Foamed aluminum honeycomb composite structure satellite solar panel support

Abstract

This invention discloses a foamed aluminum honeycomb composite structure satellite solar panel support, relating to the field of satellite solar panel support technology. It includes a solar panel body, two grounding posts (first type) located on one side of the bottom of the solar panel body, and two grounding posts (second type) located on the other side of the bottom of the solar panel body. The solar panel body comprises a functional panel layer, a transition layer, and a core layer. A transition layer is disposed within the functional panel layer, and the core layer is disposed within the transition layer. The functional panel layer is connected to the core layer through the transition layer. The functional panel layer is made of carbon fiber reinforced fluorinated epoxy resin composite material, and its surface is covered with a polyimide insulating film. This invention employs a gradient filling design with high density in the edge load-bearing area, thereby enhancing local stiffness and impact resistance. It achieves high bending strength while ensuring overall lightweight design, resolving the contradiction between lightweight design and mechanical performance in traditional supports.

Description

Technical Field

[0001] This invention relates to the field of satellite solar panel support technology, specifically to a satellite solar panel support with a foamed aluminum honeycomb composite structure. Background Technology

[0002] Satellite solar panel support is a key structural component used to support and fix satellite solar panels. It needs to maintain stability and reliability in the extreme space environment. It can provide mechanical support, maintain the correct attitude and angle of the panels, withstand the severe vibration and impact during launch, support dynamic operations such as unfolding, folding or solar tracking, and improve energy utilization efficiency.

[0003] Most existing satellite solar panel supports are made of metal panels bonded together by adhesive or brazing. However, with the increasing demands for structural versatility, lightweight design, and spatial adaptability from satellite platforms, the high porosity of traditional supports limits their lateral load-bearing capacity. The single core structure makes it difficult to optimize mechanical performance and quality in a coordinated manner. Insufficient interlayer interface reliability easily leads to delamination and failure. Furthermore, traditional support height and angle adjustment mechanisms are either operated separately or simultaneously. Separate operation requires adjusting the height of the support component first, followed by adjusting its angle. Since operators cannot accurately predict the height changes after angle adjustment, it is easy to encounter situations where the initial height adjustment is not compatible with the rotation angle, necessitating a second height adjustment. This makes support adjustment cumbersome and time-consuming. When the solar panels are positioned at a specific height, multi-angle adjustments cannot be performed, thus reducing the accuracy of the device during use.

[0004] Therefore, a satellite solar panel support structure with aluminum foam honeycomb composite structure is needed to solve problems such as the limited lateral load-bearing capacity caused by the high porosity inside the traditional support, the difficulty in synergistic optimization of mechanical performance and quality due to the single core structure, and the insufficient reliability of interlayer interface bonding in the existing technology. Summary of the Invention

[0005] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows: A foamed aluminum honeycomb composite structure satellite solar panel support includes a solar panel body, two grounding posts one located on one side of the bottom of the solar panel body, and two grounding posts two located on the other side of the bottom of the solar panel body. The solar panel body includes a functional panel layer, a transition layer, and a core layer. The transition layer is disposed inside the functional panel layer, and the core layer is disposed inside the transition layer. The functional panel layer is connected to the core layer through the transition layer. The functional panel layer is made of carbon fiber reinforced fluorinated epoxy resin composite material. The surface of the functional panel layer is covered with a polyimide insulating film. The transition layer is made of high temperature resistant epoxy resin film material. The core layer is composed of a regular hexagonal honeycomb aluminum core and open-cell foam aluminum filled in the honeycomb holes. The first and second grounding stakes are connected to a support and positioning assembly.

[0006] A further improvement of the technical solution of the present invention is that: the support positioning includes a support column, a connecting shell, a first rod groove, a second rod groove, a first threaded rod, a first threaded sleeve, a second connecting shaft, and a contacting component. The first rod groove is opened at the inner cavity position of the second grounding stake, the second rod groove is opened at the inner cavity position of the first grounding stake, and the first threaded rod is rotatably connected to the inner cavities of the first and second rod grooves.

[0007] A further improvement of the technical solution of the present invention is that: the threaded sleeve is threadedly connected to the top of the outer peripheral surface of two of the threaded rods, the support column is threadedly connected to the top of the outer peripheral surface of the other two threaded rods, the connecting shaft is fixed to the side of the support column that is close to each other, one side of the connecting shaft is rotatably connected to the surface of the battery panel body, and the abutting component is connected to the threaded sleeve.

