Multifunctional outer cabin plate dot matrix structure for satellite

Abstract

The application discloses a multifunctional outer cabin plate dot matrix structure for a satellite, which mainly comprises an inner cabin plate, an outer cabin plate, a side wall plate, a pre-embedded heat pipe, a rod-shaped regular tetrahedron dot matrix structure and a shear-resistant bearing rod, and a satellite single machine is installed on the inner cabin plate, and the outer cabin plate is directly contacted with a vacuum environment and serves as a heat dissipation plate. The pre-embedded heat pipes are all installed on the inner surface of the inner cabin plate, the pipe fin surface of the pre-embedded heat pipe is closely attached to the inner surface of the inner cabin plate, the contact area is increased, and the heat exchange efficiency is improved. The rod-shaped regular tetrahedron dot matrix structure has a whole regular tetrahedron appearance, and the unit cell structure is similar to a diamond single crystal. The rod-shaped regular tetrahedron dot matrix structure is adopted, a plurality of stable triangular structures are formed between the internal supporting arms of the dot matrix unit cell, the mechanical strength and the structural rigidity of the cabin plate are greatly enhanced, and the cabin plate load bearing capacity is improved. Meanwhile, the heat pipes can be pre-embedded in the gap of the dot matrix structure, and low-density and high-thermal-conductivity materials are filled in the blank part, so that the mechanical properties are ensured, and the heat conduction efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of satellite load-bearing and heat dissipation control, and in particular to a multifunctional outer panel matrix structure for satellites. Background Technology

[0002] With the rapid development of satellite technology, the integration level of new-generation satellites is becoming increasingly higher. To ensure normal operation and extend the service life of satellites, thermal control is a crucial aspect of satellite design. Satellites experience significant acceleration during launch, placing high demands on their structural strength. Furthermore, satellites generate substantial heat during operation from electronic components, communication equipment, and other sources. Inadequate heat management can negatively impact satellite performance and lifespan. Traditional satellite thermal control designs often utilize aluminum honeycomb core sandwich structures coated with a special coating to achieve load-bearing and heat dissipation. However, this design has several technical limitations. Traditional heat sinks rely primarily on the thermal radiation of the surface coating; aging or damage to this coating significantly reduces heat dissipation efficiency, leading to instability under high power consumption. Today, satellites perform increasingly diverse missions, placing even higher demands on load-bearing and heat dissipation capabilities. Therefore, a satellite module structure integrating load-bearing and heat dissipation capabilities is needed. This structure should possess high thermal conductivity, meet lightweight requirements, and exhibit excellent mechanical strength and rigidity to satisfy the stability and safety requirements of satellites in various operating environments.

[0003] Patent CN112960144A discloses a 3D-printed monolithic cabin panel. The panel is integrally formed using 3D printing technology, with an internally integrated honeycomb core structure, achieving both heat dissipation and lightweight design. However, this printing design suffers from limited interlayer bonding strength, which restricts the load-bearing capacity of the cabin panel. Summary of the Invention

[0004] To address the aforementioned technical challenges, this invention proposes a satellite cabin structure with high heat transfer efficiency and strong load-bearing capacity.

[0005] The technical solution of the present invention is: a multifunctional outer cabin panel lattice structure for satellites, mainly including an inner cabin panel, an outer cabin panel, side wall panels, embedded heat pipes, a rod-shaped tetrahedral lattice structure and a shear-resistant bearing rod. The satellite unit is installed on the inner cabin panel, and the outer cabin panel is in direct contact with the vacuum environment, acting as a heat dissipation plate.

[0006] Preferably, the pre-embedded heat pipes are all installed on the inner surface of the inner compartment plate, with the fins of the pre-embedded heat pipes in close contact with the inner surface of the inner compartment plate, increasing the contact area and improving the heat exchange efficiency.

[0007] Preferably, the cross-sectional shape of the pre-embedded heat pipe includes, but is not limited to, a single channel, a figure-eight channel, and an inverted figure-eight channel.

[0008] The gaseous medium diffuses through the pipes inside the pre-embedded heat pipe to the condensation section, where it releases heat and condenses into a liquid. Driven by capillary force, the liquid working fluid flows back to the evaporation section via the capillary wick structure on the inner wall of the pre-embedded heat pipe, continuously circulating this process. The capillary wick structure is integrally formed using selective laser melting technology. This technology results in a uniform capillary wick structure with minimal porosity, which further facilitates the reflux of the working fluid.

[0009] Preferably, the capillary core structure of the pre-embedded heat pipe includes, but is not limited to, a capillary micropore structure, and may also be in the form of a channel array, such as a triangular channel, a rectangular channel, a trapezoidal channel, or an Ω-shaped channel.

