A system and method for closing a flat box satellite automated production line

Abstract

The application discloses a cabin combining system and method of a flat box type satellite automatic production line, adopts a vertical cabin combining mode of a clam mode, is matched with a stepless overturning structure of a satellite cabin plate of a Z mode, is adapted to multi-attitude operation, and solves the core problems of a fixed attitude of traditional cabin combining and inconvenient operation. Moreover, a special clamp and a precise track system of the satellite cabin plate of the Z mode are configured, precise movement and positioning of the cabin plate are realized, and the core problems of low precision and poor stability of traditional cabin combining are solved. In addition, a whole-process operation scheme of two-person cooperation is provided, a tool linkage process is integrated, a cabin combining period is greatly shortened, and the core problems of low efficiency and high labor cost of traditional cabin combining are solved.

Description

Technical Field

[0001] This invention relates to the field of satellite manufacturing, and in particular to a hull-mounted system and method for an automated production line of flat-panel satellites. Background Technology

[0002] With the continued acceleration of the large-scale deployment of low-Earth orbit (LEO) satellite constellations, the commercial space industry is experiencing explosive growth, and the satellite manufacturing industry is rapidly transforming from a traditional single-piece customization model to a standardized, mass production model. Assembling, integrating, and testing (AIT), as the core link in the entire satellite manufacturing process, directly determines the level of cost control and on-orbit deployment speed of LEO satellite constellations through its operational efficiency and precision, and is one of the key factors restricting the large-scale development of the commercial space industry.

[0003] The satellite assembly process is a core and critical step in the AIT (Autonomous In-Service) process. This process requires the sequential completion of a series of complex operations, including panel transfer, precise attitude adjustment, high-precision docking of the modules, structural fastening, and system integration. The maturity and stability of satellite assembly technology directly affect the mechanical strength of the satellite structure, its on-orbit reliability, and its long-term service life. It also has a significant impact on optimizing and controlling satellite manufacturing costs, serving as a core technological support for ensuring the quality and efficiency of mass-produced satellites.

[0004] Currently, domestic and international satellite docking technology has initially transitioned from purely manual operation to semi-automated operation. However, significant technical deficiencies remain in areas such as adaptability to mass production, stability of docking accuracy, and process efficiency. Specifically, existing technologies struggle to meet the high-efficiency collaborative requirements of mass production of hundreds of satellite constellations. Docking accuracy is susceptible to fluctuations due to environmental factors and operational errors, and insufficient continuity in process connections leads to low process efficiency. This fails to meet the core demands of the commercial aerospace industry for low-cost, high-reliability, and large-scale satellite production, thus hindering the large-scale deployment of low-Earth orbit satellite constellations.

[0005] Therefore, there is an urgent need to develop a highly automated and high-precision satellite assembly technology suitable for the mass production of hundreds of satellites. By constructing a multi-process collaborative control system, optimizing attitude adjustment and docking positioning mechanisms, and improving environmental interference resistance, a highly automated closed-loop operation of cabin transfer, attitude adjustment, precise docking, and fastening integration can be achieved. This will fundamentally solve the core defects of existing technologies in terms of mass production adaptability, precision stability, and process efficiency, meet the core demands of the commercial aerospace industry for low-cost, high-reliability, and large-scale satellite production, and provide key technical support for the efficient deployment of low-Earth orbit satellite constellations and the continuous upgrading of the commercial aerospace industry. Summary of the Invention

[0006] Therefore, the present invention provides a capsule assembly system and method for a flat-panel box-type automated satellite production line to solve the problems of low precision, insufficient stability and low efficiency of traditional capsule assembly.

[0007] This invention provides a pod-combining system for an automated production line of flat-panel box-type satellites, comprising: Satellite panels, including +Z and -Z satellite panels, are configured to achieve clamshell vertical closure via stepless flipping; ±Z satellite module clamps are configured to clamp and rotate the satellite module, including +Z satellite module clamps and -Z satellite module clamps, and are equipped with module positioning pins. The module assembly is completed by inserting and pulling the module positioning pins with the corresponding positioning pin holes. ±Z satellite panel flip-over trays are configured to carry satellite panels, including +Z satellite panel flip-over trays and -Z satellite panel flip-over trays; The clamp lifting device is configured to adjust the height of the ±Z satellite panel clamp.

