Satellite-borne high-orbit earth-communication antenna driving mechanism high-efficiency heat insulation device

Abstract

The utility model provides a kind of high-efficiency heat insulation device of spaceborne high-orbit ground-transmitting antenna driving mechanism, including the X-axis light shield connected by heat insulation pad on the sun side outside of X-axis drive assembly, the Y-axis light shield connected by heat insulation pad on the sun side outside of Y-axis drive assembly, respectively paste in the multiple heat insulation components of X-axis light shield, Y-axis light shield sun side and spray white paint layer in the inside of X-axis light shield, Y-axis light shield.The heat control structure of the utility model can be in mechanism space envelope range, significantly increase the heat transfer resistance of outer heat flow to drive assembly, to strengthen drive assembly and external environment heat insulation effect.The structure uses multiple heat insulation components and antistatic inorganic white paint cooperate light shield to form heat insulation barrier, can be while blocking external radiation heat input, using antistatic inorganic white paint enhances radiation heat dissipation capacity, effectively solve the overheating problem caused by that drive mechanism is long-term exposed in high orbit long-term illumination environment.

Description

Technical Field

[0001] This utility model relates to the field of satellite technology, specifically to a high-efficiency heat insulation device for a drive mechanism of a spaceborne high-orbit ground-to-ground data transmission antenna. Background Technology

[0002] The drive mechanism of the Earth-to-ground data transmission antenna for high-orbit satellites is typically located on the outside of the cabin, directly exposed to the frigid environment and intense solar radiation. The thermal conditions in high orbit are complex and variable, far more severe than in low orbit. The long orbital period significantly extends both the periods of sunlight and shadow, causing intense high and low temperature fluctuations and worsening the thermal environment around the antenna. As a core active component, the drive assembly has high power density and stringent temperature sensitivity, posing a risk of overheating under prolonged exposure to sunlight.

[0003] Therefore, an efficient shading and heat insulation solution is needed to suppress temperature fluctuations in the drive components and ensure their reliable operation. Summary of the Invention

[0004] This invention addresses the overheating risk of a ground-to-ground data transmission antenna drive mechanism operating under long-term illumination and power-on conditions in high-orbit environments. It provides a highly efficient heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-ground data transmission antenna. The light-shielding plate serves as both a heat insulation device for the drive component and an assembly component of the drive mechanism. The thermal control and structural design are integrated, saving design space and reducing weight for the overall antenna structure. Compared to the traditional approach of directly covering the drive component with multiple layers of heat insulation components, the light-shielding plate effectively avoids the risk of movement of the multi-layered interference mechanism, increases the heat dissipation surface, and reduces the overall absorption ratio of external heat flow to the drive component, significantly improving the overall thermal resistance of external heat flow to the drive component. This minimizes the impact of external heat flow on the orbit, extends temperature stability, and reduces the high-temperature level of the drive component, lowering the maximum temperature from 70.8℃ to 57.3℃. The multi-layered heat insulation component uses a black film with high emissivity and high solar absorptivity to avoid stray light interference to other systems. The thermal control coating uses an anti-static inorganic white paint to prevent the accumulation of surface static electricity from affecting the discharge of the drive component.

[0005] This utility model provides a high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-ground data transmission antenna, including a drive mechanism base, an X-axis drive assembly connected to the drive mechanism base, a U-shaped frame connected to the output end of the X-axis drive assembly, a Y-axis drive assembly connected to the U-shaped frame by screws, an X-axis light shield connected to the outside of the sun-facing side of the X-axis drive assembly by a heat insulation pad, and a Y-axis light shield connected to the outside of the sun-facing side of the Y-axis drive assembly by a heat insulation pad. The output of the Y-axis drive component is connected to the onboard high-orbit ground-to-ground data transmission antenna. The X-axis drive component is used to drive the onboard high-orbit ground-to-ground data transmission antenna and the Y-axis drive component to move along the X-axis. The Y-axis drive component is used to drive the onboard high-orbit ground-to-ground data transmission antenna to move along the Y-axis. The X-axis light shield is a semi-cylindrical alloy sheet metal radiator. The Y-axis light-shielding plate has openings for heat dissipation.

