Bionic structure bearing and radiating cabin plate device for satellite

Abstract

The application provides a satellite bionic structure bearing and heat dissipation cabin plate device, which mainly comprises an upper top plate, transverse heat pipes, longitudinal heat pipes, a lower base plate and a reed bionic dot matrix structure. A plurality of longitudinal heat pipes are embedded in parallel and equidistantly on the inner surface of the upper top plate, a plurality of transverse heat pipes are embedded in parallel and equidistantly on the inner surface of the lower base plate, the transverse heat pipes and the longitudinal heat pipes are orthogonal to each other, and the outer surfaces of the projection overlapping areas of the transverse heat pipes and the longitudinal heat pipes are in close contact. The space formed by the upper top plate and the lower base plate is filled with the reed bionic dot matrix structure in a staggered manner. The cell branch arm structure of the reed bionic dot matrix structure is similar to a reed stem, the branch arm is hollow, and the pipe diameter gradually increases from the middle of each section to the two ends. The whole cabin plate serves as a heat dissipation panel by equidistantly and uniformly distributing the transverse and longitudinal heat pipes and orthogonally attaching the heat pipe fins outside, the transverse and longitudinal heat pipes arranged at a high density can play a role of reinforcing the rib plate, and the reed bionic dot matrix structure is adopted, so that the hollow structure in the reed bionic dot matrix structure can ensure the strength while greatly reducing the mass of the cabin plate.

Description

Technical Field

[0001] This invention relates to the field of satellite thermal control, and in particular to a biomimetic structure device for supporting heat dissipation panels for satellites. Background Technology

[0002] With the rapid development of aerospace technology, satellite technology is also moving towards integration. In the field of satellite payload and thermal control, traditional heat sink designs typically use aluminum metal materials, achieving heat dissipation through surface coatings. However, this design has some technical limitations. First, traditional heat sink structures are usually complex and heavy, increasing the overall weight of the satellite and affecting launch and orbit adjustment. Second, traditional heat sinks have limited thermal conductivity, failing to quickly and effectively transfer heat from satellite components to the heat sink surface, thus affecting the satellite's thermal control performance. With the continuous expansion of satellite missions and the increase in satellite payload, higher demands are placed on satellite heat dissipation performance. New heat sinks need to have higher thermal conductivity, capable of quickly and effectively transferring heat generated by various components to the heat sink surface and dissipating it through radiation, convection, and conduction to ensure stable satellite operation under various environmental conditions. Secondly, new satellite heat sinks need a lighter design to reduce the overall weight of the satellite and improve its launch efficiency. Furthermore, new heat sinks also need high mechanical strength and rigidity to ensure the structural stability and safety of the satellite during launch, orbit adjustment, and operation. Therefore, there is an urgent need for an integrated satellite module that meets the requirements of high thermal conductivity, lightweight, high mechanical strength and rigidity, in order to satisfy the stability and safety requirements of satellites in different working environments.

[0003] Patent CN112960144A discloses a 3D-printed integrated cabin panel. The panel is integrally formed using 3D printing technology, featuring internal channeled heat pipes, an external integrated printed lattice structure, and an internal integrated printed honeycomb core structure, achieving integrated load-bearing and heat dissipation design for the satellite cabin panel, resulting in a lightweight design. However, due to the limited interlayer bonding strength in 3D printing technology, the load-bearing capacity of this cabin panel is somewhat limited, and the external printed lattice structure compromises the structural integrity of the cabin panel.

[0004] Patent CN116374215A discloses a heat pipe lattice satellite vapor chamber structure and its design and manufacturing methods. The cubic lattice structure truss is made into a hollow tubular structure, with the interior evacuated under negative pressure and filled with a phase change medium to form a heat pipe lattice structure with heat exchange capabilities. Because the internal heat pipes are arranged in a lattice structure, the number of heat pipes inside the chamber is relatively large, resulting in a significant overall weight. Summary of the Invention

[0005] To address the aforementioned technical challenges, this invention proposes a satellite cabin structure with high heat transfer efficiency and strong load-bearing capacity.

