Spacecraft assembly operations platform

Abstract

The application relates to the technical field of spacecraft assembly, in particular to a spacecraft assembly operation platform, which comprises a base frame, a support frame, a lifting mechanism and a flexible envelope mechanism, the support frame is arranged on the base frame and comprises at least one support frame which are sequentially connected in the vertical direction; the lifting mechanism is arranged in each support frame and is used for adjusting the height of each support frame; the flexible envelope mechanism is arranged between the base frame and the adjacent support frame and between the adjacent two layers of support frames, and comprises a plurality of envelope units, each envelope unit can move along a preset direction to adjust the edge shape of an envelope area formed by the flexible envelope mechanism. The application can adjust the height of the whole operation platform and the edge shape of the envelope area, thereby meeting the multiple adjustment process equipment of various spacecraft out-of-vehicle assembly and test experiments, and realizing the universal design suitable for various spacecraft and different working condition test requirements.

Description

Technical Field

[0001] This application relates to the field of spacecraft assembly technology, and in particular to a spacecraft assembly operation platform. Background Technology

[0002] Large spacecraft operation platforms are primarily used for operations at heights exceeding five meters. They are indispensable ground mechanical support equipment (MGSE) in the spacecraft assembly process, typically used for vertical assembly of large spacecraft compartments and various tests and experiments. For example, the Shenzhou spacecraft's assembly and testing utilizes a large assembly operation platform. During spacecraft assembly, the components to be installed are complex and expensive. The platform must not only meet the operators' requirements for comfort and safety during the assembly process, but also ensure the spacecraft's positioning at all angles and altitudes to avoid blind spots. Furthermore, it must consider product docking, lifting, and transportation.

[0003] Due to the high vertical placement height of large spacecraft, the assembly and operation platform has multiple workbenches, mainly composed of a fixed platform, platform supports, stairs, and guardrails. Operators stand on the platform to perform external assembly operations on the spacecraft. However, the operation platform has poor adaptability, only meeting the requirements of one type of spacecraft under one operating condition. If the test conditions need to be changed, redesign and disassembly are required. Applying multiple operating conditions is cumbersome and labor-intensive. At the same time, it cannot achieve universality for more spacecraft models, increasing the production cost of spacecraft. In addition, large operation platforms are inconvenient to move and adjust, and occupy a large amount of factory space after assembly. With the development trend of functional integration, universality, and intelligence of large spacecraft tooling equipment, there is an urgent need to develop a multifunctional, size-adjustable large spacecraft operation platform. Summary of the Invention

[0004] This application provides a spacecraft assembly and operation platform to solve the problem that existing operation platforms have poor adaptability, can only meet the requirements of one type of spacecraft under one working condition, and cannot achieve universality for more spacecraft models.

[0005] This application provides a spacecraft assembly and operation platform, including:

[0006] Basic framework;

[0007] A support frame, set on the base frame, including at least one, the support frames being connected sequentially in the vertical direction;

[0008] Lifting mechanisms are installed in each support frame to adjust the height of each support frame;

[0009] The flexible envelope mechanism is respectively set between the base frame and the adjacent support frame, and between two adjacent support frames. It includes multiple envelope units, each of which can move along a preset direction to adjust the edge shape of the envelope area formed by the flexible envelope mechanism.

[0010] In one possible design, the basic framework includes:

[0011] First substrate;

[0012] The second substrate is disposed above the first substrate;

[0013] The base column is vertically set, with its lower end connected to the first substrate and its upper end connected to the second substrate. The base column has a cavity filled with counterweights.

[0014] In one possible design, the support frame includes:

[0015] Base plate;

[0016] The top plate is located above the bottom plate;

[0017] The column is set vertically, with its upper end connected to the top plate and its lower end connected to the lifting mechanism. Driven by the lifting mechanism, it can push the top plate vertically to adjust the vertical distance between the bottom plate and the top plate.

[0018] In one possible design, the lifting mechanism includes a driver, a reversing reducer, and a screw jack. The output end of the driver is connected to the reversing reducer, the output end of the reversing reducer is connected to the screw jack, and the output end of the screw jack is connected to the lower end of the column.