[0008] In one embodiment of the present invention, the +Z satellite module clamp includes: The flip frame is configured as a frame structure to provide support for the flipping of the satellite module. The frame rotation axis is configured as a pivot point for rotating the flip frame, enabling the satellite panel to flip. A locking interface device, configured to connect the +Z satellite panel clamp to the +Z satellite panel, includes: A locking cylinder is configured to drive the extension and retraction of a locating pin to achieve locking and fixation; Positioning pin.

[0009] In one embodiment of the present invention, the -Z satellite panel clamp includes: The Z-axis rotation axis is configured to adjust the Z-axis swing angle of the Z-satellite panel; The compartment positioning pin is configured to achieve the closing of the ±Z compartment panels; -Z satellite panel fixture positioning pin, which is configured to connect the -Z satellite panel fixture and the grid frame lifting point tooling; The grid-frame lifting point fixture is configured to lift and fix the -Z satellite module to connect the -Z satellite module clamp to the -Z satellite module; The lifting ring, configured to achieve the lifting and transfer of the -Z satellite module, is connected to the lattice frame lifting point tooling; The X-axis rotation axis is configured as the -Z satellite panel flipping fulcrum to adjust the panel attitude; -Z satellite panel clamp locking cylinder, which is configured to drive the extension and retraction of the -Z satellite panel clamp positioning pin to achieve locking and fixation; -Z Satellite Cabin Panel Fixture Positioning Pin.

[0010] In one embodiment of the present invention, the clamp lifting device includes a +Z satellite cabin clamp lifting device and a -Z satellite cabin clamp lifting device, wherein the -Z satellite cabin clamp lifting device includes: An electric hoist is configured to drive the Z-satellite cabin panel to tilt and lift to adjust its attitude; An electric hoist controller, configured to drive an electric hoist; -Z satellite panel clamp controller, which is configured to control the lifting and lowering of the -Z satellite panel clamp and the extension and retraction of the locking cylinder; -Z satellite panel clamp lifting mechanism handle, which is configured to finely adjust the height of the -Z satellite panel clamp manually.

[0011] In one embodiment of the invention, a fixture transfer vehicle is also included, which is configured to carry the +Z satellite module fixture and transfer it between workstations along a track.

[0012] In one embodiment of the invention, a flip-pallet transfer vehicle is also included, which is configured to carry and transport ±Z satellite panel flip-pallets and satellite panels.

[0013] In one embodiment of the present invention, the satellite cabin panel and the ±Z satellite cabin panel flip tray are connected by screws.

[0014] In one embodiment of the present invention, the -Z satellite module and the grid frame lifting point fixture are connected by screws.

[0015] In one embodiment of the present invention, the lifting ring is connected to the lifting point fixture of the grid frame by screws.

