Double-layer aluminum extrusion multifunctional spacecraft sealed cabin and column section and column section main body thereof

Abstract

The application relates to the technical field of spacecrafts, in particular to a column segment main body of a double-layer aluminum extrusion multifunctional spacecraft sealed cabin, which comprises a functional structure interlayer, an external thermal insulation assembly, cabin equipment and a wallboard; the wallboard comprises an inner channel, an inner skin, a reinforcing rib, an outer skin and an outer channel; the functional structure interlayer comprises an impact protection layer, a thermal insulation layer and an electro-hydraulic pipeline; the reinforcing rib is located in an annular cavity between the inner skin and the outer skin, and divides the annular cavity into a plurality of wallboard cavities; the impact protection layer is filled in a part of the wallboard cavities on the radial outer side; the electro-hydraulic pipeline is arranged in a part of the wallboard cavities on the radial inner side; and the thermal insulation layer is filled in a part of the wallboard cavities on the radial inner side; the inner channel is located on the inner side of the inner skin, and the cabin equipment is installed to the inner channel; the outer channel is located on the outer side of the outer skin, and the external thermal insulation assembly is inserted from the opening of the outer channel and fixed in the outer channel. The application can realize the installation and fastening of the functional structure, and shortens the manufacturing period of the spacecraft sealed cabin.

Description

Technical Field

[0001] This application relates to the field of spacecraft technology, and more particularly to a double-layered aluminum extruded multifunctional spacecraft sealing chamber and its column segments and column segments. Specifically, it relates to the thermal insulation function, impact protection function, and electro-hydraulic pipeline accommodation function required to maintain the internal environment of the spacecraft sealing chamber. Background Technology

[0002] With the development of my country's space station and the increasing demands of space missions, research on spacecraft cabins has received increasing attention. Through the coordinated efforts of life support systems, thermal control systems, and space debris protection systems, spacecraft cabins can provide environmental conditions, such as air, pressure, and temperature, that are roughly the same as on Earth, ensuring that astronauts and instruments can live and work normally in high altitudes or outer space.

[0003] In the mechanical environment of spacecraft launch, on-orbit operation, and reentry, the spacecraft's sealed bulkheads must withstand launch loads, potential aerodynamic loads, and internal pressure loads. Furthermore, during on-orbit operation, the outer surface of the sealed bulkheads exposed to solar radiation can reach temperatures exceeding 150 degrees Celsius, while temperatures on the shaded side can drop below -100 degrees Celsius. Moreover, with the increasing number of near-Earth space launches, the probability of microplanet or space debris impacting the spacecraft's sealed bulkheads is constantly rising. Structural damage to the sealed bulkheads can lead to the loss of function or even the disintegration of a single spacecraft compartment or the entire space station.

[0004] To meet the diverse functional requirements of spacecraft cabin walls, existing technologies typically employ different functional structures on the inner and outer surfaces of the cabin walls, creating multifunctional spacecraft cabins. For example, the walls of the International Space Station's dome module are layered from the outside in with an external thermal insulation blanket, a microplanet and space debris protection layer, a Kevlar fiber restraint layer, an airbag layer, and an internal wear-resistant layer. NASA's SHIIVER tanks prevent the liquid fuel inside from condensing into ice crystals or boiling overpressure due to drastic temperature changes during deep space exploration missions by spraying foam insulation material onto the tank surface and wrapping it with multiple layers of insulation material. my country's Tiangong space station uses thermal insulation blankets and thermal control coatings to block heat exchange between the interior and exterior of the cabin, and balances the heat within the cabin through fluid pathways.

[0005] Patent CN217477564U discloses a spacecraft sealed cabin structure, which includes an outer structure, an inner sealed shell, and a heat insulation layer. The heat insulation layer is installed in the non-sealed area between the outer structure and the sealed shell. This structure has the following inconveniences in practical applications: the installation and fixation of the heat insulation layer depends on the sealed shell and additional fixing devices on the sealed shell; the outer structure needs to be wrapped around the outermost part after the heat insulation layer is installed, thus the outer structure does not play a role in positioning and securing the heat insulation layer.

