A conformal, high-heat-dissipation flat-panel satellite signal transmission device and heat dissipation method

Abstract

This application provides a conformal high-heat-dissipation flat-panel satellite signal transmission device and heat dissipation method. The device adopts a passive antenna support heat transfer frame conformally designed on the outer wall of the satellite compartment. The conformal design allows the passive antenna support heat transfer frame to use the satellite compartment as the structural base, eliminating the need for an independent shell and reducing its own weight. At the same time, the conformal design can avoid poor thermal contact between the satellite compartment and the passive antenna support heat transfer frame, improving the thermal radiation of both. The passive antenna heat transfer cavity is provided with multiple transmitting units through arrayed accommodating cavities. On the one hand, the accommodating cavities can enhance resonance, and on the other hand, the sidewalls of the accommodating cavities can quickly absorb the thermal radiation of the transmitting units. The heat-conducting sheet and the non-load-bearing energy storage component work together to conduct the active heat of the active component to the passive antenna support heat transfer frame and the passive antenna heat transfer cavity for heat dissipation, which can replace the heat dissipation components of the active component itself.

Description

Technical Field

[0001] This invention belongs to the field of flat-panel satellite technology, specifically relating to a conformal high-heat-dissipation flat-panel satellite signal transmission device and heat dissipation method. Background Technology

[0002] A spaceborne phased array antenna typically consists of an antenna array, an antenna support heat transfer frame, cables, antenna element connectors, TR components, and a power divider network. The antenna support heat transfer frame must not only accommodate the installation of antenna elements and internal modules but also possess sufficient heat transfer and dissipation capabilities to ensure temperature uniformity and structural stability of the entire array. The antenna frame is usually made of aluminum alloy, and its structural design prioritizes hollow or thin-walled cavity structures. One side of the frame houses numerous antenna elements, while the other side houses other modules and internal wiring. Because phased array antennas generally have a large aperture and overall area, the back of the antenna is often hollowed out to reduce weight. Furthermore, to meet installation requirements, the antenna's bottom surface contacts the satellite's sub-panel via several mounting feet, resulting in a relatively small contact area between the antenna and the satellite. Against this backdrop, spaceborne phased array antennas typically employ the following related heat dissipation technologies to meet on-orbit thermal control requirements:

[0003] For antennas that only need to meet their own array heat dissipation requirements and have low heat dissipation, and have no other heat dissipation loads under the satellite's main body, the antennas are mostly passive or printed circuit board type. When the contact area between the antenna and the satellite main body is small, a thermal control coating is sprayed on the outer surface of the support frame or a germanium film is wrapped around the entire array to ensure the array's temperature uniformity. However, this is only applicable to antennas that only need to meet their own array temperature uniformity requirements and have low heat dissipation. On the other hand, flat-panel satellites have high heat dissipation loads installed on both sides. Since one side is blocked by the antenna array, the contact area between the antenna and the satellite main body is small, and the antenna's own heat capacity cannot be used for heat transfer. The heat cannot be dissipated or radiated away in time, resulting in a significant reduction in the overall heat dissipation capacity of the satellite. Increasing the contact area between the antenna and the satellite main body often leads to an increase in the overall weight.

[0004] For active antennas with high heat dissipation and complex composition, an integrated design is often adopted, with all modules installed inside the antenna. The contact area between the antenna and the satellite module is small, and an independent thermal control design is required for the antenna. This involves spraying a thermal control coating on the antenna support heat transfer frame or wrapping the entire array surface with a germanium film. At the same time, heating elements are attached inside the frame, multiple layers are wrapped, and thermal grease is applied, etc., forming a complex thermal control system. Furthermore, the entire satellite needs to provide some energy and resources to ensure the thermal control of the payload unit. This still does not solve the need for flat panel satellites to rely on the payload for heat dissipation. In addition, the cost is high, the operation process is cumbersome, the time cycle is long, and it is not conducive to mass production.

