A rigid-flexible combined lightweight manned sealed cabin

Abstract

The application discloses a rigid-flexible combined light-weight manned sealed cabin, which comprises a metal shell and a flexible film; the metal shell is an integrated structure composed of a front spherical cone, a column segment and a rear cone, the front end of the front spherical cone is provided with a docking cabin door for docking with a spaceship; the bottom end of the rear cone is sealed through the flexible film, and the flexible film is attached to the surface of a storage tank extending into the inside of the sealed cabin under the action of internal pressure; the column segment is provided with an egress cabin door, and the column segment is also provided with an equipment mounting platform for carrying instruments. The application can meet the requirements of extreme light weight and conformal design with the storage tank and the like.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, specifically to a lightweight manned sealed cabin that combines rigidity and flexibility. Background Technology

[0002] Traditional manned spacecraft sealed cabin structures are all rigid structures, with sidewall structures generally falling into two categories: semi-monocoque and panel-type. The former consists of a skin, bulkhead, and stringers welded together, as seen in the return capsule of China's Shenzhou spacecraft and the orbital module of Russia's Soyuz series spacecraft. The latter consists of panels and a frame welded together as a single unit, as seen in China's Tiangong space station and Russia's Mir space station. The spherical base typically does not require equipment installation, therefore a rigid skin is chosen for its structure, with a spherical shape to withstand internal pressure.

[0003] With the development of my country's manned lunar exploration and other projects, there is a strong demand for lightweight and integrated manned spacecraft cabins. On the one hand, the cabin structure is required to be extremely lightweight, and on the other hand, the cabin must be designed in a common and integrated manner with large storage tanks to reduce the launch envelope. Traditional rigid manned cabins cannot meet the above mission requirements. Summary of the Invention

[0004] In view of this, the present invention provides a lightweight manned sealed cabin that combines rigidity and flexibility, which can meet the requirements of extreme lightweighting and conformal design with tanks and other similar structures.

[0005] The technical solution adopted in this invention is as follows:

[0006] A lightweight, rigid-flexible manned cabin, comprising a metal shell and a flexible membrane;

[0007] The metal shell is an integrated structure consisting of a front spherical cone, a cylindrical section, and a rear cone. The front spherical cone has a docking hatch at its front end for docking with the spacecraft. The bottom of the rear cone is sealed with a flexible membrane, which adheres to the surface of the storage tank extending into the sealed cabin under internal pressure. The cylindrical section has an exit hatch and an equipment mounting platform for carrying instruments.

[0008] Furthermore, the metal shell is an integral wall panel structure, which is integrally welded together from multiple annular metal connecting frames and wall panels.

[0009] Furthermore, the flexible membrane is fixedly connected to the metal shell by a metal pressure ring and screws, and a sealing ring is provided between the flexible membrane and the metal shell.

[0010] Furthermore, the upper end of the column section is equipped with a porthole to ensure that astronauts can observe the outside world from orbit and the lunar surface.

[0011] Furthermore, the sealed chamber is equipped with a floor, which is connected to the metal connecting frame of the sealed chamber's metal shell by screws; the floor has a honeycomb sandwich panel structure.

[0012] Furthermore, the equipment installation platform is a grid formed by assembling honeycomb sandwich structure panels.

[0013] Furthermore, the equipment installation platform includes a top plate, a bottom plate, a partition plate, a main plate, and two side plates;

[0014] The top plate, bottom plate, partition, main plate, and two side plates are all honeycomb sandwich structure plates. The inner and outer skins are bonded to the central aluminum honeycomb core with adhesive. The two side plates are fixed between the top plate and the bottom plate to form a frame. The partition is set inside the frame. One open end of the frame is fixedly connected to the sealed chamber body through a bent connecting corner piece, and the other open end is closed by the main plate.

[0015] Furthermore, the top plate and side plate, the bottom plate and side plate, and the partition plate and side plate are fixedly connected by perforated sleeves and lateral embedded parts.

