A thermal design method of a spaceborne active data-transmission antenna

Abstract

This invention discloses a thermal design method for a spaceborne active data transmission antenna, belonging to the field of remote sensing satellite thermal control. This invention solves the technical problems of rapid temperature rise during operation and high power consumption during non-operational periods in existing high-power antennas. The method includes: determining the antenna's permissible temperature range, heating power, single operating time, orbital period, and total number of orbits; selecting i different phase change materials with phase change temperatures all within the antenna's permissible temperature range; determining the material's thermal properties; calculating the required mass and volume of the phase change material based on the operating time; calculating the equivalent specific heat capacity; designing microchannel structure parameters based on the volume, with aluminum fins used for isolation between different channels; and verifying and optimizing using three-dimensional thermal simulation software. This invention employs a multi-stage phase change energy storage method that is purely passive. During operation, the multi-stage phase change materials relay heat absorption to reduce the temperature rise rate, and during non-operational periods, they solidify and release latent heat to maintain the temperature without active heating. The structure is simple and requires minimal resources.

Description

Technical Field

[0001] This invention relates to the technical field of thermal control for remote sensing satellites, specifically a thermal design method for a spaceborne active data transmission antenna. Background Technology

[0002] With the rapid development of low-Earth orbit (LEO) remote sensing satellite technology, onboard data transmission antennas are evolving towards higher power, higher integration, and intermittent operation. A typical LEO remote sensing satellite data transmission antenna needs to operate continuously for multiple orbits during a single overhead pass, with a single operational period reaching up to 300 seconds and generating over 200W of heat. Meanwhile, the non-operational period within the orbital cycle lasts for thousands of seconds. During operation, the antenna temperature rises sharply, potentially causing thermal shock or even damage to core components such as internal TR modules and power amplifier modules. Conversely, during non-operational periods, the antenna temperature drops rapidly, requiring the satellite's precious electrical energy for active heating compensation to maintain the components within permissible temperature ranges. These contradictions are particularly pronounced under high power consumption, short-cycle, and intermittent operation modes, becoming a key technical bottleneck restricting the performance improvement of onboard data transmission antennas.

[0003] To address the aforementioned issues, phase change energy storage technology, due to its passive nature and high heat storage density, is widely recognized as a key technological approach for solving the thermal control problems of intermittent high-power equipment. By absorbing heat during operation and releasing latent heat to maintain temperature during non-operational periods, phase change energy storage holds the promise of fundamentally reducing the temperature rise rate of antennas during operation and decreasing heat preservation power consumption during non-operational periods. In recent years, the academic and engineering communities have conducted extensive research on the application of phase change materials in the thermal control of spaceborne antennas. For example, patent CN115175544B proposes a transient heat dissipation structure based on phase change materials, which combines a heat spreader with a split phase change heat storage device. The phase change heat storage device consists of a metal shell, a metal frame, and phase change materials. During transient operation, the phase change materials absorb latent heat of phase change, solving the problem of heat diffusion from concentrated heat sources. Patent CN114264684A proposes a thermal analysis method for phase change energy storage structures based on equivalent specific heat capacity. By equating the latent heat value of the phase change material to its specific heat capacity and simulating the phase change process as a single-phase substance with a fixed specific heat capacity, it provides an effective analytical tool for the thermal design of phase change energy storage structures. The above research shows that the application prospects of phase change energy storage technology in the field of spaceborne antenna thermal control have been widely recognized.

[0004] However, existing technical solutions still have the following systemic defects, making it difficult for them to meet the engineering application requirements of high-power data transmission antennas under dynamic on-orbit conditions:

[0005] First, there is a lack of quantitative design methods that translate static design inputs into dynamic thermal loads. While existing technologies have proposed the application of phase change materials (PCMs) in thermal control, PCM selection still relies on empirical estimations. It is impossible to directly calculate the temperature points and quantities of each PCM based on static design inputs such as heating power, operating time, and permissible temperature range. This forces engineers to rely on repeated trial and error or excessive margins to ensure reliability in actual designs, making it difficult to achieve the engineering goal of "successful design on the first attempt."