[0005] Heat conduction is achieved using satellite panels, aided by phase change materials. However, due to the high antenna array height, independent phase change modules, with their low heat transfer efficiency and large size, significantly increase the overall weight to meet the required heat conduction area. Additive manufacturing-based phase change energy storage devices employ a lattice sandwich structure, independently mounted to the corresponding heat source location via screw connections. While this reduces weight and improves heat dissipation, its cylindrical lattice structure results in a small heat exchange area and high contact thermal resistance.

[0006] Therefore, this application anticipates a device that can improve the heat dissipation efficiency of flat-panel satellites. Summary of the Invention

[0007] To address the technical problem of low heat dissipation efficiency in existing flat-panel satellite technologies, this application provides a conformal high-heat-dissipation flat-panel satellite signal transmission device and heat dissipation method.

[0008] To achieve the above objectives, the present invention provides the following technical solution:

[0009] This application provides a conformal high heat dissipation flat-panel satellite signal transmission device, including a satellite module and a passive antenna support heat transfer frame conformally designed on the outer wall of the satellite module. The side of the passive antenna support heat transfer frame close to the satellite module is a hollow cavity structure. The top of the hollow cavity structure is provided with multiple spaced heat-conducting plates through a non-load-bearing energy storage component. The side of the passive antenna support heat transfer frame away from the satellite module is provided with a passive antenna heat transfer cavity. The side wall of the passive antenna support heat transfer frame is provided with multiple external cluster connectors.

[0010] The passive antenna heat transfer cavity includes multiple arrayed receiving cavities, each containing an antenna unit. The antenna unit passes through the passive antenna support heat transfer frame and is detachably connected to the interval area between adjacent heat-conducting sheets. Cables for connecting the antenna units are provided in the interval area between adjacent heat-conducting sheets. The cables are electrically connected to multiple external cluster connectors. The external cluster connectors pass through the satellite compartment panel and are connected to active components.

[0011] Furthermore, the active component is disposed on the inner sidewall of the entire satellite and is located in the orthogonal projection area of ​​the passive antenna support heat transfer frame.

[0012] The active components include at least a power control unit, a power divider module, a transmitter / receiver assembly, and a battery. The battery provides power to the transmitter / receiver assembly and antenna unit through the power control unit and the power divider module.

[0013] Furthermore, the passive antenna heat transfer cavity has a thin-walled structure, and adjacent antenna elements share the same cavity sidewall on adjacent sides.

[0014] Furthermore, the passive antenna heat transfer cavity is provided with multiple first mounting holes, which are located at the center of the cavity junction of four adjacent receiving cavities. The first mounting holes are used to disassemble and connect the passive antenna heat transfer cavity and the passive antenna support heat transfer frame. The sidewalls of the passive antenna support heat transfer frame and the passive antenna heat transfer cavity are provided with a stepped structure, and multiple lifting holes are evenly distributed on the stepped plane. The sidewalls of the passive antenna support heat transfer frame are provided with multiple connection holes for disassembling and connecting the satellite compartment panel.

[0015] Furthermore, the non-load-bearing energy storage component includes an energy storage chain formed by multiple sequentially connected I-shaped structures, with adjacent energy storage chains spaced apart. The I-shaped structure includes a web and a wing, and adjacent I-shaped structures share the same wing.

[0016] The energy storage chain is welded to the top of the hollow cavity structure on one side and a heat-conducting sheet is welded to the other side.

[0017] Furthermore, the non-load-bearing energy storage component is provided with a second mounting hole that corresponds one-to-one with the orthographic projection position of the first mounting hole.

[0018] Furthermore, both the web and the wing plate are provided with welding grooves in the contact area of ​​the heat-conducting plate. The heat-conducting plate is provided with reinforcing ribs along its length. The reinforcing ribs include multiple parallel short ribs and a long rib perpendicular to the short ribs. The short ribs are welded to the welding grooves of the wing plate, and the long rib is welded to the welding grooves of the web.