[0016] Beneficial effects:

[0017] 1. This invention uses a flexible membrane to replace the traditional rigid skin spherical bottom, significantly reducing the structural weight. The density of commonly used sealed chamber metal materials is 2.64 g / cm³. 3 The average density of the flexible sealing base is 1.3 g / cm³. 3 In this example, the weight is reduced by 75% compared to the traditional rigid spherical bottom skin, and the weight of the sealed cabin structure is significantly reduced.

[0018] Secondly, this invention utilizes a flexible membrane as a sealing base. Due to its flexibility and sealing properties, it can fully adapt to external configurations while ensuring a tight seal. Therefore, during configuration design, the propellant tank can be extended into the sealed cabin. Under internal pressure, the flexible membrane covers the upper surface of the propellant tank, significantly reducing the overall height of the spacecraft. This results in a more compact spacecraft layout and improved space utilization. Furthermore, the flexible membrane covers the surface of the propellant tank under the pressure of the sealed cabin. During operation, the high pressure inside the propellant tank can fully withstand the pressure of the flexible membrane without crushing or deforming it. The load-bearing capacity of the propellant tank structure is reused, improving structural efficiency.

[0019] 2. The hatch design at the top and sides of the sealed cabin in this invention can ensure that astronauts can smoothly enter and exit the spacecraft, and the side window design can ensure that astronauts can observe the outside world on the lunar surface while in orbit, thus ensuring the successful completion of the space mission.

[0020] 3. The sealed chamber sidewall of this invention is designed with an equipment installation platform, which can be used to install load-bearing equipment. The configuration can be selected according to mission requirements and layout needs, and the size can also be designed. The structure is lightweight, has a strong load-bearing capacity, and offers flexible configuration and adaptability. Furthermore, the equipment installation platform is a closed structure, which can meet the temperature control requirements of the instruments.

[0021] 4. The present invention features a floor structure inside the sealed cabin. The floor is a honeycomb sandwich structure panel, which provides support for astronauts' living and activities, providing a comfortable and convenient user experience. The floor structure is lightweight yet has a strong load-bearing capacity.

[0022] 5. In this invention, all structural plates are directly connected through perforated sleeves and lateral embedded parts, further reducing weight and achieving lightweighting. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0024] Figure 2 This is a diagram showing astronauts standing in a sealed cabin while wearing spacesuits.

[0025] Figure 3 This is an illustration of another perspective of astronauts standing inside the sealed cabin while wearing spacesuits.

[0026] Figure 4 This refers to the operational mode of the sealed capsule from launch to lunar landing.

[0027] Figure 5 This refers to the connection method between the flexible membrane and the sealed chamber shell.

[0028] Figure 6 A schematic diagram of the components of the equipment installation platform.

[0029] Figure 7 A schematic diagram of the connection structure between the top or bottom plate and the side plate of the equipment mounting platform.

[0030] Figure 8 A schematic diagram of the connection structure between the mainboard and side panel of the equipment installation platform.

[0031] Figure 9 A schematic diagram of the connection structure between the side plate and the partition of the equipment installation platform.

[0032] Figure 10 A schematic diagram of the connection structure between the top plate, bottom plate, or side plate of the equipment installation platform and the cabin.

[0033] Figure 11 This is a schematic diagram of the connection structure between the floor and the sealed chamber.

[0034] Among them, 1-docking hatch, 2-portal window, 3-metal shell, 4-exit hatch, 5-floor, 6-flexible membrane, 7-storage tank, 8-equipment installation platform, 9-sealing ring, 10-metal pressure ring, 11-main board, 12-top plate, 13-side plate, 14-bent connecting corner piece, 15-bottom plate, 16-bullet. Detailed Implementation

[0035] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0036] This invention provides a lightweight, rigid-flexible manned sealed cabin, such as... Figures 1-3 As shown, it includes a metal shell 3 and a flexible membrane 6.