[0006] However, due to the limitations of the traditional spacecraft cabin structure and manufacturing process, the installation and fastening of different functional structures (such as heat insulation and protection structures) requires additional installation structures processed on the spacecraft cabin wall. These installation structures increase the design complexity of the spacecraft cabin and inevitably increase the processing time, thus affecting the economic efficiency of the spacecraft.

[0007] Therefore, how to achieve the installation and fastening of different functional structures, reduce the complexity of spacecraft cabins, shorten the manufacturing cycle of spacecraft cabins, and thus improve the launch efficiency of spacecraft are technical problems that urgently need to be solved by those skilled in the art. Summary of the Invention

[0008] This application provides a double-layer aluminum extrusion multifunctional spacecraft sealing cabin and its column segments and column segment bodies, to simplify the installation process of the heat insulation and protection functions of the spacecraft sealing cabin on the wall panels, reduce the complexity of the spacecraft sealing cabin, and shorten the manufacturing cycle of the spacecraft sealing cabin.

[0009] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0010] A column section of a double-layer aluminum extruded multifunctional spacecraft sealed cabin includes: a functional structural interlayer, an external heat insulation component, cabin equipment, and an extruded integrally formed wall panel; wherein, the wall panel includes: an inner channel, an inner skin, reinforcing ribs, an outer skin, and an outer channel; the functional structural interlayer includes: an impact protection layer, a heat insulation layer, and electro-hydraulic pipes; the reinforcing ribs are located in the annular cavity between the inner skin and the outer skin, and divide the annular cavity into multiple wall panel cavities; the impact protection layer fills the radially outer portion of the wall panel cavity; the electro-hydraulic pipes are arranged in the radially inner portion of the wall panel cavity; and the heat insulation layer fills the radially inner portion of the wall panel cavity; the inner channel is located on the inner surface of the inner skin, and the cabin equipment is installed into the inner channel through the opening of the inner channel; the outer channel is located on the outer surface of the outer skin, and the opening of the outer channel faces the circumference of the outer skin; the external heat insulation component is inserted into and fixed into the outer channel through the opening of the outer channel.

[0011] The column body of the double-layer aluminum extrusion multifunctional spacecraft sealing cabin as described above, wherein, preferably, the wall panel cavity is a triangular cavity and / or a rectangular cavity.

[0012] In the column body of the double-layer aluminum extruded multifunctional spacecraft sealing cabin described above, preferably, the impact protection layer is filled in the radially outer portion of the triangular cavity, or the impact protection layer is filled in the radially outer portion of the rectangular cavity; the electro-hydraulic pipeline is arranged in the radially inner portion of the triangular cavity, or the electro-hydraulic pipeline is arranged in the radially inner portion of the rectangular cavity; and the heat insulation layer is filled in the radially inner portion of the triangular cavity, or the heat insulation layer is filled in the radially inner portion of the rectangular cavity.

[0013] In the column body of the double-layer aluminum extrusion multifunctional spacecraft sealing cabin described above, preferably, the heat insulation layer is a soft heat insulation foam, and the electro-hydraulic pipeline is first arranged in the radially inner part of the wall panel cavity, and then the heat insulation layer is filled in the radially inner part of the wall panel cavity to fix the electro-hydraulic pipeline after the heat insulation layer has cured.

[0014] The column body of the double-layer aluminum extruded multifunctional spacecraft sealing cabin as described above, preferably, includes the following external channel: a vertical plate, a top plate, a vertical plate hole, and a top plate hole; the inner edge of the vertical plate is connected to the outer skin, and the vertical plate hole penetrates the vertical plate; the inner side of the top plate is connected to the outer edge of the vertical plate, and the top plate hole penetrates the top plate; the external heat insulation assembly includes: a heat insulation blanket, a C-shaped frame, a clamping pad, a steel wire rope, a steel wire rope cap, and an outer heat insulation blanket; the end of the heat insulation blanket is inserted and fixed to the C-shaped frame, the steel wire rope passes through the C-shaped frame hole located on the side of the C-shaped frame, and its beginning is connected to the clamping pad located in the gap between the side of the C-shaped frame and the end face of the heat insulation blanket; the C-shaped frame is inserted and fixed to the external channel, the steel wire rope passes through the vertical plate hole and the top plate hole, the steel wire rope cap is located on the outside of the top plate and installed to the end of the steel wire rope, and the outer heat insulation blanket is adhered to the heat insulation blanket and covers the external channel.

