Rocket take-off and landing platform based on in-situ resources and suitable for lunar surface complex terrain

Abstract

The invention relates to the field of spaceflight infrastructure, in particular to an in-situ resource-based rocket take-off and landing platform suitable for complex terrain on the lunar surface, which comprises a plurality of demountably connected decks, a bearing assembly for supporting each deck and a fixing assembly for anchoring the bearing assembly on the lunar surface, the decks are mutually spliced and jointly form the lifting platform, the bearing assembly comprises a plurality of main cross beams and bearing beams which abut against the lower surface of the lifting platform, the main cross beams are detachably connected with the decks on the edges of the lifting platform, and fixing assemblies are further arranged at the joints of the main cross beams. The fixing assembly comprises supporting discs arranged at the connecting points of the main cross beams, positioning blocks arranged below the supporting discs and anchor rods arranged on the surfaces of the positioning blocks in a penetrating mode, and threaded rods are arranged between the positioning blocks and the supporting discs. The problem that a rocket take-off and landing platform which can adapt to the complex terrain of the lunar surface, does not need large-area ground treatment and can be rapidly deployed does not exist at present can be effectively solved.

Description

Technical Field

[0001] This invention relates to the field of aerospace infrastructure, and more specifically to a rocket launch and landing platform adapted to the complex terrain of the lunar surface based on in-situ resources. Background Technology

[0002] As human exploration of the moon deepens, establishing lunar bases and developing lunar resources have become important directions for future space development. In lunar exploration missions, rocket launch and landing platforms, as critical infrastructure, directly impact mission success or failure due to their performance and adaptability. Traditional rocket launch and landing platforms on Earth typically require extensive ground leveling and hardening to ensure platform stability and rocket safety during launch and landing. However, the lunar surface is complex, containing numerous craters, boulders, undulating terrain, and soft lunar regolith. Under such conditions, traditional ground leveling and hardening methods are virtually impossible, presenting immense technical challenges and consuming vast amounts of energy and resources. Furthermore, the construction of traditional rocket launch and landing platforms often relies on pre-construction using engineering machinery, resulting in a lengthy process from transporting equipment to platform completion. In lunar exploration missions, especially those requiring the rapid establishment of temporary landing sites, this extended construction period severely hinders efficient mission execution. For example, when a lunar probe needs to return to Earth urgently, or when a rocket launch and landing platform needs to be rapidly deployed in a newly discovered lunar resource area for resource transportation missions, the current construction methods of the launch and landing platform cannot meet the requirements for rapid response. Therefore, developing a rocket launch and landing platform that can adapt to the complex terrain of the lunar surface, requires no large-area ground treatment, and can be deployed rapidly is of significant practical importance and urgent need. Summary of the Invention

[0003] In view of this, the purpose of this invention is to provide a rocket launch and landing platform adapted to the complex terrain of the lunar surface based on in-situ resources, in order to solve the problem of the current lack of a rocket launch and landing platform that can adapt to the complex terrain of the lunar surface, does not require large-area ground treatment, and can be deployed quickly.

[0004] To achieve the above objectives, the present invention provides the following technical solution: A rocket launch and landing platform adapted to the complex terrain of the lunar surface, based on in-situ resources, includes multiple detachably connected decks, a load-bearing assembly for supporting each deck, and a fixing assembly for anchoring the load-bearing assembly to the lunar surface. The decks are spliced ​​together to form the launch and landing platform, which is horizontally positioned on the ground. The load-bearing assembly includes multiple main crossbeams and load-bearing beams abutting against the lower surface of the launch and landing platform. Each main crossbeam is detachably connected to a deck at the edge of the launch and landing platform, and the fixing assembly is also provided at the connection point of each main crossbeam. Both ends of each load-bearing beam are detachably connected to the corresponding main crossbeam, and adjacent load-bearing beams are evenly spaced. The main beams and load-bearing beams are spaced apart and cooperate with each other to abut the lower surface of each deck. The fixing components include support plates set at the connection points of each main beam, positioning blocks set below the support plates, and anchor rods passing through the surface of the positioning blocks. Each support plate is horizontally set and detachably connected to multiple adjacent main beams. The positioning blocks are detachably connected directly below the support plates, and a threaded rod is provided between the positioning blocks and the support plates. One end of the threaded rod is fixed to the support plate, and the other end passes vertically through the positioning block and is threadedly connected to it. One end of the anchor rod is drilled vertically into the ground, and the other end extends out of the ground and is detachably connected to the positioning block.

