Maintainable grounding device for on-orbit auxiliary astronaut manual grounding

Abstract

The invention discloses a maintainable grounding device for assisting an astronaut in manual grounding on orbit, and belongs to the technical field of spaceflight equipment. The device mainly comprises a plugging and unplugging assembly and a fixing assembly, wherein the plugging and unplugging assembly comprises a plugging and unplugging device, a non-separation fastening device, a top bead mechanism and a connecting mechanism; the fixing assembly comprises a fixing plate and a mounting column. The plugging device is in butt joint connection with the mounting column, and rapid plugging and reliable fixing can be achieved through operation of an astronaut through a manual tool or an electric tool; locking of the plugging assembly and the fixing assembly can be achieved through the non-disengaging fastening device, loosening and disengaging are prevented, and on-orbit maintenance is facilitated; the top bead mechanism provides elastic force through a spring so that a top bead can be embedded into a ball socket groove of a fixing assembly, a self-locking structure is formed, and it is ensured that the structure is stable in the weightlessness or vibration environment. And the connecting mechanism realizes reliable electrical grounding with the replaceable equipment through the O-shaped terminal and the grounding wire, so that the safety and the electrical integrity of the equipment during on-orbit working are ensured.

Description

Technical Field

[0001] This application belongs to the field of aerospace equipment technology, specifically relating to a repairable grounding device for assisting astronauts in manually grounding themselves in orbit. Background Technology

[0002] In modern spacecraft systems, equipment grounding is a critical element in ensuring electrical safety and stable system operation. Currently, spacecraft interior and exterior equipment mostly use fixed grounding terminals or welded grounding points for grounding connections. While these structures are fixed during the manufacturing stage and provide a stable grounding path, grounding failures, corrosion, or poor contact prevent astronauts from directly repairing or replacing them in the orbital environment. This often necessitates rework or replacement of the entire module, resulting in high maintenance costs and time delays. Furthermore, fixed grounding solutions typically require specialized tools or specific docking clamps for installation and disassembly, making them unsuitable for astronauts operating while wearing spacesuits outside the spacecraft. With the continuous advancement of space station construction and long-term on-orbit missions, the number of replaceable electronic devices is constantly increasing, highlighting the limitations of traditional fixed grounding methods. There is an urgent need for an on-orbit, maintainable grounding device that allows for autonomous astronaut operation, convenient plug-and-play connection, reliable locking, and reusability.

[0003] While some existing pluggable connection structures can achieve modular replacement to a certain extent, they mostly focus on signal or power connections, with insufficient consideration given to the reliability and mechanical stability of grounding connections. This is especially true in microgravity environments, where problems such as loosening, shaking, or poor contact can easily occur. At the same time, some structures are bulky or complex to assemble, which not only increases the difficulty of operation for astronauts but also makes it difficult to meet the installation requirements of space-constrained modules. Summary of the Invention

[0004] One objective of this application is to provide a maintainable grounding device for on-orbit manual grounding assistance to astronauts. This achieves a combination of advantages including detachable structure, ease of operation, stable contact, and reusability. Through the cooperation of plug-in and fixed components, astronauts can manually perform plugging and locking operations both inside and outside the cabin, achieving grounding connection without the need for specialized tools.

[0005] To achieve the above objectives, the first aspect of this application provides a repairable grounding device for on-orbit manual grounding assistance to astronauts, comprising:

[0006] The plug-in assembly includes: a plug-in device located at the bottom of the plug-in assembly, capable of docking with the mounting post of the fixing assembly; a non-detachable fastening device located at the upper end of the plug-in assembly, allowing astronauts to lock the plug-in assembly to the fixing assembly using hand or power tools; a top ball mechanism disposed within the plug-in device to prevent the plug-in assembly from falling off; and a connecting mechanism for connecting to the replaceable device.

[0007] A fixing assembly is disposed on the surface of a predetermined installation position on the compartment where the replaceable equipment is located. The fixing assembly includes a fixing plate and a mounting post disposed on the surface of the fixing plate.