[0019] Furthermore, the bottom of the antenna unit is connected to a cable via a unit connector, and the antenna unit is blindly connected to the unit connector, with the height of the blind connection between the antenna unit and the unit connector being less than the height of the receiving cavity.

[0020] Furthermore, the exposed surface of the passive antenna support heat transfer frame and the inner wall of the receiving cavity, as well as the radiating surface of the antenna unit, are coated with thermal control white paint. The thermal control white paint has an absorptivity of <0.15 and an emissivity of >0.85. The heat-conducting sheet and the passive antenna heat transfer cavity are both treated with natural-colored conductive oxidation.

[0021] This application also provides a heat dissipation method for a conformal high-heat-dissipation flat-panel satellite signal transmission device, comprising the following steps:

[0022] The antenna unit operates according to the excitation signal provided by the active component. The antenna unit generates passive heat, and the active component generates active heat.

[0023] The passive heat is dissipated by thermal conduction to the passive antenna heat transfer cavity;

[0024] The active heat is conducted through the heat-conducting sheet and the non-load-bearing energy storage component to the passive antenna support heat transfer frame and the passive antenna heat transfer cavity for heat dissipation.

[0025] Compared with the prior art, the present invention has the following beneficial technical effects:

[0026] This application provides a conformal high-heat-dissipation flat-panel satellite signal transmission device and heat dissipation method. The device adopts a passive antenna support heat transfer frame conformally designed on the outer wall of the satellite module. The conformal design allows the passive antenna support heat transfer frame to use the satellite module as the structural base, eliminating the need for a separate shell and reducing its weight. At the same time, the conformal design can avoid poor thermal contact between the satellite module and the passive antenna support heat transfer frame, improving the thermal radiation of both. The passive antenna heat transfer cavity is equipped with multiple transmitting units through arrayed receiving cavities. On the one hand, the receiving cavities can enhance resonance, and on the other hand, the sidewalls of the receiving cavities can quickly absorb the thermal radiation of the transmitting units. The heat-conducting sheet and the non-load-bearing energy storage component work together to conduct the active heat of the active components to the passive antenna support heat transfer frame and the passive antenna heat transfer cavity for heat dissipation. It can replace the heat dissipation components of the active components themselves. This device integrates the heat dissipation function into the passive components, which not only meets the heat dissipation requirements of the passive components themselves, but also provides auxiliary heat dissipation for the active components, improving the heat dissipation capacity of the flat-panel satellite. Attached Figure Description

[0027] Figure 1 An exploded view of a conformal high-heat-dissipation flat-panel satellite signal transmission device according to an embodiment of this disclosure is shown;

[0028] Figure 2 A schematic diagram of the antenna element and passive antenna heat transfer cavity in an embodiment of this disclosure is shown;

[0029] Figure 3 A schematic diagram of the structure of the passive antenna heat transfer cavity in an embodiment of this disclosure is shown;

[0030] Figure 4 A schematic diagram of the structure of the heat-conducting sheet in the passive antenna support heat transfer frame in an embodiment of this disclosure is shown;

[0031] Figure 5 A schematic diagram of the structure of the non-load-bearing energy storage device in the passive antenna support heat transfer frame is shown in the embodiment of this disclosure;

[0032] Figure 6 A structural schematic diagram of a non-load-bearing energy storage device in an embodiment of this disclosure is shown;

[0033] Figure 7 A schematic diagram of the structure of the heat-conducting sheet and antenna unit in an embodiment of this disclosure is shown;

[0034] Figure 8 A schematic diagram of the structure of the heat-conducting sheet in an embodiment of this disclosure is shown;

[0035] Figure 9A partial welding schematic diagram of the satellite module and heat-conducting sheet in an embodiment of this disclosure is shown;

[0036] Figure 10 A schematic diagram of the side structure of the passive antenna support heat transfer frame in an embodiment of this disclosure is shown.

