Space station experiment cabin structure

Abstract

The invention provides a space station experiment cabin and configuration, and the experiment cabin employs 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 used for being in butt joint with a mechanism, and the rear end of the sealed experiment cabin is connected with the exposed load cabin. The sealed experiment cabin provides a sealed space for astronauts to move, 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 an exposed load outside the mounting cabin and adopts a cylindrical non-sealed cabin body structure; an air brake cabin is arranged on the exposed load cabin and has an air brake function, and a door is opened on the side wall to support personnel and goods to enter and exit from the cabin; the truss type resource cabin comprises a propelling module, a large driving mechanism, a foundation truss and a solar wing. The truss type resource cabin is adopted, so that the structural weight is reduced, the envelope size is reduced, the structure is more compact, and a thought is provided for expansion and upgrading of space stations in China.

Description

Technical Field

[0001] The present invention relates to the field of overall design of spacecraft, and in particular to a configuration of a space station experimental cabin. Background Art

[0002] The space station is a large orbital spacecraft, generally composed of multiple modules and large structures. The space station is home to astronauts who live and work in orbit for a long time, and has many platform instruments and payloads in operation. It is an ideal platform for space payload exposure experiments. On the one hand, the experimental cabin needs to have the function of supporting personnel and cargo to enter and exit the experimental cabin, and on the other hand, it is necessary to install as many exposure experimental payloads as possible under certain constraints. The exposure payload should be as close as possible to the passage for personnel and cargo to enter and exit the cabin for easy repair and maintenance.

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

[0004] To sum up, how to adopt innovative designs to make the space station an excellent space payload exposure experiment platform, control the scale of the space station, and significantly reduce the construction period and cost of the space station; at the same time, centrally provide a large number of exposure payload workstations to obtain greater application benefits, is a difficult problem with important practical significance. Summary of the invention

[0005] The purpose of the present invention is to provide a space station experimental cabin configuration, which can provide astronaut activity space, support personnel and cargo to enter and exit the experimental cabin, and also provide a large number of exposed load workstations. The "reverse hitting" method is adopted to minimize the weight and size of the top. The "reverse hitting" method is: during launch, the sealed experimental cabin is at the bottom and bears all loads. After separation, the sealed experimental cabin is at the top of the flight and bears all flight forces.

[0006] In order to achieve the above-mentioned purpose, the present invention provides a space station experiment cabin configuration, which is a spacecraft configuration with double load-bearing cylinders nested, including a sealed experiment cabin, an exposed payload cabin, and a truss-type resource cabin connected in sequence; the exposed payload cabin adopts a cylindrical non-sealed cabin configuration, including an airlock cabin, a non-airlock cabin, an airlock cabin door and an exposed load; the rear section of the airlock cabin is nested inside the non-airlock cabin; the airlock cabin door is arranged on the side of the airlock cabin; the exposed load is installed on the outer side wall of the non-airlock cabin.

[0007] The sealed experiment cabin comprises a sealed experiment cabin body, a sealed experiment cabin front end, and a sealed experiment cabin rear end; the sealed experiment cabin front end is used to achieve connection with a carrier adapter bracket; the sealed experiment cabin rear end is used to achieve connection with an exposed load cabin.

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

[0009] The front end of the sealed test cabin adopts a metal short shell structure reinforced by an external grid; the rear end of the sealed test cabin adopts a metal short shell structure reinforced by an external grid.

[0010] The rear end of the airlock cabin is provided with a rear ball bottom.

[0011] The non-airlock cabin adopts a frame-beam structure and an external grid-reinforced skin structure; the frame-beam structure is used to provide a force-transmitting skeleton for the entire cabin, bear axial loads and provide a certain rigidity; the grid-reinforced skin mainly bears shear loads and diffuses axial loads to ensure the rigidity of the entire cabin.

[0012] A propulsion tank is installed at the bottom of the rear ball of the airlock cabin.

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

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

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

[0016] The space station experiment cabin configuration of the present invention is a double load-bearing tube nested configuration, which adopts a "reverse hitting" method. One force transmission path is from top to bottom in the launch state, through the truss, the load-bearing structure of the large drive mechanism, the exposed load cabin frame beam + external grid reinforced skin structure and the sealed experiment cabin frame beam + external grid reinforced shell structure, and finally transmitted to the launch vehicle adapter bracket through the front short shell. The other force transmission path is the grid reinforced shell structure outside the airlock cabin, the rear cone of the sealed experiment cabin and the frame beam + external grid reinforced shell structure of the sealed experiment cabin.