[0008] A further improvement of the technical solution of the present invention is that: the abutting component includes an arc-shaped frame, a connecting shaft, and a pulley; the arc-shaped frame is fixed to one side of the threaded sleeve that is close to each other; the connecting shaft is rotatably connected to the surfaces of both ends of the battery panel body; and the pulley is rotatably sleeved at the position where the outer circumference of the connecting shaft is embedded in the inner cavity of the arc-shaped frame.

[0009] A further improvement of the technical solution of the present invention is that: the abutting component further includes an inner groove, a spring telescopic rod, a plug seat, an electromagnetic block, and a limiting hole. The inner groove is opened inside the connecting shaft. The spring telescopic rod is fixed to the inner cavity of the inner groove. The plug seat is fixed to one side of the spring telescopic rod. The electromagnetic block is fixed to the inner cavity of the inner groove at the top of the inner wall of the inner groove. One side of the outer circumference of the spring telescopic rod is made of a magnetic material. The limiting hole is evenly opened on the inner wall of the arc-shaped frame. The inner wall of the limiting hole and one side of the plug seat are arc-shaped.

[0010] A further improvement of the technical solution of the present invention is that: the support positioning assembly further includes a connecting shell, a first bevel gear, a rotating shaft, a first rotating rod, a second rotating rod, and a second bevel gear. The connecting shell is fixed at the middle position of the two first grounding stakes and the two second grounding stakes. The first bevel gear is fixedly sleeved at the bottom position of the outer circumference of the first threaded rod. The rotating shaft is rotatably connected to both sides of the inner cavity of the connecting shell. The first rotating rod is rotatably connected to the middle position of one of the connecting shells. The second rotating rod is slidably inserted through and into the middle position of the first rotating rod.

[0011] A further improvement of the technical solution of the present invention is that: the second bevel gear is fixedly sleeved on both sides of the outer circumferential surface of the rotating shaft, at the position of the outer circumferential surface of the first rotating rod and the second rotating rod, wherein two second bevel gears are meshed with the first bevel gears at adjacent positions, and the remaining two second bevel gears at adjacent positions are meshed with each other; the second rotating rod is rotatably connected to the inner wall of another connecting shell and one end of the second rotating rod extends out of the outside of the first rotating rod; the threaded structures of the two threaded rods at the outer circumferential surface of the first threaded rod located in the inner cavity of the first rod groove are arranged in opposite directions; the threaded structures of the two threaded rods at the outer circumferential surface of the second threaded rod located in the inner cavity of the second rod groove are arranged in opposite directions.

[0012] A further improvement of the technical solution of the present invention is that: the support and positioning assembly further includes a cable assembly, the cable assembly including a mounting base, a second movable shaft, a mounting block, a fixing plate, a second spring telescopic rod, a connecting block, and a clamping component. The second movable shaft is rotatably connected to the top of the mounting base, the mounting block is fixed to the top of the second movable shaft, the fixing plate is located at the top of the mounting block, the connecting block is located at the middle position of the mounting block and the fixing plate, and two second spring telescopic rods are rotatably connected to the inner walls of the mounting block and the fixing plate near the connecting block. One end of the second spring telescopic rod is fixed to the surface of the connecting block, and the clamping component is connected to the inner cavity of the mounting base.

[0013] A further improvement of the technical solution of the present invention is that: the cable assembly further includes a clamping ring, a fastener, a third movable shaft, a spur gear, a rack, a top opening, a second threaded rod, and a second threaded sleeve. The third movable shaft is rotatably connected to both sides of the inner cavity of the mounting base. The clamping ring is fixedly sleeved at the middle position of the outer circumferential surface of the two third movable shafts. The fastener is threadedly connected to the position between the bottoms of the two clamping rings. The spur gear is fixedly sleeved at one end of the outer circumferential surface of the third movable shaft. The rack is meshed at the top position of the spur gear. The top opening is opened at the top of the inner surface of the mounting base. The second threaded rod is rotatably connected to the inner cavity of the top opening. The second threaded sleeve is threadedly connected to both sides of the outer circumferential surface of the second threaded rod. The bottom of the second threaded sleeve is fixed to the surface of the adjacent rack. One side of the second threaded rod extends out of the outer position of the mounting base.