[0016] This invention provides a method for assembling compartments in an automated production line for flat-panel satellites, comprising: The +Z satellite panel clamp is lifted using the +Z satellite panel clamp lifting device; The +Z satellite panel fixture is transferred to the +Z satellite panel area by a fixture transfer vehicle, and then the +Z satellite panel fixture is lowered to the predetermined position by a +Z satellite panel fixture lifting device. The +Z satellite compartment panel is combined with the +Z satellite compartment panel clamp by extending the positioning pin through the locking interface device, and the connecting screws of the +Z satellite compartment panel and the +Z satellite compartment panel flip tray are removed. The +Z satellite module is transferred to the merging position using a clamp transfer vehicle; Operate the handle of the Z-satellite panel clamp lifting mechanism to raise the Z-satellite panel clamp to the predetermined height; The assembly of the -Z satellite panel and the grid frame lifting point tooling is transported to the designated position of the merging station by a -Z satellite panel flipping pallet. Operate the -Z satellite panel clamp controller to lower the -Z satellite panel clamp, engage the -Z satellite panel clamp positioning pin with the positioning pin hole at the corresponding position on the -Z flip tray, and after it is in place, operate the -Z satellite panel clamp locking cylinder through the -Z satellite panel clamp controller to extend the -Z satellite panel clamp positioning pin, and combine the -Z satellite panel clamp with the grid frame lifting point fixture; The lifting eye is combined with the grid frame lifting point fixture by screws, and the connecting screws between the grid frame lifting point fixture and the -Z satellite cabin flipping tray are removed. The electric hoist controller raises the chain to the predetermined height, and the -Z satellite compartment panel is lifted to the predetermined height using the handle of the -Z satellite compartment panel clamp lifting mechanism. The -Z satellite compartment panel is then removed and the pallet is flipped. Using the electric hoist controller, the -Z satellite cabin panel is rotated along the X-axis, changing it from a horizontal to a vertical position. Push the handle of the -Z satellite panel clamp lifting mechanism to move the -Z satellite panel along the Z direction to approach the +Z satellite panel. Adjust the satellite panel to the predetermined tilt angle through the electric hoist controller and the +Z satellite panel clamp. The angle of the satellite module is adjusted to 90 degrees using the ±Z satellite module clamps; Operate the -Z satellite panel clamp handle to bring the -Z satellite panel closer to the +Z satellite panel; As the -Z satellite module approaches the +Z satellite module, the Z-axis swing angle of the -Z satellite module is adjusted by the Z-axis rotation axis on the upper part of the -Z satellite module clamp. The closing action of the satellite compartment is completed by engaging the closing positioning pin of the -Z satellite compartment clamp with the corresponding positioning pin hole on the +Z satellite compartment clamp. Install the clamping screws.

[0017] In one embodiment of the present invention, it further includes: Remove the screws from the lattice frame lifting point fixture on one side of the -Z satellite panel, operate the -Z satellite panel clamp handle to move the lattice frame lifting point fixture away, and disassemble the lattice frame lifting point fixture; Transport the hoisting equipment for the grid frame to the storage area; Rotate the Z-shaped satellite panel clamp to bring the entire satellite to a horizontal position; Install the stacking columns, connect the entire satellite to the transport vehicle, remove the connecting screws between the +Z satellite panel and the +Z satellite panel clamp, lift the +Z satellite panel clamp to the predetermined height, and complete the satellite rollout.

[0018] The present invention has the following beneficial effects: (1) The ±Z satellite modules can be rotated steplessly, which makes it convenient for operators to perform satellite assembly before merging and screw installation after merging. (2) Only two operators are needed for the pre-combination preparation, the combination action and the unloading of the cabin panel after combination, which improves the efficiency of combination. (3) The ±Z satellite panel clamp moves with the help of a precision track system. The closing action uses the positioning pins of the ±Z satellite panel clamp to achieve precise closing of the panels, which improves the accuracy of the closing action. Attached Figure Description

[0019] Figure 1 A structural diagram of a satellite module merging system according to an embodiment of the present invention is shown; Figure 2 A schematic diagram of the +Z satellite module clamp structure is shown in one embodiment of the present invention; Figure 3 A schematic diagram of the Z-satellite panel clamp structure in one embodiment of the present invention is shown; Figure 4 A schematic diagram of the Z-satellite cabin clamp lifting device structure is shown in one embodiment of the present invention; Figure 5 A schematic diagram of the +Z satellite cabin clamp lifting device structure is shown in one embodiment of the present invention; Figure 6 A schematic diagram of the +Z satellite cabin panel clamp transfer vehicle structure is shown in one embodiment of the present invention; Figure 7 A schematic diagram of the +Z satellite cabin flip-up tray structure in one embodiment of the present invention is shown; Figure 8 A schematic diagram of the Z-satellite cabin flip-up tray structure in one embodiment of the present invention is shown; Figure 9 A schematic diagram of a flip-over pallet transfer vehicle structure is shown in one embodiment of the present invention. Detailed Implementation

[0020] In the following description, the invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments may be practiced without one or more specific details or with other alternatives and / or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure the inventive points of the invention. Similarly, for illustrative purposes, specific quantities, materials, and configurations are set forth to provide a comprehensive understanding of embodiments of the invention. However, the invention is not limited to these specific details.

[0021] In this invention, the various embodiments are merely intended to illustrate the solutions of the invention and should not be construed as limiting.