[0006] Second, the spatiotemporal distribution characteristics of distributed heat sources are ignored. Existing technologies typically assume that heat sources are concentrated and uniformly heated, designing phase change energy storage devices as single-cavity or uniformly filled structures. However, actual data transmission antennas contain multiple distributed heat sources such as TR components, power amplifier modules, and power supply components. These components have different spatial locations, significantly different heating powers, and different operating sequences. Existing technologies lack a method to convert the dynamic characteristics of "spatial distribution of heat sources - differences in operating sequences - multiple cycles of heat accumulation" into a quantitative mapping method for phase change material temperature points - material usage - channel structure parameters, making it difficult for phase change energy storage devices to achieve precise matching with dynamic heat loads.

[0007] Third, a closed-loop balance model for heat storage and insulation cannot be established. Existing technologies mostly employ structural heat dissipation or active heating to address insulation issues during non-operational periods, failing to fully utilize the latent heat of solidification of phase change materials for insulation. While some solutions incorporate heating systems, the heating power consumption directly drains the satellite's electrical energy, and there is a lack of a closed-loop balance design between the heating amount and the heat dissipation during antenna non-operational periods. Existing technologies have failed to solve the matching problem between "heat storage during operation" and "heat dissipation during non-operational periods," leading to either insufficient heat storage causing low-temperature failures or excessive heat storage resulting in wasted mass / volume.

[0008] Fourth, there is a lack of verifiable reverse design processes. Existing technologies mostly employ a forward development model of "design first, verify later," requiring multiple simulation iterations and ground-based testing to verify the design results. This results in long development cycles and high costs. More importantly, ground-based testing cannot fully simulate the dynamic environment in orbit, leading to insufficient verification of design reliability on the ground and posing a risk of "not knowing until after launch." Current technologies have not yet formed a closed-loop design methodology encompassing thermal load analysis, response modeling, parameter optimization, structural design, and verification feedback, making it difficult to meet the stringent requirements of aerospace products achieving success on the first attempt and being non-repairable.

[0009] In summary, while existing technologies have recognized the application value of phase change energy storage technology in the field of spaceborne antenna thermal control, they lack a systematic method to transform the dynamic characteristics of heat source spatial distribution, operating timing differences, and multi-cycle heat accumulation into a quantitative design formula of "phase change material temperature point - material usage - channel structure parameters." Engineers cannot directly calculate the complete design scheme of the energy storage system based on static design inputs, leading to a design process that relies on empirical estimations and iterative iterations, making it difficult to simultaneously meet the multiple engineering requirements of temperature control during operation, insulation during non-operational periods, resource constraints, and feasibility verification. Summary of the Invention

[0010] The purpose of this invention is to provide a thermal design method for a spaceborne active data transmission antenna to solve the problems mentioned in the background art.

[0011] To achieve the above objectives, the present invention provides the following technical solution: A thermal design method for a spaceborne active data transmission antenna includes the following steps: S1: Determine the permissible temperature range for the antenna load. Heating power Duration of a single work session orbital period and total number of work laps ; S2: Select Different phase transition temperatures Phase change materials, and satisfy ,in ; S3: Determine the specific heat capacity of the liquid phase change material. Solid specific heat capacity Latent heat and density ; S4: Based on the working time of each antenna revolution Calculate the required mass of phase change material and volume Among them, quality Based on heating power Working hours and latent heat The calculated volume Based on quality and density Calculated; S5: Calculate the equivalent specific heat capacity of the phase change material at different temperatures. ; S6: Design the structural parameters of the microchannels according to the volume of the required phase change material. The microchannels are used to fill different phase change materials, and aluminum fins are used to isolate different channels. S7: Use 3D thermal simulation analysis software to verify and optimize the design results.

[0012] Furthermore, in step S2, the selection of the phase change material satisfies the following condition: when the data transmission antenna operates to the... If the temperature has reached thermal equilibrium or near-thermal equilibrium during the cycle, the amount of phase change material will not be increased further.

[0013] Furthermore, in step S4, the mass of the phase change material... The calculation formula is:

[0014] Volume of the i-th phase change material The calculation formula is:

[0015] Volume fraction of each phase change material in the total mass The calculation formula is: .

[0016] Furthermore, in step S4, the temperature range of the antenna during a single operation is divided according to the following rules:

[0017] in, This is the lower limit of the antenna's operating temperature. For the first Phase transition temperature of phase change materials This represents the upper limit of the antenna's operating temperature.

