Satellite-borne antenna surface thermal characteristic analysis equivalent processing method and system

Abstract

The application provides a kind of satellite antenna surface thermal characteristic analysis equivalent processing method and system, it is related to small satellite thermal control technical field, in the thermal design stage, waveguide gap is equivalent to process, waveguide gap surface is modeled, the ideal external heat flow of waveguide gap surface in-orbit absorption is calculated;In the test stage, the waveguide gap surface is equivalent to the flat structure without concave-convex structure, so that the external heat flow absorbed by the waveguide gap surface in the thermal balance test is equal to the ideal external heat flow absorbed in the orbit as the goal, the external heat flow density simulated by the external heat flow simulation device is calculated, and the external heat flow density is taken as the result of the satellite antenna surface thermal characteristic analysis equivalent processing;The application takes the waveguide with gap as the radiation unit of the satellite antenna surface, and more accurately obtains the size of the external heat flow actually received by the satellite heat dissipation surface by converting the thermal radiation properties of the waveguide surface, so as to accurately simulate the thermal environment of the satellite running in space, and improve the accuracy and effectiveness of the thermal balance test.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of small satellite thermal control, and particularly relates to a method and system for analyzing and processing surface thermal characteristics of a satellite antenna. BACKGROUND

[0002] The waveguide is an important component of the satellite antenna structure, and plays a role in transmitting electromagnetic waves in the antenna structure. The waveguide slot antenna has the advantages of high efficiency, high isolation and low cross polarization, but has the disadvantage of complex structure. The waveguide slot antenna on the satellite is generally a flat structure, and the waveguide surface faces the ground and is not shielded. The waveguide surface is generally selected as the heat dissipation surface of the satellite antenna, and the thermal radiation properties (absorptivity and emissivity) of the heat dissipation surface sprayed with a thermal control coating determine the overall temperature level of the satellite.

[0003] The thermal control system is an important service support system of the satellite, and its performance directly affects the performance, service life and reliability. The thermal balance test is a direct means to verify whether the thermal control design is correct, but it is expensive. The thermal environment of the satellite in space is relatively complex, and the external heat flux reaching and absorbed by the surface of the satellite includes three parts of solar radiation, earth reflection and earth infrared. In the thermal balance test, infrared devices such as infrared lamp arrays and infrared cages are usually used to simulate the external heat flux. However, the satellite flight attitude generally has a certain angle with the orbital plane, and the waveguide slot antenna itself has structures such as slots and concave-convex units, and the external heat flux reaching and absorbed by the surface of the waveguide slot antenna is relatively complex. The accuracy of the external heat flux calculation and the accuracy of the external heat flux simulated by the infrared method will directly affect the results of the thermal balance test. Therefore, the calculation and infrared conversion of the thermal radiation properties of the waveguide slot heat dissipation surface become a key method to solve this problem.

[0004] The surface unit size of the waveguide slot antenna structure is small and the shape is complex. In thermal design, the surface structure characteristics are generally ignored, and a planar structure is used instead. This method has the following defects:

[0005] 1. The waveguide unit has certain concave-convex structures, and there is a certain shielding between them. The waveguide has a certain slot ratio, which has a certain influence on the absorption and dissipation of the heat flux, so that there is a certain deviation between the external heat flux prediction in the thermal design and the actual on-orbit external heat flux.

[0006] 2. The simulated external heat flux in the ground thermal balance test is derived from simulation calculation, so the accuracy of the simulated external heat flux will affect the accuracy of the thermal balance test, and further affect the judgment of the performance indicators of the whole satellite.

[0007] Therefore, the existing thermal balance test method has deficiencies in accuracy and effectiveness when simulating the thermal environment of the satellite in space, which leads to the inability to accurately verify the thermal control design of the satellite, and ultimately affects the performance, service life and reliability of the satellite in space. SUMMARY

[0008] The present application proposes a satellite antenna surface thermal characteristic analysis equivalent processing method and system to solve the above problems, taking a waveguide with a slot as a radiating unit of a satellite antenna surface, and more accurately obtaining the actual external heat flow received by a satellite heat dissipation surface through conversion of the thermal radiation properties of the waveguide surface, so as to accurately simulate the thermal environment of the satellite in space operation and improve the accuracy and effectiveness of the thermal balance test.

