Multifunctional platform structure of manned lunar landing sealed cabin

Abstract

A multifunctional platform structure of a manned lunar-landing sealed cabin belongs to the technical field of spacecraft sealed cabin structure design, and comprises an inner cabin body and an outer cabin body, a large landing impact load joint is designed outside the cabin, and because the cabin wall is thin, the joint is designed into a large-area thin flange reinforcement form in order to diffuse shear load during impact; a flange is arranged at the position inside the sealed cabin body, the supporting table is connected with the cabin body flange through an angle box, impact loads are transmitted to the supporting table through a connecting frame and the flange, the supporting table is provided with two n-shaped reinforcing beams at each impact load acting point to form a V shape, the effects of transmitting and diffusing the loads are achieved, and a floor structure at the top end of the supporting table covers the supporting table. The rigidity of the platform is improved, and landing impact loads are further diffused and transmitted. The device not only has the function of bearing large impact load and concentrated load on the thin-wall sealed cabin, but also has the functions of providing activity, standing and on-orbit cargo package installation for astronauts.

Description

Technical Field

[0001] This invention relates to a multi-functional platform structure for a manned lunar landing sealed cabin, belonging to the field of spacecraft sealed cabin structure design technology. Background Technology

[0002] Compared to other manned spacecraft in low Earth orbit, such as space stations, manned lunar landing spacecraft have a greater need for lightweight platforms due to their longer flight distances and the requirement to perform functions such as lunar surface takeoff. There are generally three ways to achieve structural lightweighting: first, using new lightweight materials; second, designing a reasonable structural form to make the force transmission path of the structure more rational and improve structural efficiency; and third, structural reuse, where the same structural component performs multiple functions, greatly improving the utilization efficiency of the structure.

[0003] Manned lunar spacecraft need to land on the lunar surface. For the first time, the sealed cabin will face the landing impact load of the landing legs, the overload of large mass equipment during the ascent phase, and the overload load during lunar landing. All of these loads are large concentrated loads, which are far higher than the load levels of previous manned spacecraft. In order to achieve extreme lightweighting, the shell of the manned lunar landing sealed cabin is a very thin skin reinforced structure, which has a very weak ability to withstand concentrated loads. Therefore, it is necessary to design a new type of sealed cabin multi-functional platform structure that can resist large concentrated loads such as landing impact. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art and provide a multi-functional platform structure for a manned lunar landing sealed cabin, which has the function of bearing large impact loads and concentrated loads on a thin-walled sealed cabin, and also has the function of providing astronauts with space to move, stand, and install cargo packages in orbit.

[0005] The objective of this invention is achieved through the following technical solutions: A multi-functional platform structure for a manned lunar landing sealed cabin includes an external cabin and an internal cabin. The internal platform structure includes a support platform, a floor, a first reinforcing beam, a second reinforcing beam, a lower connecting corner box, an upper connecting corner box, a lower connecting corner strip, an upper connecting corner strip, a support plate connecting corner strip, a floor connecting corner strip, and an embedded beam in the floor. The support platform is composed of four support plates connected by corner strips. The four support plates are combined to form a cone-shaped platform, and the overall support platform is petal-shaped. The floor is composed of four fan-shaped structural panels and a central floor panel connected by corner strips; the central floor panel is circular and is connected to the fan-shaped structural panels by corner strips. The first and second reinforcing beams are "U"-shaped beams made of carbon fiber. The first and second reinforcing beams are connected to the lower surface of the support platform by adhesive bonding and screwing. The astronaut activity platform consists of four fan-shaped structural panels and a central floor. The four fan-shaped structural panels and the central floor form a complete and flat upper surface for astronauts to move around in orbit and sleep comfortably. The astronaut activity platform has "C"-shaped embedded beams in the floor structure. The embedded beams are made of carbon fiber material and have embedded metal parts in the beams. The embedded beams are rectangular in shape and are used to support and bear the weight of the astronauts when they are wearing spacesuits and standing on the floor. The extravehicular platform structure includes two structural forms: one is a joint that bears large landing impact loads and connects to the landing legs, and the other is a large load support that bears large mass equipment. The landing legs are screwed to the landing impact load joint, which is then bonded to the sealed cabin with adhesive and screws. The support platform is connected to the sealed cabin with screws via the lower connecting corner box and the lower connecting corner strip. The four support plates are bonded to a single cone with adhesive and screws via the support plate connecting corner strip. The cone is connected to the floor via the upper connecting corner strip and the upper connecting corner box. The four floor panels are connected to each other with screws via floor connecting corner strips. The central floor panel is connected to the floor panels via floor connecting corner strips to form an internal platform.