[0005] Furthermore, each of the aforementioned decks has two oppositely arranged tenons and mortises on its peripheral surface, wherein the tenons and mortises cooperate with each other, and the vertical cross-section of each tenon is a trapezoidal structure that is narrower at the top and wider at the bottom.

[0006] Furthermore, the surface of the positioning block is provided with a plurality of positioning holes spaced circumferentially around the threaded rod. Each positioning hole is provided with a coaxial anchor rod, and one end of each anchor rod passes through the corresponding positioning hole and is detachably connected to it. Each anchor rod includes a first spiral part and a second spiral part arranged coaxially. The first spiral part is located above the second spiral part, and the diameter of the first spiral part is larger than that of the second spiral part. The outer surfaces of the first spiral part and the second spiral part are provided with a plurality of protrusions. One end of each protrusion is fixed to the surface of the anchor rod, and the other end is inclined downward and protrudes from the outer surface of the anchor rod.

[0007] Furthermore, each of the anchor rods has a limiting ring fitted and fixed on its outer surface, and the upper end face of the limiting ring abuts against the lower surface of the positioning block. One end of each anchor rod that passes through the positioning hole is threaded with a fixing ring, and the lower end face of the fixing ring abuts against the upper surface of the positioning block.

[0008] Furthermore, a support beam is detachably connected between adjacent positioning blocks. Multiple support beams surround the edge of the lifting platform and are positioned directly below and parallel to the corresponding main crossbeam. Each support beam has a vertically mounted telescopic cylinder on its surface, and the working end of the telescopic cylinder is fixedly connected to the surface of the corresponding main crossbeam. Each telescopic cylinder is electrically connected to a controller, which is also electrically connected to multiple displacement sensors installed on the ground. Each displacement sensor is installed on the ground, and the working end of each displacement sensor is vertically facing each corner of the lifting platform.

[0009] Furthermore, a positioning cylinder coaxial with the positioning block is provided at the center position, and an adjusting ring is rotatably connected to the upper end of the positioning cylinder. The lower end of the threaded rod passes through the positioning cylinder and the adjusting ring, and the threaded rod is threadedly connected to the adjusting ring.

[0010] Furthermore, each of the aforementioned support plates is detachably connected to the corresponding main crossbeam via a mortise and tenon structure.

[0011] The beneficial effects of this invention are as follows: 1. Efficient utilization of in-situ resources significantly reduces the cost of Earth-Moon transportation. The basalt involved in this invention is a naturally occurring in-situ resource on the lunar surface, which can be directly obtained through lunar mining without the need to be transported from Earth. After a series of processes adapted to the lunar environment, such as crushing, melting, and drawing, these lunar basalts can be made into high-performance basalt fibers. The core components (deck, main crossbeam, load-bearing beam, etc.) are all made from in-situ lunar soil and basalt fiber reinforced polymer (FRP) made from lunar basalt. From the acquisition of raw materials to the production of core components, the entire process relies on in-situ lunar resources, eliminating the need to transport large amounts of building materials from Earth. This not only reduces the load on the launch vehicle and lowers launch costs but also avoids the risk of material loss during long-distance transportation, providing an economical and efficient solution for the construction of lunar bases and fundamentally solving the problems of high cost and high difficulty in Earth-Moon transportation. 2. The components are assembled in a modular manner using mortise and tenon joints, threaded connections, and other detachable methods. The modular design facilitates transportation, storage, and subsequent maintenance and replacement. The platform size can be adjusted according to mission requirements to adapt to the complex scenarios of lunar operations, significantly improving construction efficiency and maintenance convenience. 3. A multi-layered stress-dispersing system enhances structural stability and anti-settlement capabilities. The rocket's impact force is transmitted through the deck to the load-bearing beams and main crossbeams. The main crossbeams then transmit the force to the ground via fixed components. Simultaneously, the lunar soil filling beneath the main crossbeams and load-bearing beams can directly transmit some of the force to the ground, achieving collaborative load-bearing between the components and the lunar soil. The triangularly distributed anchor bolts form a stable stress-bearing structure, while the stepped spiral section enhances the anchoring depth and pull-out resistance. The protrusions resembling pangolin scales increase friction with the lunar soil, effectively dispersing the impact force and reducing the risk of settlement. The edge support beams, main crossbeams, positioning blocks, and anchor bolts form a three-dimensional stress-bearing network. Combined with the telescopic cylinders and the lunar soil filling, this further disperses edge stress, resists torsional deformation, and improves overall rigidity.

