Satellite deck

Abstract

The application provides a satellite cabin plate, which comprises a plate body with a containing cavity, a cell structure in the plate body, and a thermal control structure in the plate body for heat transfer; the plate body further comprises a plurality of curved surface cells in the plate body which are correspondingly matched with the thermal control structure and used for assisting the thermal control structure in heat dissipation; the satellite cabin plate further comprises a plurality of connecting structures connected with the cell structure; and the connecting structures are configured to combine and fix the plate body with external equipment. The satellite cabin plate has simple overall structure and is convenient to assemble.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellites. More particularly, it relates to a satellite cabin plate. BACKGROUND

[0002] The mission requirements of new generation satellites are increasingly complex, the service conditions are more demanding, and the technical indicators have also been greatly improved. The existing structure design and manufacturing method cannot meet the requirements. In the field of satellite structure design, lightweight, high-strength, and deep integration of functional structures are the trend. Satellite structure design and thermal control design are strongly coupled, which lays a good foundation for the design of machine-thermal integrated satellite structures that combine heat transfer and load bearing. Currently, the coupling of satellite structure and thermal control design in China is still in the early stages of technology, which severely limits the structure of the satellite.

[0003] The conventional method for coupling the satellite platform structure and thermal control is to pre-bury heat pipes inside the honeycomb sandwich composite panel. The honeycomb sandwich composite panel is used for equipment installation and mechanical load bearing, and the internal pre-buried heat pipe is used for rapid heat transfer. On the one hand, the arrangement of the heat pipe inside the honeycomb sandwich structure panel is related to the installation position of the equipment that needs to implement thermal control. In other words, the more thermal control equipment needed, the more complex the layout of the heat pipe. On the other hand, the honeycomb sandwich structure itself does not have a connection function with the on-board equipment. The inlaid part that provides the connection interface needs to be embedded in the honeycomb sandwich structure panel by pre-embedding or post-embedding process to provide a connection interface for the on-board equipment and the satellite structure panel. Obviously, the pre-buried heat pipe method will damage the integrity of the honeycomb sandwich panel, and when there are more on-board equipment, the honeycomb sandwich structure panel needs to provide more connection interfaces, which will inevitably affect the configuration and layout of the heat pipe, and even cannot be installed normally. SUMMARY

[0004] To solve the above problems, the present application provides a satellite cabin plate, which has a simple overall structure and is easy to assemble.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0006] The present application provides a satellite cabin plate, comprising:

[0007] a plate body with a receiving cavity;

[0008] a cell structure located in the plate body; and

[0009] a thermal control structure located in the plate body for heat transfer;

[0010] The plate body further comprises a plurality of curved surface cells corresponding to the thermal control structure to assist the thermal control structure in dissipating heat.

[0011] The satellite cabin plate further comprises a plurality of connection structures connected to the cell structure.

[0012] The connecting structure is configured to fix the plate body and the external device.

[0013] In addition, preferably, a transition region is included between the cell structure and the thermal control structure; the multi-curved cell is located in the transition region.

[0014] In addition, preferably, the thermal control structure is a channel heat pipe or a capillary core.

[0015] In addition, preferably, the cell structure is a honeycomb cell structure, a lattice cell structure or a grid cell structure.

[0016] In addition, preferably, the cell structure is a lattice cell structure; the lattice cell structure includes a lattice cell reinforced region and a lattice cell non-reinforced region; the lattice cell rod diameter of the lattice cell reinforced region is greater than that of the lattice cell non-reinforced region; the lattice cell reinforced region is based on a bionic design of a node.

[0017] In addition, preferably, the cell structure is a lattice cell structure; the lattice cell structure includes a first lattice cell region and a second lattice cell region; the lattice cell density of the second lattice cell region is greater than that of the first lattice cell region; the connecting structure is fixed with the second lattice cell region.

[0018] In addition, preferably, the multi-curved cell is based on a bionic design of a sponge gourd core.

[0019] In addition, preferably, the satellite cabin plate is integrally formed.

[0020] In addition, preferably, the manufacturing process of the satellite cabin plate is a laser selective melting process.

[0021] In addition, preferably, the material of the satellite cabin plate is an aluminum alloy.