[0037] In the diagram: 1- Passive antenna support heat transfer frame; 2- Antenna unit; 3- External cluster connector; 4- Heat conductor; 5- Power control unit; 6- Power divider feed module; 7- Transmitter / receiver assembly; 8- Battery; 9- Satellite compartment panel; 10- Passive antenna heat transfer cavity; 11- Non-load-bearing energy storage component; 12- First mounting hole; 13- Lifting hole; 14- Connection hole; 15- Second mounting hole; 16- Unit connector. Detailed Implementation

[0038] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0039] Figure 1 A schematic diagram of a conformal high-heat-dissipation flat-panel satellite signal transmission device according to an embodiment of this disclosure is shown, such as... Figure 1 As shown, it includes satellite panel 9.

[0040] The passive antenna support heat transfer frame 1 is conformally designed on the outer wall of the satellite compartment 9. The side of the passive antenna support heat transfer frame 1 closest to the satellite compartment 9 is a hollow cavity structure. The top of the hollow cavity structure is provided with multiple spaced heat-conducting plates 4 through a non-load-bearing energy storage component 11. The side of the passive antenna support heat transfer frame 1 away from the satellite compartment 9 is provided with a passive antenna heat transfer cavity 10. The side wall of the passive antenna support heat transfer frame 1 is provided with multiple external cluster connectors 3.

[0041] The passive antenna heat transfer cavity 10 includes multiple arrayed receiving cavities, each containing an antenna unit 2. The antenna unit 2 passes through the passive antenna support heat transfer frame 1 and is detachably connected to the interval area of ​​adjacent heat-conducting plates 4. Cables for connecting the antenna unit 2 are provided in the interval area of ​​adjacent heat-conducting plates 4. The cables are electrically connected to multiple external cluster connectors 3. The external cluster connectors 3 pass through the satellite compartment plate 9 and are connected to active components.

[0042] like Figure 2 and Figure 3As shown in the embodiments of this disclosure, the receiving cavity is a cuboid structure and arranged in a rectangular array. In other embodiments, the arrangement of the receiving cavities can also be a hexagonal matrix, an octagonal matrix, etc., depending on the actual arrangement of the antenna elements 2. It should be noted that the receiving cavity is also used to enhance resonance. When the transmitting element 2 excites the receiving cavity at a specific frequency, the energy is reflected and superimposed within the receiving cavity, making the local field strength much higher than the input value. At the same time, the receiving cavity can suppress surface waves and mutual coupling of the transmitting element 2, enabling each transmitting element 2 to radiate independently and directionally. More importantly, the receiving cavity can absorb the thermal radiation of the transmitting element 2 and dissipate heat.

[0043] In this embodiment, the active component is disposed on the inner side wall of the entire satellite and is located in the orthographic projection area of ​​the passive antenna support heat transfer frame 1. It should be noted that, on the one hand, it can reduce the length of the line connection, and on the other hand, the heat radiation of the active component can be dissipated through the passive antenna support heat transfer frame 1.

[0044] The active components include at least a power control unit 5, a power distribution module 6, a transmit / receive assembly 7, and a battery 8. The battery 8 provides power to the transmit / receive assembly 7 and the antenna unit 2 through the power control unit 5 and the power distribution module 6. Specifically, the power control unit 5 is used to convert the voltage of the battery 8 to various voltage levels required by the system, control charging and discharging, power-on sequence, and provide overcurrent / overvoltage protection. The power distribution module 6 is used to receive stable power from the power control unit and distribute it to multiple transmit / receive assemblies 7.

[0045] In this embodiment, the passive antenna heat transfer cavity 10 has a thin-walled structure, and adjacent antenna elements 2 share the same cavity sidewall on adjacent sides. It should be noted that the thin-walled structure and the shared cavity sidewall can reduce the weight of the passive antenna heat transfer cavity 10, and meet the heat dissipation and resonance enhancement requirements of the transmitting unit 2.

