Soaking structure of commercial satellite high-power device based on liquid metal

Abstract

The invention discloses a liquid metal-based commercial satellite high-power device soaking structure, which comprises a device, the bottom of the device is in contact with an upper shell, the bottom of the upper shell is in contact with a lower shell, a sealing gasket is slidably sleeved in the lower shell, and the sealing gasket is slidably connected with the upper shell. A plurality of evenly-distributed heat pipes are fixedly connected into the upper shell and make contact with the lower shell, capillary cores are arranged in the heat pipes, flow channels are formed in the heat pipes, liquid metal is arranged in the flow channels, a plurality of connecting blocks are slidably connected to the outer side of the lower shell in a sleeving mode, and the connecting blocks are connected with the capillary cores in a sleeving mode. And the connecting block is in sliding connection with the upper shell. The invention relates to a liquid metal-based commercial satellite high-power device soaking structure, which has the characteristics of small soaking temperature difference and high extreme environment stability, is adaptive to a high-power density device and meets the long-time on-orbit requirement of a commercial satellite.

Description

Technical Field

[0001] This invention belongs to the field of heat dissipation structure technology, specifically a heat dissipation structure for high-power devices in commercial satellites based on liquid metal. Background Technology

[0002] As commercial satellites develop towards higher integration and higher power density, the application of core high-power devices such as onboard processors and phased array radars is becoming increasingly widespread, and their local heat flux density has exceeded 100W / cm². 2 This makes them highly susceptible to hotspot clustering. The persistent presence of these hotspots can cause the operating temperature of devices to exceed limits, which not only reduces core performance characteristics such as computational accuracy and transmission efficiency, but also accelerates device aging and, in severe cases, leads to malfunctions and shutdowns, directly impacting the long-term on-orbit reliability and service life of commercial satellites. Therefore, efficient and stable thermal control technology has become a key bottleneck restricting the development of high-power devices in commercial satellites.

[0003] Currently, thermal control solutions for high-power devices in commercial satellites mainly rely on traditional vapor chambers, heat pipes, and heat sink combinations. However, existing technologies have significant shortcomings: First, the conventional phase-change working fluids used in traditional vapor chambers have limited thermal conductivity and insufficient heat dissipation capacity, making it difficult to quickly dissipate locally concentrated heat and effectively solve the problem of hot spot accumulation. Second, the capillary wicks of existing vapor chambers are mostly single porous metal structures with insufficient capillary driving force, resulting in low working fluid reflux efficiency in the microgravity environment of satellites and a tendency for the heated areas to dry out and fail. Third, the material and structural design of the sealed shell are unreasonable, resulting in either low contact heat exchange efficiency or insufficient sealing and resistance to extreme environments, making it prone to working fluid leakage and shell deformation under vacuum, temperature alternation, and vibration conditions. Fourth, some solutions rely on gravity-assisted reflux, which has poor adaptability and cannot meet the usage scenarios of satellites with varying on-orbit attitudes, resulting in insufficient long-term operational stability and difficulty in supporting long-term on-orbit service requirements. Therefore, it is necessary to design a vapor chamber structure for high-power devices in commercial satellites based on liquid metal. Summary of the Invention The purpose of this invention is to provide a heat dissipation structure for high-power commercial satellite devices based on liquid metal in order to solve the above-mentioned problems, thereby resolving the issues mentioned in the background art.

[0004] To address the above problems, the present invention provides a technical solution: A heat dissipation structure for a high-power commercial satellite device based on liquid metal includes a device. The bottom of the device contacts an upper housing, and the bottom of the upper housing contacts a lower housing. A sealing gasket is slidably fitted inside the lower housing and slidably connected to the upper housing. Multiple uniformly distributed heat pipes are fixedly connected inside the upper housing and contact the lower housing. Each heat pipe has a capillary wick and a flow channel containing liquid metal. Multiple connecting blocks are slidably fitted to the outer side of the lower housing and slidably connected to the upper housing. A connecting rod is fixedly connected between adjacent connecting blocks. A connecting seat is fixedly fitted to the outer side of the connecting rod and contacts both the upper and lower housings. An installation mechanism is provided on each connecting block, and an assembly mechanism is provided on each connecting seat.

[0005] Preferably, both the upper and lower shells are made of titanium alloy, and the capillary wick adopts a composite structure of porous copper mesh and graphene. By designing the capillary wick, capillary force can be used to drive the liquid metal to evaporate in the heated zone and reflux in the condensed zone, forming a highly efficient phase change heat transfer cycle.