[0018] Furthermore, in step S5, when multiple phase change materials are used, the equivalent specific heat capacity of the composite phase change material is calculated according to the following formula:

[0019] in, For the first Mass fraction of phase change materials, For the first The phase transition range of phase change materials For the first The phase transition temperature of a phase change material For the first The latent heat of phase change in a certain phase change material.

[0020] Furthermore, in step S6, the structural parameters of the microchannel include height. ,width and length ,satisfy It employs multiple channels with consistent height across all channels.

[0021] Furthermore, in step S6, the outer wall thickness of the phase change energy storage device is... Greater than the channel spacing To enhance its mechanical and sealing properties.

[0022] Furthermore, step S8 is included: connecting the phase change energy storage device to the heat source of the data transmission antenna by fastening it with metal screws, and performing thermally conductive installation by filling the interface material, the interface material being selected from thermal grease, thermal gel or thermal pad.

[0023] Furthermore, the layout of the microchannels is designed non-uniformly based on the spatial distribution of the antenna's distributed heat sources. The phase transition temperature of the phase change material set in the high heat flux density region is lower than that of the phase change material set in the low heat flux density region.

[0024] Furthermore, based on the heat accumulation effect during multiple continuous operations, a stepped design is implemented for the amount of phase change material used in each cycle. The mass of phase change material in each cycle is calculated according to the following formula:

[0025] in, The equivalent heat capacity of the antenna structure, For the first The difference between the starting temperature of the circle and the lower limit of the permissible temperature.

[0026] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention achieves quantitative design from static input to dynamic heat load by establishing... The mass calculation formula directly links the three parameters of heat generation power, working time, and latent heat. Engineers can directly calculate the amount of multi-stage phase change material based on static design input, without relying on experience estimation or repeated trial and error, thus meeting the engineering requirement of "successful design on the first attempt" for aerospace products.

[0027] 2. Spatial matching between distributed heat sources and energy storage modules is achieved. This invention achieves precise matching between the spatial distribution of phase change materials and the spatial distribution of heat sources by using a non-uniform layout design of microchannels. According to the spatial distribution of distributed heat sources, materials with lower phase change temperature points are set in high heat flux density areas, and materials with higher phase change temperature points are set in low heat flux density areas. This significantly improves the heat absorption efficiency.

[0028] 3. Achieving thermal accumulation balance in multi-cycle continuous operation: This invention uses a multi-level phase change temperature point selection strategy and a stepped design formula to finely adjust the amount of phase change material used in each cycle based on the difference between the starting temperature and the lower limit of the permissible temperature for each cycle. This ensures that the heat generated in each cycle is absorbed by the corresponding phase change material, effectively avoiding the temperature increase caused by thermal accumulation.

[0029] 4. A closed-loop balance between heat storage and insulation is achieved. This invention adopts a purely passive energy storage scheme. During operation, each phase change material melts sequentially according to its temperature point and takes turns absorbing heat. During non-operation, the phase change material solidifies and releases latent heat to balance the environment and dissipate heat, thus achieving temperature self-sustaining. There is no need to consume satellite power for insulation, which significantly reduces the overall energy consumption of the satellite.

[0030] 5. Simple structure and low resource consumption: The present invention adopts a multi-channel + aluminum fin structure, which is flexible in layout. The pure passive solution does not require temperature sensors, heating belts and control circuits, resulting in low system complexity and high reliability. Attached Figure Description

[0031] Figure 1 A schematic diagram of a common satellite antenna operating mode for a thermal design method of a spaceborne active data transmission antenna provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the thermal design process of a thermal design method for a spaceborne active data transmission antenna provided in an embodiment of the present invention. Figure 3 This is a design effect diagram of an energy storage device for a thermal design method of a spaceborne active data transmission antenna provided in an embodiment of the present invention; Figure 4 A channel design diagram for a thermal design method of a spaceborne active data transmission antenna provided in an embodiment of the present invention; Figure 5 This is a schematic diagram illustrating the design results of a thermal design method for a spaceborne active data transmission antenna provided in an embodiment of the present invention. Figure 6 This is a schematic diagram of the thermal design power of a spaceborne active data transmission antenna provided in an embodiment of the present invention. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Example 1 Reference Figure 2This embodiment provides a thermal design method for a spaceborne active data transmission antenna. This method addresses the thermal control requirements of low-orbit remote sensing satellite data transmission antennas in short-cycle, high-power, and intermittent operation modes. It employs multi-stage phase change energy storage technology to control the temperature rise during antenna operation and reduce heating power consumption during non-operation periods in a purely passive manner.