[0019] In one possible design, the first substrate, the second substrate, the bottom plate, and the top plate are all annular plates. The circumferential direction of the annular plates is the first direction, and the radial direction of the annular plates is the second direction. Envelope units are arranged on the second substrate and / or the top plate along the first direction, and each envelope unit can move along the second direction to adjust the edge shape of the formed envelope region.

[0020] In one possible design, the envelope unit includes:

[0021] The guide rod is slidably disposed on the second base plate and / or the top plate, and its own length direction is parallel to the second direction;

[0022] An extension plate is mounted on the guide rod;

[0023] The first support rod is arranged at intervals along the length of the guide rod on one side of the guide rod and is rotatably connected to the guide rod. The first support rod has an elongated hole.

[0024] The second support rod is arranged at intervals along the length of the guide rod on the other side of the guide rod and is rotatably connected to the guide rod. The second support rod is provided with a pin, which slides with the inner wall of the corresponding elongated hole to make the adjacent first support rod and the second support rod movably connected.

[0025] A drive assembly, disposed on the second base plate and / or the top plate, is connected to the guide rod and is used to drive the guide rod to move along its own length.

[0026] In one possible design, the heights of two adjacent extension plates are different so that an overlapping area is formed between the two adjacent extension plates.

[0027] In one possible design, the height of the extension plate gradually increases or decreases along the first direction.

[0028] In one possible design, the first substrate, the second substrate, the bottom plate, and the top plate each include multiple sub-modules, and adjacent sub-modules are connected by a latch. The platform also includes a transfer seat located below the first substrate, which is used to transfer the corresponding sub-modules.

[0029] In one possible design, a folding ladder is provided on the first substrate and the bottom plate, and a manhole corresponding to the folding ladder is provided on the second substrate, the bottom plate, and the top plate.

[0030] The beneficial effects of this application are as follows:

[0031] The spacecraft assembly operation platform of this application can adjust the overall height of the operation platform by setting a lifting mechanism in the support frame to adjust the height of the support frame; by setting a flexible envelope mechanism, the edge shape of the envelope area formed by the flexible envelope mechanism can be adjusted by adjusting the corresponding envelope unit, thereby meeting the multiple adjustment process equipment for the external assembly and testing of various shaped spacecraft, realizing the universal design applicable to various spacecraft and the testing needs under different working conditions, improving the flexibility, applicability and reliability of large spacecraft equipment assembly, and greatly improving the assembly efficiency of spacecraft. Attached Figure Description

[0032] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0033] Figure 1 A schematic diagram of the structure of the spacecraft assembly and operation platform provided in the embodiments of this application;

[0034] Figure 2A schematic diagram of the basic framework of the spacecraft assembly and operation platform provided in the embodiments of this application;

[0035] Figure 3 A schematic diagram of the support frame of the spacecraft assembly and operation platform provided in the embodiments of this application;

[0036] Figure 4 A schematic diagram of the lifting mechanism and flexible envelope mechanism of the spacecraft assembly and operation platform provided in the embodiments of this application;

[0037] Figure 5 A schematic diagram of the envelope unit of the spacecraft assembly and operation platform provided in the embodiments of this application;

[0038] Figure 6 A schematic diagram showing the disassembled structure of multiple sub-modules of the spacecraft assembly and operation platform provided in this application embodiment;

[0039] Figure 7 A schematic diagram of the rotation process of the transfer seat of the spacecraft assembly and operation platform provided in the embodiments of this application.

[0040] Figure label:

[0041] 100. Basic frame; 110. First base plate; 120. Second base plate; 130. Base column; 200. Support frame; 210. Base plate; 220. Top plate; 230. Column; 300. Lifting mechanism; 310. Driver; 320. Reversing reducer; 330. Screw jack; 400. Flexible envelope mechanism; 410. Envelope unit; 411. Guide rod; 412. Extension plate; 413. First support rod; 414. Second support rod; 415. Drive assembly; 4151. Gear; 4152. Rack; 500. Submodule; 600. Transfer seat; 700. AGV mobile lifting drive vehicle; 800. Folding ladder; 900. Manhole. Detailed Implementation

[0042] The technical solutions of this application will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0043] The following is combined with Figures 1-7 This describes the spacecraft assembly and operation platform provided in the embodiments of this application.