[0006] In one embodiment of the present invention, in order to reduce weight, some material is cut off from the non-load-bearing areas of the four support plates.

[0007] In one embodiment of the present invention, the support plate is a lightweight carbon fiber skin aluminum honeycomb core sandwich structure plate.

[0008] In one embodiment of the present invention, the floor is a lightweight carbon fiber skin aluminum honeycomb core sandwich structure panel.

[0009] In one embodiment of the present invention, the central floor is a carbon fiber panel honeycomb sandwich structure, wherein the panel is carbon fiber and the honeycomb core is a lightweight paper honeycomb.

[0010] In one embodiment of the present invention, in order to prevent the composite material structure from releasing harmful gases on track, the support platform, floor, and central floor are placed in an autoclave or oven for baking and gas release after curing during the manufacturing process.

[0011] In one embodiment of the present invention, the upper connecting corner box and the lower connecting corner box are made of 7075 high-strength aluminum alloy; the lower connecting corner strip, the upper connecting corner strip, the support plate connecting corner strip, and the floor connecting corner strip are made of 2A12 aluminum alloy.

[0012] In one embodiment of the present invention, the joint that bears large landing impact loads has a thin flange reinforced structure. The upper end of the joint is connected to the landing leg, and the lower end is glued to the cabin structure and screwed in. The reinforcing ribs are in the form of outward radiation, which plays the role of diffusing load.

[0013] In one embodiment of the present invention, the support for bearing the concentrated load of large mass equipment installation has a thin-walled conical rotating body structure, with its upper end connected to the large load installation point and its lower end connected to the cabin by screws.

[0014] In one embodiment of the present invention, during landing, the impact load of the landing leg is transmitted upward along the landing leg, the cabin and the support platform, while the load of the astronaut and equipment on the floor is transmitted downward from the floor, the support platform and the cabin. The loads in the two directions are cleverly offset, reducing the structural bearing pressure.

[0015] Compared with the prior art, the present invention has the following advantages: (1) The present invention designs a structure that efficiently transmits and bears landing impact loads or other large concentrated loads from outside the sealed cabin to inside the sealed cabin. It is the first time that an extremely thin sealed cabin has been able to bear such large loads, providing a solution for subsequent manned lunar landing models with this bearing requirement.

[0016] (2) This invention fulfills the function of the manned lunar landing sealed cabin activity platform, providing an open on-orbit activity space and a comfortable sleeping plane for astronauts in an extremely limited space, and efficiently realizing the load-bearing of astronauts' lunar landing and lunar surface ascent.

[0017] (3) The multi-functional platform structure of the sealed cabin of the present invention solves two problems at the same time, meets two needs, and achieves the purpose of efficient reuse of the structure. It solves the problem that the space inside the sealed cabin of the manned lunar landing is extremely limited but a flat and large space is needed for astronauts to move and stand on. It also solves the problem that the thin-walled cabin needs to withstand large landing impact loads or other large concentrated loads.

[0018] (4) The two loads acting in opposite directions are borne by the sealed cabin multi-functional platform structure of the present invention, and some loads can cancel each other out, further improving the structural utilization efficiency.

[0019] (5) This invention uses both metal and carbon fiber composite material structures. The external metal joints and cabin body have strong impact load resistance. Then, the lightweight carbon fiber composite material is used to disperse the impact force, and the excellent energy absorption properties of carbon fiber material are used to absorb the energy of the impact load. For the first time, cross-material design is used in manned spacecraft. The performance advantages of the two materials are utilized to efficiently solve the problem of bearing large impact loads or concentrated loads.