[0008] The plug-in component is positioned opposite to the fixed component, enabling a plug-in connection.

[0009] According to a specific embodiment of this application, the insertion and removal device is disposed at the bottom of the insertion and removal assembly. The insertion and removal device is a semi-enclosed docking channel. The outer surface of the docking channel is provided with a guide groove. The guide groove is used to guide the alignment of the docking components when the insertion and removal assembly is inserted into the fixing assembly, so as to ensure smooth insertion.

[0010] According to a specific embodiment of this application, the non-disengaging fastening device includes an adjustable threaded rod and a threaded rod sleeve. The threaded rod sleeve is fitted onto the threaded rod, and the threaded rod is movable within the threaded rod sleeve. The threaded rod is located at the top center of the insertion / removal assembly.

[0011] According to a specific embodiment of this application, the top ball mechanism is disposed inside the docking channel, and the spring is disposed behind the top ball to provide elastic force to the top ball so that the top ball can be pushed into the fixing component to prevent the insertion and removal component from falling off.

[0012] According to a specific embodiment of this application, both the top of the docking channel and the mounting post of the fixing component are provided with chamfered structures to guide the insertion and removal component to be smoothly inserted into the fixing component.

[0013] According to a specific embodiment of this application, the connection mechanism includes an O-type terminal and a grounding wire; the O-type terminal is fixedly disposed at one end of the grounding wire for connection to the grounding post of the replaceable device; the other end of the grounding wire is fixedly installed on one side surface of the plug-in assembly.

[0014] According to a specific embodiment of this application, the fixing plate is an L-shaped structure, and the L-shaped structure includes a mounting surface and a fixing surface. Both the mounting surface and the fixing surface are provided with multiple mounting holes, and the fixing component is fixedly mounted on the surface of the cabin plate through the fixing surface.

[0015] According to a specific embodiment of this application, the mounting post is vertically fixed at the center of the surface of the mounting surface and is used to engage with the plug-in assembly.

[0016] According to a specific embodiment of this application, the mounting post is a hollow cylindrical structure, and the mounting post is provided with a ball-and-socket groove that matches the top ball mechanism of the plug-in assembly, for accommodating the top ball of the plug-in assembly.

[0017] According to a specific embodiment of this application, the top of the mounting column is provided with a connecting hole, which is used to accommodate the bottom of the threaded rod.

[0018] Compared with the prior art, the above-described solutions of this application have at least the following beneficial effects:

[0019] This application proposes a maintainable grounding device for on-orbit manual grounding assistance to astronauts, significantly improving the maintainability and reliability of grounding connections. The device employs a modular plug-in assembly and a separate fixing assembly design. A semi-enclosed guide docking channel and a chamfered guide structure ensure accurate plug-in alignment. A top ball mechanism and a ball-and-socket groove cooperate to form a self-locking position, preventing accidental dislodgement of the plug-in assembly and maintaining stable contact under vibration or thermal cycling conditions. The non-disengageable fastening device allows astronauts to perform one-handed locking and unlocking operations using a knob, enabling maintenance and replacement without the need for additional tools. Attached Figure Description

[0020] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings:

[0021] Figure 1 This is a schematic diagram showing the relative position of the replaceable external equipment and the repairable grounding device in an on-orbit assisted astronaut manual grounding repairable grounding device before replacement, according to the present application.

[0022] Figure 2 This is an overall structural diagram of a repairable grounding device for manual grounding assistance to astronauts in orbit, as per this application.

[0023] Figure 3 This is a structural diagram of the fixed component of a repairable grounding device for manual grounding assistance to astronauts in orbit, as per this application.

[0024] Figure 4 This is a structural diagram of the pluggable assembly of a repairable grounding device for manual grounding assistance to astronauts in orbit, as described in this application.