[0044] Reference Figure 1As shown, the spacecraft assembly and operation platform provided in this embodiment includes a base frame 100, a support frame 200, a lifting mechanism 300, and a flexible envelope mechanism 400. The base frame 100 is located at the bottom and is the main load-bearing structure. The support frames 200 are disposed on the base frame 100, including at least one, and the support frames 200 are connected sequentially in the vertical direction. The lifting mechanisms 300 are respectively disposed in each support frame 200, and are used to adjust the height of each support frame 200, thereby adjusting the height of each layer of the operation platform. The flexible envelope mechanism 400 is disposed between the base frame 100 and the adjacent support frame 200, and between two adjacent layers of support frames 200. The flexible envelope mechanism 400 includes multiple envelope units 410, each of which can move along a preset direction to adjust the edge shape of the envelope area formed by the flexible envelope mechanism 400. This satisfies the multiple adjustment process equipment for the external assembly and testing of various shaped spacecraft, realizes the general design applicable to various spacecraft and the testing requirements under different working conditions, improves the flexibility, applicability and reliability of large spacecraft equipment assembly, and greatly improves the assembly efficiency of spacecraft.

[0045] Reference Figure 2 As shown, in some specific embodiments, the base frame 100 includes a first substrate 110, a second substrate 120, and a base pillar 130. The second substrate 120 is located above the first substrate 110, and the base pillar 130 is vertically disposed between the first substrate 110 and the second substrate 120. The lower end of the base pillar 130 is connected to the first substrate 110, and the upper end is connected to the second substrate 120. To ensure the stability of the overall platform, a cavity is provided inside the base pillar 130, and the cavity is filled with counterweights. Specifically, lead is poured into the cavity to increase the counterweight of the bottom base frame 100 and ensure the stability and reliability of the bottom base frame 100.

[0046] Reference Figure 3 , Figure 4As shown, in some specific embodiments, there are two support frames 200, which are connected sequentially in the vertical direction. Each support frame 200 includes a base plate 210, a top plate 220, and a column 230. Guardrails are installed on the edges of the base plate 210, and the top plate 220 is located above the base plate 210. The column 230 is vertically arranged, with its upper end connected to the top plate 220 and its lower end connected to the lifting mechanism 300. Driven by the lifting mechanism 300, the column 230 can push the top plate 220 in the vertical direction to adjust the vertical distance between the base plate 210 and the top plate 220. Specifically, the lifting mechanism 300 includes a driver 310, a reversing reducer 320, and a screw jack 330. The driver 310 uses a drive motor, the output of which is connected to the reversing reducer 320. The output of the reversing reducer 320 is also connected to the screw jack 330. The output of the screw jack 330 is connected to the lower end of the column 230 via a coupling. Thus, the driver 310 drives the output of the screw jack 330 to move vertically, which in turn moves the column 230 vertically. This, in turn, moves the top plate 220 vertically, adjusting its position and thus its height.

[0047] In some specific embodiments, the first substrate 110, the second substrate 120, the bottom plate 210, and the top plate 220 are all annular plates, with the circumferential direction of the annular plates being the first direction and the radial direction of the annular plates being the second direction. In this embodiment, an envelope unit 410 is respectively provided on the second substrate 120 and the top plate 220. Specifically, the envelope units 410 are arranged along the first direction on the second substrate 120 and the top plate 220, and each envelope unit 410 can be moved along the second direction to adjust the edge shape of the formed envelope area.

