A lunar base hull structure, a space capsule and a construction method thereof

Abstract

The present invention discloses a lunar base shell structure, a space capsule, and a construction method thereof. The structure relates to a lunar base, comprising a thin-walled corrugated disk and an expansion drive device. The thin-walled corrugated disk is made of a lightweight, high-strength alloy and collapses into a circular disk during transportation. During construction, it is expanded into a conical shell by the expansion drive device. The expansion drive device includes a plurality of electromagnets and a control circuit. Each corrugation of the thin-walled corrugated disk is provided with at least one pair of electromagnets. When the thin-walled corrugated disk collapses, the pair of electromagnets for the same corrugation are disposed face-to-face on the inner side of the corrugation. When energized, the two electromagnets have the same polarity, generating a repulsive force between them. The control circuit controls whether the electromagnets are energized. Controllable, staged expansion is achieved through the electromagnetic device, providing a safe and reliable deployment method. The expansion process of the space capsule can be precisely controlled by adjusting the current. This deployment method, utilizing electromagnetic technology, can rapidly expand the space capsule shell and is suitable for lunar base construction situations requiring rapid response.

Description

Technical Field

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

[0002] With the continuous advancement of lunar exploration technology, current lunar exploration plans all view the establishment of lunar bases as a key goal. These bases will not only support future unmanned exploration missions but also provide the infrastructure for manned lunar exploration. Due to the limited payload space on rockets, especially when large quantities of supplies need to be transported to the moon, a deployable space capsule has become an effective solution. This design allows the capsule to remain compact during launch, maximizing the space available on the launch vehicle. Once on the lunar surface, these structures can be deployed to provide ample living and working space for astronauts. This effectively addresses transportation constraints while ensuring the necessary functionality and comfort of the base.

[0003] Common deployable structures for space capsules include folding, sleeve-type, and inflatable types. Folding deployment structures usually require complex hinges or other connecting devices, increasing manufacturing costs and potential failure points. Additional mechanical components will increase the overall weight. Once a failure occurs in orbit, its moving parts are very difficult to repair. The sleeve-type deployment structure is not sufficient to provide sufficient rigidity when the extension length is long. The sleeve structure has a limited extension ratio and may not be suitable for situations that require a very large extension ratio. Inflatable deployment structures are usually made of flexible materials with poor durability and poor thermal insulation performance. Inflatable space capsules rely on internal air pressure to maintain structural stability. Once a leak occurs, the capsule will quickly lose its function. The deployment of inflatable space capsules requires an additional air pump for control, which increases the complexity and overall weight of the system. Summary of the Invention

[0004] Purpose of the invention: In view of the above shortcomings, the present invention provides a lunar base shell structure, a space capsule and a construction method thereof that can be deployed quickly, safely and reliably.

[0005] Technical solution: To solve the above problems, the present invention adopts a lunar base shell structure, including a thin-walled corrugated disk and an expansion drive device. The thin-walled corrugated disk is made of lightweight and high-strength alloy, and shrinks into a disc state during transportation. During construction, it is expanded into a conical shell state through the expansion drive device; the expansion drive device includes a number of electromagnets and a control circuit. Each corrugation of the thin-walled corrugated disk is provided with at least one pair of electromagnets. When the thin-walled corrugated disk shrinks, a pair of electromagnets of the same corrugation are arranged face to face on the inner side of the corrugation, and the two electromagnets have the same polarity after being energized, generating a repulsive force between the two. The control circuit is used to control whether the electromagnet is energized.

[0006] Furthermore, six pairs of electromagnets are evenly spaced around each corrugation of the thin-walled corrugated disk. Each electromagnet comprises an electromagnetic coil, an iron core, and an electromagnet housing. Both the iron core and the electromagnet housing are arc-shaped to accommodate the corrugated disk. The electromagnets on the same side of each corrugation of the thin-walled corrugated disk are connected in series, while the electromagnets on different sides and between different corrugations are connected in parallel. The electromagnet housing is secured to the inside of the thin-walled corrugated disk by gluing or laser welding.