[0046] like Figure 3 and Figure 10As shown, the passive antenna heat transfer cavity 10 is provided with a plurality of first mounting holes 12. The first mounting holes 12 are located at the center of the cavity junction of four adjacent receiving cavities. The first mounting holes 12 are used to disassemble and connect the passive antenna heat transfer cavity 10 and the passive antenna support heat transfer frame 1. The sidewalls of the passive antenna support heat transfer frame 1 and the passive antenna heat transfer cavity 10 are provided with a stepped structure. A plurality of lifting holes 13 are evenly distributed on the stepped plane. The sidewalls of the passive antenna support heat transfer frame 1 are provided with a plurality of connecting holes 14 for disassembling and connecting the satellite compartment panel 9. It should be noted that the first mounting holes 12 are centrally clustered on the passive antenna heat transfer cavity 10. The closer to the center of the passive antenna heat transfer cavity 10, the denser the first mounting holes 12 are. In this embodiment, there are eight first mounting holes 12 and four lifting holes 13. The passive antenna support heat transfer frame 1 is a truncated pyramid structure, with the large end close to the satellite compartment plate 9 and the small end equipped with the passive antenna heat transfer cavity 10. The inclined surfaces, which serve as side walls, are equipped with eight connecting holes 14 and two external cluster connectors 3.

[0047] like Figure 4 , Figure 5 and Figure 6 As shown, the non-load-bearing energy storage component 11 includes an energy storage chain formed by multiple sequentially connected I-shaped structures. Adjacent energy storage chains are spaced apart. The I-shaped structure includes a web and a wing, and adjacent I-shaped structures share the same wing. One side of the energy storage chain is welded to the top of the hollow cavity structure, and the other side is welded to a heat-conducting sheet 4. Furthermore, the non-load-bearing energy storage component 11 is provided with a second mounting hole 15 corresponding to the orthographic projection position of the first mounting hole 12. That is, in this embodiment, in order to improve the structural stability of the passive antenna heat transfer cavity 10, fastening bolts are sequentially passed through the first mounting hole 12 and the second mounting hole 15 and connected to the satellite compartment plate 9.

[0048] Furthermore, such as Figure 8 As shown, both the web and the wing plate have welding grooves in the contact area with the heat-conducting plate 4. The heat-conducting plate 4 has reinforcing ribs 22 along its length. Each reinforcing rib 22 includes multiple parallel short ribs and a long rib perpendicular to the short ribs. The short ribs are welded to the welding grooves in the wing plate, and the long rib is welded to the welding grooves in the web. In this embodiment, the I-shaped structure has a certain thickness of 6 mm-9 mm, the welding groove depth is 3 mm-5 mm, and the reinforcing rib 22 is connected by welding plates. The width of both the welding plates and the welding grooves is 4 mm-6 mm. The thickness of the heat-conducting plate 4 is 1.5 mm-3 mm, and the thickness of the reinforcing rib 22 is 3 mm-5 mm. A 20 mm-35 mm spacing between adjacent heat-conducting plates 4 is used for the installation of the unit connector 16 and some cable routing. The top surface of the heat-conducting plate 4 is in direct contact with the satellite cabin plate 9. It should be noted that, as... Figure 9As shown, welding enables faster heat conduction between the non-load-bearing energy storage component 11 and the heat-conducting plate 4. At the same time, the combination of the reinforcing rib 22 and the fastening bolts prevents the heat-conducting plate 4 from becoming the main load-bearing structure.