[0034] 1. Determining the Input Parameters First, determine the thermal design input conditions for the antenna load. Specifically, this includes obtaining the permissible temperature range for the antenna load. For example, the permissible temperature range of a certain type of data transmission antenna is 10℃~30℃; obtain the heat generation power of the antenna during operation. For example, 200W; get the duration of a single work session. For example, 300s; obtain the orbital period. For example, 5700s; get the total number of work cycles. For example, 4 orbits. The above parameters are the inherent physical characteristics of the satellite and data transmission antenna. Generally, the operating mode of a low-Earth orbit remote sensing satellite data transmission antenna is to operate continuously for 4 orbits and then shut down. Here, the number of continuous operating orbits is designed as the maximum number of orbits during on-orbit operation (see...). Figure 1 (The commonly used satellite antenna operating modes are shown).

[0035] 2. Selection of multi-stage phase change materials Select based on work cycle Different phase transition temperatures The phase change material is selected, and it is ensured that each phase change temperature point is within the antenna's permissible temperature range. ( Specifically, when the data transmission antenna operates continuously for 4 cycles, three phase change materials with different phase transition temperature points are selected, denoted as materials m1, m2, and m3, with phase transition temperatures of 12℃, 16℃, and 20℃, respectively. When the data transmission antenna operates for the 4th cycle, if the temperature has reached thermal equilibrium or quasi-thermal equilibrium, the number and types of phase change materials need not be increased. Thermal equilibrium refers to the state where the heat generated and the heat dissipated by the antenna are equal during operation, and the temperature no longer changes with time. Quasi-thermal equilibrium refers to an approximate steady-state state where the antenna temperature change rate is less than a preset threshold (e.g., 0.5℃ / s). The selection of phase change materials should meet the requirements of high reliability and long cycle life, with paraffin-based materials being preferred due to their stable performance.

[0036] 3. Obtaining the thermophysical parameters of materials Determine the thermophysical properties of the selected phase change material, including its specific heat capacity in liquid state. Solid specific heat capacity Latent heat and density The material selected in this embodiment has the following physical properties: specific heat capacity in liquid state 2100 J / (kg·℃), specific heat capacity in solid state 2000 J / (kg·℃), latent heat 240 J / g, and density 0.7 g / cm³.

[0037] 4. Calculation of the amount and volume fraction of phase change material Based on the working time of each antenna revolution Calculate the required mass of phase change material and volume Specifically, the formula for calculating mass is:

[0038] in This refers to the antenna's heat dissipation power. For the first Working time per round This represents the latent heat of the corresponding phase change material. The volume calculation formula is:

[0039] Based on this, calculate the volume fraction of each material in the total mass:

[0040] In this embodiment, based on the antenna operating parameters (the longest single working time is 300s, and the continuous working time is 4 cycles), the total mass of the required phase change material is set to 240g, and the total volume is 168cm³.

[0041] Furthermore, the mass of the phase change material is calculated using the median of two phase change point temperatures, meaning the antenna's temperature range for a single operation is divided according to the following rules:

[0042] in, This is the lower limit of the antenna's operating temperature. For the first Phase transition temperature of phase change materials This represents the upper limit of the antenna's operating temperature.

[0043] 5. Calculation of equivalent specific heat capacity Calculate the equivalent specific heat capacity of phase change materials at different temperatures. This is used for subsequent thermal analysis modeling. When multiple phase change materials are used, the equivalent specific heat capacity of the composite phase change material is calculated according to the following formula:

[0044] in, For the first Mass fraction of phase change materials, For the first The phase transition range of phase change materials For the first The phase transition temperature of a phase change material For the first The latent heat of phase change in this phase change material. (This embodiment...) Take 1℃.