[0012] Other advantages, objectives, and features of the invention will be set forth in the following description and will be apparent to those skilled in the art in some respects, or may be learned by practice of the invention. The objectives and other advantages of the invention can be realized and obtained through the following description. Attached Figure Description

[0013] To make the objectives, technical solutions, and beneficial effects of this invention clearer, the following figures are provided for illustration: Figure 1 This is a schematic diagram of the take-off and landing platform structure of the present invention; Figure 2 This is a side view of the take-off and landing platform of the present invention; Figure 3 This is a schematic diagram of the structure of the supporting component and the fixing component of the present invention; Figure 4 for Figure 3 Enlarged view of point A in the middle; Figure 5 This is a schematic diagram of the fixed component structure of the present invention.

[0014] The following labels are shown in the attached diagram: 1 Deck, 2 Main beam, 3 Bearing beam, 4 Fixing assembly, 401 Support plate, 402 Positioning block, 403 Anchor bolt, 4031 First spiral part, 4032 Second spiral part, 404 Threaded rod, 405 Positioning hole, 406 Protrusion, 5 Tenon, 6 Mortise groove, 7 Limiting ring, 8 Fixing ring, 9 Support beam, 10 Telescopic cylinder, 11 Positioning cylinder, 12 Adjusting ring. Detailed Implementation

[0015] like Figures 1-5 As shown, A rocket takeoff and landing platform adapted to complex lunar terrain based on in-situ resources, comprising multiple detachable decks 1, a bearing component for supporting each deck 1, and a fixing component 4 for anchoring the bearing component on the lunar surface. The decks 1 are spliced with each other and jointly form the takeoff and landing platform. Each deck 1 is rectangular, the takeoff and landing platform is rectangular in the horizontal plane, and the takeoff and landing platform is horizontally laid above the ground. The bearing component includes multiple main beams 2 and bearing beams 3 that abut against the lower surface of the takeoff and landing platform. Each main beam 2 is detachably connected to the deck 1 at the edge of the takeoff and landing platform through a mortise and tenon structure, and the fixing component 4 is also provided at the connection of each main beam 2. The two ends of each bearing beam 3 are detachably connected to the corresponding main beams 2 through a mortise and tenon structure, and the adjacent bearing beams 3 are evenly spaced. Each main beam 2 and bearing beam 3 cooperate together and abut against the lower surface of each deck 1. Among them, each main beam 2 is arranged in a "field" shape in the horizontal plane, each bearing beam 3 is evenly spaced and arrayed in one direction, and each bearing beam 3 is in the same vertical plane as the axis of the corresponding deck 1. The fixing component 4 includes a support plate 401 provided at the connection point of each main beam 2, a positioning block 402 provided below the support plate 401, and an anchor rod 403 penetrating through the surface of the positioning block 402. Each support plate 401 is horizontally arranged and is detachably connected to multiple adjacent main beams 2 at the same time. The positioning block 402 is detachably connected directly below the support plate 401, and a threaded rod 404 is provided between the positioning block 402 and the support plate 401. One end of the threaded rod 404 is fixed to the support plate 401, and the other end vertically penetrates through the positioning block 402 and is threadedly connected to it. One end of the anchor rod 403 drills into the ground vertically, and the other end extends out of the ground and is detachably connected to the positioning block 402.