[0017] Beneficial effects achieved by the present invention:

[0018] A double load-bearing cylinder nested configuration is adopted, and an exposed load cabin is nested outside the airlock cabin, which increases the installation space for the exposed load. At the same time, a storage tank is installed at the rear spherical bottom of the airlock cabin, which improves the structural utilization efficiency and the structural stiffness of the whole device. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] A space station experimental module configuration of the present invention is given by the following embodiments and drawings.

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

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

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

[0023] Figure 4 This is a schematic diagram of the main force transmission route of the entire device of the space station experimental cabin configuration of the present invention.

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

[0025] Specific implementation methods

[0026] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0027] The following is a detailed description of an embodiment of the present invention. This embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation method and specific operation process are given, but the protection scope of the present invention is not limited to the following embodiment.

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

[0029] The sealed experiment cabin 1 comprises a sealed experiment cabin body 15 , a sealed experiment cabin front end 13 and a sealed experiment cabin rear end 14 .

[0030] The sealed experiment cabin body 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 test cabin adopts a metal short shell structure with external grid reinforcement, which is used to connect with the carrier adapter bracket; the rear end 14 of the sealed test cabin adopts a metal short shell structure with external grid reinforcement, which is used to connect with the exposed load cabin 3.

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

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

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

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

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

[0037] The truss-type resource cabin 7 includes a propulsion module 9, a large-scale driving mechanism 4, a basic truss 6 and a solar wing 5; the large-scale driving mechanism 4 is connected to the non-airlock cabin of the exposed payload cabin 3.

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

[0039] like Figure 4 As shown, the space station experiment cabin configuration of the present invention is a double load-bearing cylinder nested configuration, using a "reverse hitting" method, one force transmission path is from top to bottom in the launch state through the truss resource cabin 7, the load-bearing structure of the large drive mechanism 4, the exposed load cabin 3 frame beam + external grid reinforced skin structure and the sealed experiment cabin 1 frame beam + external grid reinforced shell structure, and finally transmitted to the launch vehicle adapter bracket through the front end 13 of the sealed experiment cabin. The other force transmission path is the outer grid reinforced shell structure of the airlock cabin 2, the rear end 14 of the sealed experiment cabin and the frame beam + outer grid reinforced shell structure of the sealed experiment cabin body 15.

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

Claims

1. A space station experimental cabin configuration, characterized in that: The space station experiment cabin configuration is a double-load-bearing-tube nested spacecraft configuration, including a sealed experiment cabin, an exposed payload cabin, and a truss-type resource cabin connected in sequence; The exposed load cabin adopts a cylindrical non-sealed cabin configuration, including an airlock cabin, a non-airlock cabin, an airlock cabin door and an exposed load; The rear section of the airlock cabin is nested inside the non-airlock cabin; The airlock door is arranged on the side of the airlock; and the exposed load is installed on the outer side wall of the non-airlock.

2. A space station experimental cabin configuration as claimed in claim 1, characterized in that: The sealed experiment cabin comprises a sealed experiment cabin body, a sealed experiment cabin front end, and a sealed experiment cabin rear end; the sealed experiment cabin front end is used to achieve connection with a carrier adapter bracket; the sealed experiment cabin rear end is used to achieve connection with an exposed load cabin.

3. A space station experimental cabin configuration as claimed in claim 2, characterized in that: The sealed experimental cabin body adopts a frame beam combined with an external grid reinforced metal shell structure, and cabinets and equipment are installed inside.

4. A space station experimental cabin configuration as claimed in claim 2, characterized in that: The front end of the sealed test cabin adopts a metal short shell structure reinforced by an external grid; the rear end of the sealed test cabin adopts a metal short shell structure reinforced by an external grid.

5. A space station experimental module configuration as claimed in claim 1, characterized in that: The rear end of the airlock cabin is provided with a rear ball bottom.

6. A space station experimental module configuration as claimed in claim 1, characterized in that: The non-airlock cabin adopts a frame-beam structure and an external grid-reinforced skin structure; the frame-beam structure is used to provide a force-transmitting skeleton for the entire cabin, bear axial loads and provide a certain rigidity; the grid-reinforced skin mainly bears shear loads and diffuses axial loads to ensure the rigidity of the entire cabin.

7. A space station experimental module configuration as claimed in claim 5, characterized in that: A propulsion tank is installed at the bottom of the rear ball of the airlock cabin.

8. A space station experimental module configuration as claimed in claim 1 or 5, characterized in that: The airlock cabin adopts a frame beam combined with an external grid reinforced metal shell structure.

9. A space station experimental module configuration as claimed in claim 1, characterized in that: The truss-type resource cabin includes a propulsion module, a large drive mechanism, a basic truss and a solar wing.

10. A space station experimental module configuration as claimed in claim 1, characterized in that: The double-load-bearing-tube-nested spacecraft configuration consists of a non-airlock cabin with an exposed payload cabin and an inner-nested airlock cabin.

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