A lunar base sandwich shell structure, lunar base and construction method thereof

Abstract

The present invention discloses a lunar base sandwich shell structure, a lunar base, and a construction method thereof. The shell structure comprises an inner thin-walled corrugated disk, an outer thin-walled corrugated disk positioned outside the inner thin-walled corrugated disk, and a thermal insulation layer positioned between the inner and outer thin-walled corrugated disks. Before being transported to the lunar surface, the inner and outer thin-walled corrugated disks shrink into a disc-like state, and an annular isolation membrane divides the inner and outer thin-walled corrugated disks into a plurality of annular cavities for accommodating reaction raw materials. The reaction raw materials include a first reaction raw material and a second reaction raw material alternately arranged in the annular cavities. During construction, the shell structure is expanded axially along the corrugated disk into a conical shell state, the annular isolation membrane ruptures, and the first and second reaction raw materials mix. After being irradiated by a thermal radiation light source, the materials react and solidify to form a thermal insulation layer. The reaction raw materials in the thermal insulation layer are directly encapsulated within the shell structure, facilitating transportation.

Description

Technical Field

[0001] The present invention relates to a lunar base shell structure, and in particular to a lunar base sandwich shell structure, a lunar base and a construction method thereof. Background Art

[0002] As human exploration of the moon continues to deepen, lunar exploration and base construction have become hot topics. However, existing lunar base structures often suffer from bulk, transportation difficulties, and difficulty adapting to the lunar environment. The lunar surface environment is extremely harsh, with drastic temperature fluctuations, placing extremely high demands on the heat resistance of lunar base structural materials. To protect the base structure from temperature fluctuations, it is necessary to equip it with an insulation layer. The materials within the insulation layer ensure that the base remains stable in extreme temperatures.

[0003] The structure of the lunar base usually needs to withstand long-term ultraviolet radiation and huge temperature changes on the lunar surface. Directly transporting the paint to the moon may cause the existing high-temperature resistant paint to have insufficient adhesion at high temperatures and easy coating peeling, which greatly reduces the thermal insulation effect of the base and thus loses its protection against extreme environments.

[0004] In the prior art, Chinese patent application number 202410801058.X discloses a portable lunar base shell structure. The thermal insulation layer uses ZS-1 high-temperature resistant thermal insulation coating, which is sprayed or painted by a space robot arm or astronauts after the corrugated disk is unfolded. The coating is an inorganic single component and has good adhesion, high heat resistance, and a thermal insulation suppression efficiency of about 90%. However, this liquid high-temperature resistant coating is heavy and inconvenient to transport. The coating easily falls off during the formation of the thermal insulation layer, which greatly reduces the thermal insulation effect. Summary of the Invention

[0005] Purpose of the invention: In view of the above shortcomings, the present invention provides a lunar base sandwich shell structure, a lunar base and a construction method thereof, which has a high-temperature resistant coating that is easy to transport and not easy to peel off.

[0006] Technical solution: To solve the above problems, the present invention adopts a sandwich shell structure of a lunar base, comprising an inner thin-walled corrugated disk located on the inner side, an outer thin-walled corrugated disk located outside the inner thin-walled corrugated disk, and an insulation layer located between the inner thin-walled corrugated disk and the outer thin-walled corrugated disk. Before being transported to the lunar surface, the inner thin-walled corrugated disk and the outer thin-walled corrugated disk are shrunk into a disc state, and the inner thin-walled corrugated disk and the outer thin-walled corrugated disk are divided into a number of annular cavities for accommodating reaction raw materials by an annular isolation membrane. The reaction raw materials include a first reaction raw material and a second reaction raw material, and the first reaction raw material and the second reaction raw material are alternately arranged in the annular cavities; during construction, the structure is expanded into a conical shell state along the axial direction of the corrugated disk, the annular isolation membrane is broken, the first reaction raw material and the second reaction raw material are mixed, and the reaction and solidification are carried out after irradiation by a thermal radiation light source to form an insulation layer.