[0020] (6) This invention achieves extreme lightweighting of the structure. The lower surface of the support platform features a V-shaped reinforcing beam with a spiral-shaped arrangement, efficiently bearing and dispersing large loads using limited materials. Both the support plate structure and the floor structure utilize carbon fiber panel aluminum honeycomb sandwich panels, while the central floor uses a carbon fiber panel paper honeycomb sandwich panel. The embedded beams and V-shaped beams all use carbon fiber materials, achieving structural lightweighting. Elliptical openings are provided on the support platform to further reduce weight.

[0021] (7) The “V”-shaped load diffusion beam set at the concentrated load application point in this invention can be flexibly set according to the concentrated load arrangement point of the sealed chamber. The height of the truncated cone in this invention can also be adjusted according to the layout position required by the floor platform. Therefore, this invention is highly adaptable and flexible in design.

[0022] (8) This invention innovatively uses vacuum degassing technology to treat harmful gases in composite material structural plates inside manned spacecraft, achieving structural lightweighting while avoiding harm to the health of astronauts from composite material structures. Attached Figure Description

[0023] Figure 1 A three-dimensional schematic diagram of the multi-functional platform structure for a manned lunar landing capsule.

[0024] Figure 2 This is a front view of the support platform 1, the combined floor and the central floor, and the connecting parts.

[0025] Figure 3 This is a schematic diagram of the support platform and its connecting parts.

[0026] Figure 4 This is a schematic diagram of the back of the support platform 1, including the combined floor, central floor, and connectors.

[0027] Figure 5 This is a side view of the supporting platform 1, the combined floor and the central floor, and the connecting parts.

[0028] Figure 6 This is a three-dimensional schematic diagram of the first reinforcing beam.

[0029] Figure 7 This is a schematic diagram of a fan-shaped structural slab and its embedded beams.

[0030] Figure 8 This is a diagram illustrating the astronauts standing inside the capsule during lunar landing.

[0031] Figure 9 This is a schematic diagram of the joint and landing legs that withstand large landing impact loads outside the cabin.

[0032] Figure 10 A schematic diagram of a support for bearing large loads on heavy equipment.

[0033] Figure 11 A partial cross-sectional diagram of the multi-functional platform structure at the landing impact load joint.

[0034] Figure 12 A schematic diagram of a partial cross-section of the multi-functional platform structure at the high-load support location. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0036] A multi-functional platform structure for a manned lunar landing sealed cabin includes an external cabin and an internal cabin. The internal platform structure includes a support platform 1, a floor 2, a first reinforcing beam 4, a second reinforcing beam 5, a lower connecting corner box 6, an upper connecting corner box 7, a lower connecting corner strip 8, an upper connecting corner strip 9, a support plate connecting corner strip 10, a floor connecting corner strip 11, and an embedded beam 12 in the floor. Figure 1 A three-dimensional schematic diagram of the multi-functional platform structure for a manned lunar landing capsule.

[0037] The support platform 1 is composed of four support plates 18 connected by corner strips 10. The four support plates are combined to form a conical platform. To reduce weight, some material is cut away in non-load-bearing areas, giving the support platform an overall petal shape. The support plates are lightweight carbon fiber skin aluminum honeycomb core sandwich structure panels.

[0038] Floor 2 is composed of 4 fan-shaped structural panels and 1 central floor 3 connected by floor connecting corner strips 11. The floor is a lightweight carbon fiber skin aluminum honeycomb core sandwich structure panel.

[0039] The central floor 3 is circular and is connected to the fan-shaped structural plate by corner strips 17. The central floor is a carbon fiber panel honeycomb sandwich structure, with the panel being carbon fiber and the honeycomb core being lightweight paper honeycomb.

[0040] Figure 2 This is a front view of the support platform 1, the combined floor 2 and the central floor 3, and the connecting parts. Figure 3 This is a schematic diagram of the support platform 1 and its connecting parts.

[0041] Figure 4 This is a schematic diagram of the back of the support platform 1, the combined floor 2 and the central floor 3, and the connecting parts. Figure 5 This is a side view of the support platform 1, combined with the floor 2, the central floor 3, and the connecting parts.

