Novel mechanical-thermal integrated satellite structural plate and manufacturing method thereof

Abstract

The invention provides a novel mechanical-thermal integrated satellite structure plate and a manufacturing method thereof. The novel mechanical-thermal integrated satellite structure plate comprises an upper skin (pretreated), a honeycomb core material, an embedded part, a heat pipe, a lower skin (pretreated) and an adhesive. The upper skin and the lower skin are respectively connected with the honeycomb core material through an adhesive, the heat pipe is arranged inside the honeycomb core material, the embedded part is adhered among the upper skin, the honeycomb core material and the lower skin through the adhesive, and the difference between the honeycomb core material and the honeycomb core material is that the upper skin and the lower skin are subjected to oxidation treatment before glue joint forming to obtain a thermal control oxidation layer. Therefore, integration of mechanical and thermal functions is achieved in the forming process, and an existing long-period structure and thermal control integration mode is improved. According to the method, multiple process links such as paint spraying and drying are reduced, the development period of a satellite structure platform is greatly shortened, and the satellite manufacturing requirement for quick response is met. Meanwhile, due to the simplification of the manufacturing process, the manufacturing cost of the satellite machine-hot platform is remarkably reduced, and the economical efficiency of satellite platform manufacturing is improved.

Description

Technical Field

[0001] This invention belongs to the technical field of satellite structural components, specifically relating to a novel integrated mechanical-thermal satellite structural plate and its manufacturing method. Here, "mechanical-thermal" signifies the integration of structural and thermal control functions. Background Technology

[0002] As a key component of a satellite, the satellite structural panel plays a crucial role in supporting internal equipment and maintaining overall structural stability. Furthermore, thermal control treatment of the panel surface ensures stable satellite operation in the complex space environment. Currently, the traditional development method for satellite structures involves first bonding honeycomb panels together, and then painting the surface after molding to achieve thermal control functionality.

[0003] Chinese patent CN117698224A discloses a satellite structural plate for space electronic radiation protection and its manufacturing method, including a honeycomb structural plate and electronic protection functional filler; the honeycomb structural plate includes an upper skin, a lower skin, and a honeycomb core; the upper skin and the lower skin are connected to the honeycomb core by an adhesive.

[0004] Chinese patent CN117698224A discloses a satellite structural plate for proton radiation protection in mid-Earth orbit and its manufacturing method, including a honeycomb structural plate and proton protection functional filler; the honeycomb structural plate includes an upper skin, a lower skin, and a honeycomb core; the upper skin and the lower skin are connected to the honeycomb core by an adhesive.

[0005] Both of the above-disclosed Chinese patents employ the traditional satellite structure development model, which involves molding the structure first and then applying surface painting and other treatments. This model has several drawbacks: firstly, the structural system and thermal control system are independent, resulting in a complex manufacturing process that requires multiple steps, including honeycomb panel molding, surface protection, surface treatment, painting, and drying, leading to a long production cycle; secondly, the existence of multiple stages significantly increases costs for raw materials, equipment, and labor, severely impacting the economic viability of satellite manufacturing. Therefore, it is urgent to improve the satellite structure manufacturing process to overcome the shortcomings of the traditional manufacturing model. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide a novel mechanical-thermal integrated satellite structural plate and its manufacturing method.

[0007] According to the present invention, a satellite structural panel includes: an upper skin (pre-treatment) 1, a honeycomb core material 2, an embedded part 3, a heat pipe 4, a lower skin 5 (pre-treatment), and an adhesive 6; Before use, the non-adhesive surfaces (product surfaces) of the upper skin 1 and lower skin 5 need to be black anodized to ensure that the infrared hemispherical emissivity of the skin product surface meets the thermal control requirements.

[0008] The upper skin 1 and the lower skin 5 are connected to the honeycomb core material 2 by adhesive 6, the heat pipe 4 is installed inside the honeycomb core material 2, and the embedded part 3 is bonded to the upper skin 1, the honeycomb core material 2 and the lower skin 5 by adhesive 6.