[0007] Furthermore, the material thickness of the inner thin-walled corrugated disk and the outer thin-walled corrugated disk is in the range of 1-2mm, the diameter of the outer thin-walled corrugated disk that is unfolded into a conical shell is in the range of 6-8m at the large end, and the diameter of the small end is in the range of 4-5m; the thickness of the thermal insulation layer is in the range of 15-20cm. The inner thin-walled corrugated disk and the outer thin-walled corrugated disk are made of titanium alloy. Titanium alloy materials have the characteristics of high specific strength, corrosion resistance, low elastic modulus, superelasticity and shape memory. High-strength and high-elasticity thin-walled materials are used, which can be compressed and unfolded. Before transportation, the thin-walled annular cone shell is compressed longitudinally into a flat corrugated disk using the high elasticity of the material to save space on the carrier and facilitate transportation. After arriving at the lunar base, the corrugated disk is unfolded and deformed into a truncated cone as the base structure.

[0008] Furthermore, the reaction raw materials include resin, talcum powder, curing agent and filler, the first reaction raw material is a mixed powder of resin and talcum powder, and the second reaction raw material is a mixed powder of curing agent and filler.

[0009] Furthermore, the resin is epoxy resin, the curing agent is fatty amine, and the filler is mica powder; the first reaction raw material is a mixed powder of epoxy resin powder and talcum powder, and the second reaction raw material is a mixed powder of fatty amine powder and mica powder. Before transportation, the upper and lower sides of the annular isolation membranes arranged in an array in the interlayer are bonded to the inner thin-walled corrugated disk and the outer thin-walled corrugated disk, dividing the interlayer into several interlayer spaces. Various raw material powders of high-temperature resistant materials are mixed and packaged in different interlayer spaces for storage. After the base structure is unfolded, the raw materials of each interlayer are mixed, and under the stimulation of a high-temperature thermal radiation light source, the mixture solidifies, eventually forming a high-temperature resistant material, which serves as a heat insulation layer to protect the lunar base.

[0010] Furthermore, the composition ratio of the first reaction raw material and the second reaction raw material in two adjacent annular cavities is: 55%-60% by weight of epoxy resin powder, 20%-25% by weight of talc powder, 1%-5% by weight of fatty amine powder, and 10%-15% by weight of mica powder.

[0011] Furthermore, the annular isolation membrane is made of aluminum thin film with a thickness of less than 0.1 mm and is in the shape of a fine fishnet. As the corrugated disc expands, the fine fishnet structure of the film breaks, and the various isolated materials mix with each other due to gravity after the film breaks.

[0012] The present invention also adopts a lunar base that uses the above-mentioned lunar base sandwich shell structure, including two lunar base sandwich shell structures, the two lunar base sandwich shell structures are vertically arranged up and down, the conical large ends of the two lunar base sandwich shell structures are fixedly connected, the conical small end of the lunar base sandwich shell structure located at the lower end is fixed to the ground, and the conical small end of the lunar base sandwich shell structure located at the upper end is the base entrance.

[0013] The present invention also adopts a method for constructing the above-mentioned lunar base, comprising the following steps:

[0014] (1) Before transportation, the conical large ends of the two disk-shaped lunar base sandwich shell structures are fixedly connected, and the reaction materials forming the thermal insulation layer are compressed and stored in the annular cavity between the inner thin-walled corrugated disk and the outer thin-walled corrugated disk, which is divided by the annular isolation membrane;

[0015] (2) After arriving at the destination, the inner thin-walled corrugated disk and the outer thin-walled corrugated disk are unfolded into a conical shell state. The annular isolation membrane is gradually torn as the corrugated disk unfolds. The reaction raw materials are mixed and solidified after being irradiated by the thermal radiation light source to form an insulation layer, thus obtaining a lunar base.