[0022] The beneficial effects of the present application are:

[0023] The present application tightly couples the cell structure and the thermal control structure through the cooperation of the cell structure and the thermal control structure located in the plate body, realizes rapid heat dissipation of the satellite under the premise that the structural strength and rigidity of the satellite cabin plate meet the equipment requirements, increases the heat transfer area by using the multi-curved cell, improves the heat transfer capacity of the satellite cabin plate, and the overall structure is simple. The connecting structure fixed with the cell structure can realize the connection and fixation with the satellite, without the need for additional connecting pieces, ensuring the integrity of the satellite cabin plate, and making the assembly more convenient and fast. In addition, the satellite cabin plate is integrally printed and formed, the cabin plate structure is continuous, does not need adhesive, has strong designability, can design cell structures with different strengths and rigidities according to the load bearing requirements of different parts of the cabin plate, is conducive to weight reduction of the cabin plate. Attached Figure Description

[0024] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0025] Figure 1 This is a horizontal cross-sectional view of the satellite module of the present invention.

[0026] Figure 2 This is a vertical cross-sectional view of the satellite module of the present invention.

[0027] Figure 3 This is a schematic diagram of the structure of the lattice cell reinforcement region and the lattice cell non-reinforcement region of the present invention.

[0028] Figure 4 This is a schematic diagram of the structure of the first lattice cell region and the second lattice cell region of the present invention. Detailed Implementation

[0029] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention.

[0030] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the invention or its application or use.

[0031] Technologies and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such technologies and equipment should be considered part of the specification.

[0032] In all the examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values.

[0033] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0034] To address the problems of cumbersome structures and difficult assembly in existing satellite module designs, this invention provides a satellite module that combines... Figures 1 to 4 As shown, the satellite module specifically includes: a plate with a receiving cavity; a cellular structure located within the plate; the cellular structure can be a honeycomb cellular structure, a lattice cellular structure, or a grid cellular structure, with the minimum size and angle of the cell determined by the printing process and load-bearing requirements; and a thermal control structure located within the plate for heat transfer, wherein the thermal control structure is a channel heat pipe or a capillary core. To highlight the 3D printing integrated molding process, refer to...Figure 1 As shown, the heat control structure is a channel heat pipe 3 with porosity, the inside of which is chemically washed to achieve the required internal roughness and reduce the resistance of working fluid backflow; the plate body further comprises a plurality of curved surface cells 5 corresponding to the heat control structure to assist the heat control structure in heat dissipation; the satellite cabin plate further comprises a plurality of connection structures 6 connected to the cell structure; the connection structure 6 is configured to combine and fix the plate body with external equipment. It should be noted that the plate body comprises an upper plate 1 and a lower plate 2, and the upper plate 1 and the lower plate 2 are thin-walled structures; the cell structure, the heat control structure and the curved surface cell 5 are located between the upper plate 1 and the lower plate 2; the thickness of the upper plate 1 and the lower plate 2 is 0.4mm-1mm; the satellite cabin plate can also be designed with non-equal thickness, and according to the stiffness and strength requirements of the satellite for the satellite cabin plate and the field of view requirements of the equipment installation, the cabin plate can be designed to be concave and convex to form the effect of reinforcing ribs, further improving the overall structural strength; a cavity for laying cables can also be formed in the plate body.

[0035] Compared with the traditional satellite cabin plate composed of aluminum honeycomb sandwich plate with pre-buried heat pipes inside, the traditional satellite cabin plate will limit the equipment layout due to the heat pipes, and the overall integrity of the honeycomb core is destroyed, the strength and stiffness are reduced, a large amount of adhesive is used for pre-buried heat pipes and reinforcing members, and the weight of the cabin plate is increased, while the satellite cabin plate provided by the present application can be integrally formed without using adhesive, and the overall strength and stiffness of the cabin plate can be ensured to meet the equipment installation requirements by using the cell structure, and the heat control structure can be integrally printed with the skin and the cell, and the heat control structure in the plate body can be flexibly designed according to the heat control requirements.

[0036] In the above embodiment, further, a transition area is included between the cell structure and the heat control structure; the curved surface cell 4 is located in the transition area; the curved surface cell 4 is based on the biomimetic design of the sponge gourd pulp; through the above arrangement, the internal heat transfer area of the cabin plate can be increased, thereby further improving the heat transfer capacity.

