Satellite antenna structure and low-temperature precision machining method thereof

Abstract

This invention relates to the field of aerospace satellite structural components and manufacturing technology, specifically a satellite antenna structural component and its cryogenic precision machining method. The structural component includes a support plate, on which a mounting frame is fixed. Two partition plates are fixed at equal intervals within the mounting frame, dividing the frame into three isolation chambers. An adaptive clamping mechanism is installed within each isolation chamber. The method includes the following steps: rough blank pretreatment and reference positioning, cooling equipment adjustment, rough milling, cryogenic stress relief, cryogenic precision machining, rewarming and settling, and matching installation. This invention provides a support component for mounting satellite antenna parts, capable of fully loading the corresponding satellite antenna parts while ensuring gas flow for efficient heat dissipation during operation. It also provides a cryogenic machining solution for the support component, effectively improving the machining quality of the structural component.

Description

Technical Field

[0001] This invention relates to the field of aerospace satellite structural components and manufacturing technology, and in particular to a satellite antenna structural component and its low-temperature precision machining method. Background Technology

[0002] Active phased array satellite communication antennas are the culmination of electronic systems, consisting of a large number of active components and devices. As the miniaturization and integration of active components continue to improve, the assembly density, power consumption and heat load of their power components are rapidly increasing, resulting in a rapid increase in the power consumption and heat flux density of the array surface, which poses a severe challenge to thermal control technology.

[0003] A miniaturized satellite communication antenna main support structure with high heat dissipation, disclosed in announcement number CN115241624B, employs a composite heat dissipation structure combining a vapor chamber and isolated open-type air cooling. It includes an A-frequency transmitting antenna mounting area, an A-frequency receiving antenna mounting area, and a B-frequency antenna mounting area. The portions of the main support structure corresponding to these three areas utilize a vapor chamber structure. The A-frequency transmitting and receiving antenna mounting areas correspond to the first circulation chamber of the vapor chamber, while the B-frequency antenna mounting area corresponds to the second circulation chamber. The main support structure outside the first and second circulation chambers is constructed of a solid metal plate. Isolated open-type air cooling channels are installed on the exterior of the vapor chamber and on the solid metal plate between the A-frequency transmitting and receiving antenna mounting areas. This invention utilizes a composite heat dissipation technology combining a vapor chamber and isolated open-type air cooling, solving the thermal control problem of satellite communication antennas. It is lightweight, load-bearing, has rapid heat dissipation, high strength, and excellent resistance to harsh environments.

[0004] The above technical solution uses two circulation chambers for classified installation and a solid metal plate as the main supporting structure. Its hardness and load-bearing capacity meet the usage requirements. However, it does not have an elastic pre-tightening structure, which cannot fully accommodate processing deviations. Moreover, conventional solid metal plates cannot quickly and uniformly dissipate heat. At the same time, there is currently no matching low-temperature precision machining method for tooling, making it difficult to simultaneously solve the three major engineering pain points: residual stress during tooling forming, surface machining accuracy, and sealing stability under low-temperature conditions. Therefore, improvements are needed. Summary of the Invention

[0005] The purpose of this invention is to address the shortcomings of existing technologies by proposing a satellite antenna structural component and its low-temperature precision machining method.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A satellite antenna structural component includes a carrier plate, on which a mounting frame is fixed. Two partitions are fixed at equal intervals within the mounting frame, dividing the mounting frame into three isolation cavities. An adaptive clamping mechanism is installed within each isolation cavity.

[0008] The bottom of the isolation chamber is provided with multiple U-shaped grooves and multiple flow guide grooves at equal intervals; the U-shaped grooves and the partition are arranged perpendicularly, the flow guide grooves and the partition are arranged parallelly, and the flow guide grooves and the U-shaped grooves are arranged alternately.

[0009] The bottoms of the flow guide groove and the loop groove are on the same horizontal plane;

[0010] Multiple through-holes are evenly spaced on the side walls of the guide channel and the U-shaped channel. Two through-holes arranged in an alternating manner are connected by a ventilation port, which is located on the support plate.

[0011] Compared with the prior art, the present invention is a carrier for mounting satellite antenna components, which can fully load the corresponding satellite antenna components, while ensuring gas flow during operation for efficient heat dissipation. It also provides a low-temperature processing solution for the carrier, which can effectively improve the processing quality of the structural components.