[0045] 6. Design of microchannel structure Design microchannel structures for filling different phase change materials based on the required phase change material volume. See Figure 2 The thermal design flow diagram shown is as follows: Figure 4 The diagram shows the channel design. The structural parameters of the microchannel include height. ,width and length ,satisfy Furthermore, the height of each channel remains consistent. (Microchannel height) The actual installation space is determined by the actual space available; in this embodiment, it is set to 10mm.

[0046] Phase change energy storage devices employ a multi-channel design to isolate different types of phase change materials, preventing cross-contamination and its impact on the phase change temperature. Specifically, aluminum fins are used between the internal channels of the phase change energy storage device to physically isolate different materials and enhance their heat exchange capacity. See [link to relevant documentation]. Figure 3 The diagram shows a design rendering of the energy storage device. The aluminum fins are made of high thermal conductivity materials such as aluminum alloy or copper alloy.

[0047] The outer wall thickness of the phase change energy storage device Generally larger than the channel spacing This is to enhance its mechanical and sealing properties. In this embodiment, the outer wall thickness is... Designed with a 2mm channel spacing The design is 1mm.

[0048] The overall design of the phase change energy storage device consists of a bottom stuffing box and a top end cap. After the stuffing is completed, a sealed body is formed by welding. High thermal conductivity materials such as aluminum alloy and copper alloy are preferred for the stuffing box.

[0049] 7. Simulation Verification The design results were verified and optimized using 3D thermal simulation analysis software, taking into account the satellite's external heat dissipation environment. (See [link to relevant documentation]). Figure 2 The diagram shows the thermal design process. During simulation verification, the external heat dissipation environment of the satellite needs to be considered for further verification calculations. Simulation boundary conditions include: an external satellite ambient temperature of -269℃ (space background temperature), a solar irradiance of 1367 W / m², and an antenna surface emissivity of 0.85.

[0050] 8. Installation of phase change energy storage devices The phase change energy storage device is connected to the heat source of the data transmission antenna using metal screws, and is installed with a thermally conductive interface material. The interface material can be in the form of thermal grease, thermal gel, or thermal pad to reduce contact thermal resistance and ensure that heat can be efficiently transferred from the heat source to the phase change energy storage device.

[0051] The thermal control system for the spaceborne active data transmission antenna designed through the above steps yields the following design results: Figure 5 As shown in the figure. Compared to the solution of simply increasing structural mass to increase heat capacity, this solution significantly reduces the rate and extent of temperature rise. Simultaneously, the reduced temperature control target leads to a significant decrease in antenna thermal control power, as shown in the figure. Figure 6 As shown.

[0052] Example 2 This embodiment is basically the same as Embodiment 1, except that the design parameters of the microchannel structure are optimized and the amount of phase change material is finely adjusted.

[0053] 1. Optimized design of microchannel structure In this embodiment, the height of the microchannel The width is set to 10mm due to space constraints during antenna installation. Different phase change materials correspond to different channel widths. The design is differentiated based on the volume fraction of each phase change material: for phase change materials with lower phase change temperatures, the amount used is relatively small, and the channel width is designed to be 8mm; for phase change materials with intermediate phase change temperatures, the amount used is moderate, and the channel width is designed to be 12mm; for phase change materials with higher phase change temperatures, the amount used is relatively large, and the channel width is designed to be 15mm. The length of each channel... Keep it consistent, both are 200mm.

[0054] 2. Parameter optimization of aluminum fins Thickness of aluminum fins The design is 1mm, with fin height and microchannel height... All fins are 10mm wide. The fin spacing is determined based on the channel width and heat exchange requirements, with the spacing between adjacent fins controlled between 3mm and 5mm. The aluminum fins undergo anodizing to improve their surface emissivity and enhance radiative heat transfer capabilities.

[0055] During four consecutive cycles of operation, the antenna's highest temperature was 28.5℃, below the permissible upper limit of 30℃; the lowest temperature was 12.5℃, above the permissible lower limit of 10℃. During non-operational periods, the antenna temperature was maintained by the latent heat released from the solidification of the phase change material. For a non-operational period of up to 5400 seconds, the antenna temperature remained above 10℃, eliminating the need to activate the active heating system.