[0009] Preferably, the upper skin 1 and the lower skin 5 are made of aluminum alloy.

[0010] Preferably, the embedded part 3 is made of aluminum alloy, magnesium-aluminum alloy or magnesium-lithium alloy.

[0011] Preferably, the side length of the honeycomb cells in the honeycomb core material 2 is 3mm to 6mm.

[0012] Preferably, the embedded part 3 provides an interface for the installation and use of the structural plate, and is designed according to the usage characteristics of the interface, including threaded hole embedded parts, stepped hole embedded parts, or grounding pile embedded parts.

[0013] Preferably, the heat pipe 4 is fixedly bonded to the inside of the honeycomb core material 2 by adhesive 6.

[0014] A method for manufacturing a satellite structural panel according to the present invention includes the following steps: S1. First, the upper skin 1 and the lower skin 5 are degreased to remove surface oil and impurities, so that the surface of the aluminum alloy material is uniform and clean. S2. Next, alkaline washing is performed on the cleaned upper skin 1 and lower skin 5 to further remove the natural oxide film and other impurities. S3. Then, the surfaces of the upper skin 1 and the lower skin 5 are subjected to black anodizing treatment. S4. Next, the adhesive surfaces of the upper skin 1 and lower skin 5 after black anodizing are subjected to phosphoric acid anodizing treatment. S5. Further, apply adhesive 6 to the bonding surface of the lower skin 1 and the upper skin 5, and then seal the lower skin 1, honeycomb core material 2, embedded part 3, heat pipe 4 and upper skin 5 in the predetermined positions. S6. Vacuum cure the packaged assembly from step S5.

[0015] Preferably, when performing black anodizing on the surfaces of the upper skin 1 and the lower skin 5, the adhesive surfaces need to be protected, and the protective measures for the adhesive surfaces are removed after the black anodizing is completed.

[0016] Preferably, when performing phosphoric acid anodizing on the adhesive surfaces of the upper skin 1 and the lower skin 5, the treated black anodized surfaces need to be protected.

[0017] Preferably, the protective measures for the black anodized surface are removed after the phosphoric acid anodizing treatment is completed.

[0018] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention provides a novel integrated mechanical-thermal satellite structural panel and its manufacturing method. By improving the integration mode of structure and thermal control, the surface treatment method is used to replace the traditional thermal control painting process, reducing the thermal control painting steps. The thermal control function is integrated during the manufacturing stage of structural panel components, simplifying the manufacturing process, shortening the development cycle, reducing manufacturing costs, and ensuring good thermal control performance and structural strength, thereby realizing the integration of structure and thermal control functions.

[0019] 2. This invention provides a novel integrated mechanical-thermal satellite structural panel and its manufacturing method. In the component stage, the non-adhesive surfaces of the upper and lower skins are anodized with black to form an oxide film with thermal control properties. This results in excellent thermal control performance, effectively regulating the absorption of solar radiation and the emission of its own thermal radiation, thus maintaining a suitable temperature for the satellite in the space environment.

[0020] 3. The satellite structural panel and its manufacturing method provided by this invention involve surface treatment of the skin at the component stage to obtain a thermally controlled oxide layer, followed by direct adhesive bonding. This reduces multiple process steps such as painting and drying, significantly shortening the satellite structural platform development cycle and meeting the needs of rapid-response satellite manufacturing. Simultaneously, the simplified manufacturing process significantly reduces the manufacturing cost of the satellite engine-thermal platform, improving the economic efficiency of satellite platform manufacturing. Attached Figure Description

[0021] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of a novel integrated mechanical-thermal satellite structural plate and its manufacturing method according to the present invention.

[0022] The figure shows: upper skin 1; honeycomb core material 2; embedded part 3; heat pipe 4; lower skin 5; adhesive 6. Detailed Implementation

[0023] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0024] like Figure 1 As shown, a novel integrated mechanical-thermal satellite structural panel according to the present invention includes an upper skin (pre-treated), a honeycomb core material, embedded parts, a heat pipe, a lower skin (pre-treated), and an adhesive.