[0025] Among them, 1. Fixed component; 2. Plug-in component; 3. Mounting surface of equipment and fixing device; 4. Replaceable equipment; 5. Grounding post; 4-1. L-shaped structure; 4-2. Mounting post; 4-3. Mounting hole; 4-4. Connection hole; 4-5. Mounting surface; 4-6. Ball socket groove; 5-1. Non-removable fastening device; 5-2. Threaded rod; 5-3. Threaded sleeve; 5-4. Top ball; 5-5. Grounding wire. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0027] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that an article or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such an article or device. Without further limitation, an element defined by the phrase "comprising one" does not exclude the presence of other identical elements in the article or device that includes said element.

[0028] The present application proposes a repairable grounding device for manual grounding by astronauts in orbit, which aims to solve several key technical problems existing in the actual use of the existing electrical grounding structure of spacecraft, including the difficulty of on-orbit maintenance of fixed grounding terminals, insufficient connection reliability, complex assembly operation, unstable contact and lack of reusability.

[0029] Traditional spacecraft grounding designs, both internal and external, often employ welded or screw-type connections. While these structures provide stable grounding during ground assembly, once in orbit, poor contact, corrosion, aging, or mechanical damage to the grounding terminals become virtually impossible for astronauts to directly repair or replace during their time in orbit. This necessitates ground-based repairs or module replacement, significantly increasing mission costs and impacting the continuous operational safety of the equipment. Furthermore, existing screw- or snap-fit ​​grounding devices are cumbersome to operate in microgravity environments. Astronauts wearing spacesuits have limited hand dexterity, making precise screwing or alignment difficult, resulting in a high failure rate for on-orbit replacements. This fails to meet the requirements of space stations or long-term missions for highly reliable and maintainable electrical systems.

[0030] At the structural design level, this application adopts a separate structure for the plug-in and fixed components, enabling the grounding device to be quickly assembled and disassembled and maintained in orbit. The plug-in component consists of a plug-in device, a non-detachable fastening device, a top ball mechanism, and a connecting mechanism, while the fixed component consists of a fixing plate and a mounting post. The two are precisely connected through a semi-enclosed docking channel. Compared to traditional fixed welded structures, the semi-enclosed docking channel of this application has guide grooves and chamfered structures on its outer surface. This design provides self-guidance during astronaut insertion and removal operations, ensuring accurate alignment of the plug-in and removal components with the mounting post even under attitude drift or limited viewing angle conditions, effectively avoiding jamming or damage caused by misalignment. Through this guiding structure design, astronauts can complete the insertion and removal by hand without complex alignment, significantly reducing the difficulty and risk of on-orbit operations and improving operational efficiency and mission success rate.

[0031] Regarding mechanical stability, this application achieves a reliable mechanical self-locking effect through the cooperation of the top ball mechanism and the ball-and-socket groove of the mounting post. The top ball mechanism consists of a spring and a top ball. When the insertion / removal assembly is inserted into the fixing assembly, the elastic preload provided by the spring causes the top ball to automatically embed into the ball-and-socket groove of the mounting post, thereby forming an anti-pull-out positioning structure. This self-locking design can withstand complex load changes such as attitude adjustment, micro-vibration, launch impact, and thermal cycling during long-term spacecraft operation, while maintaining connection stability and preventing the grounding device from loosening due to external forces or thermal stress.

[0032] In terms of ease of operation and on-orbit maintainability, the non-detachable fastening device of this application offers extremely high ergonomic adaptability. The non-detachable fastening mechanism employs a combination of a threaded rod and a threaded sleeve. After the insertion / removal assembly and the fixing assembly are basically positioned via the top ball mechanism, astronauts can press and rotate the threaded rod using manual or power tools to achieve the threaded connection between the insertion / removal assembly and the fixing assembly. The threaded rod in this fastening structure, thanks to the design of the top ball mechanism, will not detach from the main structure even after being fully unscrewed, avoiding the risk of threaded parts falling off and floating in a weightless environment. This "zero-detachment" structural design not only simplifies the operation steps but also eliminates the potential for mission interruption due to lost parts during operation, greatly improving on-orbit operational safety. Furthermore, since the insertion / removal and locking of this device are purely mechanical actions, requiring no power assistance or complex control mechanisms, it can be reliably used in both in-cabin and out-of-cabin environments, demonstrating strong adaptability.