[0037] The metal shell 3 is an integrated structure consisting of a front spherical cone, a cylindrical section, and a rear cone. The metal shell 3 is an integral wall panel structure, which is welded together from multiple annular metal connecting frames and wall panels. The wall panel structure is a skin-reinforced structure with a skin thickness of 1.2–1.5 mm, a reinforcement width of 2–3 mm, and a reinforcement height of 5–13 mm.

[0038] The front of the ball cone is equipped with a docking hatch 1, which can be opened and closed inwards and has a diameter of 850mm. After the docking hatch 1 is opened in orbit, it can dock with the spacecraft to form a transfer channel for astronauts and cargo.

[0039] The bottom of the rear cone is sealed by a flexible membrane 6, which is a flexible non-metallic material. In this embodiment, a polyurethane film is used. Under internal pressure, the flexible membrane 6 adheres to the surface of the tank 7 extending into the sealed chamber. Since the working pressure of the tank 7 is much higher than the pressure transmitted by the flexible membrane 6, it will not be crushed or deformed. Because of the flexible membrane 6, the tank 7 has a flexible layout, allowing it to extend into the sealed chamber and save space. The flexible membrane 6 can also effectively adapt to the pressure deformation of the tank 7. The flexible membrane 6 is fixedly connected to the metal shell 3 by a metal pressure ring 10 and screws. A sealing ring 9 is provided between the flexible membrane 6 and the metal shell 3 to achieve a seal between the flexible membrane 6 and the chamber. Figure 5 As shown, the flexible membrane 6 covers the upper surface of the tank 7. After the sealed chamber is pressurized, the pressure acts on the tank 7. The flexible membrane 6 itself does not bear the load but only seals, and the tank 7 is used to bear the load. The flexible membrane 6 can withstand a pressure difference of 90 kPa between the inside and outside of the chamber.

[0040] The column section is equipped with an extravehicular activity (EVA) hatch 4. When the EVA hatch 4 is opened, it forms an extravehicular activity passage for astronauts on the lunar surface, enabling astronauts to enter and exit the lunar surface. To facilitate astronaut entry and exit, the EVA hatch 4 is designed as a square hatch with a diameter of 1000mm × 1000mm. The EVA hatch 4 can be opened and closed from both inside and outside, serving as a passage for astronauts to enter and exit the lunar surface.

[0041] The column segment also features an equipment mounting platform 8 for mounting instruments. The equipment mounting platform 8 is a grid structure made of honeycomb sandwich panels, maximizing the installation surface and space for the equipment. For example... Figure 6 As shown, the equipment installation platform 8 includes a top plate 12, a bottom plate 15, a partition plate 16, a main plate 11, and two side plates 13. The top plate 12, bottom plate 15, partition plate 16, main plate 11, and two side plates 13 are all honeycomb sandwich structure panels. The skin of the honeycomb sandwich structure panels is made of M55J carbon fiber material. The inner and outer skins are bonded to the central aluminum honeycomb core with adhesive. The side plates 13 and partition plate 16, which bear the greatest load, are 25.6 mm thick, while the bottom plate 15 and top plate 12 are 15 mm thick. The skin thickness is 0.3 mm for each. The equipment installation platform 8 can be adjusted in size and parameters according to the layout of the load equipment. The two side plates 13 are fixed between the top plate 12 and the bottom plate 15 to form a frame. The partition plate 16 is set within the frame. Multiple partition plates 16 can be arranged in parallel, such as... Figure 10 As shown, the open end of one side of the frame is fixedly connected to the sealed chamber body via a bent connecting corner piece 14, while the open end of the other side is closed by the main board 11. Figures 7-9 As shown, the top plate 12 and side plate 13, the bottom plate 15 and side plate 13, the main plate 11 and side plate 13, and the partition plate 16 and side plate 13 are fixedly connected by bushings and lateral embedded parts. The lateral embedded parts are screws, and the bushings are set inside the honeycomb sandwich structure plate.