[0015] In the column body of the double-layer aluminum extrusion multifunctional spacecraft sealing cabin described above, preferably, the end of the heat insulation blanket is fixed to the inside of the C-shaped frame by adhesive bonding or riveting, and the inner and outer surfaces of the C-shaped frame are pressing surfaces to tightly compact the corresponding area of ​​the heat insulation blanket.

[0016] In the column body of the double-layer aluminum extrusion multifunctional spacecraft sealing cabin described above, preferably, the C-shaped frame and the outer channel are interference fit to achieve the fixation of the C-shaped frame and the outer channel.

[0017] In the column body of the double-layer aluminum extruded multifunctional spacecraft sealing cabin described above, preferably, nylon patches are arranged on the outer side of the heat insulation blanket, the nylon patches of the heat insulation blanket are distributed on both sides of the outer channel, and nylon patches are arranged on the two opposite side edges of the outer heat insulation blanket. The nylon patches of the outer heat insulation blanket are bonded and fixed to the nylon patches of the heat insulation blanket so that the outer heat insulation blanket covers the outer channel.

[0018] A column segment for a double-layer aluminum extrusion multifunctional spacecraft sealing compartment includes: an upper frame, a lower frame, and a column segment body as described above; the upper end of the column segment body is fixedly connected to the upper frame, and the lower end of the column segment body is fixedly connected to the lower frame.

[0019] A double-layer aluminum extrusion multifunctional spacecraft sealing chamber includes: an upper conical section, a lower conical section, and the aforementioned column section; wherein, the column section is fixedly connected to the upper conical section via an upper end frame, and the column section is fixedly connected to the lower conical section via a lower end frame.

[0020] Compared to the aforementioned background technology, this application integrates a functional structural interlayer with protective and heat insulation functions into the cavity of the wall panel, achieving positioning through the inner surface of the cavity. Furthermore, it integrates external heat insulation components and internal equipment into channels on the wall panel surface. The wall panel structure eliminates the need for additional fixing structures, making the positioning and fastening of the functional structural interlayer, external heat insulation components, and internal equipment convenient. Moreover, the positioning structure on the wall panel for positioning the functional structural interlayer, external heat insulation components, and internal equipment is formed simultaneously with the load-bearing structure on the wall panel, resulting in high processing efficiency. This effectively shortens the manufacturing cycle of the spacecraft's sealed cabin and improves the economic benefits of spacecraft launches. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0022] Figure 1 This is a schematic diagram of a column section of a double-layer aluminum extruded multi-functional spacecraft sealing cabin;

[0023] Figure 2 This is a schematic diagram of the main column section of a double-layer aluminum extruded multi-functional spacecraft sealing cabin;

[0024] Figure 3 This is a schematic diagram of the combination of a C-shaped frame, a clamping pad, and a steel wire rope;

[0025] Figure 4 This is a schematic diagram of the combination of an insulation blanket and a C-shaped frame;

[0026] Figure 5 This is a schematic diagram of the combination of a C-shaped frame and an outer channel. Figure 1 ;

[0027] Figure 6 This is a schematic diagram of the combination of a C-shaped frame and an outer channel. Figure 2 ;

[0028] Figure 7 This is a schematic diagram of the combination of an outer thermal insulation blanket and a thermal insulation blanket;

[0029] Explanation of reference numerals in the attached figures

[0030] 1-Column segment main body; 2-Upper frame; 3-Lower frame;

[0031] 11-Ball panel; 12-Functional structural interlayer; 13-External thermal insulation components; 14-Internal equipment;

[0032] 111-Inner channel; 112-Inner skin; 113-Reinforcing rib; 114-Outer skin; 115-Outer channel;

[0033] 121-Impact protection layer; 1211-Buffer body; 1212-Metal plate; 122-Insulation layer; 123-Electro-hydraulic pipeline;

[0034] 1151 - Vertical plate; 1152 - Top plate; 1153 - Small hole in vertical plate; 1154 - Small hole in top plate;

[0035] 131-Insulation blanket; Nylon patch 1311; 132-C-shaped frame; 1321-Small hole in C-shaped frame; 133-Compression gasket; 134-Steel wire rope; 135-Steel wire rope cap; 136-Outer insulation blanket. Detailed Implementation

[0036] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0037] As described in the background art, in the prior art, the installation of different functional structures (e.g., protective and thermal insulation structures) of spacecraft cabins relies on additional installation structures processed on the surface of the spacecraft cabin wall panels. The complex installation process of these functional structures limits the reduction of the spacecraft cabin manufacturing cycle and the improvement of economic efficiency.