[0007] Furthermore, the control circuit is connected to a control box located on the thin-walled corrugated disk. The control box includes a power supply. The control box controls whether the electromagnet is energized and adjusts the current of the electromagnet through the control circuit.

[0008] The present invention also adopts a space capsule that uses the above-mentioned lunar base shell structure, including a shell structure, an upper end cover and a lower end cover of the shell structure. The shell structure is arranged vertically up and down, the conical large end of the shell structure at the lower end is fixed to the ground, and the upper end cover of the conical small end of the shell structure at the upper end is provided with a hatch.

[0009] The present invention also adopts a method for constructing the above-mentioned space capsule, comprising the following steps:

[0010] (1) Before transportation, the large end of the thin-walled corrugated disk in a disc state is sealed by the lower end cover, and the small end of the thin-walled corrugated disk in a disc state is sealed by the upper end cover, and the upper end cover is provided with a hatch; the corrugations of the thin-walled corrugated disk are first-level corrugations, second-level corrugations, ..., N-level corrugations from the outside to the inside, where N is the number of corrugations of the thin-walled corrugated disk;

[0011] (2) After arriving at the destination, the control circuit energizes the electromagnets facing each other on the first-stage corrugation, and the electromagnets generate a repulsive force to expand the first-stage corrugation; after expansion, the control circuit energizes the electromagnets facing each other on the second-stage corrugation, and the electromagnets generate a repulsive force to expand the second-stage corrugation. The electromagnets on the outer to inner corrugations of the thin-walled corrugation disk are energized in sequence to expand until the space capsule is fully expanded.

[0012] Furthermore, electromagnets arranged face to face on the corrugations generate repulsive forces to drive plastic deformation at the bends of the corrugations.

[0013] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages:

[0014] (1) Controllable, staged deployment is achieved through electromagnetic devices, making the deployment method safe and reliable. The deployment process of the space capsule can be precisely controlled by adjusting the current. The deployment method using electromagnetic technology can quickly deploy the space capsule shell, which is faster than mechanical or inflation deployment methods and is suitable for the construction of lunar bases that require rapid response.

[0015] (2) Compared with traditional motors or other forms of power sources, efficient electromagnetic systems can reduce energy consumption when performing missions, which is particularly important for long-term lunar missions. Electromagnetic drives generally do not require complex mechanical components such as gears and bearings, which simplifies the overall design, reduces failure points, and improves system reliability and maintainability. In addition, electromagnetic systems do not rely on liquid media (such as lubricants) to operate, so they can maintain good performance even in extreme temperature changes, vacuum environments, or the presence of small particles.

[0016] (3) The electromagnetic control system of the hierarchical deployment structure can receive electronic signals through the control box for remote operation, which makes it easier for the ground control center to monitor and adjust the parameter settings during the deployment process in real time. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 Schematic diagram of the structure of the unfolded space capsule in the present invention.

[0018] Figure 2 It is a front view of the unfolded space capsule of the present invention and a partial enlarged view of the corrugated disk wall where the electromagnet is installed.

[0019] Figure 3 Schematic diagram of the structure of the retracted space capsule in the present invention.

[0020] Figure 4 It is a cross-sectional view of the retracted space capsule of the present invention and a partial enlarged view of the corrugated disk wall where the electromagnet is installed.

[0021] Figure 5 Schematic diagram of the control circuit in the present invention.

[0022] Figure 6 Schematic diagram of the arrangement of a corrugated single-sided electromagnet in the present invention.

[0023] Figure 7 Schematic diagram of the installation of the electromagnet in the present invention.

[0024] Figure 8 It is a structural schematic diagram of the electromagnet in the present invention.

[0025] Figure 9 Schematic diagram of the deployment principle of the deployment drive device in the present invention.

[0026] Figure 10 It is a schematic diagram of the staged deployment principle of the space capsule in the present invention.