[0033] In terms of electrical performance, this application employs an O-type terminal and grounding wire structure in the connection mechanism, enabling the device to form a stable grounding path with high conductivity and low contact resistance while the mechanical connection is completed. The O-type terminal can be connected to the equipment grounding post by screwing or crimping, and its circular port forms a complete closed loop with the metal contact surface, effectively reducing contact resistance and improving arc resistance. This design not only ensures the safe discharge of grounding current but also prevents localized heating or potential drift caused by poor contact. In addition, the contact surface between the plug-in component and the fixed component is treated with a surface coating, providing anti-oxidation and anti-corrosion properties, and maintaining stable conductivity even in outdoor exposure environments or under long-term operating conditions. This combination of double-layer conductivity and mechanical self-locking design ensures that the device maintains a highly reliable grounding effect after multiple plugging and unplugging, far exceeding the lifespan performance of existing technologies.

[0034] From a maintenance and replacement perspective, this application achieves on-orbit modular replaceability. Because the plug-in and fixed components are separate structures, when a grounding fault or aging occurs, astronauts can replace only the plug-in component, while the fixed component remains on the panel, greatly reducing on-orbit maintenance workload and spare parts weight burden. Simultaneously, this design facilitates pre-installation before missions and subsequent replacement, enabling rapid integration into different equipment models and improving system versatility and scalability. Compared to the limitations of traditional welded fixed terminals, which require complete panel replacement or factory repair upon damage, this application makes the grounding device a standard module that can be repaired on-site and repeatedly plugged in and out, significantly enhancing the autonomy and flexibility of spacecraft on-orbit maintenance.

[0035] The following is in conjunction with the appendix Figure 1-4 Detailed description of optional embodiments of this application:

[0036] like Figure 1-4 As shown, the present invention provides a repairable grounding device, which mainly includes a fixing component 1, a pluggable component 2, a device and fixing device mounting surface 3, a replaceable device 4, and a grounding post 5 electrically connected to the replaceable device.

[0037] As an optional implementation, the fixing component 1 is set on the mounting surface 3 of the equipment and fixing device, serving as the fixed foundation of the grounding system and providing plug-in and support functions for the plug-in component 2; the plug-in component 2 is used to achieve pluggable connection with the fixing component 1 under the operation of the astronaut, thereby completing grounding conduction and mechanical fixation.

[0038] As an optional implementation, the fixing component 1 is composed of an L-shaped structure 4-1, which includes a mounting surface 4-5 and a fixing surface. The mounting surface 4-5 is used to achieve face-to-face insertion with the plug-in component 2, and the fixing surface is installed on the equipment and fixing device mounting surface 3 by means of screws or welding to ensure the stability of the fixing component 1 on the surface of the spacecraft cabin.

[0039] As an optional implementation, the two surfaces of the L-shaped structure 4-1 are connected at right angles to form an integral rigid frame structure. This L-shaped design can simultaneously take into account structural strength and assembly convenience, enabling the fixing component 1 to be installed in multiple directions within a limited space, and meeting the grounding requirements of the cabin and external equipment in different directions.

[0040] As an optional implementation, in order to achieve high-precision assembly, multiple mounting holes 4-3 are provided on both the mounting surface 4-5 and the fixing surface. The mounting holes 4-3 are used to cooperate with screws, pins or welding points for fixing, so that the fixing component 1 can be accurately positioned in the designated area of ​​the cabin plate.