[0006] The high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna described in this utility model, as a preferred embodiment, further includes multi-layer heat insulation components respectively pasted on the sun-facing side of the X-axis light-shielding plate and the Y-axis light-shielding plate, and a white paint layer sprayed on the inner side of the X-axis light-shielding plate and the Y-axis light-shielding plate.

[0007] In a preferred embodiment of the high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna described in this utility model, both the housings of the X-axis drive assembly and the Y-axis drive assembly are coated with a layer of white paint. The portion of the spaceborne high-orbit ground-to-ground data transmission antenna facing the Y-axis drive assembly is coated with a layer of white paint, while the remaining sun-facing side is bonded with multiple layers of heat insulation components.

[0008] In the preferred embodiment of the high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna described in this utility model, the white paint layer is an anti-static inorganic white paint.

[0009] The present invention provides a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-ground data transmission antenna drive mechanism. In a preferred embodiment, the X-axis drive component includes a cylindrical body. The X-axis light shield includes a semi-cylindrical alloy sheet metal body, a semi-circular ring mounting surface perpendicularly connected to one end of the semi-cylindrical alloy sheet metal body, and a first mounting hole connected to the semi-circular ring mounting surface. The body of the semi-cylindrical alloy sheet metal part is located on the sun-facing side of the X-axis drive assembly, and a multi-layer heat insulation component is bonded to the outside of the body of the semi-cylindrical alloy sheet metal part. The semi-circular mounting surface is connected to the X-axis drive assembly via screws and heat insulation pads.

[0010] In a preferred embodiment of the high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-ground data transmission antenna described in this utility model, the gap between the semi-circular mounting surface and the X-axis drive assembly is greater than 15mm.

[0011] The high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna of this utility model, as a preferred embodiment, includes a cylindrical body as the Y-axis drive component. The Y-axis light shield includes mounting surfaces on both sides, a semi-cylindrical sheet metal connecting the two mounting surfaces, a heat dissipation opening on the semi-cylindrical sheet metal, and a second mounting hole connecting the mounting surfaces and the semi-cylindrical sheet metal. The mounting surface is installed on the edge of the U-shaped frame using screws and heat insulation pads. The semi-cylindrical sheet metal is located on the sun-facing exterior of the Y-axis drive assembly, and a multi-layer heat insulation assembly is bonded to the outer side of the semi-cylindrical sheet metal.

[0012] The high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna of this utility model, as a preferred embodiment, has a long strip structure for the mounting surface and a chamfer at the connection with the semi-cylindrical sheet metal. The mounting surface and the semi-cylindrical sheet metal are an integrated structure and are both alloy sheet metal radiators. The number of heat dissipation openings is at least two, and the shape is square openings; square openings are also provided on the multi-layer heat insulation components bonded to the outside of the semi-cylindrical sheet metal. The gap between the semi-cylindrical sheet metal and the Y-axis drive assembly is greater than 15mm.

[0013] The high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna of this utility model, as a preferred embodiment, includes a multi-layer heat insulation component comprising, from the inside out, an inner film layer, at least two reflective screen polyester mesh units, and a black film layer. The inner membrane layer is made of polyimide, and a white paint layer is also sprayed on the side of the inner membrane layer facing the X-axis drive component or the Y-axis drive component. The reflective screen polyester mesh unit includes a connected reflective screen layer and an insulating layer. The innermost reflective screen layer is connected to the inner film layer by sewing. The reflective screen layer is made of aluminized polyester, and the insulating layer is a polyester mesh. The black film layer is connected to the outermost insulating layer by sewing; The multi-layer thermal insulation component is an integrated structure.

[0014] In a preferred embodiment of the high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-ground data transmission antenna described in this utility model, the heat insulation pad is made of fiberglass, and the X-axis drive assembly is connected to the base of the drive mechanism by screws.