[0027] 1-space capsule shell; 2-repulsion electromagnet; 3-control box; 4-control circuit; 5-coil; 6-iron core; 7-repulsion electromagnet shell; 8-upper end cover; 9-lower end cover. DETAILED DESCRIPTION

[0028] like Figure 1 As shown, a lunar base shell structure in this embodiment includes a thin-walled corrugated disk and an expansion drive device. The thin-walled corrugated disk is connected to the expansion drive device, which can drive the thin-walled corrugated disk to expand in stages. The thin-walled corrugated disk serves as the outer shell 1 of the space capsule. The space capsule includes a thin-walled corrugated disk-shaped outer shell, an upper end cover 8, a lower end cover 9, and a control box 3. The thin-walled corrugated disk collapses into a circular disk during transportation and expands into a conical shell during construction via the expansion drive device. The expansion drive device includes several electromagnets and a control circuit. At least one pair of electromagnets is positioned inside each corrugation of the thin-walled corrugated disk. When the thin-walled corrugated disk collapses, the pair of electromagnets for the same corrugation face each other inside the corrugation. Each corrugation comprises a complete crest. When energized, the two electromagnets have the same polarity, generating a repulsive force between them.

[0029] Before launching a lunar base space capsule, the thin-walled corrugated disk-shaped capsule shell 1 can be collapsed into a disk shape. Once the spacecraft reaches a designated lunar surface area and the capsule needs to be deployed, the control box 3 is connected to the internal battery or the capsule's external power source. The astronaut sends a signal through the control box 3, which energizes a pair of repulsive electromagnets located facing each other on the inner side of the first-stage corrugations (i.e., near the outermost end of the capsule) on the capsule's inner wall via the control circuit 4. The opposing polarities of the two electromagnets generate an electromagnetic repulsive force, which in turn drives the capsule shell to deploy along its axis. Next, the second-stage electromagnets are energized, generating a repulsive force that deploys the capsule shell. This deployment process repeats for each stage until the capsule is fully deployed to its desired size.

[0030] like Figures 1 to 4 The capsule's outer shell 1 is made of a thin titanium alloy with retractable and deployable properties. Prior to being transported to the lunar surface, the capsule's outer shell 1 and its internal deployment drive mechanism are a retracted disc-shaped structure. Its interior is sealed airtight by upper and lower end covers 9. The upper cover can be designed with various hatches depending on the lunar base's space capsule mission requirements. The deployment drive mechanism consists of a repulsive electromagnet 2 and a control circuit 4.

[0031] like Figure 5 As shown, the control circuit 4 connects each repulsive electromagnet 2 within the space capsule. Repulsive electromagnets 2 on the same side of the same level of ripple are connected in series, while repulsive electromagnets 2 on different sides of different levels are connected in parallel. The control circuit 4 is connected to a control box 3 located at the bottom of the space capsule. Astronauts can use this control box 3 to issue commands and achieve precise control of the space capsule's staged deployment. In this embodiment, the control box 3 precisely controls the magnetic field strength during the staged deployment process by adjusting the current flowing through the repulsive electromagnets 2, thereby achieving fine adjustment of the deployment degree.

[0032] like Figure 6As shown, the repulsive electromagnets 2 are arranged circumferentially on the same side of the same level of corrugation in the capsule shell 1. Six repulsive electromagnets are located on the same side of the same level of corrugation. Repulsive electromagnets 2 of different levels are arranged closely against the capsule's inner wall according to the corrugated structure. Depending on the capsule's shell size, the parameters of the repulsive electromagnets 2 can be designed differently: the number of turns of the electromagnetic coil 5, the wire diameter, and the coil length. The current applied is also controlled to ensure a complete, graded deployment of the capsule.

[0033] like Figure 7 As shown, when the repulsive electromagnet 2 is fixed to the inner wall of the space capsule, the installation method can be selected to fix the electromagnet shell to the inner wall of the shell by bonding or laser welding. The electromagnet after such installation will not interfere with the expansion function of the shell structure, while also ensuring the normal operation of the electromagnet.

[0034] like Figure 8 As shown, the repulsive electromagnet 2 comprises a coil 5, an iron core 6, and a repulsive electromagnet housing 7. To reduce the weight of the entire staged deployment mechanism, the iron core of the electromagnet can be made of lightweight materials. Power is supplied to the repulsive electromagnet 2 via the control circuit 4, which polarizes the upper and lower end surfaces of the electromagnet.