[0016] As shown in the diagram, the deck 1, main crossbeam 2, and load-bearing beam 3 are all constructed using in-situ lunar regolith and basalt fiber-reinforced polymer (FRP) to form modular prefabricated lightweight, high-strength panels, eliminating the need to transport large quantities of building materials from Earth. Before constructing the take-off and landing platform, pits must be dug at designated locations, and anchor bolts 403 must be driven vertically into the lunar surface within each pit. Then, positioning blocks 402, threaded rods 404, and support plates 401 are installed. The vertical height of the support plates 401 can be adjusted using the threaded rods 404, ensuring that all support plates 401 are at the same horizontal level. Following this, the load-bearing components are constructed, starting with... Each main crossbeam 2 is fixedly connected to its corresponding support plate 401. During construction, while ensuring that each main crossbeam 2 is horizontally positioned, its lower surface also contacts the lunar surface. Its position can be adjusted by simultaneously building the main crossbeam 2 and adjusting the height of the support plate 401. For uneven surfaces, they can be repaired by removing excess soil and filling it into depressions (here, "soil" refers to lunar soil, consistent with the context). The soil is then compacted, and construction of the main crossbeam 2 continues. After the main crossbeam 2 is completed, lunar soil is further filled into the areas enclosed by each main crossbeam 2 until a certain level is reached. The height was determined, and then the supporting beam 3 was erected, ensuring that the lower surface of the supporting beam 3 was in contact with the compacted ground. After the supporting beam 3 was erected, lunar soil was transported and used to fill the gaps between the main crossbeams 2 and the supporting beam 3 until the height of the soil filling was equal to the height of the main crossbeams 2 and the supporting beam 3. Then, the deck 1 was laid. The laying sequence of the deck 1 should be from the outside to the inside. First, the deck 1 located at the edge of the landing platform was fixed to the adjacent main crossbeam 2, and then gradually laid towards the center of the landing platform until all deck 1 was laid. Since the lower surface of each deck 1 is... Since the main beam 3 and the main crossbeam 2 are in contact with each other, the impact force generated during the rocket's takeoff and landing will be transmitted to each of the supporting beams 3 and the main crossbeam 2 through the deck 1. The main crossbeam 2 will transfer part of the impact force to the ground through the fixing components 4. The anchor bolts 403 can effectively reduce the settlement of the main crossbeam 2. Furthermore, since the lower surfaces of the main crossbeam 2 and the supporting beam 3 are filled with lunar soil, the main crossbeam 2 and the supporting beam 3 can also transfer part of the impact force generated during the rocket's takeoff and landing to the ground, further dispersing the impact force received by each anchor bolt 403, and effectively preventing the takeoff and landing platform from settling.

[0017] In summary, the core components of the launch and landing platform, such as deck 1, main crossbeam 2, and load-bearing beam 3, are all made of in-situ lunar soil and basalt fiber-reinforced polymer (FRP). This means that there is no need to transport large amounts of building materials from Earth, which not only reduces the load on the launch vehicle and lowers launch costs, but also avoids problems such as material loss that may occur during long-distance transportation. This provides an economical and efficient solution for the construction and operation of the lunar base, and greatly reduces the cost and difficulty of Earth-Moon transportation.

[0018] In this embodiment, each of the deck 1 has two oppositely arranged tenons 5 and mortises 6 on its peripheral surface. The tenons 5 and mortises 6 cooperate with each other, and the vertical cross section of each tenon 5 is a trapezoidal structure that is narrow at the top and wide at the bottom.

