A space station laboratory configuration

Abstract

The application provides a space station experiment cabin and configuration, the experiment cabin adopts a double bearing cylinder configuration, and comprises a sealed experiment cabin, an exposed load cabin and a truss type resource cabin; the sealed experiment cabin is provided with a front end frame for docking with an organization, and a rear end connected with the exposed load cabin; the sealed experiment cabin is a sealed space for astronauts to move, and is provided with a cabinet and equipment in the sealed cabin and can bear the load of the whole device during launching; the exposed load cabin is used for supporting the installation of an exposed load outside the cabin and adopts a cylindrical non-sealed cabin body configuration; the exposed load cabin is provided with an airlock cabin, the airlock cabin is provided with an airlock function, a door is opened on a side wall, and personnel and goods can enter and exit the cabin; the truss type resource cabin comprises a propulsion module, a large driving mechanism, a basic truss and a solar wing. The truss type resource cabin reduces the structure weight, reduces the envelope size, makes the structure more compact, and provides a kind of thought for the expansion and upgrading of the space station of China.

Description

Technical Field

[0001] This invention relates to the field of spacecraft overall design, and more specifically to a configuration of a space station experimental module. Background Technology

[0002] A space station is a large orbital spacecraft, typically composed of multiple modules and a large structure. It houses astronauts who live and work on long-term orbits, and provides numerous platforms, instruments, equipment, and payloads for operation and use, making it an ideal platform for space payload exposure experiments. The experimental module needs to support personnel and cargo access, while also maximizing the installation of exposure payloads within certain constraints. These exposure payloads should be located as close as possible to the personnel and cargo access routes for ease of maintenance and repair.

[0003] Adhering to the design principle of "appropriate scale and room for development", the finite truss structure is suitable for my country's current national conditions and the development needs of the space station.

[0004] In conclusion, how to adopt innovative design to make the space station an excellent experimental platform for space payload exposure, control the scale of the space station to significantly reduce the construction cycle and cost, and at the same time provide a large number of exposure payload workstations to obtain greater application benefits is a problem of great practical significance. Summary of the Invention

[0005] The purpose of this invention is to provide a space station experimental module configuration that can provide astronaut activity space, support personnel and cargo entry and exit from the experimental module, and also provide numerous exposed payload workstations. It adopts a "reverse launch" method to minimize the weight and size of the top. The "reverse launch" method means that during launch, the sealed experimental module is at the bottom, bearing all loads; after separation, the sealed experimental module is at the top of the flight, bearing all flight forces.

[0006] To achieve the above objectives, the present invention provides a space station experimental module configuration, wherein the space station experimental module configuration is a spacecraft configuration of nested double load-bearing cylinders, comprising a sealed experimental module, an exposed payload module, and a truss-type resource module connected in sequence; the exposed payload module adopts a cylindrical non-sealed module configuration, including an airlock module, a non-airlock module, an airlock door, and an exposed payload; the rear section of the airlock module is nested inside the non-airlock module; the airlock door is located on the side of the airlock module; the exposed payload is installed on the outer wall of the non-airlock module.

[0007] The sealed test chamber includes a sealed test chamber body, a sealed test chamber front end, and a sealed test chamber rear end; the sealed test chamber front end is used to connect with the carrier adapter bracket; the sealed test chamber rear end is used to connect with the exposed load chamber.

[0008] The sealed experimental chamber adopts a frame beam combined with an external mesh reinforced metal shell structure, and cabinets and equipment are installed inside.

[0009] The front end of the sealed experimental chamber adopts a short metal shell structure reinforced with an external mesh; the rear end of the sealed experimental chamber adopts a short metal shell structure reinforced with an external mesh.

[0010] The airlock chamber is provided with a rear ball bottom at its rear end.

[0011] The non-airlock compartment adopts a frame beam structure and an outer mesh reinforced skin structure; the frame beam structure is used to provide the force transmission skeleton of the entire compartment, bear axial loads and provide a certain stiffness; the mesh reinforced skin mainly bears shear loads and diffuses axial loads to ensure the stiffness of the entire compartment.

[0012] The propulsion tank is installed at the bottom of the rear sphere of the airlock.