[0042] The first reinforcing beam 4 and the second reinforcing beam 5 are "U"-shaped beams made of carbon fiber. The first reinforcing beam 4 and the second reinforcing beam 5 are connected to the lower surface of the support platform by adhesive bonding and screwing.

[0043] Figure 6This is a three-dimensional schematic diagram of the first reinforcing beam 4. The upper connecting corner box 7 and the lower connecting corner box 6 are made of 7075 high-strength aluminum alloy with a wall thickness of 2.5mm.

[0044] The lower connecting corner strip 8, the upper connecting corner strip 9, the support plate connecting corner strip 10, and the floor connecting corner strip 11 are made of 2A12 aluminum alloy with a wall thickness of 2mm.

[0045] The astronaut activity platform has a C-shaped embedded beam 12 embedded in the floor structure. The embedded beam is made of carbon fiber and contains embedded metal parts. The rectangular embedded parts in the floor support and load-bearing structure are used to support the astronauts when they are wearing spacesuits and standing on the floor.

[0046] Figure 7 This is a schematic diagram of a sector-shaped structural slab and an embedded beam 12. Figure 8 This is a diagram illustrating the astronauts standing inside the capsule during lunar landing.

[0047] Multiple metal embeddings are installed in the floor for securing and installing cargo packages after they are removed from the side walls of the cabin and put into operation in orbit.

[0048] The astronaut activity platform consists of four fan-shaped structural panels and one central floor panel. The four fan-shaped structural panels and one central floor panel form a complete and flat upper surface for astronauts to use for on-orbit activities and comfortable sleeping.

[0049] To prevent the composite material structure from releasing harmful gases during the manufacturing process, the support platform 1, floor 2, and center floor 3 are placed in an autoclave or oven for baking and gas release after curing.

[0050] The extravehicular platform structure includes two structural forms: one is a joint 13 that bears large landing impact loads and connects to the landing legs 15, and the other is a large load support 14 that bears large mass equipment.

[0051] Figure 9 This is a schematic diagram of the joint 13 and landing legs 15 that withstand large landing impact loads outside the cabin. Figure 10 A schematic diagram of a large load support 14 for bearing large mass equipment.

[0052] The joint 13, which bears large landing impact loads, has a thin flange reinforced structure. The upper end of the joint 13 is connected to the landing leg 15, and the lower end is glued to the cabin structure and screwed in. Its reinforcing ribs are in the form of outward radiation, which plays the role of diffusing load.

[0053] The support 14, which bears the concentrated load of the installation of large mass equipment, has a thin-walled conical rotating body structure. Its upper end is connected to the installation point of the large load, and its lower end is connected to the cabin by screws.

[0054] The platform structure is connected as follows: the landing leg 15 is screwed to the landing impact load joint 13; the landing impact load joint 13 is glued and screwed to the sealed cabin 16; the support platform and the sealed cabin 16 are connected by screws through the lower connecting corner box 6 and the lower connecting corner strip 8; the four support plates are glued and screwed together to form a cone through the support plate connecting corner strip 10; the cone is connected to the floor through the upper connecting corner strip 9 and the upper connecting corner box 7; the four floor panels 2 are connected together by screws through the floor connecting corner strip 11; the central floor panel 3 is connected to the floor panels 2 through the floor connecting corner strip 11 to form the internal platform.

[0055] Figure 11 A partial cross-sectional diagram of the multi-functional platform structure at the landing impact load joint.

[0056] Figure 12 A partial cross-sectional diagram of the multi-functional platform structure at the high-load support area. The astronaut activity platform's working principle is as follows: The landing legs of the manned lunar landing structure experience impact loads exceeding 7 tons at a single point during landing, while other large-load equipment outside the cabin experiences loads exceeding 6 tons at a single point during launch, far exceeding the load levels of previous manned models. The sealed cabin structure, with its extremely thin skin and stiffened structure (skin only 1.2 mm), cannot withstand these loads.