[0019] As shown in the diagram, when the vertical impact force of the rocket acts on a single deck 1, the side of the trapezoidal tenon 5 (narrower at the top and wider at the bottom) first contacts the mortise 6 of the adjacent deck 1. The inclined surface converts part of the vertical force into horizontal compressive force, efficiently achieving force conversion and dispersion. This avoids the impact force being concentrated on a single deck 1, instead transferring it to adjacent decks 1. The load originally borne by a single deck 1 is distributed across multiple decks 1, significantly reducing the stress on a single deck 1. This reduces the risk of damage to deck 1 due to excessive local stress, making the stress on the entire takeoff and landing platform more balanced and reasonable. Secondly, it enhances the connection stability between decks 1 and improves the overall structural strength of the platform. When the trapezoidal tenon 5 (narrower at the top and wider at the bottom) and mortise 6 cooperate, they form a tighter fit compared to other connection structures. Under horizontal compressive force, the contact surface between the tenon 5 and mortise 6 generates greater friction, making the connection between adjacent decks 1 more secure and less prone to relative displacement. Meanwhile, the tenon 5 and mortise 6 have a simple and efficient fit. When laying the deck 1, the connection can be completed simply by splicing the tenons 5 and mortise 6 of the adjacent deck 1. There is no need to use any complicated connectors or tools, which ensures the stability of the connection and makes the operation simple and quick.

[0020] In this embodiment, each positioning block 402 has three positioning holes 405 spaced circumferentially around the threaded rod 404 on its surface. Each positioning hole 405 has a corresponding anchor rod 403 coaxially therewith, and the lower end of each anchor rod 403 passes through the corresponding positioning hole 405 and is detachably connected to it. Each anchor rod 403 includes a first spiral part 4031 and a second spiral part 4032 coaxially arranged. The first spiral part 4031 is located above the second spiral part 4032, and the diameter of the first spiral part 4031 is larger than that of the second spiral part 4032. The outer surfaces of the first spiral part 4031 and the second spiral part 4032 are provided with multiple protrusions 406, and the protrusions 406 are biomimetic to the texture of pangolin scales. One end of each protrusion 406 is welded and fixed to the surface of the anchor rod 403, and the other end is inclined downward and protrudes from the outer surface of the anchor rod 403.

[0021] As shown in the figure, the three circumferentially spaced positioning holes 405 on the positioning block 402, along with the corresponding anchor rods 403, form a triangular force-bearing structure. This structure is highly stable and can evenly distribute the force borne by the fixing component 4 to the three anchor rods 403, preventing excessive stress on any single anchor rod 403 and thus preventing loosening or subsidence. This enhances the connection strength between the entire fixing component 4 and the lunar surface. Simultaneously, the diameter of the first helical part 4031 of the anchor rod 403 is larger than that of the second helical part 4032. This stepped design allows the thicker first helical part 4031 to form a tighter engagement with the surrounding lunar soil after the anchor rod 403 penetrates the lunar surface, while the thinner second helical part 4032 can penetrate deeper into the lunar surface. This further increases the anchoring depth and pull-out resistance of the anchor rod 403, enabling the fixing component 4 to more reliably transfer the force of the main crossbeam 2 to the lunar surface, effectively resisting the impact force generated during rocket launch and landing, and significantly improving the connection strength between the platform and the lunar surface. Furthermore, the protrusions 406 on the outer surface of the anchor rod 403 adopt a biomimetic pangolin scale texture design. During the drilling process of the anchor rod 403 into the lunar surface, the downward-sloping protrusions 406 can embed themselves into the lunar soil like pangolin scales, increasing the friction and mechanical interlocking force between the anchor rod 403 and the lunar soil. Especially in the soft or gravelly soil conditions of the lunar surface, the protrusions 406 can firmly grasp the surrounding lunar soil particles, preventing the anchor rod 403 from rotating or shifting under force, significantly improving the anchoring effect of the anchor rod 403 in the complex lunar environment, ensuring that the fixing component 4 can play a stable role, and has excellent adaptability and gripping force for the complex soil environment of the lunar surface. Each anchor rod 403 is detachably connected to the positioning hole 405 on the positioning block 402. This design allows for flexible adjustment of the drilling depth and angle of the anchor rod 403 according to the actual soil conditions on the lunar surface during installation, achieving the best anchoring effect and providing flexible and efficient support for platform construction. When the main crossbeam 2 transmits the impact force to the fixing component 4, the three spaced anchor rods 403 can evenly distribute the force to the soil in different areas of the lunar surface, avoiding the force concentration in a local area and reducing the risk of lunar soil collapse due to excessive force. At the same time, the tight engagement between the first spiral part 4031 and the second spiral part 4032 of the anchor rod 403 and the lunar soil can more effectively transmit the force to the deep soil, utilizing the bearing capacity of the deep soil to resist the impact force, further enhancing the overall stability and anti-settlement capability of the platform, and further optimizing the stress system of the take-off and landing platform.