[0014] Due to the adoption of the above technical solution, the technical progress achieved by this invention compared to the prior art is as follows: 1. This invention employs a three-layer structure consisting of a functional panel layer, a transition layer, and a core layer. A gradient filling design results in a higher density in the edge load-bearing area, enhancing local stiffness and impact resistance. The functional panel layer improves the hydrophobicity of the molecular chains and the ability to regulate free volume. Combined with an outer polyimide insulating film, it forms a double-layer electrical insulation barrier, effectively preventing optical device contamination and short-circuit risks caused by material volatilization in the space environment. The intermediate transition layer has a lower density to achieve optimized mass distribution. The core layer consists of a hexagonal honeycomb aluminum skeleton filled with open-cell aluminum foam, forming an integrated core layer. Combining the high specific stiffness of the honeycomb structure with the energy-absorbing and weight-reducing properties of aluminum foam, it achieves high bending strength while ensuring overall lightweight design, resolving the contradiction between lightweight design and mechanical performance in traditional brackets.

[0015] 2. This invention allows for simultaneous height and angle adjustment of the solar panel body via support columns. Furthermore, after the solar panel body is adjusted, the tilt of the solar panel body can be adjusted separately via the arc frame. This adapts to the installation requirements of various locations, thereby improving the applicability of the device. The adjustment method is also convenient, thus enhancing the ease of use of the device.

[0016] 3. The present invention can clamp the cable passing through the bottom of the battery panel body through the clamping component. When the cable is shaken by external force during use, the mounting block and the fixing plate can rotate relative to each other, and the spring extension rod 2 can reduce the range of cable shaking, thereby avoiding the cable shaking too much and causing the connection to loosen, thus helping to fix the cable more firmly. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of the overall structure of the present invention; Figure 2 This is a three-dimensional cross-sectional view of the grounding stake one and grounding stake two of the present invention; Figure 3 In this invention Figure 2 Enlarged structural diagram at point A; Figure 4 This is a three-dimensional cross-sectional view of the connecting shell in this invention; Figure 5 This is a three-dimensional structural diagram of the arc-shaped frame in this invention; Figure 6 This is a three-dimensional cross-sectional view of the connecting shaft of the present invention; Figure 7 This is a three-dimensional structural diagram of a portion of the present invention; Figure 8 This is a three-dimensional cross-sectional view of a partial structure of the present invention; Figure 9This is a three-dimensional cross-sectional view of the solar panel body in this invention.

[0018] In the diagram: 1. Solar panel body; 2. Grounding stake one; 3. Grounding stake two; 4. Support column; 5. Connecting shell; 6. Rod groove one; 7. Rod groove two; 8. Threaded rod one; 9. Bevel gear one; 10. Rotating shaft; 11. Rotating rod one; 12. Rotating rod two; 13. Bevel gear two; 14. Threaded sleeve one; 15. Arc frame; 16. Connecting shaft one; 17. Pulley; 18. Inner groove; 19. Spring telescopic rod one; 20. Plug socket ; 21. Electromagnetic block; 22. Limiting hole; 23. Mounting base; 24. Movable shaft two; 25. Mounting block; 26. Fixing plate; 27. Spring telescopic rod two; 28. Connecting block; 29. ​​Clamping ring; 30. Fastener; 31. Movable shaft three; 32. Circular gear; 33. Rack; 34. Top opening; 35. Threaded rod two; 36. Threaded sleeve two; 37. Functional panel layer; 38. Transition layer; 39. Core layer; 40. Connecting shaft two. Detailed Implementation

[0019] The present invention will be further described in detail below with reference to embodiments: Example 1, First aspect, such as Figure 1 - Figure 9 As shown, the present invention provides a satellite solar panel support with a foamed aluminum honeycomb composite structure, including a solar panel body 1, two grounding stakes 2 located on one side of the bottom of the solar panel body 1, and two grounding stakes 3 located on the other side of the bottom of the solar panel body 1. The solar panel body 1 includes a functional panel layer 37, a transition layer 38, and a core layer 39. The transition layer 38 is disposed inside the functional panel layer 37, and the core layer 39 is disposed inside the transition layer 38. The functional panel layer 37 is connected to the core layer 39 through the transition layer 38. The functional panel layer 37 is made of carbon fiber reinforced fluorinated epoxy resin composite material. The surface of the functional panel layer 37 is covered with a polyimide insulating film. The transition layer 38 is made of high temperature resistant epoxy resin film material. The core layer 39 is composed of a regular hexagonal honeycomb aluminum core and open-cell foam aluminum filled in the honeycomb holes.