[0006] Preferably, the mounting mechanism includes a slot, with the bottom of the connecting block having a slot. An insert block is slidably connected inside the slot, and a fixing seat is slidably fitted onto the outer side of the insert block. The fixing seat is slidably connected to the connecting block. A slider is slidably fitted inside the fixing seat and is fixedly installed at the bottom of the insert block. A fixing rod is slidably fitted inside the slider and is fixedly connected to the fixing seat. A ball is fixedly connected to the bottom of the slider and is fixedly connected to the fixing seat. A push rod is fixedly connected to one end of the slider and is slidably connected to the fixing seat. A magnetic block is fixedly connected to the other end of the slider and is slidably connected to the fixing seat. A magnet is fixedly connected to the inner sidewall of the fixing seat. A connecting rod is fixedly connected to the top of the fixing seat, and a mounting base is fixedly connected to the top of the connecting rod. The mounting base is fixedly installed to the bottom of the device by bolts. This mounting mechanism facilitates the installation and use of the heat spreader structure.

[0007] Preferably, there are multiple slots, which are evenly distributed on the bottom of the connecting block, and each slot has a plug slidably fitted inside. By designing the insertion and engagement of the slots and plugs, the connecting block can be limited in position.

[0008] Preferably, a first spring is provided on the outer side of the fixing rod, one end of the first spring is fixedly connected to the slider, and the other end of the first spring is fixedly connected to the fixing seat. By designing the first spring, the elastic force of the first spring can be applied to the slider.

[0009] Preferably, the combined mechanism includes a screw, which is rotatably sleeved inside the connecting seat. A rotating block is fixedly connected to the outside of the screw, and the rotating block is rotatably connected to the connecting seat. An internal hexagonal groove is formed inside the rotating block. A push block is threadedly connected to the outside of the screw, and the push block is slidably connected to the connecting seat. A guide rod is slidably sleeved inside the push block, and the guide rod is fixedly connected to the connecting seat. Two symmetrically distributed limiting rods are fixedly connected to the outside of the push block. The limiting rods pass through the connecting rod and are slidably connected to it. The limiting rods are slidably connected to the upper and lower housings respectively. Both ends of the upper and lower housings are provided with... The device includes a limiting groove adapted to a limiting rod, with the limiting rod slidably fitted inside the limiting groove. A rotating shaft is fixedly connected to the outer side of the screw, and a limiting seat is rotatably fitted to the outer side of the rotating shaft. The limiting seat is rotatably connected to the screw and fixedly connected to a connecting seat. A retaining groove is formed on the outer surface of the rotating shaft, and a retaining ball is movably fitted inside the retaining groove. The retaining ball is movably connected to the limiting seat, and a clamping block is movably fitted to the outer side of the retaining ball. The clamping block is slidably connected to the limiting seat, and a sliding rod is fixedly connected to the outer side of the clamping block. The sliding rod is slidably connected to the limiting seat, and a rubber pad is fixedly connected to the outer side of the clamping block, contacting the rotating shaft. This modular design facilitates the separation of the upper and lower housings.

[0010] Preferably, there are multiple slots, which are arranged in a ring and evenly distributed on the outer surface of the rotating shaft. By designing multiple slots, the ball can roll into the slots at different positions.

[0011] Preferably, a second spring is provided on the outer side of the slide rod, one end of the second spring is fixedly connected to the abutment block, and the other end of the second spring is fixedly connected to the limiting seat. By designing the second spring, the elastic force of the second spring can be applied to the abutment block.

[0012] The beneficial effects of this invention are as follows: This invention relates to a heat dissipation structure for high-power devices in commercial satellites based on liquid metal. It features a small heat dissipation temperature difference, strong stability in extreme environments, adaptability to high-power-density devices, and meets the long-term on-orbit requirements of commercial satellites. In practical applications, compared with traditional heat dissipation structures for high-power devices in commercial satellites based on liquid metal, this heat dissipation structure for high-power devices in commercial satellites based on liquid metal has the following beneficial effects: Firstly, by using liquid metal as the heat transfer medium, the vapor chamber comprises a sealed shell, a liquid metal working medium, a capillary wick structure, and a vapor flow channel. The sealed shell is made of ultra-thin titanium alloy, with a micro-concave structure designed on the side that contacts the device surface to enhance contact heat transfer. The capillary wick uses a composite structure of porous copper mesh and graphene, utilizing capillary force to drive the liquid metal to evaporate in the heated zone and reflux in the condensed zone, forming a highly efficient phase change heat transfer cycle. Compared with traditional vapor chambers, the high thermal conductivity of liquid metal allows the vapor chamber's temperature difference to be controlled within 5°C, and it can maintain stable performance even under extreme vacuum and temperature alternation environments, effectively extending the operating life of high-power devices and meeting the long-term on-orbit operation requirements of commercial satellites. Secondly, by designing the insertion and engagement of the plug and slot, the connecting block can be limited, which in turn can limit the lower and upper housings, enabling the heat spreader to contact the device. The mounting base and device can be installed and fixed by bolts, and the mounting base can be installed and fixed. The plug and slot can be separated by pushing the push rod, which facilitates the disassembly and assembly of the heat spreader structure and makes it easy to use.