[0010] Preferably, the pre-embedded heat pipe is installed by screw fastening. The pre-embedded heat pipe fin has pre-set threaded holes that cooperate with the corresponding reserved light holes on the inner panel for connection and positioning. After the screw connection, spot welding is performed to prevent loosening.

[0011] Preferably, the method of filling the pre-embedded heat pipe with working fluid is as follows: first, the gas inside the heat pipe is extracted to form a negative pressure, then the working fluid is filled, and finally, the two ends of the pre-embedded heat pipe are welded with sealing plugs to keep the pre-embedded heat pipe sealed.

[0012] Preferably, the rod-shaped tetrahedral lattice structure has an overall tetrahedral appearance, and its unit cell structure is similar to that of a diamond single crystal. The diamond crystal structure contains multiple stable triangular structures, and simulations have confirmed that this structure can guarantee the strength and stability of the unit cell structure.

[0013] Preferably, the rod-shaped tetrahedral lattice structure comprises an upper top unit, six long arms, a central unit, four short arms, and three lower bottom units. Both the upper top and lower bottom units are hemispherical structures, with their circular planes tightly attached to the inner and outer deck panels, respectively. Each upper top and lower bottom unit is externally connected to three long arms and one short arm; the junctions of the three long arms form a regular arcuate triangle, and the junction of the short arm is located at the center of this arcuate triangle. The central unit is located at the center of the tetrahedron, with four short arms evenly distributed externally. This structural design allows for high symmetry in the unit cell, ensuring uniform stress distribution across the lattice structure under load and preventing stress concentration.

[0014] Preferably, in the rod-shaped tetrahedral lattice structure, the included angle between the axes of the short arms is 109°28′. This angle allows the central unit to be located at the center of the tetrahedron, maintaining the symmetry of the structure.

[0015] Preferably, the rod-shaped tetrahedral lattice structure, based on a lateral comparison of simulation results, selects optimal structural parameters. The height of the tetrahedron should be approximately 10mm, the diameter of the support arm should be ≤1mm, and the diameter of the unit sphere should be 3.3 to 3.5 times the diameter of the support arm. The length of the support arm can be calculated based on the height of the tetrahedron. Excessive longitudinal height will increase the length of the support arm and reduce the strength of the lattice structure; excessively large support arm diameters and unit sphere diameters will increase the weight of the cabin plate and increase launch costs; excessively small unit sphere diameters will cause interference between the support arms and model overlap.

[0016] Preferably, the rod-shaped tetrahedral lattice structure, along with the inner and outer cabin panels, sidewalls, and shear-resistant load-bearing rods, is integrally manufactured using selective laser melting technology, employing aerospace-grade 7075 hard aluminum alloy powder. 7075 hard aluminum alloy possesses lightweight and high-strength properties, meeting the requirements for the cabin panels. The lattice structure is relatively complex and difficult to process using traditional manufacturing processes; selective laser melting integral molding technology can manufacture complex structural components, and the molded parts exhibit excellent density properties.

[0017] Preferably, in the described rod-shaped tetrahedral lattice structure, adjacent lattice structures share 1 to 2 lower base units. Sharing units can increase the unit cell density, ensure structural compactness, and improve load-bearing capacity.

[0018] Preferably, the blank areas between the rod-shaped tetrahedral lattice structures can be filled with low-density, high-thermal-conductivity materials, such as graphene, to accelerate heat conduction and radiation.

[0019] Preferably, the shear-resistant bearing rod has the same length and diameter as the long support arm, connects the upper and lower top units of two adjacent rod-shaped tetrahedral lattice structures, and the surface of the shear-resistant bearing rod is tangent to the surface of the cabin plate, thereby enhancing the shear and bending resistance of the cabin plate.

[0020] The distribution density and spacing of the pre-embedded heat pipes described in this invention need to be calculated and determined based on actual operating conditions. If the cabin is located in a shaded area, only needs to bear loads without heat dissipation requirements, and needs to maintain satellite heat, then pre-embedded heat pipes are not necessary; instead, lightweight heat insulation material, such as fireproof cotton, can be filled into the blank spaces of the dot matrix structure.

[0021] The advantages and benefits of this invention are as follows: The multifunctional outer sub-panel lattice structure for satellites provided by this invention adopts a rod-shaped tetrahedral lattice structure, analogous to diamond single crystal, the strongest crystal in nature. Multiple stable triangular structures are formed between the internal arms of the lattice unit cell, significantly enhancing the mechanical strength and structural stiffness of the sub-panel, and improving its load-bearing capacity. Simultaneously, heat pipes can be pre-embedded in the gaps of the lattice structure, and the blank spaces can be filled with low-density, high-thermal-conductivity materials, such as graphene, thus improving thermal conductivity while ensuring mechanical performance. Furthermore, the use of the lattice structure reduces mass and saves launch costs compared to traditional structural panels. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of a multifunctional outer cabin panel dot matrix for satellites according to the present invention.