[0006] The technical solution of this invention is: a biomimetic structure supporting a heat dissipation compartment for satellites, mainly comprising an upper top plate, horizontal heat pipes, vertical heat pipes, a lower base plate, and a reed-inspired biomimetic lattice structure. Multiple vertical heat pipes are pre-embedded parallel and equidistantly on the inner surface of the upper top plate, and multiple horizontal heat pipes are pre-embedded parallel and equidistantly on the inner surface of the lower base plate. The horizontal and vertical heat pipes are orthogonal to each other, and the outer surfaces of the overlapping areas of the two types of heat pipes are in close contact, enabling thermal coupling between the upper and lower plates. The space formed by the two plates is interleaved with a reed-inspired biomimetic lattice structure. This single-cell branch arm structure resembles a reed stem, with hollow interiors and a pipe diameter that gradually increases from the middle to both ends of each segment.

[0007] Preferably, in the biomimetic structure-supported heat dissipation bladder device for satellites of the present invention, both the transverse and longitudinal heat pipes are inverted figure-eight shaped double-hole structures. This structure can increase the heat-receiving area of ​​the heat pipe fins and improve heat exchange efficiency. After absorbing heat in the evaporation section, the working fluid inside the heat pipe evaporates and absorbs heat. The gaseous working fluid diffuses to the condensation section, releases heat, and condenses back into liquid. The liquid then flows back to the evaporation section under the action of capillary force through the capillary wick structure on the inner wall of the heat pipe, and this cycle repeats. The entire heat pipe is made of aerospace-grade 7075 hard aluminum alloy, and its capillary wick structure is integrally formed by selective laser melting technology. The capillary wick structure formed by selective laser melting technology is uniform and has small pores, which is more conducive to the reflux of the working fluid.

[0008] Preferably, the spacing between the horizontal and vertical heat pipes is generally recommended to be around 10cm, and the heat pipe distribution density is recommended to be 1 heat pipe / dm² (dm is decimeter). If the cabin has special requirements for the power consumption or temperature of a single unit, the parameters can be adjusted appropriately.

[0009] Preferably, the number of horizontal and vertical heat pipes is at least 3 and should not exceed 10. Too few heat pipes will result in the satellite's heat not being able to be transferred in time, while too many heat pipes will increase the weight of the cabin.

[0010] Preferably, the transverse heat pipe, longitudinal heat pipe, and external heat pipe are all evacuated to a negative pressure state before being filled with the working fluid, and after being filled with the working fluid, both ends are provided with sealing plugs to maintain the heat pipe's sealed state.

[0011] Preferably, the pre-embedded heat pipe is installed by screw fixing. The heat pipe fins have pre-drilled threaded holes that mate with corresponding holes on the upper or lower base plate for positioning and connection. After screw connection, spot welding is performed to prevent loosening.

[0012] Preferably, the reed biomimetic lattice structure is based on a kagome structure, with branch arms mimicking the reed bamboo joint structure. The reed bamboo joint structure has excellent tensile and bending resistance, good toughness, and is not easily broken.

[0013] Preferably, the number of segments of the reed biomimetic lattice structure can be adjusted according to the load-bearing capacity of the cabin plate during actual satellite operation; in this invention patent, the number is selected as 2.

[0014] Preferably, the number of layers of the reed biomimetic lattice structure needs to be determined according to the nature of the load to be borne in the satellite's working environment and the size of the heat pipe. For example, if the satellite needs greater rigidity and the height of the heat pipe needs to be increased, the number of lattice structure layers can be appropriately increased.

[0015] Preferably, in the reed biomimetic lattice structure, the individual branch arm bamboo segments are hollow inside, and the diameter of each bamboo segment is smaller in the middle and gradually increases towards both ends, with the bamboo joints being solid. Preferably, the reed biomimetic lattice structure, the upper top plate, and the lower base plate are all manufactured using selective laser melting technology in an integrated molding process, and the material used is aerospace-grade 7075 hard aluminum alloy.