[0012] Preferably, the adaptive clamping mechanism includes four notches formed in the four walls of the isolation cavity;

[0013] A horizontal shaft is fixed inside the notch, and two round tubes are slidably mounted on the horizontal shaft. An inclined plate is rotatably connected to each of the two round tubes. A gear is mounted on the front end of the two inclined plates, and an abutment plate is mounted on the gear.

[0014] Both ends of the horizontal shaft are fitted with springs, and the two ends of the springs are fixed to the horizontal shaft and the round tube respectively.

[0015] Furthermore, in actual production, the horizontal shaft and the inner wall of the notch are clamped by bolts and other components. That is, holes are opened on the opposite side walls inside the notch to facilitate the subsequent installation and fixing of the horizontal shaft. At the same time, spring components and round tube components are set on the horizontal shaft. The round tube components can be moved by the spring components so that the round tube components can move on the spring components.

[0016] Meanwhile, the gear assembly consists of two meshing gears and a frame for mounting the two gears. The frame is fixedly connected to the contact plate, and the two gears are fixedly connected to the two inclined plates respectively. The reverse operation between the two gears can cause the two inclined plates to operate in opposite directions, which can control the position of the contact plate and the isolation cavity, and can also fully contact the outside of the satellite antenna component to fix the satellite antenna component.

[0017] Preferably, multiple heat dissipation plates are fixed at equal intervals around the perimeter of the mounting frame; one end of each heat dissipation plate penetrates through the support plate and is flush with the inner wall of the support plate.

[0018] Furthermore, the heat dissipation plate can absorb the heat dissipated by the satellite antenna components inside the mounting frame. The heat dissipation plate and the mounting frame can effectively increase the surface area on the outside of the mounting frame to improve heat dissipation efficiency. At the same time, one end of the support plate is flush with the inner wall of the mounting frame to avoid damage to the satellite antenna components.

[0019] Preferably, the upper end of the partition is provided with a plurality of grooves at equal intervals, and a through groove is provided between two adjacent grooves; the two through grooves at both ends are provided through the mounting frame.

[0020] Furthermore, the combination of grooves and through slots enables gas flow, and during processing, the through slots can connect to the mounting frame, improving heat dissipation efficiency.

[0021] Preferably, the groove extends through both ends.

[0022] Furthermore, the through-type design allows the grooves to be connected, meaning the lower end of the baffle is also opened up, allowing gas to flow within the grooves and guide channels.

[0023] Preferably, the staggered positions of the meander groove and the guide groove are arranged in an arc shape.

[0024] Furthermore, the U-shaped grooves and guide grooves can form staggered channels, which pass through the mounting frame and enable gas flow. At the same time, the channels are evenly distributed at the bottom of the mounting frame, which can effectively contact the satellite antenna components installed in the mounting frame, so as to achieve heat dissipation and cooling of the lower end of the satellite antenna components. Meanwhile, the edges are processed into arc shapes to avoid direct collisions.

[0025] Furthermore, in actual production and processing, the lower ends of the spiral groove and the guide groove do not need to be set in the same horizontal plane. At the same time, the depth of the spiral groove is greater than the depth of the guide groove, which allows the gas to flow better. The flow of gas can effectively remove the high temperature generated by the satellite antenna components during operation.

[0026] This invention also proposes a low-temperature precision machining method for satellite antenna structural components, applicable to the aforementioned satellite antenna structural component, comprising the following steps:

[0027] S1. Pre-treatment and datum positioning of rough blank: blank blank is cut, upper and lower datum planes are rough milled, and finishing allowance is reserved; the rough blank is placed in a constant temperature pre-treatment furnace to eliminate forging stress; the rough blank is clamped and a flexible pad is set to isolate it from the clamping fixture to avoid the influence of rigid clamping on the rough blank; the outline structure of the rough blank is fully entered.

[0028] S2. Cooling equipment adjustment: Install liquid nitrogen cooling equipment on the machining center equipment and control the nozzles to achieve full spraying of the rough blank; preheat the machining center equipment to eliminate temperature difference deformation caused by low temperature;

[0029] S3, Rough Milling: Start the liquid nitrogen cooling equipment to pre-cool the blank, while controlling the spray and continuously monitoring to control the temperature in the processing area; achieve low-temperature processing; control the processing tools to rough mill the blank to process the groove and notch in the mounting frame; and process the insertion position of the heat sink; and leave the finishing allowance at the same time.