[0013] In addition, by designing the insertion of the limiting rod into the limiting groove on the outer side of the upper and lower shells, the upper and lower shells can be limited to achieve the combined and fixed use of the heat spreader. By rotating the rotating block to drive the screw to rotate, the push block can be made to move in a threaded motion. The push block can drive the limiting rod to move, and finally the limiting rod can be separated from the limiting groove. Then the upper and lower shells can be separated, which facilitates the inspection and maintenance of the internal structure of the heat spreader. Attached Figure Description For ease of explanation, the present invention will be described in detail below with reference to specific embodiments and accompanying drawings.

[0014] Figure 1 This is a perspective view of the overall structure of the present invention; Figure 2 For the present invention Figure 1 A three-dimensional sectional view of the shell structure; Figure 3 For the present invention Figure 1 A three-dimensional sectional view of the fixed base structure; Figure 4 For the present invention Figure 3 Enlarged view of point A; Figure 5 For the present invention Figure 1 A three-dimensional sectional view of the connector structure; Figure 6 For the present invention Figure 5 Enlarged view of point B; Figure 7 For the present invention Figure 6 The front sectional view of the limiting seat.

[0015] In the diagram: 1. Component; 2. Upper housing; 3. Lower housing; 4. Sealing gasket; 5. Heat pipe; 6. Capillary wick; 7. Flow channel; 8. Mounting mechanism; 9. Assembly mechanism; 10. Connecting block; 11. Connecting rod; 12. Connecting seat; 81. Slot; 82. Insert block; 83. Fixing seat; 84. Slider; 85. Fixing rod; 86. First spring; 87. Ball; 88. Push rod; 89. Magnetic block; 891. Magnet; 892. Connecting rod; 893. Mounting seat; 91. Screw; 92. Rotating block; 93. Push block; 94. Guide rod; 95. Limiting rod; 96. Limiting groove; 97. Rotating shaft; 98. Limiting seat; 99. Slot; 991. Ball; 992. Pressing block; 993. Slide rod; 994. Second spring; 995. Rubber pad. Detailed Implementation like Figure 1-7 As shown, the specific implementation adopts the following technical solution: Example: A heat dissipation structure for high-power commercial satellite devices based on liquid metal includes a device 1. The bottom of the device 1 contacts an upper housing 2, and the bottom of the upper housing 2 contacts a lower housing 3. A sealing gasket 4 is slidably fitted inside the lower housing 3, and the sealing gasket 4 is slidably connected to the upper housing 2. Multiple uniformly distributed heat pipes 5 are fixedly connected inside the upper housing 2, and the heat pipes 5 contact the lower housing 3. A capillary wick 6 is disposed inside the heat pipes 5. Both the upper housing 2 and the lower housing 3 are made of titanium alloy. The capillary wick 6 adopts a composite structure of porous copper mesh and graphene. By designing the capillary wick 6, the heat dissipation structure can be optimized using the heat dissipation structure. Liquid metal is driven by a fine force to evaporate in the heated zone and reflux in the condensed zone, forming a highly efficient phase change heat transfer cycle. The heat pipe 5 has a flow channel 7 inside, and liquid metal is placed inside the flow channel 7. Multiple connecting blocks 10 are slidably sleeved on the outside of the lower shell 3. The connecting blocks 10 are slidably connected to the upper shell 2. A connecting rod 11 is fixedly connected between two adjacent connecting blocks 10. A connecting seat 12 is fixedly sleeved on the outside of the connecting rod 11. The connecting seat 12 contacts the upper shell 2 and the lower shell 3 respectively. An installation mechanism 8 is provided on the connecting block 10, and a combination mechanism 9 is provided on the connecting seat 12.