[0048] Reference Figure 4 , Figure 5As shown, in some specific embodiments, each envelope unit 410 includes a guide rod 411, an extension plate 412, a first support rod 413, a second support rod 414, and a drive assembly 415. Multiple limiting seats are respectively provided on the second base plate 120 and the top plate 220. The outer wall of each guide rod 411 slides in cooperation with the inner wall of the corresponding limiting seat. The length direction of the guide rod 411 is consistent with the radial direction of the annular plate. The inner end of the guide rod 411 extends out of the inner side of the annular plate and is fixedly mounted with the extension plate 412. The guide rod 411 can slide on the inner wall of the limiting seat, thereby driving the corresponding extension plate 412 to move radially. Thus, by pushing the corresponding guide rod 411 to move along its length, the corresponding extension plate 412 is moved radially, thereby adjusting the position of each extension plate 412 so that all extension plates 412 can be combined to form envelope areas of different shapes. The edges of all extension plates 412 are the edges of the envelope areas. By adjusting the edge shape of the envelope area formed by the flexible envelope mechanism 400, multiple adjustment process equipment for the external assembly and testing of various spacecraft shapes can be met, realizing the universal design applicable to various spacecraft and the testing requirements under different working conditions.

[0049] First support rods 413 are spaced apart along the length of guide rods 411 on one side of guide rods 411. The first support rods 413 and guide rods 411 are rotatably connected via a pivot. Each first support rod 413 has an elongated hole along its length. Second support rods 414 are spaced apart along the length of guide rods 411 on the other side of guide rods 411. One end of each second support rod 414 is rotatably connected to the guide rod 411 via a pivot, and the other end of each second support rod 414 has a pin. The pin slides against the inner wall of the corresponding elongated hole, allowing adjacent first support rods 413 and second support rods 414 to be movably connected. In this way, all guide rods 411 and extension plates 412 form a single unit, strengthening the overall support of the extended platform, ensuring personnel safety, and forming a complete platform structure after the cabin access passage is closed, making it convenient and reliable to use. At the same time, it ensures that each guide rod 411 and its corresponding extension plate 412 can be adjusted individually, which has high safety and flexibility, thereby achieving the purpose of flexibly adjusting the edge of the envelope area so as to meet the requirements of different spacecraft assembly and testing conditions.

[0050] Reference Figure 4As shown, multiple sets of driving components 415 are respectively provided on the second base plate 120 and the top plate 220. Each set of driving components 415 is connected to a corresponding guide rod 411 and is used to drive the guide rod 411 to move along its own length direction. In some embodiments, the driving component 415 includes a gear 4151 and a rack 4152. The rack 4152 is welded to the side wall of the guide rod 411. The length direction of the rack 4152 is parallel to the guide rod 411. The gear 4151 is rotatably mounted on the second base plate 120 and the top plate 220 through a sliding bearing. The gear 4151 and the rack 4152 mesh with each other. A through hole is provided on the top plate 220. The axle of the gear 4151 passes through the corresponding through hole and is fitted with a handwheel. By rotating the handwheel, the corresponding rack 4152 can be moved, thereby driving the corresponding guide rod 411 and extension plate 412 to move radially.

[0051] Reference Figure 4 As shown, the heights of adjacent extension plates 412 are different to create an overlapping area between them. This ensures that there are no gaps in the envelope formed by all the extension plates 412, thus enhancing safety. In one embodiment, the height of the extension plates 412 gradually increases or decreases along the circumference of the second substrate 120 / top plate 220, for example, gradually increasing in a clockwise direction. This distributes the stress on the local extension plates 412, allowing the local stress to be evenly dispersed circumferentially, improving the stability and load-bearing capacity of the extension plates 412. In some embodiments, the extension plates 412 include a first extension plate 412 and a second extension plate 412, which are welded or bolted to the upper and lower sides of the guide rod 411, respectively. Reinforcing ribs are provided between the first and second extension plates 412, which helps to increase the overall load-bearing capacity of the extension plates 412.

[0052] Reference Figure 6 As shown, in some specific embodiments, the first substrate 110, the second substrate 120, the bottom plate 210, and the top plate 220 each include multiple sub-modules 500, for example, six sub-modules 500, with adjacent sub-modules 500 connected by latches. The platform also includes a transfer seat 600 and an AGV mobile lifting drive vehicle 700. There are also six transfer seats, located below the first substrate 110, with each sub-module 500 correspondingly positioned on its respective transfer seat 600. The AGV mobile lifting drive vehicle 700 moves the transfer seat 600 and the corresponding sub-modules 500, facilitating transportation and temporary parking while reducing the space occupied.