[0013] The airlock chamber adopts a frame beam combined with an external grid reinforced metal shell structure.

[0014] The truss-type resource module includes a propulsion module, a large drive mechanism, a basic truss, and solar panels.

[0015] The spacecraft configuration with nested double load-bearing tubes consists of a non-airlock compartment with an exposed payload bay and an inner-nested airlock compartment.

[0016] The space station experimental module of this invention features a nested double-load-bearing tube configuration, employing a "reverse" approach. One force transmission path, during launch, proceeds from top to bottom through the truss, the load-bearing structure of the large drive mechanism, the exposed payload module frame beam + outer mesh reinforced skin structure, and the sealed experimental module frame beam + outer mesh reinforced shell structure, finally transmitting power to the launch vehicle adapter bracket via the forward short shell. The other force transmission path passes through the airlock module's outer mesh reinforced shell structure, the sealed experimental module's aft cone, and the sealed experimental module frame beam + outer mesh reinforced shell structure.

[0017] The beneficial effects achieved by this invention are as follows:

[0018] The system adopts a double-load-bearing tube nested configuration, with an exposed load chamber nested outside the airlock chamber, which increases the installation space for exposed loads. At the same time, a storage tank is installed at the bottom of the spherical structure behind the airlock chamber, which improves the structural utilization efficiency and the overall structural rigidity of the device. Attached Figure Description

[0019] The following embodiments and figures illustrate a configuration of a space station experimental module according to the present invention.

[0020] Figure 1 This is a schematic diagram of the space station experimental module and its configuration according to the present invention.

[0021] Figure 2 This is a schematic diagram of the exposed payload compartment configuration of the space station experimental module of the present invention.

[0022] Figure 3 This is a schematic diagram of the airlock configuration of the space station experimental module of the present invention.

[0023] Figure 4 This is a schematic diagram of the main power transmission route of the space station experimental module configuration of the present invention.

[0024] 1 is the sealed experimental chamber; 2 is the airlock chamber; 3 is the exposed load chamber; 4 is the large drive mechanism; 5 is the solar array; 6 is the basic truss; 7 is the truss resource chamber; 8 is the exposed load; 9 is the propulsion module; 10 is the propellant tank; 11 is the hatch; 12 is the front frame of the sealed experimental chamber; 13 is the front cone section of the sealed experimental chamber; 14 is the rear end of the sealed experimental chamber; 15 is the sealed experimental chamber itself; 16 is the bottom of the rear sphere.

[0025] Specific implementation methods

[0026] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0027] The embodiments of the present invention are described in detail below. These embodiments are implemented based on the technical solution of the present invention, and provide detailed implementation methods and specific operation processes. However, the scope of protection of the present invention is not limited to the following embodiments.

[0028] like Figure 1 As shown, the space station experimental module has a spacecraft configuration of nested double load-bearing cylinders, including a sealed experimental module 1, an exposed payload module 3, and a truss-type resource module 7 connected in sequence; the sealed experimental module 1 is equipped with a front end frame 12 for docking with the mechanism.

[0029] The sealed test chamber 1 includes a sealed test chamber body 15, a sealed test chamber front end 13, and a sealed test chamber rear end 14.

[0030] The sealed experimental chamber 15 adopts a frame beam combined with an external grid reinforced metal shell structure, and cabinets and equipment are installed inside.

[0031] The front end 13 of the sealed experimental chamber adopts a short metal shell structure with external mesh reinforcement for connection with the carrier adapter bracket; the rear end 14 of the sealed experimental chamber adopts a short metal shell structure with external mesh reinforcement for connection with the exposed load chamber 3.

[0032] The exposed load chamber 3 adopts a cylindrical non-sealed chamber configuration, including an airlock chamber 2, a non-airlock chamber, an airlock door 11, and an exposed load 8; the rear section of the airlock chamber 2 is nested inside the non-airlock chamber; the rear end of the airlock chamber 2 is provided with a rear ball bottom 16; the airlock door 11 is provided on the side of the airlock chamber 2; the exposed load 8 is installed on the outer wall of the non-airlock chamber.