[0038] To solve the above problems, such as Figure 1As shown, this application provides a double-layer aluminum extrusion multifunctional spacecraft sealing chamber, including: an upper conical section, a cylindrical section, and a lower conical section (the upper and lower conical sections are not shown in the figure); wherein, the cylindrical section includes: a cylindrical section body 1, an upper end frame 2, and a lower end frame 3, the upper end of the cylindrical section body 1 is fixedly connected to the upper end frame 2, and the lower end of the cylindrical section body 1 is fixedly connected to the lower end frame 3, thereby forming a cylindrical section; the cylindrical section is fixedly connected to the upper conical section through the upper end frame 2, and the cylindrical section is fixedly connected to the lower conical section through the lower end frame 3, thereby forming a complete sealed cavity.

[0039] The main body 1 of the column segment includes: a wall panel 11, a functional structural interlayer 12, an external heat insulation component 13, and an internal equipment 14; wherein, the functional structural interlayer 12, the external heat insulation component 13, and the internal equipment 14 are all integrated into the wall panel 11, and the integration of the functional structural interlayer 12, the external heat insulation component 13, and the internal equipment 14 into the wall panel 11 is achieved by means of an integrally formed cavity or channel on the wall panel 11.

[0040] In this embodiment, combined with Figure 2 As shown, the wall panel 11 is formed using an aluminum extrusion process, a manufacturing process that involves extruding aluminum alloy material through a die. A single extrusion produces an extruded long profile of at least 20 meters, which is then divided into wall panels 11 of specific lengths according to the size requirements of the spacecraft's sealed cabin. The extruded long profile is formed by continuously extruding aluminum alloy billets through an extrusion die under high temperature and pressure, from an outlet of a specific shape in the die, to create a long strip-shaped metal component with a fixed cross-sectional shape and continuous length. The wall panels 11 can be cylindrical after division, or they can be curved plates, formed by splicing several curved wall panels 11 to create a cylindrical wall panel 11.

[0041] The wall panel 11 includes: an inner channel 111, an inner skin 112, a reinforcing rib 113, an outer skin 114, and an outer channel 115. The inner channel 111, inner skin 112, reinforcing rib 113, outer skin 114, and outer channel 115 are integrally extruded. Among them, the reinforcing rib 113 is located in the annular cavity between the inner skin 112 and the outer skin 114, and divides the annular cavity between the inner skin 112 and the outer skin 114 into multiple wall panel cavities, which can be triangular cavities and / or rectangular cavities. These wall panel cavities serve as positioning references for installing the functional structural interlayer 12, thereby avoiding the need to process additional positioning structures and improving manufacturing efficiency.

[0042] The reinforcing rib 113 extends from the inner skin 112 to the outer skin 114, then bends and extends back from the outer skin 114 to the inner skin 112, thus forming a triangular cavity with a similar cross-section. The reinforcing rib 113 can extend radially between the inner skin 112 and the outer skin 114, thereby dividing the annular cavity into rectangular cavities with a similar cross-section. Optionally, all the divided wall panel cavities are uniform cavities, so that each part of the wall panel 11 has a balanced function (e.g., heat insulation and protection).

[0043] In this embodiment, combined with Figure 2 As shown, the functional structural interlayer 12 includes an impact protection layer 121, a heat insulation layer 122, and electro-hydraulic conduits 123. The impact protection layer 121 fills the radially outer portion of the wall panel cavity, using the inner surface of the wall panel cavity as a positioning reference for convenient positioning and fastening. Specifically, the impact protection layer 121 fills the radially outer portion of the triangular cavity, that is, the portion of the triangular cavity facing the outer skin 114; or the impact protection layer 121 fills the radially outer portion of the rectangular cavity, that is, the portion of the rectangular cavity facing the outer skin 114.