[0056] The phase-change energy storage device designed in this embodiment has a total volume of 168 cm³ and a total mass of 240 g, meeting the volume and mass constraints of the antenna components for the entire satellite. The design results can be directly used for antenna structure fabrication without the need for subsequent iterative optimization.

[0057] Example 3 This embodiment is basically the same as Embodiment 1 and Embodiment 2, except that it adopts a non-uniform channel layout design to take into account the spatial distribution characteristics of the distributed heat source.

[0058] 1. Analysis of the spatial distribution of heat sources The data transmission antenna in this embodiment includes multiple TR components and a power amplifier module, with the heat sources spatially non-uniformly distributed. Specifically, the TR component density is higher and the heat generation power density is greater in the central region of the antenna, while the TR component density is lower and the heat generation power density is smaller in the edge region of the antenna. The operating timing of each heat source differs: the power amplifier module of the transmitting channel operates during transmission, and the TR component of the receiving channel operates during reception, with the two operating at overlapping times.

[0059] 2. Non-uniform channel layout design Based on the spatial distribution and operating sequence of the heat sources, the microchannels are designed with a non-uniform layout that matches the location of the heat sources. For the high heat flux density region at the center of the antenna, phase change materials with lower and intermediate phase change temperatures are used, with channel widths of 12mm and 15mm respectively, and the channel length covering the entire high heat flux density region. For the low heat flux density region at the antenna edge, only phase change materials with higher phase change temperatures are used, with a channel width of 8mm and the channel length determined based on the heat source distribution range.

[0060] 3. Differentiated design of aluminum fins To accommodate the varying heat flux densities in different regions, the thickness and spacing of the aluminum fins are designed differently. In high heat flux density regions, the fin thickness is designed to be 1.2 mm and the fin spacing to be 3 mm to enhance heat exchange capacity; in low heat flux density regions, the fin thickness is designed to be 0.8 mm and the fin spacing to be 5 mm to reduce structural weight.

[0061] Because the microchannel layout matches the spatial distribution of the heat source, the heat absorption efficiency of each phase change material is significantly improved. Compared with the uniform layout in Example 2, the maximum antenna temperature in this example is reduced by 2.3°C to 26.2°C; the total mass of the phase change material is reduced by 8% to 221g. Meanwhile, the temperature maintenance capability remains stable during non-operational periods, eliminating the need for an active heating system.

[0062] Example 4 This embodiment is basically the same as the previous embodiment, except that the amount of phase change material used in each cycle is designed in a stepwise manner to address the heat accumulation effect during multi-cycle continuous operation.

[0063] 1. Analysis of multiple cycles of secondary heat accumulation In this embodiment, the data transmission antenna operates continuously for four cycles, each cycle lasting 300 seconds, with an orbital period of 5700 seconds. During continuous operation, heat accumulates with each cycle, causing the antenna temperature to rise progressively. During the first cycle, the antenna's initial temperature is 10°C, rising to approximately 15°C upon completion. During the second cycle, the initial temperature is 15°C, rising to approximately 20°C upon completion. During the third cycle, the initial temperature is 20°C, rising to approximately 25°C upon completion. During the fourth cycle, the initial temperature is 25°C, rising to approximately 30°C upon completion.

[0064] 2. Stepped design of phase change material usage Based on the aforementioned heat accumulation pattern, a stepped design is implemented for the amount of phase change material used in each cycle. The mass of phase change material in each cycle is calculated using the following formula:

[0065] in, The equivalent heat capacity of the antenna structure, For the first The difference between the starting temperature of the circle and the lower limit of the permissible temperature.

[0066] Because the starting temperature is higher and the temperature rise space is smaller during the fourth cycle, the amount of heat absorbed in this cycle is relatively less, so the amount of fourth-stage phase change material is reduced accordingly. Specifically, in this embodiment, the amount of first-stage phase change material is 80g, the amount of second-stage phase change material (16℃) is 80g, and the amount of third-stage phase change material (20℃) is 60g, for a total mass of 220g.

[0067] During four consecutive cycles of operation, the temperature rise in each cycle was effectively absorbed by the corresponding phase change material, with the highest antenna temperature reaching 28.8°C. Compared to Example 1, this example demonstrates stronger temperature maintenance during non-operational periods. During a non-operational period of up to 5400 seconds, the antenna temperature remained consistently above 12°C, further reducing reliance on the active heating system.