[0057] This invention designs a multi-functional platform structure for a manned lunar landing sealed cabin, consisting of an inner and outer cabin. The outer cabin features a large landing impact load joint. Due to the thin cabin walls, the joint is designed as a large-area thin flange with reinforcement to diffuse the shear load during impact. A flange is installed at this location inside the sealed cabin. The support platform is connected to the cabin flange via corner boxes. The impact load is transferred to the support platform through the connecting frame and flange. The support platform has two "U"-shaped reinforcing beams forming a "V" shape at each impact load application point, which plays a role in load transfer and diffusion. The floor structure at the top of the support platform covers the platform, improving the platform's rigidity and further diffusing and transferring the landing impact load.

[0058] Meanwhile, the floor structure provides a platform for astronauts to stand, move around, and sleep during lunar landing and ascent, as well as for the installation of cargo packages in orbit.

[0059] During landing, the impact load of the landing legs is transmitted upward along the landing legs, the cabin, and the support platform, while the load of the astronauts and equipment on the floor is transmitted downward from the floor, the support platform, and the cabin. The loads in the two directions are cleverly offset, reducing the structural load-bearing pressure.

[0060] The operating principle of the cabin when bearing heavy loads is the same as when bearing impact loads, only the applied load is lower than that of the landing impact load.

[0061] Example: A multi-functional platform structure for a manned lunar landing capsule, including two parts: outside the capsule and inside the capsule. The platform structure inside the capsule includes a support platform 1, a floor 2, a first reinforcing beam 4, a second reinforcing beam 5, a lower connecting corner box 6, an upper connecting corner box 7, a lower connecting corner bar 8, an upper connecting corner bar 9, a support plate connecting corner bar 10, a floor connecting corner bar 11, and an embedded beam in the floor 12.

[0062] The support platform 1 is composed of 4 support plates 18 combined through the support plate connecting corner bar 10. The 4 support plates are combined into a conical platform. To reduce weight, some materials are cut off locally in non-large load-bearing parts, and the overall support platform is in a petal shape. To reduce weight, the support plate is a light material CCM55J carbon fiber skin aluminum honeycomb core sandwich structure plate, with the overall thickness of the support plate being 15 mm and the skin thickness being 0.3 mm.

[0063] The floor 2 is composed of 4 fan-shaped structure plates and 1 central floor 3 combined through the floor connecting corner bar 11. To reduce weight, the support plate is a light material CCM55J carbon fiber skin aluminum honeycomb core sandwich structure plate, with the overall thickness of the floor being 25.6 mm and the skin being 0.3 mm.

[0064] The central floor 3 is circular and is connected to the floor through the corner bar 17. The central floor 3 is a carbon fiber panel honeycomb sandwich structure, with the panel being CCM55J carbon fiber and the honeycomb core being a light paper honeycomb. The overall thickness of the central floor is 10 mm and the panel thickness is 0.2 mm.

[0065] The first reinforcing beam and the second reinforcing beam are "U"-shaped CCM55J carbon fiber beams, with the beam width being 20 mm, the height being 14.4 mm, and the wall thickness being 1.5 mm. To disperse the concentrated load, there are two "square" reinforcing beams at each concentrated load point to form a "V" shape, which plays the role of load transfer and dispersion.

[0066] The upper connecting corner box and the lower connecting corner box are made of 7075 high-strength aluminum alloy material, with a wall thickness of 2.5 mm.

[0067] The materials of the lower connecting corner bar, the upper connecting corner bar, the support plate connecting corner bar, and the floor connecting corner bar are 2A12 aluminum alloy materials, with a wall thickness of 2 mm. For the astronaut activity platform, a "C"-shaped embedded beam is buried in the floor structure. The material of the embedded beam is CCM55J, with the beam width being 20 mm and the wall thickness being 1.5 mm. Metal embedded parts are buried in the beam. The embedded beam is rectangular in the floor and is used for the support and load-bearing when the astronaut wears a spacesuit and stands on the floor with feet.

[0068] Multiple metal embedded parts are buried in the floor structure for the fixation and installation after the cargo package on the side wall of the capsule is removed during in-orbit operation.

[0069] The astronaut activity platform consists of four floor panels and a central small floor panel forming a complete and flat upper surface, used for astronauts' activities in orbit and for comfortable sleeping.