[0044] Optionally, the impact protection layer 121 is fixed to the inner surface of the wall panel cavity by adhesive bonding. Alternatively, the impact protection layer 121 can be a single-layer plate made of a single protective material, or a composite plate formed by layering and compressing multiple protective materials, thereby improving protective capabilities. Still optional, the impact protection layer 121 includes: an outer buffer body 1211 and an inner metal plate 1212; the buffer body 1211 is composed of high-strength composite fiber cloth. The impact protection layer 121 located within the wall panel cavity, together with the outer skin 114, forms the Whipple structure widely used in the field of spacecraft microplanet or space debris protection. By dispersing impact energy and reducing the risk of penetration, the wall panel 11 possesses excellent impact resistance.

[0045] In this embodiment, combined with Figure 2As shown, the electro-hydraulic conduit 123 is arranged in the radially inner portion of the wall panel cavity, and the heat insulation layer 122 is filled in the radially inner portion of the wall panel cavity. Both the electro-hydraulic conduit 123 and the heat insulation layer 122 use the inner surface of the wall panel cavity as a positioning reference to achieve convenient positioning and fastening. Specifically, the electro-hydraulic conduit 123 is arranged in the radially inner portion of the triangular cavity, that is, in the portion of the triangular cavity facing the inner skin 112; or the electro-hydraulic conduit 123 is arranged in the radially inner portion of the rectangular cavity, that is, in the portion of the rectangular cavity facing the inner skin 112; the heat insulation layer 122 is filled in the radially inner portion of the triangular cavity, that is, in the portion of the triangular cavity facing the inner skin 112; or the heat insulation layer 122 is filled in the radially inner portion of the rectangular cavity, that is, in the portion of the rectangular cavity facing the inner skin 112.

[0046] Optionally, the insulation layer 122 is made of flexible insulating foam. Alternatively, the electro-hydraulic conduit 123 is pre-arranged in the radially inner cavity of the wall panel before the insulation layer 122, and the insulation layer 122, after curing, is used to fix the electro-hydraulic conduit 123. Still alternatively, the electro-hydraulic conduit 123 is tightly attached to the inner skin 112, so that the electro-hydraulic conduit 123 is as far away as possible from the outer side of the wall panel 11.

[0047] Furthermore, the width of the annular cavity between the inner skin 112 and the outer skin 114 (i.e., the distance between the inner skin 112 and the outer skin 114) is variable. For example, it can be adjusted by modifying the cross-sectional shape of the extruded long profile. The thickness of the impact protection layer 121 and the heat insulation layer 122 is also designable. By adjusting the thickness of the impact protection layer 121 and the heat insulation layer 122, the impact resistance and environmental retention capabilities of the spacecraft cabin can be optimized, thereby helping to improve the carrying capacity and structural life of the spacecraft cabin.

[0048] In this embodiment, the inner channel 111 is located on the inner side of the inner skin 112, and the opening of the inner channel 111 is away from the inner skin 112. It is suitable for installing the cabin equipment 14 and can also be used for loading cargo. The outer channel 115 is located on the outer side of the outer skin 114, and the opening of the outer channel 115 faces the circumference of the outer skin 114. It is suitable for installing and fastening the external thermal insulation component 13 so that the external thermal insulation component 13 is tightly attached to the outer skin 114. By using the inner channel 111 and the outer channel 115 of the wall panel 11 as positioning references for the cabin equipment 14 and the external thermal insulation component 13, it is possible to avoid processing additional positioning structures and improve manufacturing efficiency.

[0049] Combination Figures 3 to 7As shown, the outer channel 115 includes: a vertical plate 1151, a top plate 1152, a vertical plate hole 1153, and a top plate hole 1154; the inner edge of the vertical plate 1151 is connected to the outer skin 114, and the vertical plate hole 1153 passes through the vertical plate 1151; the centerline of the inner side of the top plate 1152 is connected to the outer edge of the vertical plate 1151, and the top plate hole 1154 passes through the top plate 1152. The external thermal insulation assembly 13 includes: a thermal insulation blanket 131, a C-shaped frame 132, a compression gasket 133, a steel wire rope 134, a steel wire rope cap 135, and an outer thermal insulation blanket 136.