[0016] The mounting mechanism 8 includes a slot 81. A slot 81 is provided at the bottom of the connecting block 10. A plug 82 is slidably connected inside the slot 81. Multiple slots 81 are evenly distributed at the bottom of the connecting block 10. A plug 82 is slidably fitted inside each slot 81. By designing the insertion and engagement of the slots 81 and plugs 82, the connecting block 10 can be limited. A fixing seat 83 is slidably fitted to the outside of the plug 82. The fixing seat 83 is slidably connected to the connecting block 10. A slider 84 is slidably fitted inside the fixing seat 83. The slider 84 is fixedly installed at the bottom of the plug 82. A fixing rod 85 is slidably fitted inside the slider 84. The fixing rod 85 is fixedly connected to the fixing seat 83. A first spring 86 is provided on the outside of the fixing rod 85. One end of the first spring 86 is connected to… The slider 84 is fixedly connected, and the other end of the first spring 86 is fixedly connected to the fixed base 83. By designing the first spring 86, the elastic force of the first spring 86 can act on the slider 84. A ball 87 is fixedly connected to the bottom of the slider 84, and the ball 87 is fixedly connected to the fixed base 83. A push rod 88 is fixedly connected to one end of the slider 84, and the push rod 88 is slidably connected to the fixed base 83. A magnetic block 89 is fixedly connected to the other end of the slider 84, and the magnetic block 89 is slidably connected to the fixed base 83. A magnet 891 is fixedly connected to the inner side wall of the fixed base 83. A connecting rod 892 is fixedly connected to the top of the fixed base 83, and a mounting base 893 is fixedly connected to the top of the connecting rod 892. The mounting base 893 is fixedly installed to the bottom of the device 1 by bolts. By designing the mounting mechanism 8, the installation and use of the heat spreader structure is convenient.

[0017] The combined mechanism 9 includes a screw 91, which is rotatably sleeved inside the connecting seat 12. A rotating block 92 is fixedly connected to the outside of the screw 91, and the rotating block 92 is rotatably connected to the connecting seat 12. The rotating block 92 has an internal hexagonal groove. A push block 93 is threadedly connected to the outside of the screw 91, and the push block 93 is slidably connected to the connecting seat 12. A guide rod 94 is slidably sleeved inside the push block 93, and the guide rod 94 is fixedly connected to the connecting seat 12. Two symmetrically distributed push blocks 93 are fixedly connected to the outside of the push block 93. A limiting rod 95 is provided, which passes through the connecting rod 11 and is slidably connected to the connecting rod 11. The limiting rod 95 is slidably connected to the upper housing 2 and the lower housing 3 respectively. Both ends of the upper housing 2 and the lower housing 3 are provided with limiting grooves 96 that are adapted to the limiting rod 95. The limiting rod 95 is slidably sleeved inside the limiting grooves 96. A rotating shaft 97 is fixedly connected to the outside of the screw 91. A limiting seat 98 is rotatably sleeved on the outside of the rotating shaft 97. The limiting seat 98 is rotatably connected to the screw 91 and fixedly connected to the connecting seat 12. The rotating shaft 97 is slidably sleeved to the connecting seat 12. The outer surface of the shaft 97 is provided with a slot 99, and a retaining ball 991 is movably fitted inside the slot 99. There are multiple slots 99, which are evenly distributed in a ring on the outer surface of the shaft 97. By designing multiple slots 99, the retaining ball 991 can roll into the slots 99 at different positions. The retaining ball 991 is movably connected to a limiting seat 98. A pressing block 992 is movably fitted outside the retaining ball 991. The pressing block 992 is slidably connected to the limiting seat 98. A sliding rod 993 is fixedly connected to the outside of the pressing block 992. The rod 993 is slidably connected to the limiting seat 98. A second spring 994 is provided on the outer side of the rod 993. One end of the second spring 994 is fixedly connected to the pressing block 992, and the other end of the second spring 994 is fixedly connected to the limiting seat 98. By designing the second spring 994, the elastic force of the second spring 994 can act on the pressing block 992. A rubber pad 995 is fixedly connected to the outer side of the pressing block 992. The rubber pad 995 contacts the rotating shaft 97. By designing the combination mechanism 9, it is convenient to separate the upper shell 2 and the lower shell 3.