[0030] S4. Low-temperature stress relief: The rough-processed semi-finished products are cooled and then kept at a constant temperature; then the temperature is slowly raised to room temperature to release the surface tensile stress.

[0031] S5. Low-Temperature Finishing: The rough-machined semi-finished product is clamped again, and the liquid nitrogen cooling equipment is restarted to cool the rough-machined semi-finished product and lower and maintain the temperature in the processing area; the processing equipment is controlled to achieve layered micro-cutting to process the spiral groove, guide groove, recess, and through groove; at the same time, the spiral groove and guide groove are linked, and the three spiral grooves on the same side in the three isolation chambers are connected; and the edges are treated.

[0032] S6. Warm-up and stand: After finishing, do not disassemble the workpiece. Keep it at a low temperature of liquid nitrogen for 2 hours, then slowly raise the temperature to room temperature and stand for 24 hours.

[0033] S7. Installation: Install the heat sink, and at the same time install the horizontal shaft and its matching parts inside the notch.

[0034] Preferably, the step of eliminating forging stress in S1 is: controlling the temperature of the constant temperature pretreatment furnace to rise to 120°C and holding it at that temperature for 4 hours.

[0035] Preferably, the temperature range within the processing area in S3 is -60 to 120°C; the temperature within the processing area in S5 is maintained at -90°C.

[0036] Preferably, the step of slowly heating to room temperature in S6 is a step heating: -90℃ to -40℃; -40℃ to room temperature, with each step held for 1.5 hours.

[0037] The beneficial effects of this invention are:

[0038] 1. By opening grooves and through slots in the notch, the surface area inside the mounting frame can be increased, which helps to quickly absorb the heat emitted by the satellite antenna components. In addition, the support plate is the support mechanism for the satellite antenna components, and the components can be installed on the support plate as needed, which helps to fully ensure the heat dissipation effect.

[0039] 2. The U-shaped grooves and guide grooves form staggered channels that connect to the mounting frame and allow for gas flow. These channels are evenly distributed at the bottom of the mounting frame, effectively contacting the satellite antenna components and facilitating heat dissipation and cooling of their lower ends. The curved edges prevent direct collisions. The lower ends of the U-shaped grooves and guide grooves do not need to be on the same horizontal plane, and the depth of the U-shaped grooves is greater than that of the guide grooves, allowing for better gas flow. This gas flow effectively removes the high temperatures generated by the satellite antenna components during operation.

[0040] 3. By using low-temperature temperature control, the internal stress generated during forging and milling can be fully released. Furthermore, the finished product exhibits minimal fluctuations in form and position tolerances after thermal cycling, ensuring stable positioning accuracy over long-term use and meeting the high-precision ground assembly and adjustment requirements of satellite antennas. Attached Figure Description

[0041] Figure 1 This is a structural diagram of a satellite antenna structure proposed in this invention;

[0042] Figure 2 This is a structural diagram of the contact plate, gear component, and inclined plate component in a satellite antenna structural component proposed in this invention;

[0043] Figure 3 Appendix to this invention Figure 1 Enlarged view of point A;

[0044] Figure 4 This is a structural diagram of the ventilation port in a satellite antenna structure proposed in this invention.

[0045] In the diagram: 1. Bearing plate, 2. Mounting frame, 3. Heat sink, 4. U-shaped groove, 5. Partition, 6. Groove, 7. Through groove, 8. Guide groove, 9. Gear, 10. Contact plate, 11. Inclined plate, 12. Round tube, 13. Horizontal shaft, 14. Spring, 15. Notch, 16. Ventilation port, 17. Through port. Detailed Implementation

[0046] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0047] Reference Figures 1-4A satellite antenna structural component includes a support plate 1, on which a mounting frame 2 is fixed. The support plate 1 is a single piece of raw material. The mounting frame 2 can be machined on the support plate 1 using a machining tool and a groove can be set inside the mounting frame 2. Two partitions 5 are fixed at equal intervals inside the mounting frame 2, dividing the mounting frame 2 into three isolation cavities. An adaptive clamping mechanism is installed in each isolation cavity. In actual processing, the number of partitions 5 can be set according to the number and specifications of the satellite antenna components to be installed, so as to realize the sequential installation of multiple satellite antenna components.