[0016] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages:

[0017] (1) The raw materials for the heat-insulating layer reaction are directly encapsulated in the shell structure for easy transportation. The heat-insulating layer is suitable for the harsh lunar environment and provides a safe and reliable environment inside the base. The on-site preparation of high-temperature resistant materials avoids damage during transportation, adapts to the extreme environment of the lunar surface, ensures the immediacy and effectiveness of the materials, improves the adhesion and durability of the materials, and ensures the uniformity and consistency of the materials, thereby enhancing the protective capability of the base. The high-temperature resistant materials are directly prepared by mixing the raw materials of each part under the condition of light irradiation. The high-temperature resistant materials have excellent adhesion and durability. By optimizing the component ratio and curing process, the coating of the present invention can form a coating with excellent adhesion after curing at high temperature. This coating can adhere tightly to the base material and is not easy to peel off even under extreme temperature changes and mechanical stress, thereby ensuring long-term durability and protective effect.

[0018] (2) Excellent curing performance. The high-temperature resistant coating of the present invention can cure rapidly when heated under light, forming a stable coating. This greatly improves the coating's construction efficiency and applicability in extreme temperatures. In high-temperature environments such as lunar bases, this coating can cure quickly, providing immediate protection for base structures and avoiding the need for long curing cycles.

[0019] (3) The annular array of isolation membranes between the raw materials plays a key role. It is made of soft aluminum and designed as a fine mesh structure. It is not only lightweight but also has a certain degree of flexibility, allowing it to adapt to the expansion of the structure during the deployment of the lunar base. Due to the relatively low strength of soft aluminum, when the corrugated disk is deployed, the isolation membrane is pulled apart at the predetermined position. This design cleverly utilizes the physical properties of the material to achieve the precise controlled release of the raw materials.

[0020] (4) Environmental adaptability and a wide range of applications. The high-temperature resistant coating of the present invention is not only suitable for extreme environments such as lunar bases, but can also be applied to high-temperature industrial equipment and aerospace surfaces on Earth. Its high-temperature curing, excellent adhesion, and durability enable it to play an excellent protective role in a variety of environments, and it has broad application prospects and market value. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a cross-sectional view of the structure of the interlayer formed between the inner thin-wall corrugated disk and the outer thin-wall corrugated disk in the present invention.

[0022] Figure 2 This is a cross-sectional exploded view of the structure of the annular array isolation membrane and the corrugated disk in the present invention.

[0023] Figure 3 Schematic diagram of the reaction raw materials stored in the interlayer in the present invention.

[0024] Figure 4 The figure is a flow chart of mixing high temperature resistant raw materials before being transported in the present invention.

[0025] Figure 5 This is a cross-sectional view of the structure of the diaphragm rupture when the lunar base is deployed in the present invention.

[0026] Figure 6 Schematic diagram of the heat insulation layer of the present invention being cured after being irradiated with a lamp.

[0027] Figure 7 This is a schematic diagram of the deployment process of the lunar base structure in the present invention. DETAILED DESCRIPTION

[0028] Example 1

[0029] In this embodiment, a sandwich shell structure of a lunar base includes an inner thin-walled corrugated disk, an outer thin-walled corrugated disk located outside the inner thin-walled corrugated disk, and a thermal insulation layer located between the inner and outer thin-walled corrugated disks. The thin-walled corrugated disk is made of a high-strength, high-elasticity thin-walled titanium alloy material with a wall thickness of 1-2 mm. The corrugated disk can be contracted and expanded. The diameter of the large end of the corrugated disk can reach 6-8 meters, and the diameter of the small end can reach 4-5 meters. After expansion, the shell-like thin-walled structure is formed. Figure 1 As shown, the inner thin-walled corrugated disk and the outer thin-walled corrugated disk together form a closed internal space. After being transported to the lunar surface and unfolded, the two corrugated disks overlap and are fixed at their large ends to form a lunar base.