[0022] In this specification, references to "an embodiment" or "this embodiment" mean that a particular feature, structure, or characteristic described in connection with that embodiment is included in at least one embodiment of the invention. The phrase "in one embodiment" appearing throughout this specification does not necessarily refer to the same embodiment in all instances.

[0023] Furthermore, the numbering of the steps in the methods of the present invention does not limit the execution order of the method steps. Unless otherwise specified, the method steps may be executed in different orders.

[0024] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0025] Figure 1 A structural diagram of a satellite module closure system according to an embodiment of the present invention is shown.

[0026] like Figure 1 As shown, in this embodiment, the satellite module closure system includes: Satellite panels, including +Z and -Z satellite panels, are configured to achieve clamshell vertical closure via stepless flipping.

[0027] ±Z satellite module clamp 200, configured to clamp and rotate the satellite module, includes +Z satellite module clamp 210 and -Z satellite module clamp 220, and is equipped with module positioning pin 7. The module is assembled by inserting and pulling the module positioning pin 7 with the corresponding positioning pin hole.

[0028] like Figure 2 As shown, the +Z satellite panel clamp 210 includes: Flip frame 1, which is configured as a frame structure to provide support for the flipping of the satellite module; The frame rotation axis 2 is configured as the rotation fulcrum of the flipping frame 1 to realize the flipping action of the satellite panel; The locking interface device 3, configured to connect the +Z satellite panel clamp 210 to the +Z satellite panel, includes: Locking cylinder 4 is configured to drive the locating pin 5 to extend and retract to achieve locking and fixation; Positioning pin 5.

[0029] like Figure 3 As shown, the -Z satellite panel clamp 220 includes: Z-axis rotation axis 6, which is configured to adjust the Z-axis swing angle of the Z-satellite panel; The cabin positioning pin 7 is configured to achieve the closing of the ±Z cabin panels; -Z satellite panel clamp positioning pin 8, which is configured to connect -Z satellite panel clamp 220 and grid frame lifting point tooling 9; The grid-frame lifting point fixture 9 is configured to lift and fix the -Z satellite module to connect the -Z satellite module clamp 220 and the -Z satellite module; The lifting ring 10, which is configured to realize the lifting and transfer of the -Z satellite panel, is connected to the grid frame lifting point fixture 9 by screws; X-axis rotation 11 is configured as the -Z satellite panel flipping fulcrum to adjust the panel attitude; -Z satellite panel clamp locking cylinder, which is configured to drive the extension and retraction of the -Z satellite panel clamp positioning pin to achieve locking and fixation; -Z Satellite Cabin Panel Fixture Positioning Pin.

[0030] ±Z satellite panel flip tray, such as Figure 7 and Figure 8 As shown, it is configured to carry satellite panels, including a +Z satellite panel flip tray 310 and a -Z satellite panel flip tray 320, with the satellite panels connected to the ±Z satellite panel flip trays by screws.

[0031] The clamp lifting device 500 is configured to adjust the height of the ±Z satellite cabin clamp 200, such as... Figure 4 and Figure 5 As shown, the clamp lifting device 500 includes a +Z satellite cabin clamp lifting device 510 and a -Z satellite cabin clamp lifting device 520, wherein the -Z satellite cabin clamp lifting device 520 includes: Electric hoist 12 is configured to drive the Z-satellite panel to flip and lift to adjust its attitude; Electric hoist controller 13, which is configured to drive electric hoist 12; -Z satellite cabin clamp controller 14, which is configured to control the lifting and lowering of -Z satellite cabin clamp 220 and the extension and retraction of locking cylinder 4; -Z satellite panel clamp lifting mechanism handle 15, which is configured to manually fine-tune the height of -Z satellite panel clamp 220.

[0032] Fixture transfer cart 400, such as Figure 6 As shown, it is configured as a carrier +Z satellite module clamp 200 to achieve inter-station transfer along the track.

[0033] 30-ton flip-over pallet transfer cart, such as Figure 9 As shown, it is configured to carry and transport ±Z satellite panel flipping trays and satellite panels.