[0048] In this embodiment, multiple U-shaped grooves 4 and multiple flow guide grooves 8 are equally spaced at the bottom of the isolation cavity; the U-shaped grooves 4 and the partition plate 5 are arranged vertically, the flow guide grooves 8 and the partition plate 5 are arranged parallelly, and the flow guide grooves 8 and the U-shaped grooves 4 are staggered; through the above components, there are more U-shaped grooves 4 and flow guide grooves 8, so that corresponding grooves can be set at the bottom of the mounting frame 2. The grooves allow gas to flow, and the gas flow can carry away the heat generated by the satellite antenna components in the mounting frame 2; the bottoms of the flow guide grooves 8 and the U-shaped grooves 4 are at the same level. On the horizontal plane, multiple through-holes 17 are evenly spaced on the side walls of the guide channel 8 and the loop 4. Two through-holes 17 arranged in an alternating manner are connected by a ventilation port 16, which is opened on the support plate 1. By opening grooves 6 and through-holes 7 on the notch 15, the surface area inside the mounting frame 2 can be increased, which helps to quickly absorb the heat emitted by the satellite antenna components. The support plate 1 is the support mechanism for the satellite antenna components, and the components can be installed on the support plate 1 as needed, which helps to fully ensure the heat dissipation effect.

[0049] In this embodiment, the adaptive clamping mechanism includes four notches 15 formed on the four walls of the isolation cavity; corresponding components can be installed in the notches 15 to achieve abutment clamping of the four sides of the satellite antenna component, facilitating subsequent fixation by the corresponding components.

[0050] A horizontal shaft 13 is fixed inside the notch 15. Two round tubes 12 are slidably mounted on the horizontal shaft 13. An inclined plate 11 is rotatably connected to each of the two round tubes 12. A gear 9 is mounted on the front end of both inclined plate 11, and a contact plate 10 is mounted on the gear 9. The horizontal shaft 13 and the inner wall of the notch 15 are clamped together by bolts or other components. Holes are made on opposite sidewalls inside the notch 15 to facilitate the subsequent installation and fixing of the horizontal shaft 13. A spring 14 and a round tube 12 are also provided on the horizontal shaft 13. The spring 14 allows the round tube 12 to move, thus enabling the round tube 12 to move. 2. The spring component 14 moves on the horizontal shaft component 13. Both ends of the horizontal shaft component 13 are fitted with spring components 14, and both ends of the spring components 14 are fixed to the horizontal shaft component 13 and the round tube component 12 respectively. At the same time, the gear component 9 consists of two meshing gear components and a frame for mounting the two gear components. The frame is fixedly connected to the contact plate 10. The two gear components 9 are fixedly connected to the two inclined plate components 11 respectively. The reverse operation between the two gears can make the two inclined plate components 11 operate in opposite directions, which can control the position of the contact plate 10 and the isolation cavity, and can also fully contact the outside of the satellite antenna component to achieve the fixation of the satellite antenna component.

[0051] In this embodiment, multiple heat dissipation plates 3 are fixed at equal intervals around the perimeter of the mounting frame 2; one end of the heat dissipation plate 3 penetrates through the support plate 1 and is flush with the inner wall of the support plate 1; the heat dissipation plate 3 can absorb the heat dissipated by the satellite antenna components inside the mounting frame 2, and the heat dissipation plate 3 and the mounting frame 2 can effectively increase the surface area of ​​the outer side of the mounting frame 2 in order to improve the heat dissipation efficiency. At the same time, the fact that one end of the support plate 1 is flush with the inner wall of the mounting frame 2 can prevent damage to the satellite antenna components.

[0052] In this embodiment, the upper end of the partition 5 is provided with a plurality of grooves 6 at equal intervals, and a through groove 7 is provided between two adjacent grooves 6; the two through grooves 7 located at both ends are provided through the mounting frame 2; the cooperation of the grooves 6 and the through grooves 7 enables the flow of gas, and during processing, the through grooves 7 can be made to pass through the mounting frame 2, thereby improving the heat dissipation efficiency.

[0053] In this embodiment, both ends of the spiral groove 4 are through-connected; the through-connection allows the spiral grooves 4 to be connected, that is, the lower end of the partition 5 is also opened, so that the gas can flow in the spiral groove 4 and the guide groove 8.

[0054] In this embodiment, the staggered positions of the U-shaped groove 4 and the flow guide groove 8 are arranged in an arc shape; the U-shaped groove 4 and the flow guide groove 8 can form staggered grooves, which pass through the mounting frame 2 and enable gas flow. At the same time, the grooves are evenly distributed at the bottom of the mounting frame 2, which can effectively contact the satellite antenna components installed in the mounting frame 2, so as to realize heat dissipation and cooling of the lower end of the satellite antenna components; at the same time, the edges are processed into an arc shape to avoid direct collision.