[0035] like Figure 9 As shown, after the repulsive electromagnet 2 is energized, the electromagnets of the adjacent two stages generate repulsive force to drive the corrugated bends of the space capsule shell 1 to undergo plastic deformation, and the folded compact disc structure is expanded into a stepped structure. Figure 10 As shown, the positions of the repulsive electromagnets 2 between adjacent stages of the space capsule change before and after staged deployment, transforming the capsule's shape from a compact disk to a stepped cone. The overall capsule deployment process is safe and reliable, with fast response and low energy consumption, offering great potential for lunar base construction.

[0036] After the lunar base space module described in the present invention is deployed in stages, the staged deployment mechanism, control circuit 4 and control box 3 that have completed their functions are retained in the space module. During the deployment process, the module body is in a sealed state and will not affect the subsequent use of the space module.

Claims

1. A lunar base shell structure, characterized in that: The device comprises a thin-walled corrugated disk and an expansion drive device. The thin-walled corrugated disk is made of a lightweight, high-strength alloy and contracts into a disc during transportation. During construction, it is expanded into a conical shell by the expansion drive device. The expansion drive device comprises a plurality of electromagnets and a control circuit. Each corrugation of the thin-walled corrugated disk is provided with at least one pair of electromagnets. When the thin-walled corrugated disk contracts, a pair of electromagnets of the same corrugation are arranged face to face on the inner side of the corrugation. When the two electromagnets are energized, their polarities are the same, generating a repulsive force between them. The control circuit is used to control whether the electromagnets are energized.

2. The lunar base shell structure according to claim 1, characterized in that: Six pairs of electromagnets are evenly arranged around each corrugation of the thin-wall corrugated disk.

3. The lunar base shell structure according to claim 1 or 2, characterized in that: The electromagnet comprises an electromagnetic coil, an iron core and an electromagnet shell, and both the iron core and the electromagnet shell are arc-shaped to adapt to the corrugated disk.

4. The lunar base shell structure according to claim 2, characterized in that: The electromagnets on the same side of each corrugation of the thin-wall corrugated disk are connected in series, and the electromagnets on different sides of the corrugation and between different corrugations are connected in parallel.

5. The lunar base shell structure according to claim 4, characterized in that: The electromagnet is fixed to the inner side of the thin-wall corrugated disk by gluing or laser welding.

6. The lunar base shell structure according to claim 5, characterized in that: The control circuit is connected to a control box located on the thin-wall corrugated disk. The control box includes a power supply. The control box controls whether the electromagnet is energized and adjusts the current of the electromagnet through the control circuit.

7. The lunar base shell structure according to claim 1, characterized in that: The thin-wall corrugated disk is made of titanium alloy.

8. A space module using the lunar base shell structure according to claim 1, characterized in that: It includes a shell structure, an upper end cover and a lower end cover of the shell structure. The shell structure is vertically arranged up and down. The conical large end of the shell structure at the lower end is fixed to the ground, and the upper end cover of the conical small end of the shell structure at the upper end is provided with a hatch.

9. A method for constructing the space capsule according to claim 8, characterized in that: The following steps are involved: (1) Before transportation, the large end of the thin-walled corrugated disk in a disc state is sealed by the lower end cover, and the small end of the thin-walled corrugated disk in a disc state is sealed by the upper end cover, and the upper end cover is provided with a hatch; the corrugations of the thin-walled corrugated disk are first-level corrugations, second-level corrugations, ..., N-level corrugations from the outside to the inside, where N is the number of corrugations of the thin-walled corrugated disk; (2) After arriving at the destination, the control circuit energizes the electromagnets facing each other on the first-stage corrugation, and the electromagnets generate a repulsive force to expand the first-stage corrugation; after expansion, the control circuit energizes the electromagnets facing each other on the second-stage corrugation, and the electromagnets generate a repulsive force to expand the second-stage corrugation. The electromagnets on the outer to inner corrugations of the thin-walled corrugation disk are energized in sequence to expand until the space capsule is fully expanded.

10. The method for constructing a space capsule according to claim 9, characterized in that: Electromagnets arranged face to face on the corrugations generate repulsive forces that drive the corrugations to undergo plastic deformation at their bends.

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