[0022] In this embodiment, a limiting ring 7 is integrally formed and fitted onto the outer surface of each anchor rod 403. The diameter of the limiting ring 7 is larger than that of the anchor rod 403, and the upper end face of the limiting ring 7 abuts against the lower surface of the positioning block 402. A fixing ring 8 is threaded to one end of each anchor rod 403 that passes through the positioning hole 405, and the lower end face of the fixing ring 8 abuts against the upper surface of the positioning block 402. The limiting ring 7 and the fixing ring 8 abut against and clamp the two end faces of the positioning block 402, thereby fixing the anchor rod 403 to the positioning block 402.

[0023] As shown in the figure, the anchor rod 403 is drilled into the ground until the lower end face of the limiting ring 7 abuts against the ground. The limiting ring 7 serves a positioning function, and its diameter is larger than that of the anchor rod 403. The limiting ring 7, in conjunction with components such as the first spiral part 4031 and the second spiral part 4032, further prevents the anchor rod 403 from settling under stress. The limiting ring 7 and the fixing ring 8 apply clamping force evenly from the upper and lower end faces of the positioning block 402, making the force distribution on the positioning block 402 more balanced and reducing the risk of damage to the positioning block 402 due to excessive force at a single point. Furthermore, by placing shims between the limiting ring 7 and each positioning block 402 (the shims are fitted onto the outer ring surface of the corresponding anchor rod 403), installation errors of the positioning block 402 can be compensated, ensuring that the threaded rod 404 always remains vertical. The bidirectional clamping mechanism of the limiting ring 7 and the fixing ring 8 effectively eliminates the gap between the anchor rod 403 and the positioning block 402, preventing relative swaying or loosening during strong vibrations during rocket takeoff and landing. Even under long-term impact, the threaded fixing ring 8 maintains a stable clamping force, which, combined with the support of the limiting ring 7, ensures that the anchor rod 403 and the positioning block 402 remain firmly connected, providing a reliable structural foundation for the force transmission of the entire fixing assembly 4. The threaded connection between the fixing ring 8 and the anchor rod 403 makes operation simple and efficient during the platform construction and commissioning phase, helping to improve the efficiency of the takeoff and landing platform construction.

[0024] In this embodiment, a support beam 9 is detachably connected between adjacent positioning blocks 402. The two ends of the support beam 9 are respectively inserted through the upper ends of the corresponding anchor rods 403, and the support beam 9 is fixedly connected to the positioning block 402 by a fixing ring 8. Multiple support beams 9 are arranged around the edge of the lifting platform, and the support beams 9 are positioned directly below the corresponding main crossbeam 2 and parallel to each other. Each support beam 9 has a vertically placed telescopic cylinder 10 (the telescopic cylinder 10 is hydraulic) fixed to its surface, and the working end of the telescopic cylinder 10 is fixedly connected to the surface of the corresponding main crossbeam 2. Each telescopic cylinder 10 is electrically connected to a controller, and the controller is also electrically connected to multiple displacement sensors installed on the ground. Each displacement sensor is installed on the ground, and the working end of each displacement sensor is vertically facing each corner of the lifting platform and detecting its displacement (the displacement sensors and controller are not shown in the figure). The lower surface of the support beam 9 is also in contact with the ground, and lunar soil is filled between the support beam 9 and the main crossbeam 2.