[0009] According to some embodiments, the present application adopts the following technical solutions:

[0010] A satellite antenna surface thermal characteristic analysis equivalent processing method takes a waveguide slot surface including a plurality of waveguide units as a satellite antenna surface, and is divided into two stages:

[0011] In the thermal design stage, the waveguide slot is equivalent processed, the waveguide slot surface is modeled based on the absorptivity and emissivity of the waveguide slot surface and the slot ratio and structure size of each face of the waveguide unit, and the ideal external heat flow absorbed by the waveguide slot surface in orbit is calculated based on the equivalent absorptivity and equivalent emissivity of each face of the waveguide unit and the structure size.

[0012] In the test stage, the waveguide slot surface is equivalent to a flat plate structure without concave-convex structure, the effective area, equivalent slot ratio and effective emissivity of the flat plate structure are calculated, the target external heat flow simulated by the external heat flow simulation device is calculated with the goal that the external heat flow absorbed by the waveguide slot surface in the thermal balance test is equal to the ideal external heat flow absorbed in orbit, and the external heat flow density simulated by the external heat flow simulation device is calculated based on the target external heat flow, the effective area and the effective emissivity, and the external heat flow density is taken as the result of the satellite antenna surface thermal characteristic analysis equivalent processing.

[0013] According to some embodiments, the present application adopts the following technical solutions:

[0014] A satellite antenna surface thermal characteristic analysis equivalent processing system takes a waveguide slot surface including a plurality of waveguide units as a satellite antenna surface, and includes:

[0015] The thermal design module is configured to: equivalent process the waveguide slot, model the waveguide slot surface based on the absorptivity and emissivity of the waveguide slot surface and the slot ratio and structure size of each face of the waveguide unit, and calculate the ideal external heat flow absorbed by the waveguide slot surface in orbit based on the equivalent absorptivity and equivalent emissivity of each face of the waveguide unit and the structure size.

[0016] The test module is configured to: equivalent the waveguide slot surface to a flat plate structure without concave-convex structure, calculate effective area, equivalent slot ratio and effective emissivity of the flat plate structure, take the equalization of the external heat flow absorbed by the waveguide slot surface in the thermal balance test and the ideal external heat flow absorbed in orbit as a target, calculate the target external heat flow simulated by the external heat flow simulation device, based on the target external heat flow, the effective area and the effective emissivity, calculate the external heat flow density simulated by the external heat flow simulation device, and take the external heat flow density as the result of the equivalent processing of the surface thermal characteristic analysis of the satellite-borne antenna.

[0017] According to some embodiments, the present application adopts the technical scheme as follows:

[0018] A computer program product comprising a computer program which, when executed by a processor, implements the satellite-borne antenna surface thermal characteristic analysis equivalent processing method.

[0019] According to some embodiments, the present application adopts the technical scheme as follows:

[0020] A non-transitory computer-readable storage medium for storing computer instructions, which, when executed by a processor, implement the satellite-borne antenna surface thermal characteristic analysis equivalent processing method.

[0021] According to some embodiments, the present application adopts the technical scheme as follows:

[0022] An electronic device comprising a processor, a memory and a computer program, wherein the processor is connected to the memory, and the computer program is stored in the memory, and when the electronic device is running, the processor executes the computer program stored in the memory to make the electronic device execute the satellite-borne antenna surface thermal characteristic analysis equivalent processing method.