[0023] Figure 2 This is a schematic diagram of the heat pipe cross-section and capillary core structure of a multifunctional outer cabin lattice structure for satellites according to the present invention.

[0024] Figure 3 This is a schematic diagram of a rod-shaped tetrahedral dot matrix structure of a multifunctional outer cabin panel dot matrix structure for satellites according to the present invention.

[0025] Figure 4 This is a cross-sectional view of a rod-shaped tetrahedral lattice structure of a multifunctional outer cabin lattice structure for satellites according to the present invention.

[0026] Figure 5 This is a schematic diagram of the shear-resistant load-bearing rod and common unit connection of a multifunctional outer cabin lattice structure for satellites according to the present invention.

[0027] In the diagram: 1. Inner compartment panel; 2. Outer compartment panel; 3. Side wall panel; 4. Embedded heat pipe; 5. Rod-shaped tetrahedral lattice structure; 5-1. Top unit; 5-2. Long support arm; 5-3. Central unit; 5-4. Short support arm; 5-5. Bottom unit; 6. Shear-resistant load-bearing rod. 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 Figures 1-5 As shown, this invention discloses a multifunctional outer sub-panel lattice structure for satellites, mainly comprising an inner sub-panel 1, an outer sub-panel 2, sidewall panels 3, embedded heat pipes 4, a rod-shaped tetrahedral lattice structure 5, and shear-resistant load-bearing rods 6. The satellite unit is mounted on the inner sub-panel 1, while the outer sub-panel 2 directly contacts the vacuum environment, acting as a heat dissipation plate. The embedded heat pipes 4 are all installed on the inner surface of the inner sub-panel 1, with the heat pipe fins tightly adhering to the inner surface of the inner sub-panel 1, increasing the contact area and improving heat exchange efficiency. The cross-sectional shapes of the embedded heat pipes 4 include, but are not limited to, single-channel, figure-eight-shaped, and inverted figure-eight-shaped channels. The installation method is screw fastening connection. The heat pipe fins have pre-set threaded holes that mate with corresponding pre-reserved optical holes on the inner sub-panel 1 for connection and positioning. After screw connection, spot welding is performed to prevent loosening.

[0030] The working principle of the pre-embedded heat pipe 4 is as follows: the working fluid in the evaporation section absorbs heat and changes from a liquid state to a gaseous state. It then diffuses through the pipes within the heat pipe to the condensation section, where it releases heat and condenses into a liquid. Driven by capillary force, the liquid working fluid flows back to the evaporation section under the action of the capillary wick structure on the inner wall of the heat pipe, continuously circulating this process. The capillary wick structure is integrally formed using selective laser melting technology. This technology results in a uniform capillary wick structure with tiny pores, which is more conducive to the reflux of the working fluid. Furthermore, the capillary wick structure includes, but is not limited to, microporous capillary structures; it can also be in the form of a channel array, such as triangular channels, rectangular channels, trapezoidal channels, or Ω-shaped channels. The pre-embedded heat pipe 4 is filled with the working fluid as follows: first, the gas inside the heat pipe is extracted to create a negative pressure; then, the working fluid is filled; finally, end caps are welded to both ends of the heat pipe to maintain its seal.

[0031] The rod-shaped tetrahedral lattice structure 5 has an overall tetrahedral structure, with a unit cell structure similar to that of a diamond single crystal. It consists of an upper top unit 5-1, six long arms 5-2, a central unit 5-3, four short arms 5-4, and three lower bottom units 5-5. Both the upper top unit 5-1 and the lower bottom units 5-5 are hemispherical structures, with their circular planes closely attached to the inner and outer compartment panels 1 and 2, respectively. Each of the upper top unit 5-1 and the lower bottom unit 5-5 is externally connected to three long arms 5-2 and one short arm 5-4. The junctions of the three long arms 5-2 form a regular arcuate triangle, with the junction of the short arm 5-4 located at the center of this arcuate triangle. The central unit 5-3 is located at the center of the tetrahedron, with four short arms 5-4 evenly distributed around its exterior.

[0032] The rod-shaped tetrahedral lattice structure 5 has adjacent lattice structures sharing 1-2 bottom units. The empty areas between the lattice structures can be filled with low-density, high-thermal-conductivity materials, such as graphene, to accelerate heat conduction and radiation. Sharing units increases the unit cell density, ensuring structural compactness and improving load-bearing capacity.

[0033] The rod-shaped tetrahedral lattice structure 5 has an included angle of 109°28′ between the axes of the short arms 5-4. This angle ensures that the central unit 5-3 is located at the center of the tetrahedron, maintaining the symmetry of the structure. Based on the simulation results and lateral comparison, the optimal structural parameters are selected: the height of the tetrahedron should be approximately 10mm, the diameter of the arms should be ≤1mm, and the diameter of the unit spheres should be 3.3 to 3.5 times the diameter of the arms. The length of the arms can be calculated based on the height of the tetrahedron. Excessive longitudinal height will increase the arm length and reduce the strength of the lattice structure; excessive arm diameter and unit sphere diameter will increase the weight of the deck and increase launch costs; excessively small unit sphere diameter will cause interference between the arms and model overlap.