[0034] The satellite module assembly system of this invention first performs pre-assembly preparation work on the satellite modules. This is mainly achieved using tooling such as the +Z satellite module clamp 210, the -Z satellite module clamp 220, the +Z satellite module flipping tray 310, the -Z satellite module flipping tray 320, and the clamp transfer vehicle 400. Through a control system and close human-machine collaboration, the ±Z satellite modules are assembled with the corresponding tooling in the assembly system. Specifically, the +Z satellite module clamp 210 is lifted using a clamp lifting device 500, and the clamp transfer vehicle 400 transports the +Z satellite module clamp 210 to the +Z satellite module area via a track system. Then, the clamp lifting device 500 lowers the +Z satellite module clamp 210 to a suitable position, and the locking cylinder 4 extends the positioning pin 5 to engage the +Z satellite module with the clamp. The connecting screws between the +Z satellite module and the +Z satellite module flipping tray 310 are then removed. Finally, the control system operates the clamps and transfer vehicle to transport the +Z satellite module to the assembly position. Operate the handle 15 of the -Z satellite panel clamp lifting mechanism to raise the -Z satellite panel clamp 220 to a suitable height. Use the -Z satellite panel flipping pallet 320 tooling to transport the assembly of the -Z satellite panel and the grid frame lifting point tooling 9 to the designated position of the merging station. Operate the -Z satellite panel clamp controller 14 to lower the -Z satellite panel clamp 220, and engage the positioning pin 8 of the -Z satellite panel clamp on the +Y side with the positioning pin hole at the corresponding position on the -Z satellite panel flipping pallet 320. After it is in place, operate the locking cylinder on the -Z satellite panel clamp to extend the positioning pin through the -Z satellite panel clamp controller 14, and engage the -Z satellite panel clamp 220 with the grid frame lifting point tooling 9. Engage the lifting ring 10 on the -Y side with the grid frame lifting point tooling 9 with screws, remove the connecting screws between the grid frame lifting point tooling 9 and the -Z satellite panel flipping pallet 320, and raise the lifting chain to a suitable height through the electric hoist controller 13. Operate the -Z satellite panel clamp 220 by using the handle 15 of the -Z satellite panel clamp lifting mechanism to lift the -Z satellite panel to a suitable height, and remove the -Z satellite panel flipping tray 320 tooling.

[0035] After the ±Z satellite panel preparation work is completed, the satellite panel closing system of this invention brings the ±Z satellite panels together and performs other pre-closing preparations. This is mainly achieved using the +Z satellite panel clamp 210 and the -Z satellite panel clamp 220. By controlling the tilt angle of the clamps, the system allows operators of any height to work comfortably. Specifically, the electric hoist controller 13 rotates the -Y side of the -Z satellite panel along the X-axis rotation axis 11 of the +Y side, lowering it from a horizontal to a vertical position. The -Z satellite panel clamp lifting mechanism handle 15 is then pushed, moving the -Z satellite panel along the Z-axis closer to the +Z satellite panel. The electric hoist controller 13 associated with the -Z satellite panel clamp 220 and the control system of the +Z satellite panel clamp 210 adjust the ±Z panels to a suitable tilt angle for operation, thus commencing pre-closing preparations.

[0036] After the pre-closure preparation work is completed, the satellite compartment closing system of this invention performs the closing operation. It mainly utilizes the +Z satellite compartment clamp 210 and the -Z satellite compartment clamp 220 to operate the ±Z satellite compartments to close, and then tightens the screws to complete the closing action. Specifically, the +Z and -Z satellite compartment clamps 210 and 220 respectively adjust the angle of the satellite compartments to 90 degrees through the control system and the electric hoist controller 13. The -Z satellite compartment clamp lifting mechanism handle 15 is operated to bring the -Z satellite compartment closer to the +Z satellite compartment. During the process of the -Z satellite compartment approaching the +Z satellite compartment, the Z-axis rotation axis 6 on the upper part of the -Z satellite compartment clamp 220 can be used to adjust the Z-axis swing angle of the -Z satellite compartment. The closing positioning pin 7 on the upper part of the -Z satellite compartment clamp 220 engages with the corresponding positioning pin 5 hole on the +Z satellite compartment clamp 210 to complete the closing action of the ±Z satellite compartments. After the cabin is closed, the satellite cabin plate can maintain a stable posture under the action of 220 air pressure of the -Z satellite cabin plate clamp, which makes it convenient for operators to install screws.