[0023] Compared with the prior art, the present application has the beneficial effects that:

[0024] 1. The present application proposes a satellite-borne antenna surface thermal characteristic analysis equivalent processing method and system, taking the waveguide with slots as the radiation unit of the satellite-borne antenna surface, comprehensively processing the two kinds of equivalent processing of the waveguide in the thermal design stage and the test stage, and more accurately obtaining the size of the external heat flow actually received by the satellite heat dissipation surface through the conversion of the thermal radiation properties of the waveguide surface, thereby improving the accuracy and efficiency of the test, saving time and cost, accurately simulating the thermal environment of the satellite running in space, and improving the accuracy and effectiveness of the thermal balance test.

[0025] 2. In the present application, the waveguide surface structure is complex, the complete concave-convex structure is considered in the thermal design stage, only the waveguide gap is equivalent, the complexity of simulation modeling is reduced, the calculation amount is reduced, the calculation accuracy is improved, the thermal analysis can be completed more quickly and accurately, the efficiency is improved and the time is saved.

[0026] 3. In the test, the waveguide surface is equivalent to a flat plate structure, and the waveguide gap is equivalent, which simplifies the calculation of infrared heat flow simulation and reduces the complexity of the test. BRIEF DESCRIPTION OF DRAWINGS

[0027] The accompanying drawings, which form a part of this specification, are included to provide a further understanding of the application, and are incorporated herein by reference. The embodiments illustrated in the drawings are intended to explain the present application and are not intended to limit the present application.

[0028] Figure 1 It is a waveguide surface structure diagram of example 1.

[0029] Figure 2 It is a schematic diagram of the placement position of the infrared heating cage of example 1.

[0030] Figure 3 It is a diagram of the change range of the track β angle of example 1.

[0031] Figure 4 It is a curve diagram of the total outflow of the waveguide surface absorption of example 1.

[0032] Figure 5 It is a curve diagram of the heat flow density value of example 1. DETAILED DESCRIPTION

[0033] The present application will be further described below in conjunction with the drawings and examples.

[0034] It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the present application. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present application belongs.

[0035] It should be noted that the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, the singular form is intended to include the plural form unless the context clearly indicates otherwise, and it should be understood that when the terms "comprise" and / or "comprising" are used in the specification, there is a presence of the features, steps, operations, devices, components and / or combinations thereof.

[0036] Example 1

[0037] An equivalent processing method for thermal characteristic analysis of a satellite antenna surface is provided in an embodiment of the present application, in which a waveguide slot surface composed of a plurality of waveguide units is taken as a satellite antenna surface, and the processing is divided into two stages:

[0038] In the thermal design stage, the waveguide slot is processed equivalently, the waveguide slot surface is modeled based on the absorptivity and emissivity of the waveguide slot surface and the slot ratio and structure size of each face of the waveguide unit, and the ideal external heat flow absorbed by the waveguide slot surface in orbit is calculated based on the equivalent absorptivity and equivalent emissivity of each face of the waveguide unit and the structure size.

[0039] In the test stage, the waveguide slot surface is equivalent to a flat plate structure without concave-convex structure, the effective area, equivalent slot ratio and effective emissivity of the flat plate structure are calculated, the target external heat flow simulated by the external heat flow simulation device is calculated with the goal that the external heat flow absorbed by the waveguide slot surface in the thermal balance test is equal to the ideal external heat flow absorbed in orbit, and the external heat flow density simulated by the external heat flow simulation device is calculated based on the target external heat flow, the effective area and the effective emissivity, which is taken as the result of the equivalent processing for thermal characteristic analysis of the satellite antenna surface.

[0040] The embodiment provides an equivalent processing method for thermal radiation property of a waveguide slot antenna heat dissipation surface and a conversion method for ground infrared heat flow, the actual external heat flow received by a satellite heat dissipation surface is more accurately obtained through conversion of the thermal radiation property of a surface radiation unit, the size of the simulated external heat flow in the thermal balance test in an infrared manner is more accurately calculated, the prediction accuracy in thermal design is improved, and the accuracy and effectiveness of the thermal balance test are improved, and the specific implementation process is as follows:

[0041] The waveguide slot surface is referred to as a waveguide surface, as shown in Figure 1 , the waveguide surface is composed of n units, A1, A2, A3 and A4 are four faces of each waveguide unit. A1 is a waveguide bottom face, and the corresponding slot ratio is ξ1; A2 is a left side face of a waveguide convex structure, and the corresponding slot ratio is ξ2; A3 is a waveguide top face, and the corresponding slot ratio is ξ3; A4 is a right side face of the waveguide convex structure, and the corresponding slot ratio is ξ4; the absorptivity of the waveguide surface coating is , and the emissivity is . The total width of the waveguide surface is a, the total length is b, the width of the waveguide bottom face, i.e. A1, in the waveguide unit is c, the height of the left side face, i.e. A2 and A4, in the waveguide unit is d, the width of the waveguide top face, i.e. A3, in the waveguide unit is e, and the height of the right side face, i.e. A4, in the waveguide unit is f, where ; these parameters are all set in the thermal design stage.

[0042] The external heat flux received by the waveguide slot surface in orbit includes solar radiation, earth albedo radiation and earth infrared radiation. When the satellite is in orbit, the satellite has a certain angle with the sun and the earth orbit plane. The external heat flux absorbed by the waveguide surface depends on the surface absorption rate, the emission rate and the relative position of the waveguide surface to the sun, the earth orbit plane and the earth, i.e. the angle coefficient.

[0043] Due to the complex structure of the waveguide surface, not only there are slots, but also the surface is uneven, and each surface has mutual shielding and radiation. If a detailed thermal model of the waveguide is established, the number of simulation model nodes is large and the calculation amount is huge. If the waveguide surface is equivalent to a flat structure and the uneven structure of the waveguide surface is ignored, although the model is simple and the calculation amount is small, the calculation result deviates greatly from the actual value. Therefore, how to reduce the calculation amount and improve the accuracy of the model calculation is a problem worth studying.

[0044] The waveguide is a thin-walled cavity structure, and the surface slot size is small. Solar radiation and earth infrared radiation enter the waveguide cavity through the slot and will be absorbed by multiple reflections. Therefore, the slot can be regarded as a black body, and the absorption rate and the emission rate are set to 1. In modeling, the waveguide surface is equivalent to a model with uneven structure, i.e. the waveguide slot is equivalent to the treatment, forming two different thermal control coatings: one is the equivalent black body of the slot part, and the other is the thermal control coating of the non-slot part itself.

[0045] The absorption rate of the waveguide surface coating is The emission rate is Then

[0046] The equivalent absorption rate of A1 surface is:

[0047] The equivalent emission rate of A1 surface is:

[0048] The equivalent absorption rate of A2 surface is:

[0049] The equivalent emission rate of A2 surface is:

[0050] The equivalent absorption rate of A3 surface is:

[0051] The equivalent emission rate of A3 surface is:

[0052] The equivalent absorption rate of A4 surface is:

[0053] The equivalent emission rate of A4 surface is:

[0054] The total external heat flux absorbed by the waveguide surface is as follows:

[0055] (1)

[0056] wherein, is the total external heat flux received by the surface of the heat dissipation surface; is the solar irradiance; is the average albedo of the celestial body; 、 、 are the solar radiation angle coefficients, the celestial body albedo radiation angle coefficients and the celestial body infrared radiation angle coefficients of each surface of the waveguide unit, respectively, and β is related to the angle (the angle between the sunlight and the orbital plane), the orbital height of the satellite and the relative position of the satellite to the sun and the earth (related to the flight attitude of the satellite).

[0057] Under the parameters of the absorptivity, the emissivity and the gap ratio set in the above thermal design stage, the ideal external heat flux absorbed by the waveguide gap surface in orbit is In order to better simulate the external heat flux in orbit, the target external heat flux to be provided by the external heat flux simulation device needs to be accurately calculated in the thermal balance test, so as to achieve the consistency of the test thermal environment and the in-orbit thermal environment.