[0025] As shown in the diagram, each support beam 9 is positioned at the edge of the landing platform. A telescopic cylinder 10 for support is installed between the support beam 9 and the main crossbeam 2. Both ends of the support beam 9 are fixed to the positioning block 402 and anchor rod 403 via fixing rings 8. This allows the support beam 9 to not only transmit force through the positioning block 402 and anchor rod 403, but also directly transfer some force to the ground, further enhancing its load-bearing capacity. This arrangement creates a three-dimensional force network between the support beam 9, the main crossbeam 2, the positioning block 402, and the anchor rod 403: the impact force borne by the main crossbeam 2 can be transmitted to the support beam 9 through the telescopic cylinder 10, and the support beam 9 then distributes the force to multiple positioning blocks 402, anchor rods 403, and the ground, achieving multi-level force transmission and coordinated load-bearing. Furthermore, the lunar soil filling between the support beam 9 and the main crossbeam 2 acts as a buffer layer, transferring some of the impact force to a wider area of ​​the ground, further dispersing the force. Compared to a single component bearing independent force, this networked structure can effectively resist the twisting or warping of the platform caused by excessive local stress. Especially under the instantaneous impact of rocket take-off and landing, it can significantly reduce the risk of structural damage caused by stress concentration at the edge of the platform, making the entire platform more balanced in stress and more stable in structure, and significantly improving the overall stiffness and deformation resistance of the take-off and landing platform.

[0026] Meanwhile, displacement sensors are installed on the ground and aligned with the corners of the takeoff and landing platform to monitor the displacement of key components in real time. The data is fed back to the controller, which then drives the telescopic cylinders 10 at the corresponding positions to extend and retract. When the platform experiences localized settlement due to long-term use or impact, the telescopic cylinders 10 can extend in time to lift the main crossbeam 2, compensating for the settlement. If a certain area experiences slight upward tilting due to excessive force, the telescopic cylinders 10 can be appropriately shortened to balance the attitude. The contact between the lower surface of the support beam 9 and the ground, as well as the lunar soil filling the space between the support beam 9 and the main crossbeam 2, provides a more stable foundation for this dynamic adjustment. This dynamic adjustment mechanism overcomes the limitations of traditional fixed structures, ensuring the platform remains level at all times. It provides a high-precision reference surface for rocket takeoff and landing, preventing landing deviations or takeoff imbalances caused by platform tilt, and achieving real-time correction of the takeoff and landing platform's attitude, thus ensuring takeoff and landing accuracy.

[0027] In this embodiment, a positioning cylinder 11 coaxial with the positioning block 402 is welded and fixed at the center position, and an adjusting ring 12 is rotatably connected to the upper end of the positioning cylinder 11. The lower end of the threaded rod 404 passes through the positioning cylinder 11 and the adjusting ring 12, and the threaded rod 404 is threadedly connected to the adjusting ring 12.

[0028] As shown in the figure, when it is necessary to install the threaded rod 404 and the support plate 401, it is only necessary to align one end of the threaded rod 404 with the adjusting ring 12, and then rotate the adjusting ring 12 to connect it with the threaded rod 404, so that one end of the threaded rod 404 extends vertically into the positioning cylinder 11, thereby fixing the positioning block 402 and the support plate 401. Furthermore, the height of the support plate 401 can be dynamically adjusted through the adjusting ring 12, so that the lifting platform always remains in a horizontal position.

[0029] In this embodiment, each of the support plates 401 is detachably connected to the corresponding main crossbeam 2 via a mortise and tenon structure, which makes disassembly and assembly convenient and ensures stable stress.

[0030] Finally, it should be noted that the above preferred embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail through the above preferred embodiments, those skilled in the art should understand that various changes can be made to it in form and detail without departing from the scope defined by the claims of the present invention.