[0055] Furthermore, during actual production and processing, the lower ends of the spiral groove 4 and the guide groove 8 do not need to be set in the same horizontal plane. At the same time, the depth of the spiral groove 4 is greater than the depth of the guide groove 8, which allows the gas to flow better. The flow of gas can effectively remove the high temperature generated by the satellite antenna components during operation.

[0056] Meanwhile, aerogel, polyurethane low-temperature insulation foam and thermally conductive silicone pads are installed at the bottom of the mounting frame 2, which can effectively absorb the high temperature generated by the operation of the satellite antenna components and transfer it to the support plate 1 and the mounting frame 2. Moreover, the pads are made of flexible materials, which can effectively protect the satellite antenna components.

[0057] In this invention, a low-temperature precision machining method for a satellite antenna structural component, applicable to the aforementioned satellite antenna structural component, includes the following steps:

[0058] S1. Pre-treatment and datum positioning of rough blank: Blank blank is cut, upper and lower datum planes are rough milled, and finishing allowance is reserved; the rough blank is placed in a constant temperature pre-treatment furnace to eliminate forging stress; the rough blank is clamped and a flexible pad is set to isolate it from the clamping fixture to avoid the influence of rigid clamping on the rough blank; the outline structure of the rough blank is fully entered; the step of eliminating forging stress in S1 is: control the temperature of the constant temperature pre-treatment furnace to rise to 120℃ and hold it at that temperature for 4 hours;

[0059] S2. Cooling equipment adjustment: Install liquid nitrogen cooling equipment on the machining center equipment and control the nozzles to achieve full spraying of the rough blank; preheat the machining center equipment to eliminate temperature difference deformation caused by low temperature;

[0060] S3, Rough Milling: Start the liquid nitrogen cooling equipment to pre-cool the blank, while controlling the spray and continuously monitoring to control the temperature in the processing area; achieve low-temperature processing; control the processing tools to rough mill the blank to process the groove and notch 15 inside the mounting frame 2; and process the insertion position of the heat sink 3; simultaneously leave the finishing allowance; the temperature range in the processing area in S3 is -60-120℃;

[0061] S4. Low-temperature stress relief: The rough-processed semi-finished products are cooled and then kept at a constant temperature; then the temperature is slowly raised to room temperature to release the surface tensile stress.

[0062] S5, Low-Temperature Finishing: The rough-machined semi-finished product is clamped again, and the liquid nitrogen cooling equipment is restarted to cool the rough-machined semi-finished product and lower and maintain the temperature in the machining area; the machining equipment is controlled to achieve layered micro-cutting to machine the spiral groove 4, the guide groove 8, the groove 6, and the through groove 7; at the same time, the spiral groove 4 and the guide groove 8 are linked, and the three spiral grooves 4 located on the same side in the three isolation chambers are connected; and the edges are treated; the temperature in the machining area in S5 is maintained at -90℃;

[0063] S6. Warm-up and settling: After finishing, without disassembling the workpiece, keep it at a low temperature of liquid nitrogen for 2 hours, then slowly raise the temperature to room temperature and let it stand for 24 hours; the step of slowly raising the temperature to room temperature in S6 is a step-by-step temperature increase: -90℃ to -40℃; -40℃ to room temperature, with each step held for 1.5 hours.

[0064] S7. Installation: Install the heat sink 3, and at the same time install the horizontal shaft 13 and its matching components in the notch 15.

[0065] The above are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A satellite antenna structural component, comprising a support plate (1), characterized in that: An installation frame (2) is fixed on the bearing plate (1). Two partitions (5) are fixed at equal intervals inside the installation frame (2). The two partitions (5) divide the installation frame (2) into three isolation chambers. An adaptive clamping mechanism is installed inside the isolation chamber. The bottom of the isolation chamber is provided with multiple spiral grooves (4) and multiple flow guide grooves (8) at equal intervals; the spiral grooves (4) and the partition (5) are arranged vertically, the flow guide grooves (8) and the partition (5) are arranged parallel, and the flow guide grooves (8) and the spiral grooves (4) are arranged alternately. The bottoms of the guide groove (8) and the loop groove (4) are on the same horizontal plane; Multiple through-holes (17) are equally spaced on the side walls of the guide groove (8) and the loop groove (4). Two through-holes (17) are staggered and are connected by a common air exchange port (16). The air exchange port (16) is opened on the support plate (1).