[0068] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art can make various improvements and modifications without departing from the spirit and principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

[0069] Based on the above embodiments, the present invention also provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements the above-described functionality.

[0070] Those skilled in the art will recognize that the modules and method steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0071] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the devices, equipment, and modules described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0072] In addition, the functional modules in the various embodiments of the present invention can be integrated into one processing module, or each module can exist physically separately, or two or more modules can be integrated into one module.

[0073] If the aforementioned functions are implemented as software functional modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program instructions, such as USB flash drives, portable hard drives, read-only storage servers, random access storage servers, magnetic disks, or optical disks.

[0074] Furthermore, it should be noted that the combination of the various technical features in this case is not limited to the combination methods described in the claims of this case or the combination methods described in the specific embodiments. All technical features described in this case can be freely combined or combined in any way, unless they contradict each other.

[0075] It should be noted that the above examples are merely specific embodiments of the present invention, and the present invention is obviously not limited to the above embodiments, with many similar variations. All modifications that can be directly derived or conceived by those skilled in the art from the content disclosed in this invention should fall within the protection scope of this invention.

[0076] The above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A thermal design method for a spaceborne active data transmission antenna, characterized in that, Includes the following steps: S1: Determine the permissible temperature range for the antenna load. Heating power Duration of a single work session orbital period and total number of work laps ; S2: Select Different phase transition temperatures Phase change materials, and satisfy ,in ; S3: Determine the specific heat capacity of the liquid phase change material. Solid specific heat capacity Latent heat and density ; S4: Based on the working time of each antenna revolution Calculate the required mass of phase change material and volume Among them, quality Based on heating power Working hours and latent heat The calculated volume Based on quality and density Calculated; S5: Calculate the equivalent specific heat capacity of the phase change material at different temperatures. ; S6: Design the structural parameters of the microchannels according to the volume of the required phase change material. The microchannels are used to fill different phase change materials, and aluminum fins are used to isolate different channels. S7: Use 3D thermal simulation analysis software to verify and optimize the design results.

2. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, In step S2, the selection of the phase change material satisfies the following condition: when the data transmission antenna operates to the... If the temperature has reached thermal equilibrium or near-thermal equilibrium during the cycle, the amount of phase change material will not be increased further.

3. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, In step S4, the phase change material mass The calculation formula is: Volume of the i-th phase change material The calculation formula is: Volume fraction of each phase change material in the total mass The calculation formula is: 。 4. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, In step S4, the temperature range of the antenna during a single operation is divided according to the following rules: in, This is the lower limit of the antenna's operating temperature. For the first Phase transition temperature of phase change materials This represents the upper limit of the antenna's operating temperature.

5. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, In step S5, when multiple phase change materials are used, the equivalent specific heat capacity of the composite phase change material is calculated according to the following formula: in, For the first Mass fraction of phase change materials, For the first The phase transition range of phase change materials For the first The phase transition temperature of a phase change material For the first The latent heat of phase change in a certain phase change material.

6. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, In step S6, the structural parameters of the microchannel include height. ,width and length ,satisfy It employs multiple channels with consistent height across all channels.

7. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, In step S6, the outer wall thickness of the phase change energy storage device Greater than the channel spacing To enhance its mechanical and sealing properties.

8. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, The method also includes step S8: connecting the phase change energy storage device to the heat source of the data transmission antenna by means of metal screw fastening, and performing thermally conductive installation by filling the interface material, wherein the interface material is selected from thermal grease, thermal gel or thermal pad.

9. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, The layout of the microchannels is designed non-uniformly based on the spatial distribution of the antenna's distributed heat source. The phase transition temperature of the phase change material set in the high heat flux density region is lower than that of the phase change material set in the low heat flux density region.

10. The thermal design method for a spaceborne active data transmission antenna according to claim 1, characterized in that, Based on the heat accumulation effect during multi-cycle continuous operation, the amount of phase change material used in each cycle is designed in a stepped manner, and the mass of phase change material in each cycle is calculated according to the following formula: in, The equivalent heat capacity of the antenna structure, For the first The difference between the starting temperature of the circle and the lower limit of the permissible temperature.

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