[0016] Preferably, the reed biomimetic lattice structure is selected based on the horizontal comparison of simulation results, with the longitudinal height ≤ 8mm, the diameter of the bamboo joint being one-quarter of the longitudinal height, and the wall thickness of the bamboo segment being greater than 0.1mm. Excessive longitudinal height or thin wall thickness will result in insufficient strength of the lattice structure, while excessively thick bamboo segments will increase the mass of the lattice structure.

[0017] Preferably, the horizontal and vertical heat pipes penetrate the satellite compartment panel and also function as reinforcing ribs.

[0018] Preferably, the external heat pipe is disposed on the outside of the cabin plate, that is, on the outer surface of the lower substrate.

[0019] Preferably, the installation density of the external heat pipes is determined according to the installation position of the individual satellites on the deck. That is, the installation density of the external heat pipes is higher on the side corresponding to the satellite with higher heat generation power, and lower on the other side.

[0020] Preferably, the external heat pipe should be installed between two adjacent horizontal or vertical heat pipes.

[0021] The advantages and benefits of this invention are as follows: The biomimetic structure for satellite heat dissipation panels provided by this invention achieves thermal coupling between the upper and lower heat dissipation panels by externally connecting horizontal and vertical heat pipes. The heat pipes have high axial heat transfer efficiency. With the horizontal and vertical heat pipes evenly distributed and the heat pipe fins orthogonally attached, the entire panel acts as a heat dissipation panel. When a single unit mounted on the panel begins operation, i.e., when there is a local heat source, all heat pipes are forced to participate in the heat dissipation process. Utilizing this semi-active thermal control method, where heat pipes near the heat source of a single unit passively dissipate heat while all pre-embedded heat pipes are forced to dissipate heat simultaneously, the satellite's heat dissipation efficiency is significantly improved. Furthermore, the high-density arrangement of horizontal and vertical heat pipes can act as reinforcing ribs, greatly improving the satellite's load-bearing rigidity. Simultaneously, the reed-inspired lattice structure integrates the excellent shear and bending mechanical properties of reeds, further enhancing the mechanical properties of the panel. Moreover, the internal hollow structure significantly reduces the panel's mass while ensuring strength. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of a satellite-borne biomimetic structure heat dissipation liner device according to the present invention.

[0023] Figure 2 This is a schematic diagram of the horizontal and vertical heat pipe layout of a satellite biomimetic structure supporting heat dissipation compartment device according to the present invention.

[0024] Figure 3 This is a cross-sectional view of the heat pipe of a satellite-borne biomimetic structure heat dissipation hull device according to the present invention.

[0025] Figure 4 This is a schematic diagram of a reed-inspired biomimetic lattice structure for a satellite-borne heat dissipation liner device according to the present invention.

[0026] Figure 5 This is a cross-sectional view of the reed-inspired biomimetic lattice structure of a satellite-borne heat dissipation hull plate device according to the present invention.

[0027] The symbols in the diagram have the following meanings: 1. Top plate; 2. Bottom plate; 3. Horizontal heat pipe; 4. Vertical heat pipe; 5. Reed biomimetic lattice structure; 5-1. First bamboo segment; 5-2. Biomimetic bamboo joint; 5-3. Second bamboo segment; 6. External heat pipe. Detailed Implementation

[0028] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0029] like Figure 1-5As shown, this invention discloses a satellite-borne biomimetic structure heat dissipation nacelle device, mainly comprising an upper top plate 1, a lower base plate 2, horizontal heat pipes 3, vertical heat pipes 4, a reed-inspired biomimetic lattice structure 5, and externally attached heat pipes 6. Multiple vertical heat pipes 4 are pre-embedded parallel and equidistantly on the inner surface of the upper top plate 1, and multiple horizontal heat pipes 3 are pre-embedded parallel and equidistantly on the inner surface of the lower base plate 2. The horizontal heat pipes 3 and vertical heat pipes 4 are orthogonal to each other, and the outer surfaces of the overlapping areas of the two types of heat pipes are in close contact, enabling thermal coupling between the upper top plate 1 and the lower base plate 2. The space formed by the two plates of the upper top plate 1 and the lower base plate 2 is filled with an alternating reed-inspired lattice structure 5. This single-cell branch arm structure is similar to a reed stem, with hollow interiors and a pipe diameter that gradually increases from the middle to both ends of each segment.