[0020] The functional panel layer 37 is prepared using T1100 grade carbon fiber and fluorinated epoxy resin as prepreg. It is laid up using an automated fiber placement process, with the layup directions alternating between 0°, 45°, -45°, and 90°. It is pre-cured at 120°C and 0.5MPa for 30 minutes to obtain the pre-fabricated panel. The inner surface of the pre-fabricated panel undergoes plasma roughening treatment, and the outer surface is coated with a polyimide insulating coating and cured at 150°C for 2 hours to obtain the functional panel layer for later use. The core layer 39 is prepared using 3003 aluminum alloy foil to create a regular hexagonal honeycomb aluminum core. After stretching and forming, it is annealed at 500°C to remove internal stress. Subsequently, the honeycomb aluminum core undergoes a composite cleaning process: alkaline washing with 5% NaOH solution at 60°C for 5 minutes, followed by acid washing with 10% HNO3 solution at room temperature for 3 minutes to remove the surface oxide film. It is then dried for later use. Foamed aluminum raw material preparation... Aluminum powder with a purity ≥99.7% and TiH2 foaming agent added at 1.5%–2.0% of the aluminum powder mass are selected, mixed, and an appropriate amount of binder is added. The mixture is then spray-dried to produce foamed aluminum particles with a particle size of 0.4–1.8 mm. The particles are cured at 120℃ for 4 hours and then sorted according to the gradient filling requirements for later use. A high-precision CNC machined steel mold is used, and the inner surface of the mold is coated with a high-temperature resistant release agent. The pre-treated honeycomb aluminum core is placed in the mold, and foamed aluminum particles of different sizes are precisely filled into the honeycomb cells according to the preset density gradient using a high-pressure centrifugal fan. The edge bearing area is filled with high-density foamed aluminum particles, and the middle transition area is filled with low-density foamed aluminum particles. The filling amount is 75%–80% of the honeycomb cell volume. An epoxy resin film is laid on the inner surface of the functional panel layer 37 and then covered on the upper and lower surfaces of the honeycomb aluminum core in the mold, ensuring that the film is flat and free of air bubbles.

[0021] After mold closing, the mold is sent to the molding press and integrated molding is carried out using a segmented heating and pressurization process: In the first stage, the temperature is raised to 100℃, a pressure of 0.3MPa is applied, and the temperature is held for 30 minutes to promote the initial foaming of aluminum foam particles; In the second stage, the temperature is raised to 160℃, the pressure is applied to 1.2~1.5MPa, and the temperature is held for 90 minutes to achieve complete foaming of aluminum foam, curing of the film and firm bonding of each layer; During the foaming process, the aluminum foam expands to fill the honeycomb holes and forms a mechanical interlock with the tooth grooves of the pre-embedded components. After molding, it is cooled to room temperature in the furnace, and the cooling rate is controlled at 5℃ / min to avoid thermal stress.

[0022] In Example 2, a second aspect, grounding stake 2 and grounding stake 3 are connected to a support positioning assembly. The support positioning assembly includes a support column 4, a connecting shell 5, a rod groove 6, a rod groove 7, a threaded rod 8, a threaded sleeve 14, a connecting shaft 40, and a contacting component. The rod groove 6 is located in the inner cavity of the grounding stake 3, and the rod groove 7 is located in the inner cavity of the grounding stake 2. The threaded rod 8 is rotatably connected to the inner cavities of the rod groove 6 and the rod groove 7. The threaded sleeve 14 is threadedly connected to the top of the outer peripheral surface of two of the threaded rods 8. The support column 4 is threadedly connected to the top of the outer peripheral surface of the other two threaded rods 8. The connecting shaft 40 is fixed to one side of the support column 4 that is close to each other. One side of the connecting shaft 40 is rotatably connected to the surface of the battery panel body 1. The contacting component is connected to the threaded sleeve 14.