[0030] like Figure 2 As shown, the interlayer is located between the inner and outer corrugated disks. Before being transported to the lunar surface, in order to fix the reaction materials of the thermal insulation layer, the annular array isolation membranes that separate the various reaction materials are glued to the thin walls of the corrugated disks on both sides. Figure 3 As shown, the interlayer is divided into many parts by the annular array isolation membrane, and each part is filled with a mixed powder composed of two high-temperature resistant raw materials, including a mixed powder 1 composed of epoxy resin powder and talcum powder and a mixed powder 2 composed of fatty amine powder and mica powder. Figure 4 As shown, the high-temperature resistant solid coating in this embodiment is composed of four raw materials: epoxy resin powder, talcum powder, fatty amine powder, and mica powder. The mass ratio of these four raw materials is 100:40:5:32. The high-temperature resistant material prepared from these four raw materials has excellent high-temperature resistance and good chemical stability after curing. The epoxy resin serves as a matrix, providing good bonding properties and thermal stability; the fatty amine ensures that the resin forms a strong coating during the curing process; and the mica powder, as a filler, not only increases the mechanical strength of the coating but also improves its thermal insulation properties.

[0031] like Figure 2 、 3As shown, the raw materials are separated by a fine mesh isolation membrane made of soft aluminum. When the base is compressed, the aluminum membrane is erected inside the insulation layer, and the annular array isolation membrane adopts a fishing net structure. Figure 5 As shown, during the base stretching process, the aluminum film is pulled apart along with the corrugated disk. Ideally, it would be in the shape of a ring. However, due to the low strength of aluminum, the film would be torn apart by the tensile force and the squeezing force between the raw material powders during the stretching process, forming a cracked film. Subsequently, in the absence of any separator, the raw materials are mixed with each other under the action of gravity to form a mixed powder. Multiple annular cavities are set up to increase the mixing between the powders. The two reaction powder raw materials are placed alternately in different spaces to achieve maximum mixing of the two raw materials. Figure 6 As shown, under the irradiation of a strong thermal radiation light source, the mixed raw materials quickly solidify to form a layer of uniform, strong, high-temperature resistant material, thus forming the thermal insulation layer of the lunar base.

[0032] This process can be carried out automatically in the lunar environment without the need for complex mechanical devices or human intervention. Under the intense lighting on the lunar surface, the mixed raw materials rapidly undergo a chemical reaction and solidify. The radiant energy from the lighting provides the necessary heat for the curing process, allowing the mixture to form a uniform, strong, and high-temperature-resistant layer in a short period of time. This coating not only possesses excellent thermal stability, capable of withstanding the extreme temperature fluctuations caused by the lunar surface's day-night temperature difference, but its uniform coating structure also ensures reliable thermal insulation performance, providing a solid thermal barrier for the lunar base and effectively protecting the base's interior from the harsh external environment.

[0033] Example 2

[0034] like Figure 7 As shown, in this embodiment, a lunar base adopts the lunar base sandwich shell structure described in Example 1, including two lunar base sandwich shell structures. The two lunar base sandwich shell structures are vertically arranged up and down to form a vertical space base. The conical large ends of the two lunar base sandwich shell structures are fixedly connected, and the conical small end of the lunar base sandwich shell structure at the lower end is fixed to the ground. The conical small end of the lunar base sandwich shell structure at the upper end is used as the base entrance to set a base hatch for staff to enter and exit the base.

[0035] The thin-walled corrugated disk structure is a disk-shaped structure in a contracted state before being transported to the lunar surface. The structure is composed of two alloy thin-walled corrugated disks that are formed and then welded.