[0015] The technical problem solved by this utility model is: under the condition that the space and weight resources for implementing the thermal control of the drive mechanism are severely limited, the design of the thermal control structure of the drive component's light shield is carried out. The aim is to eliminate the overheating risk of the drive component in the high-track, long-light, and long-power-on working mode, and ensure that the temperature of the drive component shell does not exceed the safe temperature threshold of 60°C. At the same time, since the overall volume of the drive structure is small, thermal design measures such as the light shield must not interfere with or affect the movement of the mechanism.

[0016] The technical solution of this utility model is as follows: Based on the design concept of miniaturization and integration of the antenna drive mechanism and the stray light suppression design requirements of the satellite, the external heat flow conditions of the high-orbit antenna satellite platform and the internal heat transfer path of the antenna mechanism are analyzed step by step, and then a targeted thermal control structure design is carried out. Analysis shows that the drive component and the mechanism adopt a screw-connected dry contact installation method, with a small installation surface area and poor heat transfer. Therefore, most of its heat can only be dissipated into deep space through radiation. However, the Z-plane of the satellite in this orbit is constantly exposed to sunlight, resulting in a harsh heat dissipation environment for the drive component. Directly covering the component with multiple layers of heat insulation components would not only reduce the heat dissipation surface of the drive component but also pose a risk of interfering with the rotation of the mechanism. To solve the above contradictions, this utility model provides a compact semi-cylindrical light-shielding plate installed on the sun-facing side of the mechanism base, leaving sufficient space for heat dissipation of the drive component while meeting the maximum envelope range requirements of the mechanism. To further reduce the temperature fluctuation of the drive component shell, the sun-facing side of the light-shielding plate is covered with a 15-unit multi-layer heat insulation component. The multi-layer film is a black film with high emissivity and high solar absorptivity, avoiding stray light interference to other satellite systems. The inner side of the sunshade is coated with a low solar absorptivity, high infrared emissivity, and antistatic inorganic white paint, which meets the electrostatic discharge protection design requirements of high orbits while dissipating heat into deep space through radiation. Finally, the sunshade and the drive assembly are installed with thermal insulation pads.

[0017] The drive mechanism converts contact conduction into radiation conduction by setting up a light-shielding plate and cooperating with corresponding thermal control measures, thereby maximizing the thermal resistance of external heat flow to the drive component. The integrated thermal control design of the light-shielding plate structure achieves efficient heat insulation between the drive component and the external environment, increasing the temperature stability of the drive component and reducing the high temperature level from 70.8℃ to 57.3℃.

[0018] This thermal control structure significantly increases the thermal resistance of external heat flow to the drive components within the spatial envelope of the mechanism, thereby enhancing the thermal insulation effect between the drive components and the external environment. The structure employs multi-layered thermal insulation components and an antistatic inorganic white paint synergistically with a light-shielding plate to form a thermal barrier. This effectively blocks external radiative heat input while enhancing radiative heat dissipation through the antistatic inorganic white paint, thus solving the overheating problem caused by the drive mechanism's long-term exposure to high-orbit radiation.

[0019] The high-efficiency heat insulation device for the drive mechanism of the spaceborne high-orbit ground-to-ground data transmission antenna of this utility model is designed with a light-shielding plate. A light-shielding plate is added at the end of the heat transfer path of core active components such as the drive assembly to block direct sunlight, thereby increasing the thermal resistance of radiative heat transfer and reducing the impact of thermal radiation on the temperature rise of the drive assembly housing.

[0020] The light shield is modular and detachable, and is installed on heat-generating components such as the drive assembly via a heat insulation pad to reduce the impact of heat conduction on the temperature rise of the drive assembly housing.

[0021] The sun-facing side of the shading panel is covered with multiple layers of heat insulation components, while the shaded side is sprayed with a low solar absorptivity, high infrared emissivity, and antistatic inorganic white paint. This reduces the average absorption ratio of the entire system to external heat flow, minimizing the contribution of external heat flow to the temperature fluctuation of the drive component housing, and meeting the thermal control requirements of the drive component under long-term high-orbit radiation.