[0023] Because the support column 4 is restrained by the inner cavity of the groove 6, and the threaded sleeve 14 is restrained by the inner cavity of the groove 7, the support column 4 and the threaded sleeve 14 can only move vertically. When the threaded rod 8 connected to the support column 4 rotates, the support column 4 and the threaded sleeve 14 can move vertically through the cooperation of their inner walls and the threaded structure on the outer circumference of the threaded rod 8. As the height of the support column 4 increases, the angle of the solar panel body 1 changes, allowing the solar panel body 1 to adapt to the needs of the installation operation. When the highest point of the solar panel body 1 is adjusted to meet the requirements of the site... However, when the angle of the solar panel body 1 needs to be adjusted, the threaded rod 8 connected to the inner groove 18 is rotated, so that the threaded sleeve 14 can move in the vertical direction. Under the action of the contacting parts, the side of the solar panel body 1 closest to the two grounding stakes 2 can change position, thereby adjusting the tilt angle of the solar panel body 1. Thus, the height angle of the solar panel body 1 can be adjusted simultaneously, and the tilt angle of the solar panel body 1 can be adjusted separately after the adjustment is completed. This can adapt to the installation requirements of various different places, thereby improving the applicability of the device. Moreover, the adjustment method is convenient, thereby improving the ease of use of the device.

[0024] The contacting components include an arc-shaped frame 15, a connecting shaft 16, and a pulley 17. The arc-shaped frame 15 is fixed to one side of the threaded sleeve 14 that is close to each other. The connecting shaft 16 is rotatably connected to the surfaces at both ends of the battery panel body 1. The pulley 17 is rotatably sleeved at the position where the outer circumference of the connecting shaft 16 is embedded in the inner cavity of the arc-shaped frame 15.

[0025] When the solar panel body 1 changes angle, it can drive the connecting shaft 16 to move and make the pulley 17 move along the trajectory of the inner cavity of the connecting shaft 16. Thus, the inner wall of the connecting shaft 16 can limit the movement trajectory of the connecting shaft 16 and the solar panel body 1. At the same time, the action of the pulley 17 can reduce the friction with the inner cavity surface of the connecting shaft 16, thereby avoiding the situation where the solar panel body 1 gets stuck due to excessive resistance.

[0026] The contacting components also include an inner groove 18, a spring telescopic rod 19, a plug socket 20, an electromagnetic block 21, and a limiting hole 22. The inner groove 18 is opened inside the connecting shaft 16. The spring telescopic rod 19 is fixed in the inner cavity of the inner groove 18. The plug socket 20 is fixed on one side of the spring telescopic rod 19. The electromagnetic block 21 is fixed in the inner cavity of the inner groove 18 at the top of the inner wall of the inner groove 18. One side of the outer circumference of the spring telescopic rod 19 is made of magnetic material. The limiting holes 22 are evenly opened on the inner wall of the arc frame 15. The inner wall of the limiting holes 22 and one side of the plug socket 20 are arc-shaped.

[0027] When the height of the solar panel body 1 needs to be adjusted, and the tilt of the solar panel body 1 needs to be adjusted as well, the threaded sleeve 14 moves vertically, causing the arc-shaped frame 15 to move vertically. This, combined with the contact between the inner wall of the arc-shaped frame 15 and the pulley 17, and the connection of the connecting shaft 16, allows the tilt of the solar panel body 1 to change. During this process, a set of limiting holes 22 will sequentially contact the arc surface of the plug socket 20. When the inner wall of the connecting shaft 16 contacts the plug socket 20, the spring telescopic rod 19 will deform. When the limiting holes 22 move close to the plug socket 20, under the restoring force of the spring telescopic rod 19, the tilt of the solar panel body 1 can be adjusted. The arc surface of the plug socket 20 is embedded in the inner cavity of the limiting hole 22. Thus, after the tilt of the solar panel body 1 is adjusted by the arc frame 15, the plug socket 20 is embedded in one of the limiting holes 22 under the action of the spring telescopic rod 19. When the electromagnetic block 21 is energized, the plug socket 20 is positioned under the magnetic attraction of the magnetic material on one side of the outer peripheral surface of the electromagnetic block 21 and the spring telescopic rod 19, and the spring telescopic rod 19 cannot retract or extend. Thus, the solar panel body 1 is supported at various tilt angles by the contact action between the plug socket 20 and the inner wall of the limiting hole 22, so that the solar panel body 1 can be more stable after adjustment.