[0058] When doing the thermal balance test in the ground vacuum environment, the commonly used external heat flux simulation device to simulate the external heat flux in orbit includes the solar simulator, the infrared heating cage, the infrared lamp array and the surface contact type electric heater. Considering the size of the vacuum tank, the time period and the cost, the uniformity of the heat flux, the test feasibility and other factors, the infrared heating cage is applied more, so the infrared heating cage is selected as the external heat flux simulation device in the embodiment; from the uniformity of the heat flux, in the test, the waveguide surface and the placement position of the infrared heating cage are relatively parallel, as shown in Figure 2 The external heat flux density simulated by the infrared heating cage is The external heat flux absorbed by the waveguide surface simulated by the infrared heating cage is:

[0059] (2)

[0060] In the formula, is the effective emissivity of the waveguide surface in the test; is the effective area of the waveguide surface in the test.

[0061] The areas, the equivalent absorptivity and the equivalent emissivity of each surface of the waveguide unit are different, so how to reasonably calculate the effective emissivity and the effective area directly affects the accuracy of the external heat flux density simulated by the infrared heating cage.

[0062] Since the waveguide surface is parallel to the infrared heating cage, which is different from the actual on-orbit state, the left and right sides (A2 and A4 surfaces) of the waveguide unit are perpendicular to the infrared heating cage and hardly receive infrared heat flow. The effective area for absorbing infrared heat flow is the bottom and top surfaces (A1 and A3 surfaces) of the waveguide unit. Therefore, the waveguide surface can be equivalent to a flat plate structure without concave-convex structure. After the equivalence, the effective area, equivalent gap ratio, and effective emissivity of the flat plate structure are calculated. Figure 1 Figure 1

[0063] The effective area is:

[0064] (3)

[0065] The equivalent gap ratio of the flat plate structure is:

[0066] (4)

[0067] The effective emissivity is:

[0068] (5)

[0069] In the experiment, the absorbed infrared heating cage simulates the total external heat flow in the on-orbit absorption, so:

[0070] (6)

[0071] According to formulas (1), (2), (3), (4), (5), and (6), the external heat flow density simulated by the infrared heating cage is:

[0072] (7)

[0073] A specific example is provided. The waveguide slot antenna size is a=384 mm, b=400 mm, c=14.6 mm, d=8 mm, e=9.4 mm, f=8 mm, and the number of waveguide units n=16. Therefore, the areas of the waveguide unit surfaces are M1=0.00584 m 2 , M2=0.0032 m 2 , M3=0.00376 m 2 , M4=0.0032 m 2 , M s =0.1536 m 2 .

[0074] The waveguide slot antenna is an aluminum alloy structure, and the surface treatment method is aluminum alloy bright anodic oxidation. The absorption rate is , and the emissivity is ​​The waveguide unit A1 surface aperture ratio is ξ1=0.12, the waveguide A2 surface aperture ratio is ξ2=0.1, the waveguide A3 surface aperture ratio is ξ3=0.15, and the waveguide A4 surface aperture ratio is ξ4=0.1.

[0075] After the equivalent treatment of the aperture, the equivalent absorptivity of each surface of the waveguide unit is calculated and the equivalent emissivity , and the following is obtained 0.34, =0.472; 0.325, =0.46; 0.3625, =0.49; 0.325, =0.46; =0.47905.

[0076] The satellite is in a sun-synchronous orbit at a distance of 500km from the ground, and the descending node local time is 18:00PM. The variation range of the orbit β angle in one year is as shown in Figure 3 , and the example takes β=-70°.

[0077] The average value of the earth albedo is a=0.3, the average value of the solar irradiance is S=1349W / m 2 , and the satellite flight attitude is left side view 30°.

[0078] A thermal simulation model of the waveguide aperture antenna is established in the thermal analysis software, the orbit parameters (including orbit height, β angle, earth albedo, solar irradiance, satellite flight attitude) are set, the material parameters and surface optical parameters (absorptivity and emissivity) of the waveguide are set, the satellite rotates around the earth, and the relative positions of the satellite, the sun and the earth change with the orbit period, and the total outflow of the waveguide surface in one orbit period is calculated and shown as Figure 4 .

