger the radiative heat dissipation, because the heat from the increased angle can be compensated by applying external heat flow through the infrared heating cage and the heating substrate. Therefore, the preferred angle is ≥15°. According to basic heat transfer principles, once the second sub-unit board 22 to the seventh sub-unit board 27 meet the radiation requirements, the remaining first sub-unit board 21, the seventh sub-unit board 27, and the eighth sub-unit board 28 will definitely meet the radiation requirements. The radiation situation of the remaining sub-unit boards will be solved below.

[0073] The radiated heat dissipation of the outermost first sub-unit plate 21 in the antenna sub-assembly is calculated as follows:

[0074]

[0075] Where C0 is the blackbody radiation coefficient, and A 21 Let ε be the area of ​​the first sub-unit plate 21. 21 T represents the infrared emissivity of the outer surface of the first sub-unit board 21. 21 The temperature of the first sub-unit plate 21.

[0076] The seventh subunit plate 27, the eighth subunit plate 28, the side of satellite 1, and the surface of the vacuum tank in the antenna subassembly radiate heat to each other. The calculation method for the radiated heat dissipation of these four surfaces is as follows:

[0077] Step A1: Calculate the angle coefficient X between every two adjacent faces. i,j , where X i,j Let represent the angle coefficient of the i-th face to the j-th face, and

[0078] Step A2: Calculate the effective radiation J1 to J4 of each surface:

[0079]

[0080] Among them, J i Let A represent the effective radiation of the i-th surface. i Let be the area of ​​surface i, σ be the blackbody radiation constant, and T be the surface area of ​​surface i. i Let ε be the temperature of surface i. i Let i be the infrared emissivity of surface i;

[0081] Step A3: Calculate the radiative heat transfer on each surface.

[0082] The radiated heat dissipation of the sub-unit board surface near the satellite in the antenna sub-assembly is calculated as follows:

[0083]

[0084] Where C0 is the blackbody radiation coefficient, and A 28 ε is the area of ​​the sub-unit plate closest to the satellite. 21 For the infrared emissivity of the heat dissipation surface of the sub-unit board near the satellite, T 21 This refers to the temperature of the sub-unit board closest to the satellite.

[0085] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for vacuum thermal testing of an ultra-large aperture antenna along with a satellite, characterized in that, include: The satellite and antenna are arranged in a vacuum container. The antenna is folded and arranged on both sides of the satellite. Heating components are set around the satellite and on the heat dissipation surface of the antenna to simulate external heat flow. The folding angle of the antenna is adjusted according to the heat radiation level of the satellite and antenna surface. After adjustment, a vacuum thermal test is carried out on the satellite and antenna.

2. The method for vacuum thermal testing of ultra-large aperture antennas with a whole satellite according to claim 1, characterized in that, The antenna includes two antenna sub-assemblies respectively located on both sides of the satellite. Each antenna sub-assembly is composed of multiple sub-unit boards spliced ​​together in sequence. The two sub-unit boards closest to the satellite are placed horizontally above the satellite, while the remaining sub-unit boards are arranged in a "W" shape on both sides of the satellite. The antenna is supported by an antenna fixture located inside a vacuum container.

3. The method for vacuum thermal testing of ultra-large aperture antennas with a whole satellite according to claim 1, characterized in that, An aluminum plate is provided on the back of the antenna, and the aluminum plate is used to mount the load connecting the T / R assembly.

4. The method for vacuum thermal testing of ultra-large aperture antennas with a whole satellite according to claim 1, characterized in that, The heating assembly includes an infrared heating cage and a heating substrate. The infrared heating cage is used around the satellite to simulate external heat flow, and the heating substrate is used at the heat dissipation surface of the antenna to simulate external heat flow.

5. The method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 1, characterized in that, The back of the antenna is covered with an aluminum plate and multiple layers of heat insulation components.

6. The method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 2, characterized in that, The sub-unit plates radiate heat to the vacuum tank. Based on the calculation formula for the radiative heat dissipation of each sub-unit plate's heat dissipation surface, and combined with the actual radiative heat dissipation obtained from simulation calculations, the included angle between adjacent sub-unit plates is calculated.

7. The method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 6, characterized in that, In the non-edge sub-unit plates of the antenna sub-assembly, the radiative heat dissipation of any two adjacent sub-unit plates is calculated as follows: Step S1: Calculate the angle coefficient between the first sub-unit plate and the second sub-unit plate. In the formula, A1 is the area of ​​the first sub-unit board, and A2 is the area of ​​the second sub-unit board. The normal direction of the first sub-unit board 101 micro-element. denoted as the normal of the second sub-unit plate 102 micro-element, and r is the distance between the first sub-unit plate 101 micro-element and the second sub-unit plate 102 micro-element; Step S2: Based on the fact that the areas of the first sub-unit board and the second sub-unit board are equal and interchangeable, we obtain... , The angular coefficients of the first and second sub-unit plates with respect to the vacuum tank. ; Step S3: Use the network method for radiative heat transfer to solve for the effective radiation of the first and second sub-unit plates by solving the system of equations: in, , , ; In the formula, For the effective radiation of the first sub-unit board, For the effective radiation of the second sub-unit board, The infrared emissivity of the surface of the first sub-unit board facing the second sub-unit board. The infrared emissivity of the second sub-unit board facing the surface of the first sub-unit board, and , The temperature of the first sub-unit board. The temperature of the second sub-unit plate. The temperature of the heat sink in the vacuum tank. The blackbody radiation coefficient; Since the temperatures of the first and second sub-unit plates are in the form of temperature fields, the integral method is used to solve the problem. , ; Step S4: Radiative heat transfer of the first sub-unit plate The radiative heat transfer of the second table unit panel .

8. The method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 6, characterized in that, The radiated heat dissipation of the outermost sub-unit plate in the antenna sub-assembly is calculated as follows: in, Let A be the blackbody radiation coefficient. 21 The area of ​​the outermost sub-unit plate. The infrared emissivity of the outermost sub-unit plate. This refers to the temperature of the outermost sub-unit plate.

9. The method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 2, characterized in that, The antenna subassembly features heat dissipation through mutual radiation from the back of the two sub-unit boards closest to the satellite, the side of the satellite, and the surface of the vacuum tank. The heat dissipation from each surface is calculated as follows: Step A1: Calculate the angle coefficient between every two adjacent faces. ,in, Indicates the first i The first one to face j The angle coefficients of each face, and , ; Step A2: Calculate the effective radiation of each surface : in, Indicates the first i Effective radiation from each surface For noodles i area, Let be the blackbody radiation constant. For noodles i temperature, For noodles i Infrared emissivity; Step A3: Calculate the radiative heat transfer on each surface. .

10. The method for vacuum thermal testing of an ultra-large aperture antenna with a whole satellite according to claim 6, characterized in that, The radiative heat dissipation of the sub-unit board heat dissipation surface near the satellite in the antenna sub-assembly is calculated as follows: in, Let A be the blackbody radiation coefficient. 28 The area of ​​the sub-unit panel closest to the satellite, For the infrared emissivity of the heat dissipation surface of the sub-unit board near the satellite, This refers to the temperature of the sub-unit board closest to the satellite.

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