[0034] The rod-shaped tetrahedral lattice structure 5, along with the inner cabin panel 1, outer cabin panel 2, side wall panel 3, and shear-resistant load-bearing rod 6, is integrally manufactured using selective laser melting technology. The material used is aerospace-grade 7075 hard aluminum alloy powder. 7075 hard aluminum alloy has characteristics such as lightweight and high strength, meeting the requirements of the cabin panel. The lattice structure is relatively complex and difficult to process using traditional manufacturing processes. Selective laser melting integral molding technology can manufacture complex structural components, and the formed parts have excellent density properties.

[0035] The shear-resistant bearing rod 6 has the same length and diameter as the long support arm 5-2, and connects the top and bottom units of two adjacent rod-shaped tetrahedral lattice structures 5. The surface of the shear-resistant bearing rod is tangent to the surface of the cabin plate, which enhances the shear and bending resistance of the cabin plate.

[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 multifunctional outer panel lattice structure for satellites, characterized in that: The main components include an inner cabin panel, an outer cabin panel, sidewall panels, embedded heat pipes, a rod-shaped tetrahedral lattice structure, and shear-resistant load-bearing rods. The satellite unit is mounted on the inner cabin panel, while the outer cabin panel is in direct contact with the vacuum environment and acts as a heat dissipation plate. The embedded heat pipes are all installed on the inner surface of the inner cabin panel, with the fins of the embedded heat pipes tightly attached to the inner surface of the inner cabin panel. The rod-shaped tetrahedral lattice structure consists of an upper top unit, six long arms, a central unit, four short arms, and three lower bottom units. Both the upper top unit and the lower bottom unit are hemispherical structures, with their circular planes tightly attached to the inner and outer cabin panels, respectively. Each upper top unit and lower bottom unit is externally connected to three long arms and one short arm. The junctions of the three long arms form a regular arc triangle, and the junction of the short arm is located at the center of this regular arc triangle. The central unit is located at the center of the tetrahedron, and the four short arms are evenly distributed on the outside.

2. The satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: The pre-embedded heat pipe has a cross-sectional shape of a single channel, a figure-eight channel, or an inverted figure-eight channel. Under the action of the capillary core structure on the inner wall of the pre-embedded heat pipe, the liquid working fluid flows back to the evaporation section through the drive of capillary force and continuously circulates this process. The capillary core structure of the pre-embedded heat pipe is a capillary micropore structure, or a channel array with a cross-section of triangle, rectangle, trapezoid, or Ω shape.

3. The satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: The pre-embedded heat pipe is installed by screw fastening. The pre-embedded heat pipe fin has pre-set threaded holes, which are matched with the corresponding reserved light holes on the inner panel for connection and positioning. After the screw connection, spot welding is performed.

4. The satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: The rod-shaped tetrahedral lattice structure has an overall tetrahedral appearance and a unit cell structure similar to that of a diamond single crystal; the included angle between the axes of the short arms is 109°28′.

5. The satellite multifunctional outer panel lattice structure according to claim 4, characterized in that: Based on the horizontal comparison of the simulation results, the structural parameters are as follows: the height of the regular tetrahedron should be 10mm, the diameter of the support arm should be ≤1mm, the diameter of the unit sphere should be 3.3 to 3.5 times the diameter of the support arm, and the length of the support arm is calculated based on the height of the regular tetrahedron.

6. The satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: The aforementioned rod-shaped tetrahedral lattice structure, along with the inner cabin panel, outer cabin panel, side wall panel, and shear-resistant load-bearing rod, is integrally formed using selective laser melting technology, and the material used is aerospace-grade 7075 hard aluminum alloy powder.

7. The satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: The aforementioned rod-shaped tetrahedral lattice structure has adjacent lattice structures sharing 1 to 2 lower base units; The blank areas between the lattice structures are filled with a high thermal conductivity material with low density.

8. The satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: The shear-resistant bearing rod has the same length and diameter as the long support arm, and connects the upper and lower top units of two adjacent rod-shaped tetrahedral lattice structures. The surface of the shear-resistant bearing rod is tangent to the surface of the cabin plate.

9. A satellite multifunctional outer panel lattice structure according to claim 1, characterized in that: If the panel is located in a shaded area, only needs to bear loads without heat dissipation requirements, and needs to maintain satellite heat, then pre-embedded heat pipes are unnecessary; only lightweight heat insulation material is filled into the blank areas of the dot matrix structure.

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