[0079] The above parameters are brought into formula (7), and the heat flux density value required by the infrared heating cage can be obtained, as shown in Figure 5 .

[0080] Embodiment 2

[0081] In an embodiment of the present application, a satellite antenna surface thermal characteristic analysis equivalent processing system is provided, taking the waveguide aperture surface including a plurality of waveguide units as a satellite antenna surface, and comprising:

[0082] The thermal design module is configured to: equivalently process the waveguide slot, model the waveguide slot surface based on the absorptivity, emissivity of the waveguide slot surface and the slot ratio, structure size of each face of the waveguide unit, calculate the ideal external heat flux absorbed by the waveguide slot surface in orbit based on the equivalent absorptivity, equivalent emissivity and structure size of each face of the waveguide unit.

[0083] The test module is configured to: equivalently process the waveguide slot surface as a flat plate structure without concave-convex structure, calculate the effective area, equivalent slot ratio and effective emissivity of the flat plate structure, take the external heat flux absorbed by the waveguide slot surface in the thermal balance test equal to the ideal external heat flux absorbed in orbit as the target, calculate the target external heat flux simulated by the external heat flow simulation device, calculate the external heat flux density simulated by the external heat flow simulation device based on the target external heat flux, effective area and effective emissivity, and take the external heat flux density as the result of the equivalent processing of the surface thermal characteristic analysis of the satellite-borne antenna.

[0084] Embodiment 3

[0085] In an embodiment of the present application, a computer program product is provided, comprising a computer program, which, when executed by a processor, implements the surface thermal characteristic analysis equivalent processing method of a satellite-borne antenna.

[0086] Embodiment 4

[0087] In an embodiment of the present application, a non-transitory computer readable storage medium is provided, which is used to store computer instructions, and the computer instructions, when executed by a processor, implement the surface thermal characteristic analysis equivalent processing method of a satellite-borne antenna.

[0088] Embodiment 5

[0089] In an embodiment of the present application, an electronic device is provided, comprising a processor, a memory and a computer program; wherein the processor is connected with the memory, and the computer program is stored in the memory; when the electronic device is running, the processor executes the computer program stored in the memory, so that the electronic device implements the surface thermal characteristic analysis equivalent processing method of a satellite-borne antenna.

[0090] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks or in conjunction with the flowcharts described above. Figure 1 one or more functions specified in the flowchart block or blocks. Figure 1 one or more functions specified in the flowchart block or blocks.

[0091] These computer program instructions can also be loaded into a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks or in conjunction with the flowcharts described above. Figure 1 one or more functions specified in the flowchart block or blocks. Figure 1 one or more functions specified in the flowchart block or blocks.

[0092] The above description is only specific embodiments of the present application, and is not intended to limit the protection scope of the present application. Any modification or change made by those skilled in the art without departing from the technical solutions of the present application shall fall within the protection scope of the present application.