[0050] The end of the heat insulation blanket 131 is inserted into and fixed to the C-shaped frame 132. Optionally, the heat insulation blanket 131 is rectangular. Alternatively, the end of the heat insulation blanket 131 is inserted into the C-shaped frame 132 and fixed to the C-shaped frame 132 by gluing or riveting. Still alternatively, the inner and outer surfaces of the C-shaped frame 132 are pressing surfaces, tightly pressing the corresponding area of ​​the heat insulation blanket 131. The side of the C-shaped frame 132 is provided with small C-shaped frame holes 1321 for leading out the steel wire rope 134; a gap is left between the side of the C-shaped frame 132 and the end face of the heat insulation blanket 131 for installing a clamping washer 133, and the clamping washer 133 is used to fix the beginning of the steel wire rope 134.

[0051] The C-shaped frame 132 is inserted into and fixed within the outer channel 115. Optionally, the C-shaped frame 132 and the outer channel 115 are interference-fitted to achieve fixation. Alternatively, the insulation blanket 131 covers and secures to the outer surface of the outer skin 114. The small holes 1153 in the vertical plate and 1154 in the top plate are both located on the same horizontal plane as the small holes 1321 in the C-shaped frame, and are both suitable for leading out the wire rope 134. A wire rope cap 135 is provided on the outer surface of the top plate 1152, suitable for fixing the end of the wire rope 134.

[0052] In this embodiment, nylon patches 1311 are arranged on the outer surface of the heat insulation blanket 131, and the nylon patches 1311 are distributed on both sides of the outer channel 115. Nylon patches are also arranged on the two opposite side edges of the outer heat insulation blanket 136. The nylon patches of the outer heat insulation blanket 136 are bonded and fixed to the nylon patches 1311 on the heat insulation blanket 131, so that the outer heat insulation blanket 136 covers the outside of the outer channel 115. Optionally, the outer heat insulation blanket 136 gradually bulges outward from the two side edges of the outer heat insulation blanket 136 with nylon patches towards the middle part of the outer heat insulation blanket 136, so that the shape of the outer heat insulation blanket 136 is arc-shaped, so as to cover the outside of the outer channel 115.

[0053] When installing external thermal insulation component 13, combine Figures 3 to 7As shown, first, connect the steel wire rope 134 to the clamping pad 133, place the clamping pad 133 on the inside of the C-shaped frame 132, and pass the steel wire rope 134 through the small hole 1321 of the C-shaped frame on the side of the C-shaped frame 132. Then, insert and fix the edge of the heat insulation blanket 131 into the connecting C-shaped frame 132. Next, pass the steel wire rope 134 through the small hole 1153 of the upright plate and the small hole 1154 of the top plate. Apply lead powder or other lubricating substances to the corresponding positions of the outer side of the C-shaped frame 132 and the outer channel 115. Then, press the C-shaped frame 132 into the outer channel 115 and tighten the steel wire rope 134 to secure the heat insulation blanket 131. Then, install the steel wire rope cap 135 at the end of the steel wire rope 134 and cut off the excess part of the steel wire rope 134. Finally, attach the outer heat insulation blanket 136 to the heat insulation blanket 131 to cover the outer channel 115.

[0054] This application uses the wall panel itself as the mounting and fastening base for the functional structural interlayer 12, the external heat insulation component 13, and the internal equipment 14. This avoids the need to process additional fixing structures on the wall panel 11. Furthermore, the cavity on the wall panel 11 for mounting and fastening the functional structural interlayer 12, as well as the groove for mounting and fastening the external heat insulation component 13 and the internal equipment 14, are formed synchronously with the load-bearing structure of the wall panel 11. This effectively simplifies the processing and manufacturing process of the spacecraft sealed cabin, thereby shortening the manufacturing cycle of the spacecraft sealed cabin and improving the economic efficiency of spacecraft launch.