[0037] After the satellite module assembly system of this invention is completed, the entire satellite is removed from the assembly line. Using the +Z satellite module clamp 210, stacking columns, and a satellite transport vehicle, the ±Z satellite modules are separated from the assembly system. Specifically, after installing the assembly screws, the screws on the grid-frame lifting point fixture 9 on one side of the -Z module are removed. The handle 15 of the -Z satellite module clamp lifting mechanism is then operated to move the grid-frame lifting point fixture 9 away, disassembling it and transporting it to the storage area using the grid-frame lifting point fixture transport vehicle. The +Z satellite module clamp 210 is rotated by the control system to bring the entire satellite to a horizontal position. Stacking columns are then installed on the entire satellite, which is then connected to the transport vehicle. The connecting screws between the +Z satellite module and the +Z satellite module clamp 210 are removed. The +Z satellite module clamp 210 is then lifted to a suitable height by the control system, thus completing the satellite removal process.

[0038] Although various embodiments of the invention have been described above, it should be understood that they are presented by way of example only and not as limitations. It will be apparent to those skilled in the art that various combinations, modifications, and alterations can be made without departing from the spirit and scope of the invention. Therefore, the breadth and scope of the invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined solely by the appended claims and their equivalents.

Claims

1. A pod-joining system for a flat-panel box-type automated satellite production line, characterized in that, include: Satellite panels, including +Z and -Z satellite panels, are configured to achieve clamshell vertical closure via stepless flipping; ±Z satellite module clamps are configured to clamp and rotate the satellite module, including +Z satellite module clamps and -Z satellite module clamps, and are equipped with module positioning pins. The module assembly is completed by inserting and pulling the module positioning pins with the corresponding positioning pin holes. ±Z satellite panel flip-over trays are configured to carry satellite panels, including +Z satellite panel flip-over trays and -Z satellite panel flip-over trays; The clamp lifting device is configured to adjust the height of the ±Z satellite panel clamp.

2. The system according to claim 1, characterized in that, The +Z satellite panel fixture includes: The flip frame is configured as a frame structure to provide support for the flipping of the satellite module. The frame rotation axis is configured as a pivot point for rotating the flip frame, enabling the satellite panel to flip. A locking interface device, configured to connect the +Z satellite panel clamp to the +Z satellite panel, includes: A locking cylinder is configured to drive the extension and retraction of a locating pin to achieve locking and fixation; Positioning pin.

3. The system according to claim 1, characterized in that, The -Z satellite panel fixture includes: The Z-axis rotation axis is configured to adjust the Z-axis swing angle of the Z-satellite panel; The compartment positioning pin is configured to achieve the closing of the ±Z compartment panels; -Z satellite panel fixture positioning pin, which is configured to connect the -Z satellite panel fixture and the grid frame lifting point tooling; The grid-frame lifting point fixture is configured to lift and fix the -Z satellite module to connect the -Z satellite module clamp to the -Z satellite module; The lifting ring, configured to achieve the lifting and transfer of the -Z satellite module, is connected to the lattice frame lifting point tooling; The X-axis rotation axis is configured as the -Z satellite panel flipping fulcrum to adjust the panel attitude; -Z satellite panel clamp locking cylinder, which is configured to drive the extension and retraction of the -Z satellite panel clamp positioning pin to achieve locking and fixation; -Z Satellite Cabin Panel Fixture Positioning Pin.

4. The system according to claim 1, characterized in that, The clamp lifting device includes a +Z satellite cabin panel clamp lifting device and a -Z satellite cabin panel clamp lifting device, wherein the -Z satellite cabin panel clamp lifting device includes: An electric hoist is configured to drive the Z-satellite cabin panel to tilt and lift to adjust its attitude; An electric hoist controller, configured to drive an electric hoist; -Z satellite panel clamp controller, which is configured to control the lifting and lowering of the -Z satellite panel clamp and the extension and retraction of the locking cylinder; -Z satellite panel clamp lifting mechanism handle, which is configured to finely adjust the height of the -Z satellite panel clamp manually.