[0030] The horizontal heat pipe 3, the vertical heat pipe 4, and the externally attached heat pipe 6 all feature an inverted figure-eight double-hole structure. This structure increases the heat-receiving area of ​​the heat pipe fins and improves heat exchange efficiency. The capillary wick structure is integrally formed using selective laser melting technology. This technology results in a uniform capillary wick structure with small pores, which is more conducive to the reflux of the working fluid.

[0031] The recommended spacing between horizontal heat pipes 3 and vertical heat pipes 4 is approximately 10cm, and the recommended heat pipe density is 1 pipe / dm². If the cabin has special requirements for the power consumption or temperature of a single unit, these parameters can be adjusted accordingly. The minimum number of horizontal heat pipes 3 and vertical heat pipes 4 should be 3, and the maximum should not exceed 10. Too few heat pipes will result in insufficient heat transfer from the satellite unit, while too many will increase the weight of the cabin.

[0032] Before filling with the working fluid, the horizontal heat pipe 3, the vertical heat pipe 4, and the external heat pipe 6 are all evacuated to a negative pressure state. After filling with the working fluid, both ends are equipped with sealing plugs to maintain the heat pipe's sealed state.

[0033] The pre-embedded heat pipes are installed using screw fixing. Threaded holes are pre-drilled on the heat pipe fins to mate with corresponding holes on the upper top plate 1 and lower base plate 2 for positioning and connection. After screw connection, spot welding is performed to prevent loosening. Horizontal heat pipes 3 and vertical heat pipes 4 penetrate the satellite compartment panel and also function as reinforcing ribs. The installation density of external heat pipes 6 is determined by the location of the individual satellite units on the compartment panel; that is, the installation density of external heat pipes 6 is higher on the side corresponding to the unit with higher heating power, and lower on the opposite side. External heat pipes 6 should be installed between adjacent horizontal or vertical heat pipes.

[0034] In this embodiment, the reed-inspired biomimetic lattice structure 5 uses a kagome structure as its framework. The branch arms mimic the bamboo joint structure of reeds, which possesses excellent tensile and bending resistance, good toughness, and is not easily broken. The number of segments in its unit cell branch arms can be adjusted according to the load-bearing capacity of the cabin during actual satellite operation; this invention patent selects 2. The number of layers needs to be determined based on the nature of the loads to be borne in the satellite's working environment and the size of the heat pipes. If the satellite requires greater rigidity and the height of the heat pipes needs to be increased during operation, the number of lattice structure layers can be appropriately increased. Specifically, the bamboo segment portion of the unit cell branch arms in the reed-inspired lattice structure 5 is hollow internally, and the diameter of each bamboo segment is smaller in the middle and gradually increases towards both ends, while the bamboo joint portion is solid.

[0035] The reed-inspired lattice structure 5, along with the upper top plate 1 and lower base plate 2, are all manufactured using selective laser melting technology in a single integrated molding process, increasing the reliability of the connection. The material used is aerospace-grade 7075 hard aluminum alloy. Furthermore, its longitudinal height should be ≤8mm, the diameter of the bamboo joint is preferably one-quarter of the longitudinal height, and the wall thickness of the bamboo segment should be greater than 0.1mm. Excessive longitudinal height or insufficient wall thickness will result in insufficient strength of the lattice structure, while excessively thick bamboo segments will increase the mass of the lattice structure.