[0042] The upper end of the column section is also equipped with a porthole 2 to ensure that astronauts can observe the outside world from orbit and the lunar surface.

[0043] The sealed cabin is equipped with floor 5, providing a platform for astronauts to stand and move around inside the cabin, such as... Figure 11 As shown, the metal connecting frame of the floor 5 and the metal shell 3 of the sealed chamber is connected by screws; the floor 5 is a honeycomb sandwich panel structure, the skin material is M55J carbon fiber, and the inner and outer skins are bonded to the central aluminum honeycomb core with adhesive. The thickness of the floor 5 is 25.6mm.

[0044] like Figure 4 As shown, the sealed capsule operates in the following mode from launch to the lunar surface:

[0045] 1) Launch Status

[0046] During launch, both hatches (docking hatch 1 and exit hatch 4) are closed, working together with the sealed cabin body to ensure the sealing performance of the sealed cabin.

[0047] 2) Lunar orbit docking status

[0048] The lander docked with the new spacecraft in lunar orbit, and the astronauts used the hatch key to open the sealing hatch 1 from the outside and enter the sealing cabin.

[0049] 3) Lunar Excursion Status

[0050] After the astronauts land on the moon aboard the spacecraft, and the spacecraft is depressurized, they open hatch 4 to enter the lunar surface and conduct activities. Once the astronauts return to the spacecraft after their lunar activities, a portable rapid testing device can be used to check the hatch's sealing condition. If the test is successful, the spacecraft will be repressurized.

[0051] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A lightweight, rigid-flexible manned sealed cabin, characterized in that, Includes a metal casing and a flexible membrane; The metal shell is an integrated structure consisting of a front spherical cone, a cylindrical section, and a rear cone. The front spherical cone has a docking hatch at its front end for docking with the spacecraft. The bottom of the rear cone is sealed with a flexible membrane, which adheres to the surface of the storage tank extending into the sealed cabin under internal pressure. The cylindrical section has an exit hatch and an equipment mounting platform for carrying instruments.

2. The lightweight manned sealed cabin with rigid-flexible combination as described in claim 1, characterized in that, The metal shell is an integral wall panel structure, which is formed by welding multiple annular metal connecting frames and wall panels together.

3. The lightweight manned sealed cabin with rigid-flexible combination as described in claim 1, characterized in that, The flexible membrane and the metal shell are fixedly connected by a metal pressure ring and screws, and a sealing ring is provided between the flexible membrane and the metal shell.

4. The lightweight manned sealed cabin with rigid-flexible combination as described in claim 1, characterized in that, The upper end of the column section is equipped with a porthole to ensure that astronauts can observe the outside world from orbit and the lunar surface.

5. The lightweight manned sealed cabin with rigid-flexible combination as described in claim 2, characterized in that, The sealed chamber is equipped with a floor, which is connected to the metal frame of the sealed chamber's metal shell by screws; the floor has a honeycomb sandwich panel structure.

6. The lightweight manned sealed cabin with rigid-flexible combination as described in any one of claims 1-5, characterized in that, The equipment installation platform is a grid formed by assembling honeycomb sandwich panels.

7. The lightweight manned sealed cabin with rigid-flexible combination as described in claim 6, characterized in that, The equipment installation platform includes a top plate, a bottom plate, a partition, a main board, and two side plates; The top plate, bottom plate, partition, main plate, and two side plates are all honeycomb sandwich structure plates. The inner and outer skins are bonded to the central aluminum honeycomb core with adhesive. The two side plates are fixed between the top plate and the bottom plate to form a frame. The partition is set inside the frame. One open end of the frame is fixedly connected to the sealed chamber body through a bent connecting corner piece, and the other open end is closed by the main plate.

8. The lightweight manned sealed cabin with rigid-flexible combination as described in claim 7, characterized in that, The top plate and side plate, the bottom plate and side plate, and the partition plate and side plate are fixedly connected by perforated sleeves and lateral embedded parts.

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