[0055] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0056] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A double-layered aluminum extruded multifunctional spacecraft sealed cabin column segment body, characterized in that, The utility model relates to a wallboard of integrated extrusion forming of functional structure sandwich, external thermal insulation assembly, cabin equipment and includes: The wallboard includes: inner channel, inner skin, reinforcing rib, outer skin and outer channel, the functional structure sandwich includes: impact protection layer, heat insulation layer and electro-hydraulic pipeline; The reinforcing rib is located in the annular cavity between the inner skin and the outer skin, and the annular cavity is divided into a plurality of wallboard cavities, the impact protection layer is filled in the part of the radial outer side of the wallboard cavity, the electro-hydraulic pipeline is arranged in the part of the radial inner side of the wallboard cavity, and the heat insulation layer is filled in the part of the radial inner side of the wallboard cavity; And the electro-hydraulic pipeline is arranged in the part of the radial inner side of the wallboard cavity first, and the heat insulation layer is filled in the part of the radial inner side of the wallboard cavity after, so as to fix the electro-hydraulic pipeline after the heat insulation layer solidifies; The inner channel is located on the inner side of the inner skin, and the cabin equipment is installed to the inner channel through the opening of the inner channel; The outer channel is located on the outer side of the outer skin, and the opening of the outer channel faces the circumference of the outer skin, and the external thermal insulation assembly is inserted into the outer channel from the opening of the outer channel and fixed in the outer channel; The positioning structure for the functional structure sandwich, the external thermal insulation assembly and the cabin equipment on the wallboard is synchronously formed with the bearing structure for bearing on the wallboard. The wallboard cavity is a triangular cavity and / or a rectangular cavity.

2. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to claim 1, characterized in that, The impact protection layer is filled in the part of the radial outer side of the triangular cavity, or the impact protection layer is filled in the part of the radial outer side of the rectangular cavity; 3. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to claim 2, characterized in that, The electro-hydraulic pipeline is arranged in the part of the radial inner side of the triangular cavity, or the electro-hydraulic pipeline is arranged in the part of the radial inner side of the rectangular cavity, and the heat insulation layer is filled in the part of the radial inner side of the triangular cavity, or the heat insulation layer is filled in the part of the radial inner side of the rectangular cavity. The heat insulation layer is soft heat insulation foam.

4. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to any one of claims 1 to 3, characterized in that, The outer channel includes: vertical plate, top plate, vertical plate small hole and top plate small hole; The inner edge of the vertical plate is connected to the outer skin, and the vertical plate small hole penetrates the vertical plate; The outer edge of the vertical plate is connected to the inner side of the top plate, and the top plate small hole penetrates the top plate; 5. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to any one of claims 1 to 3, characterized in that, The external thermal insulation assembly includes: heat insulation blanket, C-shaped frame, compression gasket, steel wire rope, steel wire rope cap and outer covering heat insulation blanket; The end of the heat insulation blanket is inserted into and fixed in the C-shaped frame, the steel wire rope passes through the C-shaped frame small hole located on the side surface of the C-shaped frame, and the initial end is connected with the compression gasket in the gap between the side surface of the C-shaped frame and the end surface of the heat insulation blanket; The C-shaped frame is inserted into and fixed in the outer channel, the steel wire rope passes through the vertical plate small hole and the top plate small hole, the steel wire rope cap is located on the outer side of the top plate and is installed to the end of the steel wire rope, and the outer covering heat insulation blanket is bonded on the heat insulation blanket and covers the outer channel. The end of the heat insulation blanket is fixed in the C-shaped frame in the form of cementation or riveting, and the inner and outer surfaces of the C-shaped frame are compression surfaces, which tightly compress the corresponding area of the heat insulation blanket.

6. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to claim 5, characterized in that, The C-shaped frame and the outer channel are in interference fit to realize the fixation of the C-shaped frame and the outer channel.

7. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to claim 5, characterized in that, The outer side of the heat insulation blanket is provided with nylon paste, the nylon paste of the heat insulation blanket is distributed on both sides of the outer channel, the opposite two side edges of the outer covering heat insulation blanket are provided with nylon paste, and the nylon paste of the outer covering heat insulation blanket is bonded and fixed with the nylon paste of the heat insulation blanket to cover the outer channel.

8. The double-layered aluminum extruded multi-functional spacecraft sealed cabin column segment body according to claim 5, characterized in that, ​ 9. A double-walled aluminum extruded multifunctional spacecraft sealed compartment column segment, characterized in that, The column segment body is fixedly connected with the upper end frame at the upper end and fixedly connected with the lower end frame at the lower end.

10. A double-walled aluminum extruded multi-functional spacecraft sealed cabin, characterized in that, The column segment body is fixedly connected with the upper end frame at the upper end and fixedly connected with the lower end frame at the lower end. The column segment body is fixedly connected with the upper end frame at the upper end and fixedly connected with the lower end frame at the lower end.

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