Claims

1. A method for equivalent processing of surface thermal characteristics analysis of a satellite-borne antenna, characterized in that, The waveguide slot surface including a plurality of waveguide units is taken as a spaceborne antenna surface, and is divided into two stages: In the thermal design stage, the waveguide slot is equivalently processed, the waveguide slot surface is modeled based on the absorptivity, emissivity of the waveguide slot surface and the slot ratio and structure size of each face of the waveguide unit, and the ideal external heat flow absorbed by the waveguide slot surface in orbit is calculated based on the equivalent absorptivity, equivalent emissivity and structure size of each face of the waveguide unit; In the test stage, the waveguide slot surface is equivalently processed as a flat plate structure without concave-convex structure, the effective area, equivalent slot ratio and effective emissivity of the flat plate structure are calculated, the target external heat flow simulated by the external heat flow simulation device is calculated with the equal external heat flow absorbed by the waveguide slot surface in the thermal balance test and the ideal external heat flow absorbed in orbit as the target, the external heat flow density simulated by the external heat flow simulation device is calculated based on the target external heat flow, the effective area and the effective emissivity, and the external heat flow density is taken as the equivalent processing result of the thermal characteristic analysis of the spaceborne antenna surface; The waveguide slot is equivalently processed, the waveguide is equivalently processed as a concave-convex structure without slot, and the equivalent absorptivity and equivalent emissivity of each face of the waveguide unit are calculated based on the absorptivity, emissivity of the waveguide slot surface and the slot ratio of each face of the waveguide unit; The ideal external heat flow absorbed by the waveguide slot surface in orbit is calculated, and is expressed by a formula as: in, The ideal external heat flux absorbed on the waveguide slot surface during orbit; Solar irradiance; The average albedo of a celestial body; , These are the waveguide units, numbered 1 and 2 respectively. The equivalent absorptivity and equivalent emissivity of each surface; 、 、 These are the waveguide units, numbered 1 and 2 respectively. The solar radiation angle coefficient of each facet, the celestial albedo radiation angle coefficient, and the celestial infrared radiation angle coefficient; For waveguide unit number The area of ​​each face. This represents the number of waveguide elements. The effective area, equivalent slot ratio and effective emissivity of the flat plate structure are calculated, and are expressed by a formula as: wherein, , , are effective area, equivalent slot ratio and effective emissivity, respectively, , are the width of the bottom and top surfaces of the waveguide, respectively, is the total length of the waveguide slot surface, , are the slot ratios of the bottom and top surfaces of the waveguide unit, , are the areas of the bottom and top surfaces of the waveguide unit, is the emissivity of the waveguide slot surface, is the number of waveguide units; The thermal simulation model of the waveguide slot antenna is established in the thermal analysis software, and the external heat flux density simulated by the external heat flux simulation device is calculated by using the functional relationship among the external heat flux density, the external heat flux, the effective area and the effective emissivity , and a calculation formula of the external heat flux density is obtained. wherein, is the external heat flux density simulated by the infrared heating cage, is the effective emissivity in the waveguide surface test, is the effective area in the waveguide surface test, is the external heat flux simulated by the infrared cage absorbed by the waveguide surface, is the solar irradiance; is the average albedo of the star; , are the equivalent absorptivity and equivalent emissivity of the waveguide unit No. th surface, respectively; 、 、 are the solar radiation angle coefficient, the star albedo radiation angle coefficient and the star infrared radiation angle coefficient of the waveguide unit No. th surface, respectively; is the area of the waveguide unit No. th surface, is the number of waveguide units; , are the width of the waveguide bottom surface and the waveguide top surface, respectively, is the total length of the waveguide gap surface, , are the gap proportion of the waveguide unit bottom surface and top surface, is the emissivity of the waveguide gap surface.

2. The method of claim 1, wherein the equivalent processing of the thermal characteristics of the antenna surface is performed by using a thermal analysis software. The waveguide slot surface is composed of a plurality of waveguide units, each waveguide unit includes a waveguide bottom surface, a waveguide left side surface, a waveguide top surface and a waveguide right side surface, and each face of the waveguide unit has a corresponding slot ratio.

3. The method of claim 1, wherein the method further comprises: determining a thermal equivalent of the antenna surface based on the thermal characteristics of the antenna surface. The waveguide slot surface is equivalently processed as a flat plate structure without concave-convex structure, and the waveguide unit is adjusted to be perpendicular to the external heat flow simulation device based on the position of the waveguide slot surface during the thermal balance test, and the external heat flow received by the left and right side surfaces is ignored.