[0037] In a specific embodiment, referring to Figure 3 As shown, when the cell structure is a dot matrix cell structure 5; the dot matrix cell structure 5 comprises a dot matrix cell reinforced area 52 and a dot matrix cell non-reinforced area 51; the dot matrix cell rod diameter of the dot matrix cell reinforced area 52 is greater than that of the dot matrix cell non-reinforced area 51; the dot matrix cell reinforced area 52 is based on the biomimetic design of bamboo joints. Specifically, according to the force transmission path of the satellite cabin plate, the reinforced area 52 is designed based on the biomimetic design of bamboo joints, thereby improving the overall strength and stiffness of the satellite cabin plate; the reinforced area 52 adopts uniform dot matrix cell design, and the dot matrix cell rod diameter of the reinforced area 52 is greater than that of the non-reinforced area 51; the reinforced area 52 has a cross-shaped structure, and the non-reinforced area 51 surrounds the periphery of the reinforced area 52.

[0038] In a specific embodiment, referring toFigure 4 As shown, when the cell structure is a lattice cell structure 5, the connecting structure 6 is located in the lattice cell structure 5, the lattice cell structure 5 includes a first lattice cell area 53 and a second lattice cell area 54, the lattice cell structure 5 around the connecting structure 6 adopts a variable density design, the lattice cell density of the second lattice cell area 54 is greater than that of the first lattice cell area 53, and the connecting structure 6 is fixed in combination with the second lattice cell area 54, and the advantage is that the second lattice cell area 54 with high density can ensure that the connecting structure 6 is more firmly connected with the satellite device and has better stability.

[0039] Further, the adapter structure connected with the cabin plate can also be integrally formed with the cabin plate, and the adapter structure is topologically optimized based on this, so that the use of connecting pieces can be reduced and the structure weight can be reduced.

[0040] In a specific embodiment, the material of the satellite cabin plate is aluminum alloy, and the manufacturing process of the satellite cabin plate is a selective laser melting (SLM) process, in which the aluminum alloy powder is completely melted by laser without the need for a binder for direct forming, and the precision and mechanical properties of the satellite cabin plate after forming are good.

[0041] In summary, the cell structure and the thermal control structure located in the plate body are coupled tightly, the structure strength and rigidity of the satellite cabin plate meet the equipment requirements, rapid heat dissipation of the satellite is realized, the heat transfer area is increased by using the multi-curved cell, the heat transfer capacity of the satellite cabin plate is improved, the overall structure is simple, the connecting structure fixedly connected with the cell structure can realize connection and fixation with the satellite, additional connecting pieces are not needed, the integrity of the satellite cabin plate is ensured, and the assembly is more convenient and fast; and the satellite cabin plate is integrally printed and formed, the cabin plate structure is continuous, no adhesive is needed, the designability is strong, different cell structures with different strength and rigidity can be designed according to the bearing requirements of different parts of the cabin plate, and the cabin plate is lightened.

[0042] Obviously, the above embodiments of the present application are only examples for clearly illustrating the present application, and are not intended to limit the embodiments of the present application, and for those skilled in the art, other different forms of changes or variations can be made on the basis of the above description, and it is impossible to enumerate all the embodiments here, and any obvious changes or variations derived from the technical solutions of the present application still fall within the protection scope of the present application.

Claims

1. A satellite module, characterized in that, include: A plate with a receiving cavity; Cellular structures located within the plate; as well as A thermal control structure located within the plate to achieve heat transfer; The plate also includes multi-curved surface cells that correspond to and cooperate with the thermal control structure to assist the thermal control structure in dissipating heat. The satellite module also includes several connecting structures that are connected to the cell structure; The connection structure is configured to secure the plate to an external device. A transition region is included between the cell structure and the thermal control structure; the multi-curved cell is located within the transition region; The thermal control structure is a channeled heat pipe or a capillary wick. The cell structure is a lattice cell structure; the lattice cell structure includes lattice cell reinforcement regions and lattice cell non-reinforcement regions. The diameter of the lattice cell rods in the reinforced region of the lattice cell is larger than that in the non-reinforced region of the lattice cell. The lattice cell reinforcement region is based on a bamboo-inspired biomimetic design. Alternatively, the lattice cell structure may include a first lattice cell region and a second lattice cell region; the lattice cell density of the second lattice cell region is greater than that of the first lattice cell region; and the connecting structure is fixedly attached to the second lattice cell region.

2. The satellite module according to claim 1, characterized in that, The multi-curved cell is based on the biomimetic design of loofah pulp.

3. The satellite module according to claim 1, characterized in that, The satellite module is integrally molded.

4. The satellite module according to claim 1, characterized in that, The satellite module is manufactured using a laser selective melting process.

5. The satellite module according to claim 1, characterized in that, The satellite module is made of aluminum alloy.

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