[0070] To prevent the composite material structure from releasing harmful gases in orbit, the support plates and flooring are manufactured by baking them in an autoclave or oven after curing. The baking temperature is 75±2℃, and the baking time is 48 hours. During baking, the autoclave is heated but not pressurized, and the structural plate is wrapped in a vacuum bag with a pressure of 8 kPa inside.

[0071] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0072] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A multi-functional platform structure for a manned lunar landing sealed cabin, characterized in that, It consists of two parts: the exterior and the interior. The interior platform structure includes a support platform, floor, first reinforcing beam, second reinforcing beam, lower connecting corner box, upper connecting corner box, lower connecting corner strip, upper connecting corner strip, support plate connecting corner strip, floor connecting corner strip, and floor embedded beam. The support platform is composed of four support plates connected by corner strips. The four support plates are combined to form a cone-shaped platform, and the overall support platform is petal-shaped. The floor is composed of four fan-shaped structural panels and a central floor panel connected by corner strips; the central floor panel is circular and is connected to the fan-shaped structural panels by corner strips. The first and second reinforcing beams are "U" shaped beams made of carbon fiber. The first and second reinforcing beams are connected to the lower surface of the support platform by adhesive bonding and screwing. The astronaut activity platform consists of four fan-shaped structural panels and a central floor. The four fan-shaped structural panels and the central floor form a complete and flat upper surface for astronauts to move around in orbit and sleep comfortably. The astronaut activity platform has "C"-shaped embedded beams in the floor structure. The embedded beams are made of carbon fiber and contain embedded metal parts. The rectangular embedded parts in the floor support and load-bearing structure are used for astronauts to stand on the floor while wearing spacesuits. The extravehicular platform structure includes two structural forms: one is a joint that bears large landing impact loads and connects to the landing legs, and the other is a large load support that bears large mass equipment. The landing legs are screwed to the landing impact load joint, which is then bonded to the sealed cabin with adhesive and screws. The support platform is connected to the sealed cabin with screws via the lower connecting corner box and the lower connecting corner strip. The four support plates are bonded to a single cone with adhesive and screws via the support plate connecting corner strip. The cone is connected to the floor via the upper connecting corner strip and the upper connecting corner box. The four floor panels are connected to each other with screws via floor connecting corner strips. The central floor panel is connected to the floor panels via floor connecting corner strips to form an internal platform.

2. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, To reduce weight, some material was cut off from the non-load-bearing areas of the four support plates.

3. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, The support plate is a lightweight carbon fiber skin aluminum honeycomb core sandwich structure plate.

4. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, The floor is a lightweight carbon fiber skin aluminum honeycomb core sandwich structure panel.

5. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, The central floor has a carbon fiber panel honeycomb sandwich structure, with the panel made of carbon fiber and the honeycomb core made of lightweight paper honeycomb.

6. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, To prevent the composite material structure from releasing harmful gases during the manufacturing process, the support platform, floor, and center floor are placed in an autoclave or oven for baking and gas release after curing.

7. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, The upper and lower connecting corner boxes are made of 7075 high-strength aluminum alloy; the lower connecting corner strip, upper connecting corner strip, support plate connecting corner strip, and floor connecting corner strip are made of 2A12 aluminum alloy.

8. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, The joint that withstands large landing impact loads has a thin flange reinforced structure. The upper end of the joint is connected to the landing leg, and the lower end is glued to the cabin structure and screwed in. Its reinforcing ribs are arranged in an outward radiating form, which plays a role in diffusing the load.

9. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, The support for bearing the concentrated load of large-mass equipment installation is a thin-walled conical rotating body structure. Its upper end is connected to the large load installation point, and its lower end is connected to the cabin by screws.

10. The multi-functional platform structure for a manned lunar landing sealed cabin according to claim 1, characterized in that, During landing, the impact load of the landing legs is transmitted upward along the landing legs, the cabin, and the support platform, while the load of the astronauts and equipment on the floor is transmitted downward from the floor, the support platform, and the cabin. The loads in the two directions are cleverly offset, reducing the structural load-bearing pressure.

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