[0025] The upper and lower skins are connected to the honeycomb core material via adhesives. The heat pipes are installed inside the honeycomb core material. The embedded parts are bonded to the upper skin, honeycomb core material, and lower skin via adhesives. The upper and lower skins are made of aluminum alloy, which has advantages such as low density, high strength, and ease of processing.

[0026] Before use, the non-adhesive surfaces (product surfaces) of the upper and lower skins need to undergo black anodizing treatment to ensure that the infrared hemispherical emissivity of the skin product surface meets the thermal control requirements.

[0027] The embedded parts are made of aluminum alloy, magnesium-aluminum alloy or magnesium-lithium alloy. The embedded parts provide an interface for the installation and use of the structural plate. They are designed according to the usage characteristics of the interface. Common types include threaded hole embedded parts, stepped hole embedded parts, grounding stake embedded parts, etc. The embedded parts are bonded to the upper skin, lower skin and honeycomb core with adhesive.

[0028] The honeycomb core material is made of aluminum alloy, which has good mechanical properties and can reduce weight to the maximum extent while ensuring strength. The side length of the honeycomb cells in the honeycomb core material is 3mm to 6mm, and the thickness of the honeycomb core material is selected according to the actual use requirements of the satellite structure panel.

[0029] Heat pipes are fixed to the inside of the honeycomb core material with adhesive to transfer heat inside the structural panel, thus enabling the thermal management of the satellite structural platform.

[0030] A method for manufacturing a satellite structural panel according to the present invention includes the following steps: S1. First, the upper and lower skins are degreased to remove surface oil and impurities, so that the surface of the aluminum alloy metal material is uniform and clean. S2. Next, the cleaned upper and lower skins are subjected to alkaline washing to further remove the natural oxide film and other impurities. S3. Then, the surfaces of the upper and lower skins are subjected to black anodizing treatment, immersed in a black anodizing solution, to form an oxide film in areas requiring thermal control. The emissivity and absorptivity of the oxide layer are controlled by adjusting the solution ratio and film thickness to form a black oxide film with thermal control effects. This black oxide film exhibits excellent thermal control performance, effectively regulating the absorption of solar radiation by the satellite structural panels and the emission of its own thermal radiation, thus maintaining a suitable temperature for the satellite in the space environment.

[0031] During the process, the adhesive surface (the area that does not require black anodizing) needs to be protected. After the black anodizing process is completed, the protective measures on the adhesive surface should be removed. S4. Next, the adhesive surfaces of the upper and lower skins after black anodizing are subjected to phosphoric acid anodizing treatment. They are immersed in a phosphoric acid anodizing solution for oxidation treatment, which forms a microporous structure on the adhesive surface and improves the bonding performance. During the process, the completed black anodized surface (non-adhesive surface) needs to be protected. After the phosphoric acid anodizing treatment is completed, the protective measures for the black anodized surface should be removed. S5. Further, apply adhesive to the bonding surfaces (non-black anodized surfaces) of the lower skin and upper skin, and then encapsulate the lower skin, honeycomb core material, embedded parts, heat pipes, and upper skin in sequence according to the predetermined positions. S6. Vacuum curing is performed on the packaged assembly from step S5. The heating rate of vacuum curing does not exceed 2℃ / min, the curing temperature is 80-100℃, and the holding time is 3-8h.

[0032] The adhesive used in the bonding process of this invention is an epoxy resin adhesive, which has the advantages of high bonding strength, good resistance to high and low temperatures, and strong chemical stability.

[0033] In summary, this invention abandons the cumbersome traditional process of first gluing and molding satellite structural panels and then thermally spraying them. Instead, it performs surface treatment on the skin at the component stage to obtain a thermally controlled oxide layer, followed by direct gluing and molding. This reduces multiple process steps such as painting and drying, significantly shortening the satellite structural platform development cycle and meeting the demands of rapid-response satellite manufacturing. Furthermore, the simplified manufacturing process significantly reduces the manufacturing cost of the satellite engine-thermal platform, improving the economic efficiency of satellite platform manufacturing.