[0018] The present invention is used as follows: In use, using liquid metal as the heat transfer medium, the vapor chamber includes a sealed shell, a liquid metal working medium, a capillary wick 6 structure, and a vapor flow channel 7. The sealed shell is made of ultra-thin titanium alloy, and one side of the device 1 is designed with a micro-concave structure to enhance contact heat transfer. The capillary wick 6 adopts a composite structure of porous copper mesh and graphene, utilizing capillary force to drive the liquid metal to evaporate in the heated area and reflux in the condensed area, forming a highly efficient phase change heat transfer cycle. Compared with traditional vapor chambers, the high thermal conductivity of liquid metal allows the vapor chamber temperature difference to be controlled within 5°C, and it can maintain stable performance even under extreme vacuum and temperature alternation environments, effectively extending the working life of the high-power device 1 and meeting the long-term on-orbit operation requirements of commercial satellites.

[0019] When the heat spreader needs to be disassembled, push the push rod 88 downwards. The push rod 88 moves the slider 84 downwards. The slider 84 slides along the fixed rod 85 and presses down the first spring 86. At the same time, the slider 84 presses down the ball 87. The slider 84 also moves the insert block 82 downwards. Simultaneously, the slider 84 moves the magnetic block 89 downwards. When the magnetic block 89 is attracted to the magnet 891, the insert block 82 slides out from the inside of the slot 81. Then, the heat spreader can be disassembled by moving the upper housing 2 and the lower housing 3 horizontally. The heat spreader is easy to disassemble and use.

[0020] When it is necessary to separate the upper housing 2 and the lower housing 3, first insert the hex wrench into the rotating block 92 and rotate the rotating block 92. The rotating block 92 drives the screw 91 to rotate, causing the push block 93 to make threaded motion. The push block 93 slides along the guide rod 94. At the same time, the push block 93 will drive the limiting rod 95 to move horizontally, so that the limiting rod 95 separates from the limiting groove 96. Then the upper housing 2 and the lower housing 3 can be separated, which facilitates the inspection and maintenance of the internal structure of the heat spreader.

[0021] When the screw 91 rotates, it drives the shaft 97 to rotate. The arc surface of the groove 99 inside the shaft 97 will squeeze and push the ball 991. The ball 991 will roll outward and push the pressing block 992 to move. The pressing block 992 will drive the slide rod 993 to move. The pressing block 992 will squeeze the second spring 994, which will eventually separate the ball 991 from the groove 99. When the shaft 97 stops, the elastic action of the second spring 994 will give the pressing block 992 a counter-push force, which can push the ball 991 into the groove 99 in another position. The insertion and cooperation of the ball 991 and the groove 99, as well as the contact between the rubber pad 995 and the shaft 97, can provide a certain resistance to the rotation of the screw 91, making the insertion stability of the limit rod 95 and the limit groove 96 higher, and improving the combined fixing stability of the upper shell 2 and the lower shell 3.

[0022] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the present invention. Various changes and modifications can be made to the present invention without departing from its spirit and scope. All such changes and modifications fall within the scope of the present invention as claimed, which is defined by the appended claims and their equivalents.

Claims

1. A heat dissipation structure for high-power devices in commercial satellites based on liquid metal, comprising device (1), characterized in that: The bottom of the device (1) is in contact with the upper housing (2), and the bottom of the upper housing (2) is in contact with the lower housing (3). A sealing gasket (4) is slidably fitted inside the lower housing (3). The sealing gasket (4) is slidably connected to the upper housing (2). Multiple heat pipes (5) are fixedly connected inside the upper housing (2) in a uniform distribution. The heat pipes (5) are in contact with the lower housing (3). A capillary wick (6) is provided inside the heat pipes (5). A flow channel (7) is opened inside the heat pipes (5). Liquid metal is provided. Multiple connecting blocks (10) are slidably sleeved on the outer side of the lower shell (3). The connecting blocks (10) are slidably connected to the upper shell (2). A connecting rod (11) is fixedly connected between two adjacent connecting blocks (10). A connecting seat (12) is fixedly sleeved on the outer side of the connecting rod (11). The connecting seat (12) is in contact with the upper shell (2) and the lower shell (3) respectively. An installation mechanism (8) is provided on the connecting block (10), and a combination mechanism (9) is provided on the connecting seat (12).

2. The heat dissipation structure for high-power commercial satellite devices based on liquid metal according to claim 1, characterized in that: The upper shell (2) and the lower shell (3) are both made of titanium alloy, and the capillary core (6) adopts a composite structure of porous copper mesh and graphene.