[0049] In this embodiment, the bottom of the antenna unit 2 is connected to a cable via a unit connector 16. The antenna unit 2 is blind-molded into the unit connector 16, and the height of the blind-molded connection between the antenna unit 2 and the unit connector 16 is less than the height of the receiving cavity. Specifically, as follows... Figure 7 As shown, antenna unit 2 uses an SMP connector as its signal connection interface. The cable that mates with antenna unit 2 has an SMP connector at one end for blind mating with the antenna unit 2, and an SMA connector at the other end, which connects to four external cluster connectors 3 according to their respective regions. Based on the quadrant division of the antenna array, the array is divided into four regions. Antenna units 2 within each region are connected via corresponding cables. The external cluster connectors 3 are used to transfer and output signals from the cables in each region, passing them through pre-drilled holes on the satellite module 9 to establish signal connections with the corresponding active components, thus achieving a complete signal transmission path from antenna unit 2 to the active components. After the SMP connectors of the cables are blind-mating with the antenna unit 2, their overall height in the mating direction is between 12mm and 18mm.

[0050] In some embodiments, the exposed surface and inner wall of the passive antenna support heat transfer frame 1, as well as the radiator surface of the antenna unit 2, are coated with thermal control white paint. The thermal control white paint has an absorptivity of <0.15 and an emissivity of >0.85. The heat-conducting sheet 4 and the passive antenna heat transfer cavity 10 are both treated with natural-color conductive oxidation. Specifically, the passive antenna support heat transfer frame 1, the passive antenna heat transfer cavity 10, the non-load-bearing energy storage component 11, and the heat-conducting sheet 4 are all made of 061 aluminum alloy. It should be noted that the thermal control white paint is a thermal control coating with low solar absorptivity and high infrared emissivity, which can dissipate heat into space in the form of infrared radiation and reflect most of the solar radiation energy. The natural-color conductive oxidation treatment is achieved by generating a thin and dense oxide film on the metal surface through a chemical solution, which can achieve basic protection without increasing weight.

[0051] This embodiment also provides a heat dissipation method for a conformal high-heat-dissipation flat-panel satellite signal transmission device, including the following steps:

[0052] The antenna unit 2 operates according to the excitation signal provided by the active component. The antenna unit 2 generates passive heat, and the active component generates active heat.

[0053] The passive heat is dissipated by thermal conduction to the passive antenna heat transfer cavity 10.

[0054] The active heat is conducted through the heat-conducting sheet 4 and the non-load-bearing energy storage component 11 to the passive antenna support heat transfer frame 1 and the passive antenna heat transfer cavity 10 for heat dissipation.

[0055] It should be noted that this method can dissipate the heat radiation of the antenna element 2 through the passive antenna heat transfer cavity 10, and can also absorb and dissipate the heat of the active component. On the one hand, it can assist the heat dissipation of the active component, and on the other hand, it can avoid the need for the active component to be equipped with an additional heat dissipation component for the passive component.

Claims

1. A conformal high radiating flat panel satellite signal transmission device, characterized in that, The satellite includes a satellite compartment panel (9) and a passive antenna support heat transfer frame (1) conformally designed on the outer wall of the satellite compartment panel (9). The side of the passive antenna support heat transfer frame (1) close to the satellite compartment panel (9) is a hollow cavity structure. The top of the hollow cavity structure is provided with multiple spaced heat-conducting plates (4) through a non-load-bearing energy storage component (11). The side of the passive antenna support heat transfer frame (1) away from the satellite compartment panel (9) is provided with a passive antenna heat transfer cavity (10). The side wall of the passive antenna support heat transfer frame (1) is provided with multiple external cluster connectors (3). The passive antenna heat transfer cavity (10) includes multiple arrayed cavities, each containing an antenna unit (2). The antenna unit (2) passes through the passive antenna support heat transfer frame (1) and is detachably connected to the interval area of ​​the adjacent heat-conducting sheet (4). The interval area of ​​the adjacent heat-conducting sheet (4) is provided with a cable for connecting the antenna unit (2). The cable is electrically connected to multiple external cluster connectors (3). The external cluster connectors (3) pass through the satellite compartment plate (9) and are connected to active components.