[0022] This utility model has the following advantages: (1) The light shield serves as both a heat insulation device for the drive assembly and an assembly component of the drive mechanism. The thermal control and structure are integrated into a shared design, saving design space and reducing weight for the overall antenna structure.

[0023] (2) Compared with the traditional solution of directly covering the driving component with a multi-layer heat insulation component, the light shield solution can effectively avoid the risk of movement of the multi-layer interference mechanism, increase the heat dissipation surface and reduce the absorption ratio of the overall external heat flow of the antenna, significantly improve the comprehensive thermal resistance of the external heat flow to the driving component, thereby minimizing the influence of the external heat flow of the track, extending the temperature stability and reducing the high temperature level of the driving component, with the highest temperature reduced from 70.8℃ to 57.3℃.

[0024] (3) The multi-layer heat insulation component uses a black film with high emissivity and high solar absorptivity to avoid stray light interference to other systems. The thermal control coating uses an anti-static inorganic white paint to avoid the impact of surface static electricity accumulation on the discharge of the drive component. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the overall structure of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-data transmission antenna drive mechanism. Figure 2 A side view of the main body of the drive mechanism of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-air data transmission antenna drive mechanism. Figure 3 This is a front view structural diagram of the main body of the drive mechanism of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-air data transmission antenna drive mechanism. Figure 4 Thermal design drawing of the light-shielding plate of the drive component of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-ground data transmission antenna drive mechanism. Figure 5 A partially enlarged view of the thermal design of the light-shielding plate of the drive component of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-air data transmission antenna drive mechanism. Figure 6 A schematic diagram of the X-axis light shielding plate structure of the drive component of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-ground data transmission antenna drive mechanism. Figure 7 This is a schematic diagram of the Y-axis light-shielding plate structure of the drive component of a high-efficiency heat insulation device for a spaceborne high-orbit ground-to-ground data transmission antenna drive mechanism.

[0026] Figure label: 1. Drive mechanism base; 2. X-axis drive assembly; 3. U-shaped frame; 4. Y-axis drive assembly; 5. X-axis light shield; 51. Semi-cylindrical alloy sheet metal body; 52. Semi-circular ring mounting surface; 53. First mounting hole; 6. Y-axis light shield; 61. Mounting surface; 62. Semi-cylindrical sheet metal; 63. Heat dissipation opening; 64. Second mounting hole; 7. Multi-layer heat insulation assembly; 71. Square opening; 8. White paint layer. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Example 1