2. A satellite antenna structural component according to claim 1, characterized in that, The adaptive clamping mechanism includes four openings (15) on the four walls of the isolation cavity. A horizontal shaft (13) is fixed inside the notch (15). Two round tubes (12) are slidably mounted on the horizontal shaft (13). An inclined plate (11) is rotatably connected to each of the two round tubes (12). A gear (9) is mounted on the front end of the two inclined plates (11). A contact plate (10) is mounted on the gear (9). Both ends of the horizontal shaft (13) are fitted with springs (14), and the two ends of the springs (14) are fixed on the horizontal shaft (13) and the round tube (12) respectively.

3. A satellite antenna structural component according to claim 2, characterized in that, Multiple heat dissipation plates (3) are fixed at equal intervals around the mounting frame (2); one end of each heat dissipation plate (3) passes through the support plate (1) and is flush with the inner wall of the support plate (1).

4. A satellite antenna structural component according to claim 3, characterized in that, The upper end of the partition (5) is provided with a plurality of grooves (6) at equal intervals, and a through groove (7) is provided between two adjacent grooves (6); the two through grooves (7) located at both ends are provided through the mounting frame (2).

5. A satellite antenna structural component according to claim 4, characterized in that, Both ends of the spiral groove (4) are provided through.

6. A satellite antenna structural component according to claim 5, characterized in that, The staggered positions of the spiral groove (4) and the guide groove (8) are arranged in an arc shape.

7. A low-temperature precision machining method for a satellite antenna structural component, applicable to the satellite antenna structural component of claims 1-5, characterized in that, Includes the following steps: S1. Pre-treatment and datum positioning of rough blank: blank blank is cut, upper and lower datum planes are rough milled, and finishing allowance is reserved; the rough blank is placed in a constant temperature pre-treatment furnace to eliminate forging stress; the rough blank is clamped and a flexible pad is set to isolate it from the clamping fixture to avoid the influence of rigid clamping on the rough blank; the outline structure of the rough blank is fully entered. S2. Cooling equipment adjustment: Install liquid nitrogen cooling equipment on the machining center equipment and control the nozzles to achieve full spraying of the rough blank; preheat the machining center equipment to eliminate temperature difference deformation caused by low temperature; S3, rough milling: Start the liquid nitrogen cooling equipment to pre-cool the blank, while controlling the spray and continuously monitoring to control the temperature in the processing area; realize low temperature processing operation; control the processing tool to achieve rough milling of the blank to process the groove and notch (15) inside the mounting frame (2); and process the insertion position of the heat dissipation plate (3); and leave the finishing allowance at the same time; S4. Low-temperature stress relief: The rough-processed semi-finished products are cooled and then kept at a constant temperature; then the temperature is slowly raised to room temperature to release the surface tensile stress. S5, Low-temperature finishing: The rough-finished semi-finished product is clamped again, and the liquid nitrogen cooling equipment is started again to cool the rough-finished semi-finished product and reduce and maintain the temperature in the processing area; the processing equipment is controlled to achieve layered micro-cutting to process the spiral groove (4), the guide groove (8), the groove (6) and the through groove (7); at the same time, the spiral groove (4) and the guide groove (8) are linked and the three spiral grooves (4) located on the same side in the three isolation chambers are connected; and the edges are treated. S6. Warm-up and stand: After finishing, do not disassemble the workpiece. Keep it at a low temperature of liquid nitrogen for 2 hours, then slowly raise the temperature to room temperature and stand for 24 hours. S7. Matching installation: Install the heat sink (3) and install the horizontal shaft (13) and its matching parts in the notch (15).

8. A method for low-temperature precision machining of a satellite antenna structural component according to claim 7, characterized in that, The step in S1 to eliminate forging stress is to control the temperature of the constant temperature pretreatment furnace to rise to 120°C and hold it at that temperature for 4 hours.

9. A method for low-temperature precision machining of a satellite antenna structural component according to claim 7, characterized in that, The temperature range within the processing area in S3 is -60 to 120°C; the temperature within the processing area in S5 is maintained at -90°C.

10. A method for low-temperature precision machining of a satellite antenna structural component according to claim 7, characterized in that, The step of slowly heating to room temperature in S6 is a step-by-step heating: from -90℃ to -40℃; from -40℃ to room temperature, with each step held for 1.5 hours.

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