Claims

1. A sandwich shell structure for a lunar base, characterized in that: It includes an inner thin-walled corrugated disk located on the inner side, an outer thin-walled corrugated disk located on the outer side of the inner thin-walled corrugated disk, and an insulation layer located between the inner thin-walled corrugated disk and the outer thin-walled corrugated disk. The reaction raw materials of the insulation layer are directly encapsulated in the shell structure. Before being transported to the lunar surface, the inner thin-walled corrugated disk and the outer thin-walled corrugated disk are shrunk into a disc state, and the inner thin-walled corrugated disk and the outer thin-walled corrugated disk are divided into several annular cavities for accommodating reaction raw materials by an annular isolation membrane. The reaction raw materials include a first reaction raw material and a second reaction raw material, and the first reaction raw material and the second reaction raw material are alternately arranged in the annular cavity; the annular isolation membrane is in the shape of a fine fishing net, and the annular isolation membrane adapts to the extension of the shell structure during the deployment of the lunar base. During construction, it is expanded into a conical shell state along the axial direction of the corrugated disk. The annular isolation membrane ruptures, the first reaction raw material and the second reaction raw material are mixed, and react and solidify after being irradiated by a thermal radiation light source to form an insulation layer.

2. The lunar base sandwich shell structure according to claim 1, characterized in that: The material thickness of the inner thin-wall corrugated disk and the outer thin-wall corrugated disk ranges from 1 to 2 mm. The diameter of the outer thin-wall corrugated disk expanded into a conical shell ranges from 6 to 8 m at the large end and 4 to 5 m at the small end. The thickness of the thermal insulation layer ranges from 15 to 20 cm.

3. The lunar base sandwich shell structure according to claim 1 or 2, characterized in that: The inner thin-wall corrugated disk and the outer thin-wall corrugated disk are made of titanium alloy material.

4. The lunar base sandwich shell structure according to claim 1, characterized in that: The reaction raw materials include resin, talcum powder, curing agent and filler. The first reaction raw material is a mixed powder of resin and talcum powder, and the second reaction raw material is a mixed powder of curing agent and filler.

5. The sandwich shell structure of the lunar base according to claim 4, characterized in that: The resin is epoxy resin, the curing agent is fatty amine, and the filler is mica powder; the first reaction raw material is a mixed powder of epoxy resin powder and talcum powder, and the second reaction raw material is a mixed powder of fatty amine powder and mica powder.

6. The sandwich shell structure of the lunar base according to claim 5, characterized in that: The composition ratio of the first reaction raw material and the second reaction raw material in two adjacent annular cavities is: 55%-60% by weight of epoxy resin powder, 20%-25% by weight of talc powder, 1%-5% by weight of fatty amine powder, and 10%-15% by weight of mica powder.

7. The lunar base sandwich shell structure according to claim 1, characterized in that: The annular isolation membrane is made of aluminum metal film with a thickness of less than 0.1 mm.

8. A lunar base using the lunar base sandwich shell structure according to claim 1, characterized in that: It includes two lunar base sandwich shell structures, which are vertically arranged up and down. The conical large ends of the two lunar base sandwich shell structures are fixedly connected, the conical small end of the lunar base sandwich shell structure at the lower end is fixed to the ground, and the conical small end of the lunar base sandwich shell structure at the upper end is the base entrance.

9. A method for constructing a lunar base according to claim 8, characterized in that: The following steps are involved: (1) Before transportation, the conical large ends of the two disk-shaped lunar base sandwich shell structures are fixedly connected, and the reaction materials forming the thermal insulation layer are compressed and stored in the annular cavity between the inner thin-walled corrugated disk and the outer thin-walled corrugated disk, which is divided by the annular isolation membrane; (2) After arriving at the destination, the inner thin-walled corrugated disk and the outer thin-walled corrugated disk are unfolded into a conical shell state. The annular isolation membrane is gradually torn as the corrugated disk unfolds. The reaction raw materials are mixed and solidified after being irradiated by the thermal radiation light source to form an insulation layer, thus obtaining a lunar base.

10. The construction method according to claim 9, characterized in that: The annular isolation membrane is made of aluminum metal film with a thickness of less than 0.1 mm.

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