[0034] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0035] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A novel machine-thermal integrated satellite structure panel, characterized by, The application relates to a honeycomb panel, which comprises the following components: an upper skin (1), a honeycomb core (2), a pre-embedded part (3), a heat pipe (4), a lower skin (5) and an adhesive (6). The upper skin (1) and the lower skin (5) are connected to the honeycomb core (2) through the adhesive (6), the heat pipe (4) is installed in the honeycomb core (2), and the pre-embedded part (3) is bonded between the upper skin (1), the honeycomb core (2) and the lower skin (5) through the adhesive (6). The upper skin (1) and the lower skin (5) are subjected to black anodic oxidation treatment on non-bonding surfaces serving as product surfaces before use, so that the infrared hemispherical emissivity of the product surface of the skin meets the heat control index requirement. The metal material used for the upper skin (1) and the lower skin (5) is an aluminum alloy.

2. The novel machine-thermal integrated satellite structural panel according to claim 1, wherein The metal material used for the pre-embedded part (3) is an aluminum alloy, a magnesium-aluminum alloy or a magnesium-lithium alloy.

3. The novel machine-thermal integrated satellite structural panel according to claim 1, wherein The honeycomb core (2) has a honeycomb cell with a side length of 3mm-6mm.

4. The novel machine-thermal integrated satellite structural panel according to claim 1, wherein The pre-embedded part (3) provides an interface for the installation and use of a structure plate, and is designed according to the use characteristics of the interface, including a threaded hole embedded part, a stepped hole embedded part or a grounding pile embedded part.

5. The novel machine-thermal integrated satellite structural panel according to claim 1, wherein The heat pipe (4) is fixedly bonded in the honeycomb core (2) through the adhesive (6).

6. The novel machine-thermal integrated satellite structural panel according to claim 1, wherein The application further discloses a manufacturing method of the honeycomb panel.

7. A method of manufacturing the novel machine-thermal integrated satellite structure panel according to any one of claims 1 to 6, characterized by, S1, first, the upper skin (1) and the lower skin (5) are subjected to oil removal treatment to remove surface oil stains and impurities, so that the surface of the metal material aluminum alloy presents a uniform and clean state; S2, then, the cleaned upper skin (1) and lower skin (5) are subjected to alkali washing treatment to further remove natural oxidation films and other impurities; S3, then, the surfaces of the upper skin (1) and the lower skin (5) are subjected to black anodic oxidation treatment; S4, then, the bonding surfaces of the upper skin (1) and the lower skin (5) after the black anodic oxidation treatment are subjected to phosphoric acid anodization treatment; S5, further, the adhesive (6) is coated on the bonding surfaces of the upper skin (1) and the lower skin (5), and the lower skin (1), the honeycomb core (2), the pre-embedded part (3), the heat pipe (4) and the upper skin (5) are sequentially encapsulated according to predetermined positions; S6, the encapsulated combination in step S5 is subjected to vacuum curing. When the surfaces of the upper skin (1) and the lower skin (5) are subjected to black anodic oxidation treatment, the bonding surfaces need to be protected, and the protection measures of the bonding surfaces are removed after the black anodic oxidation treatment is completed.

8. The method of manufacturing a novel machine-thermal integrated satellite structure panel according to claim 7, wherein When the bonding surfaces of the upper skin (1) and the lower skin (5) are subjected to phosphoric acid anodization treatment, the treated black anodic oxidation surfaces need to be protected.

9. The method of claim 7, wherein the method further comprises the steps of: forming a plurality of holes in the first and second metal plates; and inserting a plurality of fasteners through the holes in the first and second metal plates. The protection measures of the black anodic oxidation surfaces are removed after the phosphoric acid anodization treatment is completed.

10. The method of manufacturing a novel machine-thermal integrated satellite structure panel according to claim 9, wherein ​

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