[0036] It should be noted that the above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Those skilled in the art, once they understand the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to include the preferred embodiments as well as all changes and modifications falling within the scope of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A biomimetic structure for supporting heat dissipation panels in satellites, characterized in that: The device includes an upper top plate, horizontal heat pipes, vertical heat pipes, a lower base plate, and a reed-inspired bionic lattice structure. Multiple vertical heat pipes are pre-embedded parallel to each other at equal intervals on the inner surface of the upper top plate, and multiple horizontal heat pipes are pre-embedded parallel to each other at equal intervals on the inner surface of the lower base plate. The horizontal and vertical heat pipes are orthogonal to each other, and the outer surfaces of the overlapping areas of the two types of heat pipes are in close contact, enabling thermal coupling between the upper top plate and the lower base plate. The space formed by the two plates of the upper top plate and the lower base plate is interleaved with a reed-inspired bionic lattice structure. The single-cell branch arm structure of the reed-inspired bionic lattice structure is similar to a reed stem, with hollow interiors and a pipe diameter that gradually increases from the middle to both ends of each segment.

2. The satellite biomimetic structure support heat dissipation liner device according to claim 1, characterized in that: Both the horizontal and vertical heat pipes are inverted figure-eight shaped double-hole structures, increasing the heat-receiving area of ​​the heat pipe fins. After the heat pipe absorbs heat in the evaporation section, the internal working fluid evaporates and absorbs heat. The gaseous working fluid diffuses to the condensation section, releases heat, and condenses back into liquid. The liquid then flows back to the evaporation section through the capillary wick structure on the inner wall of the heat pipe under the action of capillary force, and so on. The overall material of the heat pipe is aerospace-grade 7075 hard aluminum alloy, and its capillary wick structure is integrally formed by selective laser melting technology.

3. The satellite biomimetic structure support heat dissipation liner device according to claim 1, characterized in that: The horizontal and vertical heat pipes are spaced 10cm apart, and the heat pipe distribution density is 1 pipe / dm².

4. The satellite biomimetic structure supporting heat dissipation hull device according to claim 1, characterized in that: The number of horizontal and vertical heat pipes shall be at least 3 and at most 10.

5. The satellite biomimetic structure support heat dissipation liner device according to claim 1, characterized in that: An external heat pipe is provided on the outer surface of the lower substrate. Before the working fluid is filled, the transverse heat pipe, the longitudinal heat pipe and the external heat pipe are all drawn into a negative pressure state. After the working fluid is filled, the two ends are provided with sealing plugs to maintain the heat pipe sealing state.

6. The satellite biomimetic structure supporting heat dissipation hull device according to claim 1, characterized in that: The pre-embedded heat pipe is installed by screw fixing. The heat pipe fins have pre-drilled threaded holes that match the corresponding holes on the top plate or bottom plate for positioning and connection. After screw connection, spot welding is performed.

7. A satellite biomimetic structure supporting heat dissipation hull device according to claim 1, characterized in that: The reed biomimetic lattice structure is based on the cage structure, and the branch arms imitate the bamboo joint structure of reeds. The bamboo segment of the single-cell branch arm of the reed biomimetic lattice structure is hollow inside, and the diameter of each bamboo segment is small in the middle and gradually increases towards both ends, while the bamboo joint is solid.

8. A satellite biomimetic structure support heat dissipation liner device according to claim 7, characterized in that: The aforementioned reed-inspired lattice structure, along with the upper top plate and lower base plate, is manufactured using selective laser melting technology in an integrated molding process, and the material used is aerospace-grade 7075 hard aluminum alloy.

9. A satellite biomimetic structure supporting heat dissipation hull device according to claim 7, characterized in that: According to simulation results, the reed biomimetic lattice structure has a longitudinal height of ≤8mm, the diameter of the bamboo joint is one-quarter of the longitudinal height, and the wall thickness of the bamboo segment is greater than 0.1mm.

10. A satellite biomimetic structure supporting heat dissipation hull device according to claim 5, characterized in that: The horizontal and vertical heat pipes penetrate the satellite compartment panel, and the external heat pipes are installed between two adjacent horizontal or vertical heat pipes.

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