Claims

1. A rocket launch and landing platform adapted to the complex terrain of the lunar surface based on in-situ resources, comprising multiple detachably connected decks (1), a load-bearing assembly for supporting each deck (1), and a fixing assembly (4) for anchoring the load-bearing assembly to the lunar surface, characterized in that: Each of the decks (1) is spliced ​​together to form a landing platform, which is horizontally set on the ground. The load-bearing component includes multiple main crossbeams (2) and load-bearing beams (3) that abut against the lower surface of the landing platform. Each of the main crossbeams (2) is detachably connected to the decks (1) at the edge of the landing platform. The connection of each main crossbeam (2) is also provided with the fixing component (4). The two ends of each load-bearing beam (3) are detachably connected to the corresponding main crossbeam (2), and adjacent load-bearing beams (3) are evenly spaced. Each of the main crossbeams (2) and load-bearing beams (3) cooperates and abuts against the lower surface of each deck (1). The fixing component (4) includes a support plate ( ) set at the connection point of each main crossbeam (2). 401) A positioning block (402) is set below the support plate (401) and an anchor rod (403) passes through the surface of the positioning block (402). Each support plate (401) is horizontally set and detachably connected to multiple adjacent main beams (2). The positioning block (402) is detachably connected directly below the support plate (401), and a threaded rod (404) is provided between the positioning block (402) and the support plate (401). One end of the threaded rod (404) is fixed to the support plate (401), and the other end passes vertically through the positioning block (402) and is threadedly connected to it. One end of the anchor rod (403) is drilled into the ground in a vertical direction, and the other end extends out of the ground and is detachably connected to the positioning block (402).

2. The rocket launch and landing platform adapted to complex lunar terrain based on in-situ resources according to claim 1, characterized in that: Each of the decks (1) has two oppositely arranged tenons (5) and mortises (6) on its periphery surface. The tenons (5) and mortises (6) fit together, and the vertical cross section of each tenon (5) is a trapezoidal structure that is narrow at the top and wide at the bottom.

3. A rocket launch and landing platform adapted to complex lunar terrain based on in-situ resources according to claim 2, characterized in that: The surface of the positioning block (402) is provided with a plurality of positioning holes (405) circumferentially spaced around the threaded rod (404). Each positioning hole (405) is provided with an anchor rod (403) coaxially therewith, and one end of each anchor rod (403) passes through the corresponding positioning hole (405) and is detachably connected thereto. Each anchor rod (403) includes a first spiral part (4031) and a second spiral part (4032) coaxially arranged. The first spiral part (4031) is located above the second spiral part (4032), and the diameter of the first spiral part (4031) is larger than that of the second spiral part (4032). The outer surfaces of the first spiral part (4031) and the second spiral part (4032) are provided with a plurality of protrusions (406). One end of each protrusion (406) is fixed to the surface of the anchor rod (403), and the other end is inclined downward and protrudes from the outer surface of the anchor rod (403).

4. A rocket launch and landing platform adapted to complex lunar terrain based on in-situ resources according to claim 3, characterized in that: Each of the anchor rods (403) has a limiting ring (7) fitted and fixed on its outer surface, and the upper end face of the limiting ring (7) abuts against the lower surface of the positioning block (402). One end of each anchor rod (403) passing through the positioning hole (405) is threadedly connected to a fixing ring (8), and the lower end face of the fixing ring (8) abuts against the upper surface of the positioning block (402).

5. A rocket launch and landing platform adapted to complex lunar terrain based on in-situ resources according to claim 4, characterized in that: A support beam (9) is detachably connected between adjacent positioning blocks (402). Multiple support beams (9) surround the edge of the lifting platform. The support beams (9) are positioned directly below and parallel to the corresponding main crossbeam (2). Each support beam (9) has a vertically mounted telescopic cylinder (10) on its surface. The working end of the telescopic cylinder (10) is fixedly connected to the surface of the corresponding main crossbeam (2). Each telescopic cylinder (10) is electrically connected to a controller. The controller is also electrically connected to multiple displacement sensors installed on the ground. Each displacement sensor is installed on the ground, and the working end of each displacement sensor is vertically facing each corner of the lifting platform.

6. A rocket launch and landing platform adapted to complex lunar terrain based on in-situ resources according to claim 1, characterized in that: The positioning block (402) has a positioning cylinder (11) coaxial with it at its center position, and the upper end of the positioning cylinder (11) is rotatably connected to an adjusting ring (12). The lower end of the threaded rod (404) passes through the positioning cylinder (11) and the adjusting ring (12), and the threaded rod (404) is threadedly connected to the adjusting ring (12).

7. A rocket launch and landing platform adapted to complex lunar terrain based on in-situ resources according to claim 1, characterized in that: Each of the support plates (401) is detachably connected to the corresponding main crossbeam (2) via a mortise and tenon structure.

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