3. The heat dissipation structure for high-power commercial satellite devices based on liquid metal according to claim 1, characterized in that: The mounting mechanism (8) includes a slot (81). The bottom of the connecting block (10) has a slot (81). An insert (82) is slidably connected inside the slot (81). A fixing seat (83) is slidably sleeved on the outside of the insert (82). The fixing seat (83) is slidably connected to the connecting block (10). A slider (84) is slidably sleeved inside the fixing seat (83). The slider (84) is fixedly installed on the bottom of the insert (82). A fixing rod (85) is slidably sleeved inside the slider (84). The fixing rod (85) is fixedly connected to the fixing seat (83). A bouncing ball is fixedly connected to the bottom of the slider (84). 87), the ball (87) is fixedly connected to the fixed seat (83), one end of the slider (84) is fixedly connected to the push rod (88), the push rod (88) is slidably connected to the fixed seat (83), the other end of the slider (84) is fixedly connected to the magnetic block (89), the magnetic block (89) is slidably connected to the fixed seat (83), the inner side wall of the fixed seat (83) is fixedly connected to the magnet (891), the top of the fixed seat (83) is fixedly connected to the connecting rod (892), the top of the connecting rod (892) is fixedly connected to the mounting seat (893), and the mounting seat (893) is fixedly installed on the bottom of the device (1) by bolts.

4. The heat dissipation structure for high-power commercial satellite devices based on liquid metal according to claim 3, characterized in that: There are multiple slots (81), which are evenly distributed at the bottom of the connecting block (10), and each slot (81) has a plug (82) slidably fitted inside it.

5. The heat dissipation structure for high-power devices in commercial satellites based on liquid metal according to claim 3, characterized in that: A first spring (86) is provided on the outside of the fixed rod (85). One end of the first spring (86) is fixedly connected to the slider (84), and the other end of the first spring (86) is fixedly connected to the fixed seat (83).

6. The heat dissipation structure for high-power commercial satellite devices based on liquid metal according to claim 1, characterized in that: The combined mechanism (9) includes a screw (91), which is rotatably sleeved inside the connecting seat (12). A rotating block (92) is fixedly connected to the outside of the screw (91). The rotating block (92) is rotatably connected to the connecting seat (12). An internal hexagonal groove is provided inside the rotating block (92). A push block (93) is threadedly connected to the outside of the screw (91). The push block (93) is slidably connected to the connecting seat (12). The push block (93) has an internal hexagonal groove. A guide rod (94) is slidably sleeved on the part, and the guide rod (94) is fixedly connected to the connecting seat (12). Two symmetrically distributed limiting rods (95) are fixedly connected to the outer side of the push block (93). The limiting rods (95) pass through the connecting rod (11) and are slidably connected to the connecting rod (11). The limiting rods (95) are slidably connected to the upper shell (2) and the lower shell (3) respectively. Both ends of the upper shell (2) and the lower shell (3) are provided with limiting grooves that are adapted to the limiting rods (95). 96), the limiting rod (95) is slidably sleeved inside the limiting groove (96), the outer side of the screw (91) is fixedly connected to the rotating shaft (97), the outer side of the rotating shaft (97) is rotatably sleeved to the limiting seat (98), the limiting seat (98) is rotatably connected to the screw (91), the limiting seat (98) is fixedly connected to the connecting seat (12), the outer surface of the rotating shaft (97) is provided with a slot (99), and a retaining ball (991) is movably sleeved inside the slot (99). The ball (991) is movably connected to the limiting seat (98). A pressing block (992) is movably sleeved on the outside of the ball (991). The pressing block (992) is slidably connected to the limiting seat (98). A sliding rod (993) is fixedly connected to the outside of the pressing block (992). The sliding rod (993) is slidably connected to the limiting seat (98). A rubber pad (995) is fixedly connected to the outside of the pressing block (992). The rubber pad (995) is in contact with the rotating shaft (97).

7. A heat dissipation structure for high-power devices in commercial satellites based on liquid metal according to claim 6, characterized in that: The number of the slots (99) is multiple, and the multiple slots (99) are evenly distributed in a ring on the outer surface of the rotating shaft (97).

8. The heat dissipation structure for high-power commercial satellite devices based on liquid metal according to claim 6, characterized in that: A second spring (994) is provided on the outside of the slide bar (993). One end of the second spring (994) is fixedly connected to the abutment block (992), and the other end of the second spring (994) is fixedly connected to the limiting seat (98).

Images