[0033] The rear end 14 of the sealed experimental chamber is connected to the front end of the airlock chamber 2; the rear end of the non-airlock chamber is connected to the truss-type resource chamber 7.

[0034] The non-airlock compartment of the exposed load compartment 3 adopts a frame beam structure and an outer grid-reinforced skin structure; the frame beam structure is used to provide the force transmission skeleton of the entire compartment, bear axial loads and provide a certain stiffness; the grid-reinforced skin mainly bears shear loads and diffuses axial loads to ensure the stiffness of the entire compartment.

[0035] like Figure 3 As shown, the propulsion tank 10 is installed at the bottom 16 of the rear ball of the airlock 2.

[0036] The airlock 2 adopts a frame beam combined with an external grid reinforced metal shell structure.

[0037] The truss-type resource compartment 7 includes a propulsion module 9, a large drive mechanism 4, a basic truss 6, and a solar array 5; the large drive mechanism 4 is connected to the non-airlock compartment of the exposed load compartment 3.

[0038] The spacecraft configuration with nested double load-bearing tubes consists of a non-airlock compartment of the exposed payload compartment 3 and an inner nested airlock compartment 2.

[0039] like Figure 4 As shown, the space station experimental module of this invention has a double-bearing-tube nested configuration, employing a "reverse" approach. One force transmission path, during launch, proceeds from top to bottom through the truss resource module 7, the load-bearing structure of the large drive mechanism 4, the exposed payload module 3 frame beam + outer mesh reinforced skin structure, and the sealed experimental module 1 frame beam + outer mesh reinforced shell structure, finally transmitting the force to the launch vehicle adapter bracket via the front end 13 of the sealed experimental module. The other force transmission path passes through the airlock module 2 outer mesh reinforced shell structure, the rear end 14 of the sealed experimental module, and the sealed experimental module body 15 frame beam + outer mesh reinforced shell structure.

[0040] Although embodiments of the present invention have been described above in conjunction with the accompanying drawings, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive.

Claims

1. A configuration for a space station experimental module, characterized in that, The space station experimental module is configured as a spacecraft with two nested load-bearing tubes, including a sealed experimental module, an exposed payload module, and a truss-type resource module connected in sequence. The exposed load chamber adopts a cylindrical non-sealed chamber configuration, including an airlock chamber, a non-airlock chamber, an airlock door, and an exposed load. The rear section of the airlock is nested inside the non-airlock compartment; The airlock door is located on the side of the airlock; the exposed load is installed on the outer wall of the non-airlock compartment. The non-airlock compartment adopts a frame beam structure and an outer mesh reinforced skin structure; the frame beam structure is used to provide the force transmission skeleton of the entire compartment, bear axial loads and provide a certain stiffness; the outer mesh reinforced skin mainly bears shear loads and diffuses axial loads to ensure the stiffness of the entire compartment. The airlock chamber adopts a frame beam combined with an external grid reinforced metal shell structure.

2. The space station experimental module configuration as described in claim 1, characterized in that, The sealed test chamber includes a sealed test chamber body, a sealed test chamber front end, and a sealed test chamber rear end; the sealed test chamber front end is used to connect with the carrier adapter bracket; the sealed test chamber rear end is used to connect with the exposed load chamber.

3. The space station experimental module configuration as described in claim 2, characterized in that, The sealed experimental chamber adopts a frame beam combined with an external mesh reinforced metal shell structure, and the equipment is installed inside.

4. The space station experimental module configuration as described in claim 2, characterized in that, The front end of the sealed experimental chamber adopts a short metal shell structure reinforced with an external mesh; the rear end of the sealed experimental chamber adopts a short metal shell structure reinforced with an external mesh.

5. The space station experimental module configuration as described in claim 1, characterized in that, The airlock chamber is provided with a rear ball bottom at its rear end.

6. The space station experimental module configuration as described in claim 5, characterized in that, The propulsion tank is installed at the bottom of the rear sphere of the airlock.

7. The space station experimental module configuration as described in claim 1, characterized in that, The truss-type resource module includes a propulsion module, a large drive mechanism, a basic truss, and solar panels.

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