5. The system according to claim 1, characterized in that, It also includes a fixture transfer vehicle, which is configured to carry +Z satellite module fixtures and transfer them between workstations along a track.

6. The system according to claim 1, characterized in that, It also includes a flip-pallet transfer vehicle, which is configured to carry and transport ±Z satellite panel flip-pallets and satellite panels.

7. The system according to claim 1, characterized in that, The satellite module and the ±Z satellite module flip-up tray are connected by screws.

8. The system according to claim 1, characterized in that, The Z-satellite module and the grid frame lifting point fixture are connected by screws.

9. The system according to claim 3, characterized in that, The lifting ring is connected to the lifting point fixture of the grid frame by screws.

10. A method for assembling compartments in a flat-panel box-type automated satellite production line, characterized in that, include: The +Z satellite panel clamp is lifted using the +Z satellite panel clamp lifting device; The +Z satellite panel fixture is transferred to the +Z satellite panel area by a fixture transfer vehicle, and then the +Z satellite panel fixture is lowered to the predetermined position by a +Z satellite panel fixture lifting device. The +Z satellite compartment panel is combined with the +Z satellite compartment panel clamp by extending the positioning pin through the locking interface device, and the connecting screws of the +Z satellite compartment panel and the +Z satellite compartment panel flip tray are removed. The +Z satellite module is transferred to the merging position using a clamp transfer vehicle; Operate the handle of the Z-satellite panel clamp lifting mechanism to raise the Z-satellite panel clamp to the predetermined height; The assembly of the -Z satellite panel and the grid frame lifting point tooling is transported to the designated position of the merging station by a -Z satellite panel flipping pallet. Operate the -Z satellite panel clamp controller to lower the -Z satellite panel clamp, engage the -Z satellite panel clamp positioning pin with the positioning pin hole at the corresponding position on the -Z flip tray, and after it is in place, operate the -Z satellite panel clamp locking cylinder through the -Z satellite panel clamp controller to extend the -Z satellite panel clamp positioning pin, and combine the -Z satellite panel clamp with the grid frame lifting point fixture; The lifting eye is combined with the grid frame lifting point fixture by screws, and the connecting screws between the grid frame lifting point fixture and the -Z satellite cabin flipping tray are removed. The electric hoist controller raises the chain to the predetermined height, and the -Z satellite compartment panel is lifted to the predetermined height using the handle of the -Z satellite compartment panel clamp lifting mechanism. The -Z satellite compartment panel is then removed and the pallet is flipped. Using the electric hoist controller, the -Z satellite cabin panel is rotated along the X-axis, changing it from a horizontal to a vertical position. Push the handle of the -Z satellite panel clamp lifting mechanism to move the -Z satellite panel along the Z direction to approach the +Z satellite panel. Adjust the satellite panel to the predetermined tilt angle through the electric hoist controller and the +Z satellite panel clamp. The angle of the satellite module is adjusted to 90 degrees using the ±Z satellite module clamps; Operate the -Z satellite panel clamp handle to bring the -Z satellite panel closer to the +Z satellite panel; As the -Z satellite module approaches the +Z satellite module, the Z-axis swing angle of the -Z satellite module is adjusted by the Z-axis rotation axis on the upper part of the -Z satellite module clamp. The closing action of the satellite compartment is completed by engaging the closing positioning pin of the -Z satellite compartment clamp with the corresponding positioning pin hole on the +Z satellite compartment clamp. Install the clamping screws.

11. The method according to claim 10, characterized in that, Also includes: Remove the screws from the lattice frame lifting point fixture on one side of the -Z satellite panel, operate the -Z satellite panel clamp handle to move the lattice frame lifting point fixture away, and disassemble the lattice frame lifting point fixture; Transport the hoisting equipment for the grid frame to the storage area; Rotate the Z-shaped satellite panel clamp to bring the entire satellite to a horizontal position; Install the stacking columns, connect the entire satellite to the transport vehicle, remove the connecting screws between the +Z satellite panel and the +Z satellite panel clamp, lift the +Z satellite panel clamp to the predetermined height, and complete the satellite rollout.

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