4. A system for equivalent processing of thermal characteristics analysis of a satellite antenna surface, characterized in that, The waveguide slot surface including a plurality of waveguide units is taken as a spaceborne antenna surface, and includes: The thermal design module is configured to equivalently process the waveguide slot, model the waveguide slot surface based on the absorptivity, emissivity of the waveguide slot surface and the slot ratio and structure size of each face of the waveguide unit, and calculate the ideal external heat flow absorbed by the waveguide slot surface in orbit based on the equivalent absorptivity, equivalent emissivity and structure size of each face of the waveguide unit; The test module is configured to equivalently process the waveguide slot surface as a flat plate structure without concave-convex structure, calculate the effective area, equivalent slot ratio and effective emissivity of the flat plate structure, take the equal external heat flow absorbed by the waveguide slot surface in the thermal balance test and the ideal external heat flow absorbed in orbit as the target, calculate the target external heat flow simulated by the external heat flow simulation device, calculate the external heat flow density simulated by the external heat flow simulation device based on the target external heat flow, the effective area and the effective emissivity, and take the external heat flow density as the equivalent processing result of the thermal characteristic analysis of the spaceborne antenna surface. The waveguide slot is equivalently processed, the waveguide is equivalent to a concave-convex structure without a slot, and based on the absorptivity and emissivity of the waveguide slot surface and the slot proportion of each surface of the waveguide unit, the equivalent absorptivity and equivalent emissivity of each surface of the waveguide unit are calculated; The ideal external heat flow absorbed by the waveguide slot surface in orbit is calculated, and is expressed by a formula as: in, The ideal external heat flux absorbed on the waveguide slot surface during orbit; Solar irradiance; The average albedo of a celestial body; , These are the waveguide units, numbered 1 and 2 respectively. The equivalent absorptivity and equivalent emissivity of each surface; 、 、 These are the waveguide units, numbered 1 and 2 respectively. The solar radiation angle coefficient of each facet, the celestial albedo radiation angle coefficient, and the celestial infrared radiation angle coefficient; For waveguide unit number The area of ​​each face. This represents the number of waveguide elements. The effective area, equivalent slot proportion and effective emissivity of the flat plate structure are calculated, and are expressed by a formula as: wherein, , , are effective area, equivalent slot ratio and effective emissivity, respectively, , are the width of the bottom and top surfaces of the waveguide, is the total length of the waveguide slot surface, , are the slot ratios of the bottom and top surfaces of the waveguide unit, , are the areas of the bottom and top surfaces of the waveguide unit, is the emissivity of the waveguide slot surface, is the number of waveguide units; The thermal simulation model of the waveguide slot antenna is established in the thermal analysis software, and the external heat flux density simulated by the external heat flux simulation device is calculated by using the functional relationship among the external heat flux density, the external heat flux, the effective area and the effective emissivity , and a calculation formula of the external heat flux density is obtained. wherein, is the external heat flux density simulated by the infrared heating cage, is the effective emissivity in the waveguide surface test, is the effective area in the waveguide surface test, is the external heat flow simulated by the infrared cage absorbed by the waveguide surface, is the solar irradiance; is the average albedo of the star; , are the equivalent absorptivity and equivalent emissivity of the waveguide unit No. th surface, respectively; 、 、 are the solar radiation angle coefficient, the star albedo radiation angle coefficient and the star infrared radiation angle coefficient of the waveguide unit No. th surface, respectively; is the area of the waveguide unit No. th surface, is the number of waveguide units; , are the width of the waveguide bottom surface and the waveguide top surface, respectively, is the total length of the waveguide gap surface, , is the gap ratio of the waveguide unit bottom surface and top surface, is the emissivity of the waveguide gap surface.

5. A non-transitory computer-readable storage medium, comprising: The non-transitory computer readable storage medium is used for storing computer instructions, and the computer instructions are executed by a processor to realize the equivalent processing method for analyzing the thermal characteristics of a satellite antenna surface according to any one of claims 1-3.

6. An electronic device, comprising: Comprise: A processor, a memory and a computer program; wherein the processor is connected with the memory, the computer program is stored in the memory, and when the electronic device is running, the processor executes the computer program stored in the memory, so that the electronic device executes the equivalent processing method for analyzing the thermal characteristics of a satellite antenna surface according to any one of claims 1-3.

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