[0053] Reference Figure 1As shown, in some embodiments, folding ladders 800 are respectively provided on the first substrate 110 and the bottom plate 210, and manholes 900 corresponding to the folding ladders 800 are respectively provided on the second substrate 120, the bottom plate 210, and the top plate 220. This facilitates operation by personnel on the platform at different heights and in different areas.

[0054] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0055] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0056] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between components; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0057] In this application, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0058] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A spacecraft assembly operations platform, characterized by, The utility model relates to a flexible package platform, including: a base frame; a plurality of support frames arranged on the base frame and connected in sequence in the vertical direction; a lifting mechanism arranged in each support frame for adjusting the height of each support frame; a flexible envelope mechanism arranged between the base frame and adjacent support frames and between two adjacent support frames, including a plurality of envelope units, each envelope unit being capable of moving in a predetermined direction to adjust the edge shape of the envelope area formed by the flexible envelope mechanism; the base frame includes: a first base plate; a second base plate arranged above the first base plate; a base column arranged vertically, with a lower end connected to the first base plate and an upper end connected to the second base plate, the base column having a cavity therein filled with a counterweight; each support frame includes: a bottom plate; a top plate arranged above the bottom plate; a vertical column arranged vertically, with an upper end connected to the top plate and a lower end connected to the lifting mechanism, capable of pushing the top plate in the vertical direction under the drive of the lifting mechanism to adjust the vertical distance between the bottom plate and the top plate.

2. The spacecraft assembly operations platform of claim 1, wherein: The lifting mechanism includes a driver, a reversing reducer, and a screw elevator, the output end of the driver being in transmission connection with the reversing reducer, the output end of the reversing reducer being in transmission connection with the screw elevator, and the output end of the screw elevator being connected to the lower end of the vertical column.

3. The spacecraft assembly operations platform of claim 1, wherein: The first base plate, the second base plate, the bottom plate, and the top plate are each annular plates, the circumferential direction of the annular plate being a first direction, the radial direction of the annular plate being a second direction, the envelope units being arranged on the second base plate and / or the top plate in the first direction, and each envelope unit being capable of moving in the second direction to adjust the edge shape of the envelope area formed.

4. The spacecraft assembly operations platform of claim 3, wherein, The envelope unit includes: a guide rod slidingly arranged on the second base plate and / or the top plate, with its length direction parallel to the second direction; an extension plate arranged on the guide rod; a first support rod arranged on one side of the guide rod in the length direction of the guide rod, in rotational connection with the guide rod, and having a long hole formed therein; a second support rod arranged on the other side of the guide rod in the length direction of the guide rod, in rotational connection with the guide rod, and having a pin shaft arranged thereon, the pin shaft being in sliding connection with the inner wall of the corresponding long hole to movably connect adjacent first support rods and second support rods; a driving assembly arranged on the second base plate and / or the top plate, in connection with the guide rod, for driving the guide rod to move in its length direction.

5. The spacecraft assembly operations platform of claim 4, wherein: The heights of adjacent extension plates are different to form an overlapping area between adjacent extension plates.

6. The spacecraft assembly operations platform of claim 5, wherein: In the first direction, the heights of the extension plates gradually increase or decrease.

7. The spacecraft assembly operations platform of any of claims 1-6, wherein: The first base plate, the second base plate, the bottom plate, and the top plate each include a plurality of sub-modules, adjacent two sub-modules being connected by a lock catch, and the platform further includes a transfer seat arranged below the first base plate for transferring the corresponding sub-modules.

8. The spacecraft final assembly operations platform of any of claims 1-6, wherein: The first substrate, the bottom plate are respectively provided with folding ladder, the second substrate, the bottom plate, the top plate are respectively provided with manhole corresponding with the folding ladder.

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