[0028] A high-efficiency heat insulation device for a drive mechanism of a spaceborne high-orbit ground-to-ground data transmission antenna includes a drive mechanism base 1, an X-axis drive assembly 2 connected to the drive mechanism base 1, a U-shaped frame 3 connected to the output end of the X-axis drive assembly 2 by screws, a Y-axis drive assembly 4 connected to the U-shaped frame 3 by screws, an X-axis light shield 5 connected to the sun-facing side of the X-axis drive assembly 2 by a heat insulation pad, a Y-axis light shield 6 connected to the sun-facing side of the Y-axis drive assembly 4 by a heat insulation pad, a multi-layer heat insulation assembly 7 respectively pasted to the sun-facing side of the X-axis light shield 5 and the Y-axis light shield 6, and a white paint layer 8 sprayed on the inner side of the X-axis light shield 5 and the Y-axis light shield 6. The output of the Y-axis drive component 4 is connected to the satellite-borne high-orbit ground-to-ground data transmission antenna. The X-axis drive component 2 is used to drive the satellite-borne high-orbit ground-to-ground data transmission antenna and the Y-axis drive component 4 to move along the X-axis. The Y-axis drive component 4 is used to drive the satellite-borne high-orbit ground-to-ground data transmission antenna to move along the Y-axis. X-axis drive assembly 2 includes a cylindrical body, and X-axis light shield 5 is a semi-cylindrical alloy sheet metal radiator. The X-axis light shield 5 includes a semi-cylindrical alloy sheet metal body 51, a semi-circular ring mounting surface 52 perpendicularly connected to one end of the semi-cylindrical alloy sheet metal body 51, and a first mounting hole 53 connected to the semi-circular ring mounting surface 52. The semi-cylindrical alloy sheet metal body 51 is located on the sun-facing side of the X-axis drive assembly 2, and the outer side of the semi-cylindrical alloy sheet metal body 51 is bonded with a multi-layer heat insulation assembly 7. The semi-circular mounting surface 52 is connected to the X-axis drive assembly 2 via screws and heat insulation pads; The gap between the semi-circular mounting surface 52 and the X-axis drive assembly 2 is 17mm; Y-axis drive assembly 4 includes a cylindrical body; The Y-axis light shield 6 includes mounting surfaces 61 on both sides, a semi-cylindrical sheet metal 62 connected between the two mounting surfaces 61, a heat dissipation opening 63 connected to the semi-cylindrical sheet metal 62, and a second mounting hole 64 connected to the mounting surfaces 61 and the semi-cylindrical sheet metal 62. Mounting surface 61 is mounted on the edge of U-shaped frame 3 by screws and heat insulation pads. Semi-cylindrical sheet metal 62 is located on the sun-facing side of Y-axis drive assembly 4. Multi-layer heat insulation assembly 7 is bonded to the outside of semi-cylindrical sheet metal 62. The mounting surface 61 is a long strip structure, and the connection between it and the semi-cylindrical sheet metal 62 is chamfered. The mounting surface 61 and the semi-cylindrical sheet metal 62 are an integrated structure and are both alloy sheet metal radiators. The number of heat dissipation openings 63 is at least two, and the shape is square openings; square openings 71 are also provided on the multi-layer heat insulation component 7 bonded to the outside of the semi-cylindrical sheet metal 62; The gap between the semi-cylindrical sheet metal 62 and the Y-axis drive assembly 4 is greater than 15mm; The Y-axis light-shielding plate 6 has an opening for heat dissipation; Both the housings of the X-axis drive assembly 2 and the Y-axis drive assembly 4 are coated with a layer of white paint 8. The portion of the spaceborne high-orbit ground data transmission antenna facing the Y-axis drive assembly 4 is coated with a white paint layer 8, and the remaining sun-facing side is bonded with a multi-layer heat insulation assembly 7. The multi-layer thermal insulation component 7 consists of, from the inside out, an inner membrane layer, at least two reflective polyester mesh units, and a black membrane layer; The inner membrane layer is made of polyimide, and a white paint layer 8 is also sprayed on the side of the inner membrane layer facing the X-axis drive component 2 or the Y-axis drive component 4. The reflective screen polyester mesh unit includes a connected reflective screen layer and an insulating layer. The innermost reflective screen layer is connected to the inner film layer by sewing. The reflective screen layer is made of aluminized polyester, and the insulating layer is a polyester mesh. The black film layer is connected to the outermost insulating layer by sewing; The multi-layer thermal insulation component 7 is an integrated structure.

[0029] White paint layer 8 is an anti-static inorganic white paint.

[0030] The heat insulation pad is made of fiberglass.

[0031] Figure 1 This is a structural diagram of the high-orbit ground-to-ground data transmission antenna drive mechanism, which clarifies the overall appearance and structural form of the high-orbit ground-to-ground data transmission antenna drive mechanism.