2. The conformal high emissivity flat panel satellite signal transmission device of claim 1, wherein, The active component is disposed on the inner side wall of the entire satellite and is located in the orthographic projection area of ​​the passive antenna support heat transfer frame (1). The active components include at least a power control unit (5), a power distribution module (6), a transmitter / receiver unit (7), and a battery (8). The battery (8) provides power to the transmitter / receiver unit (7) and the antenna unit (2) through the power control unit (5) and the power distribution module (6).

3. The conformal high emissivity flat panel satellite signal transmission device of claim 1, wherein, The passive antenna heat transfer cavity (10) is a thin-walled structure, and adjacent antenna elements (2) share the same cavity sidewall on adjacent sides.

4. The conformal high emissivity flat panel satellite signal transmission device of claim 1, wherein, The passive antenna heat transfer cavity (10) is provided with a plurality of first mounting holes (12). The first mounting holes (12) are located at the center of the cavity junction of four adjacent accommodating cavities. The first mounting holes (12) are used to disassemble and connect the passive antenna heat transfer cavity (10) and the passive antenna support heat transfer frame (1). The side walls of the passive antenna support heat transfer frame (1) and the passive antenna heat transfer cavity (10) are provided with a stepped structure. The stepped plane is evenly distributed with a plurality of lifting holes (13). The side walls of the passive antenna support heat transfer frame (1) are provided with a plurality of connecting holes (14) for disassembling and connecting the satellite compartment panel (9).

5. The conformal high emissivity flat panel satellite signal transmission device of claim 4, wherein, The non-load-bearing energy storage component (11) includes an energy storage chain formed by multiple sequentially connected I-shaped structures, with adjacent energy storage chains spaced apart. The I-shaped structure includes a web and a wing, and adjacent I-shaped structures share the same wing. The energy storage chain is welded to the top of the hollow cavity structure on one side and a heat-conducting sheet (4) is welded to the other side.

6. The conformal high-heat-dissipation flat-panel satellite signal transmission device according to claim 5, characterized in that, The non-load-bearing energy storage component (11) is provided with a second mounting hole (15) that corresponds one-to-one with the orthographic projection position of the first mounting hole (12).

7. The conformal high-heat-dissipation flat-panel satellite signal transmission device according to claim 5, characterized in that, Both the web and the wing plate are provided with welding grooves in the area of ​​contacting the heat-conducting plate (4). The heat-conducting plate (4) is provided with reinforcing ribs (22) along its length. The reinforcing ribs (22) include multiple parallel short ribs and a long rib perpendicular to the short ribs. The short ribs are welded to the welding groove of the wing plate, and the long rib is welded to the welding groove of the web.

8. The conformal high-heat-dissipation flat-panel satellite signal transmission device according to claim 1, characterized in that, The bottom of the antenna unit (2) is connected to a cable via a unit connector (16). The antenna unit (2) is blindly connected to the unit connector (16), and the height of the blind connection between the antenna unit (2) and the unit connector (16) is less than the height of the receiving cavity.

9. The conformal high-heat-dissipation flat-panel satellite signal transmission device according to claim 1, characterized in that, The exposed surface of the passive antenna support heat transfer frame (1) and the inner wall of the cavity, as well as the radiator surface of the antenna unit (2), are coated with thermal control white paint. The thermal control white paint has an absorptivity of <0.15 and an emissivity of >0.

85. The heat-conducting sheet (4) and the passive antenna heat transfer cavity (10) are both treated with natural-colored conductive oxidation.

10. A heat dissipation method for a conformal high-heat-dissipation flat-panel satellite signal transmission device, characterized in that, The conformal high heat dissipation flat-panel satellite signal transmission device according to any one of claims 1-9 includes the following steps: The antenna unit (2) operates according to the excitation signal provided by the active component. The antenna unit (2) generates passive heat, and the active component generates active heat. The passive heat is dissipated by heat conduction to the passive antenna heat transfer cavity (10); The active heat is conducted through the heat-conducting sheet (4) and the non-load-bearing energy storage component (11) to the passive antenna support heat transfer frame (1) and the passive antenna heat transfer cavity (10) for heat dissipation.

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