[0028] The support and positioning assembly also includes a connecting shell 5, a bevel gear 9, a rotating shaft 10, a rotating rod 11, a rotating rod 12, and a bevel gear 13. The connecting shell 5 is fixed at the middle position of the two grounding stakes 2 and 3. The bevel gear 9 is fixedly sleeved at the bottom position of the outer circumference of the threaded rod 8. The rotating shaft 10 is rotatably connected to both sides of the inner cavity of the connecting shell 5. The rotating rod 11 is rotatably connected to the middle position of one of the connecting shells 5. The rotating rod 12 is slidably inserted through the middle position of the rotating rod 11. The bevel gear 13 is fixedly sleeved on the rotating shaft 8. At the locations on both sides of the outer circumferential surface of the rotating shaft 10, and on the outer circumferential surfaces of rotating rod 11 and rotating rod 2 12, two bevel gears 2 13 are meshed with adjacent bevel gears 9, and the remaining two adjacent bevel gears 2 13 are meshed with each other. Rotating rod 2 12 is rotatably connected to the inner wall of another connecting shell 5, and one end of it extends out of the outside of rotating rod 11. The threaded structures on the outer circumferential surfaces of the two threaded rods 1 8 located in the inner cavity of rod groove 1 6 are arranged in opposite directions, and the threaded structures on the outer circumferential surfaces of the two threaded rods 1 8 located in the inner cavity of rod groove 2 7 are arranged in opposite directions.

[0029] Rotating rotating rod 11 and rotating rod 12 causes the bevel gear 13 located in the middle of the inner cavity of the two connecting shells 5 to rotate. The meshing action between the bevel gear 13 and its two adjacent bevel gears 13 causes the rotating shaft 10 to rotate. The meshing action of the remaining two bevel gears 13 and bevel gear 9 causes the two threaded rods 8 to rotate. Since the threaded rods 8 located on both sides of the connecting shell 5 rotate in opposite directions, and the threaded structures on the outer circumferences of the two threaded rods 8 located in the inner cavity of the rod groove 6 are arranged in opposite directions, as are the threaded structures on the outer circumferences of the two threaded rods 8 located in the inner cavity of the rod groove 7, the two support columns 4 can move synchronously in the vertical direction, and the two threaded sleeves 14 can move synchronously in the vertical direction. Furthermore, rotating rod 11 and rotating rod 12 can rotate at the same position on the device, allowing the user to simultaneously adjust the height and angle of the battery panel body 1 according to actual conditions, as well as to adjust the tilt of the battery panel body 1 individually.

[0030] In embodiment 3, the third aspect, the support positioning assembly further includes a cable assembly, which includes a mounting base 23, a second movable shaft 24, a mounting block 25, a fixing plate 26, a second spring telescopic rod 27, a connecting block 28, and a clamping component. The second movable shaft 24 is rotatably connected to the top of the mounting base 23, the mounting block 25 is fixed to the top of the second movable shaft 24, the fixing plate 26 is located at the top of the mounting block 25, and the connecting block 28 is located at the middle position between the mounting block 25 and the fixing plate 26. Two second spring telescopic rods 27 are rotatably connected to the inner walls of the mounting block 25 and the fixing plate 26 near the connecting block 28. One end of the second spring telescopic rod 27 is fixed to the surface of the connecting block 28, and the clamping component is connected to the inner cavity of the mounting base 23.

[0031] The clamping component at the bottom of the mounting base 23 can clamp the cable passing through the bottom of the solar panel body 1. The fixing plate 26 can be fixed to the bottom of the solar panel body 1 by bolts. When the cable is shaken by external force during use, the mounting block 25 and the fixing plate 26 can rotate relative to each other, and the spring extension rod 27 can reduce the range of cable shaking, thereby preventing the cable from shaking too much and causing the connection to loosen, thus helping to fix the cable more firmly.