[0032] Figure 2 , 3This diagram shows the main structure of the drive mechanism, clearly illustrating the installation method of the light-shielding plate. The high-orbit ground-to-ground data transmission antenna drive mechanism is a two-dimensional rotation mechanism capable of rotation in both the X and Y directions. The drive assembly is also divided into an X-axis drive assembly 2 and a Y-axis drive assembly 4. The X-axis drive assembly 2 is mounted on the drive mechanism base 1 with screws, and the drive mechanism base 1 and the X-axis light-shielding plate 5 are thermally insulated by a 5mm fiberglass heat-insulating pad. The Y-axis drive assembly 4 is mounted on a U-shaped frame 3 with screws, and the U-shaped frame 3 and the Y-axis light-shielding plate 6 are thermally insulated by a 5mm fiberglass heat-insulating pad. The light-shielding plate and the drive assembly do not directly contact each other; there is a certain gap (17mm) between the light-shielding cover and the radiating surface of the drive assembly, transforming contact conduction into radiation conduction with greater thermal resistance.

[0033] Figure 4 , 5 This is a thermal design diagram of the drive assembly's light-shielding plate. The diagram clarifies the thermal control design scheme in conjunction with the light-shielding plate. Inorganic white paint is sprayed onto the housing of the X-axis drive assembly 2, the X-axis light-shielding plate 5+Z surface, the housing of the Y-axis drive assembly 4, and the Y-axis light-shielding plate 6+Z surface for heat dissipation. The X-axis light-shielding plate 5-Z surface and the Y-axis light-shielding plate 6-Z surface are covered with a multi-layer thermal insulation assembly 7 to isolate the influence of external heat flow. The reflective screen polyester mesh unit in the multi-layer thermal insulation assembly 7 has 15 units.

[0034] Due to the large antenna aperture, the Y-axis drive assembly 4+Z is obstructed from dissipating heat towards deep space. Figure 1 The overall appearance and structure of the antenna drive mechanism. Therefore, the heat dissipation environment of the Y-axis drive assembly 4 is more severe than that of the X-axis drive assembly 2. The Y-axis light-shielding plate 6 needs to be partially hollowed out to ensure sufficient heat dissipation surface for the Y-axis drive assembly 4. Simultaneously, the portion of the reflective surface facing the Y-axis drive assembly 4 needs to be coated with thermally controlling white paint to provide a good thermal radiation environment for the Y-axis drive assembly.

[0035] Figure 6 , 7 This is a structural design drawing for the light-shielding plate of the drive component. The light-shielding plate is a radiator made of 2mm thick semi-cylindrical alloy sheet metal. This design is easy to form and lightweight, while also meeting the requirement of low cost. In order to balance thermal control and structural mechanical strength, the hollowed-out part of the Y-axis light-shielding plate 6 is divided into multiple small cavities to form a reinforcing structure, minimizing the impact of the thin sheet metal and large-area hollowing on the structural strength.

[0036] In this utility model, the X-axis light-shielding plate 5 and the Y-axis light-shielding plate 6 are both made of forged aluminum.

[0037] The physical prototype of this utility model has passed environmental and reliability tests during the prototype stage and has been delivered to the satellite system.

[0038] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A high-efficiency heat insulation device for a spaceborne high-orbit ground-to-data transmission antenna drive mechanism, characterized in that: Includes a drive mechanism base (1), an X-axis drive assembly (2) connected to the drive mechanism base (1), a U-shaped frame (3) connected to the output end of the X-axis drive assembly (2), a Y-axis drive assembly (4) connected to the U-shaped frame (3) by screws, an X-axis light shield (5) connected to the outside of the sun-facing side of the X-axis drive assembly (2) by a heat insulation pad, and a Y-axis light shield (6) connected to the outside of the sun-facing side of the Y-axis drive assembly (4) by a heat insulation pad; The output end of the Y-axis drive component (4) is connected to the satellite-borne high-orbit ground-to-ground data transmission antenna. The X-axis drive component (2) is used to drive the satellite-borne high-orbit ground-to-ground data transmission antenna and the Y-axis drive component (4) to move along the X-axis. The Y-axis drive component (4) is used to drive the satellite-borne high-orbit ground-to-ground data transmission antenna to move along the Y-axis. The X-axis light-shielding plate (5) is a semi-cylindrical alloy sheet metal radiator. The Y-axis light-shielding plate (6) is provided with an opening for heat dissipation.

2. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 1, characterized in that: It also includes a multi-layer heat insulation component (7) that is respectively pasted on the sun-facing side of the X-axis light shield (5) and the Y-axis light shield (6), and a white paint layer (8) sprayed on the inner side of the X-axis light shield (5) and the Y-axis light shield (6).

3. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 2, characterized in that: The white paint layer (8) is sprayed onto the housings of the X-axis drive assembly (2) and the Y-axis drive assembly (4). The portion of the satellite-borne high-orbit ground-to-ground data transmission antenna facing the Y-axis drive assembly (4) is coated with the white paint layer (8), and the remaining sun-facing side is bonded with the multi-layer heat insulation assembly (7).

4. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 2, characterized in that: The white paint layer (8) is an antistatic inorganic white paint.

5. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 2, characterized in that: The X-axis drive assembly (2) includes a cylindrical body; The X-axis light shield (5) includes a semi-cylindrical alloy sheet metal body (51), a semi-circular ring mounting surface (52) perpendicularly connected to one end of the semi-cylindrical alloy sheet metal body (51), and a first mounting hole (53) connected to the semi-circular ring mounting surface (52). The semi-cylindrical alloy sheet metal body (51) is located on the sun-facing side of the X-axis drive assembly (2), and the multi-layer heat insulation assembly (7) is bonded to the outside of the semi-cylindrical alloy sheet metal body (51). The semi-circular mounting surface (52) is connected to the X-axis drive assembly (2) by screws and the heat insulation pad.

6. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 5, characterized in that: The gap between the semi-circular mounting surface (52) and the X-axis drive assembly (2) is greater than 15 mm.

7. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 2, characterized in that: The Y-axis drive assembly (4) includes a cylindrical body; The Y-axis light shield (6) includes mounting surfaces (61) on both sides, a semi-cylindrical sheet metal (62) connected between the two mounting surfaces (61), a heat dissipation opening (63) connected to the semi-cylindrical sheet metal (62), and a second mounting hole (64) connected to the mounting surfaces (61) and the semi-cylindrical sheet metal (62). The mounting surface (61) is mounted on the edge of the U-shaped frame (3) by screws and the heat insulation pad. The semi-cylindrical sheet metal (62) is located on the sun-facing side of the Y-axis drive assembly (4). The multi-layer heat insulation assembly (7) is bonded to the outside of the semi-cylindrical sheet metal (62).

8. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 7, characterized in that: The mounting surface (61) is a long strip structure and has a chamfer at the connection with the semi-cylindrical sheet metal (62). The mounting surface (61) and the semi-cylindrical sheet metal (62) are an integrated structure and are both alloy sheet metal radiators. The number of heat dissipation openings (63) is at least two, and the shape is square openings; a square opening (71) is also provided on the multi-layer heat insulation component (7) bonded to the outside of the semi-cylindrical sheet metal (62). The gap between the semi-cylindrical sheet metal (62) and the Y-axis drive assembly (4) is greater than 15mm.

9. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 2, characterized in that: The multi-layer heat insulation component (7) consists of an inner film layer, at least two reflective polyester mesh units, and a black film layer from the inside out. The inner membrane layer is made of polyimide, and the white paint layer (8) is also sprayed on the side of the inner membrane layer facing the X-axis drive assembly (2) or the Y-axis drive assembly (4). The reflective screen polyester mesh unit includes a connected reflective screen layer and an insulating layer. The innermost reflective screen layer is connected to the inner film layer by sewing. The reflective screen layer is made of aluminized polyester, and the insulating layer is a polyester mesh. The black film layer is connected to the outermost insulating layer by sewing; The multi-layer thermal insulation component (7) is an integrated structure.

10. The high-efficiency heat insulation device for the drive mechanism of a spaceborne high-orbit ground-to-data transmission antenna according to claim 1, characterized in that: The heat insulation pad is made of fiberglass, and the X-axis drive assembly (2) is connected to the drive mechanism base (1) by screws.

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