[0032] The cable assembly also includes clamping rings 29, fasteners 30, movable shafts 31, spur gears 32, racks 33, top openings 34, threaded rods 35, and threaded sleeves 36. Movable shafts 31 are rotatably connected to both sides of the inner cavity of the mounting base 23. Clamping rings 29 are fixedly sleeved at the middle position of the outer circumferential surfaces of the two movable shafts 31. Fasteners 30 are threadedly connected to the position between the bottoms of the two clamping rings 29. Spur gears 32 are fixedly sleeved at one end of the outer circumferential surface of the movable shafts 31. Racks 33 are meshed at the top position of the spur gears 32. Top openings 34 are opened at the top of the inner surface of the mounting base 23. Threaded rods 35 are rotatably connected to the inner cavity of the top openings 34. Threaded sleeves 36 are threadedly connected to both sides of the outer circumferential surface of threaded rods 35. The bottom of threaded sleeves 36 is fixed to the surface of the adjacent racks 33. One side of threaded rods 35 extends out of the outer position of the mounting base 23.

[0033] Because the external thread structures on both sides of the outer circumference of the threaded rod 35 are arranged in opposite directions, when the threaded rod 35 is rotated, the inner wall of the top opening 34 can resist and limit the threaded sleeve 36, allowing it to move only in the horizontal direction. Under the cooperation of the inner wall of the threaded sleeve 36 and the threaded structure at the adjacent position of the threaded rod 35, the threaded sleeve 36 can move towards or away from each other, which in turn allows the rack 33 to move towards or away from each other. Under the meshing action between the rack 33 and the spur gear 32, the movable shaft 31 rotates, causing the clamping rings 29 to rotate towards or away from each other. As the two clamping rings 29 rotate towards each other, they clamp the cable. Under the cooperation of the fastener 30 and the threaded structure of the clamping rings 29, the clamping rings 29 cannot be separated, thus ensuring that the cable is securely clamped by the clamping rings 29.

[0034] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0035] The present invention has been described in detail above. However, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, any modifications or improvements that do not depart from the spirit of the present invention are within the scope of protection of the present invention.

Claims

1. A satellite solar panel support with a foamed aluminum honeycomb composite structure, comprising a solar panel body (1), two grounding posts (2) located on one side of the bottom of the solar panel body (1), and two grounding posts (3) located on the other side of the bottom of the solar panel body (1), characterized in that: The solar panel body (1) includes a functional panel layer (37), a transition layer (38) and a core layer (39). The functional panel layer (37) has a transition layer (38) inside it, and the transition layer (38) has a core layer (39) inside it. The functional panel layer (37) is connected to the core layer (39) through the transition layer (38). The functional panel layer (37) is made of carbon fiber reinforced fluorinated epoxy resin composite material. The surface of the functional panel layer (37) is covered with a polyimide insulating film. The transition layer (38) is made of high temperature resistant epoxy resin film material. The core layer (39) is composed of a regular hexagonal honeycomb aluminum core and open-cell foam aluminum filled in the honeycomb holes. The grounding stake one (2) and grounding stake two (3) are connected to a support positioning component.

2. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 1, characterized in that: The support positioning includes a support column (4), a connecting shell (5), a first rod groove (6), a second rod groove (7), a first threaded rod (8), a first threaded sleeve (14), a second connecting shaft (40), and a contacting component. The first rod groove (6) is located in the inner cavity of the second grounding stake (3), the second rod groove (7) is located in the inner cavity of the first grounding stake (2), and the first threaded rod (8) is rotatably connected to the inner cavities of the first rod groove (6) and the second rod groove (7).

3. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 2, characterized in that: The threaded sleeve (14) is threaded to the top of the outer peripheral surface of two of the threaded rods (8), the support column (4) is threaded to the top of the outer peripheral surface of the other two threaded rods (8), the connecting shaft (40) is fixed to the side of the support column (4) that is close to each other, and one side of the connecting shaft (40) is rotatably connected to the surface of the battery panel body (1). The abutting part is connected to the threaded sleeve (14).

4. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 3, characterized in that: The contacting component includes an arc frame (15), a connecting shaft (16), and a pulley (17). The arc frame (15) is fixed to the side of the threaded sleeve (14) that is close to each other. The connecting shaft (16) is rotatably connected to the surfaces of both ends of the battery panel body (1). The pulley (17) is rotatably sleeved at the position where the outer circumference of the connecting shaft (16) is embedded in the inner cavity of the arc frame (15).

5. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 4, characterized in that: The contacting component also includes an inner groove (18), a spring telescopic rod (19), a plug seat (20), an electromagnetic block (21), and a limiting hole (22). The inner groove (18) is opened inside the connecting shaft (16). The spring telescopic rod (19) is fixed in the inner cavity of the inner groove (18). The plug seat (20) is fixed on one side of the spring telescopic rod (19). The electromagnetic block (21) is fixed in the inner cavity of the inner groove (18) at the top of the inner wall of the inner groove (18). One side of the outer circumference of the spring telescopic rod (19) is made of magnetic material. The limiting hole (22) is evenly opened on the inner wall of the arc frame (15). The inner wall of the limiting hole (22) and one side of the plug seat (20) are arc-shaped.

6. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 5, characterized in that: The support and positioning assembly also includes a connecting shell (5), a bevel gear one (9), a rotating shaft (10), a rotating rod one (11), a rotating rod two (12), and a bevel gear two (13). The connecting shell (5) is fixed at the middle position of the two grounding stakes one (2) and the two grounding stakes two (3). The bevel gear one (9) is fixedly sleeved at the bottom position of the outer circumference of the threaded rod one (8). The rotating shaft (10) is rotatably connected to both sides of the inner cavity of the connecting shell (5). The rotating rod one (11) is rotatably connected to the middle position of one of the connecting shells (5). The rotating rod two (12) is slidably inserted through the middle position of the rotating rod one (11).

7. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 6, characterized in that: The bevel gear 2 (13) is fixedly sleeved on both sides of the outer peripheral surface of the rotating shaft (10), and on the outer peripheral surfaces of the rotating rod 1 (11) and the rotating rod 2 (12). Two bevel gears 2 (13) are meshed with the adjacent bevel gear 1 (9), and the remaining two adjacent bevel gears 2 (13) are meshed with each other. The rotating rod 2 (12) is rotatably connected to the inner wall of another connecting shell (5), and one end of it extends out of the outside of the rotating rod 1 (11). The threaded structures on the outer peripheral surfaces of the two threaded rods 1 (8) in the inner cavity of the rod groove 1 (6) are arranged in opposite directions. The threaded structures on the outer peripheral surfaces of the two threaded rods 1 (8) in the inner cavity of the rod groove 2 (7) are arranged in opposite directions.

8. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 1, characterized in that: The support and positioning assembly also includes a cable assembly, which includes a mounting base (23), a second movable shaft (24), a mounting block (25), a fixing plate (26), a second spring telescopic rod (27), a connecting block (28), and a clamping component. The second movable shaft (24) is rotatably connected to the top of the mounting base (23). The mounting block (25) is fixed to the top of the second movable shaft (24). The fixing plate (26) is located at the top of the mounting block (25). The connecting block (28) is located in the middle of the mounting block (25) and the fixing plate (26). Two second spring telescopic rods (27) are rotatably connected to the inner walls of the mounting block (25) and the fixing plate (26) near the connecting block (28). One end of the second spring telescopic rod (27) is fixed to the surface of the connecting block (28). The clamping component is connected to the inner cavity of the mounting base (23).

9. The satellite solar panel support structure with aluminum foam honeycomb composite structure according to claim 8, characterized in that: The cable assembly also includes clamping rings (29), fasteners (30), three movable shafts (31), a spur gear (32), a rack (33), a top opening (34), a threaded rod (35), and a threaded sleeve (36). The three movable shafts (31) are rotatably connected to both sides of the inner cavity of the mounting base (23). The clamping rings (29) are fixedly sleeved at the middle position of the outer circumference of the two movable shafts (31). The fasteners (30) are threadedly connected to the position between the bottoms of the two clamping rings (29). The spur gear (32) is fixedly sleeved on the three movable shafts. (31) At one end of the outer peripheral surface, the rack (33) is meshed with the top of the spur gear (32), the top opening (34) is opened on the top of the inner surface of the mounting base (23), the threaded rod (35) is rotatably connected to the inner cavity of the top opening (34), the threaded sleeve (36) is threaded to both sides of the outer peripheral surface of the threaded rod (35), the bottom of the threaded sleeve (36) is fixed to the surface of the adjacent rack (33), and one side of the threaded rod (35) extends to the outer position of the mounting base (23).

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