[0041] As an optional implementation, a mounting post 4-2 is vertically arranged at the center of the mounting surface 4-5. The mounting post 4-2 is a hollow cylindrical structure with a connecting hole 4-4 at its top. The inner wall of the connecting hole 4-4 is provided with an internal thread for accommodating and threadedly connecting with the bottom part of the threaded rod 5-2 in the insertion assembly 2, so that the two form a stable guide and limit when inserted.

[0042] As an alternative implementation, the hollow structure of the mounting post 4-2 allows it to reduce weight during plug-in connection and provides space to accommodate the top bead 5-4 and the spring assembly.

[0043] As an optional implementation, the outer wall of the mounting post 4-2 is machined with a ball-and-socket groove 4-6, which cooperates with the top bead 5-4 inside the insertion and removal assembly 2. When the insertion and removal assembly 2 is inserted into the fixing assembly 1, the top bead 5-4 is pushed by the spring and embedded in the ball-and-socket groove 4-6 to form a mechanical self-locking structure to prevent the insertion and removal assembly 2 from falling off under microgravity, vibration or thermal deformation environment.

[0044] As an optional implementation, the plug-in assembly 2 is set at the corresponding position of the fixed assembly 1, with a plug-in device at its lower end, a non-disengaging fastening device 5-1 at its upper end, and a top ball mechanism and a connecting mechanism in the middle.

[0045] As an optional implementation, the bottom of the insertion and removal assembly 2 is a semi-enclosed docking channel structure. The outer surface of the docking channel is provided with a guide groove, which is used to guide the alignment of the plug part with the mounting post 4-2 during the insertion and removal process, so as to ensure smooth insertion even if the attitude is unstable during astronaut operation.

[0046] As an optional implementation, a top ball mechanism is provided inside the plug-in assembly 2, which consists of a top ball 5-4 and a spring.

[0047] As an optional implementation, the top ball 5-4 is installed in the inner wall groove of the docking channel, and a spring is provided behind it to provide a continuous elastic preload.

[0048] As an optional implementation, during the insertion and removal operation, when the insertion and removal component 2 is inserted into the mounting post 4-2, the top ball 5-4 is compressed and springs back under the action of the inclined surface. When the insertion and removal depth reaches the designed position, the spring releases its elastic force, causing the top ball 5-4 to automatically spring into the ball socket groove 4-6 on the outer wall of the mounting post 4-2, forming a self-locking locking structure.

[0049] As an optional implementation, this structure mechanically prevents detachment and electrically ensures a tight fit between the contact surfaces, further improving grounding conductivity. The top bead 5-4 is made of high-strength stainless steel or nickel-plated copper alloy to balance wear resistance and conductivity, ensuring good elasticity and low contact resistance even after repeated insertions and removals.

[0050] As an optional implementation, the upper end of the plug-in assembly 2 is equipped with a non-removable fastening device 5-1, which includes a threaded rod 5-2 and a threaded sleeve 5-3. The threaded rod 5-2 is installed at the central axis position of the plug-in assembly 2, and its lower end can be inserted into the connecting hole 4-4 of the mounting post 4-2 of the fixing assembly 1.

[0051] As an alternative implementation, astronauts can use a manual or power tool to press the threaded rod 5-2, causing the threaded rod 5-2 to move downward after the screw sleeve 5-3 moves downward. Then, they can rotate the threaded rod 5-2 so that the bottom end of the threaded rod 5-2 connects with the internal thread on the inner wall of the inwardly recessed connecting hole 4-4 on the mounting post 4-2, thereby achieving mechanical locking between the insertion / removal assembly 2 and the fixing assembly 1.

[0052] As an optional implementation, a connection mechanism is provided on one side of the plug-in assembly 2, the connection mechanism including an O-type terminal and a grounding wire 5-5.

[0053] As an optional implementation, the O-type terminal is fixed to one end of the grounding wire 5-5 for connection to the grounding post 5 of the replaceable device 4.

[0054] As an optional implementation, the other end of the grounding wire 5-5 is fixedly installed on the outer surface of the plug-in assembly 2, so that the plug-in assembly 2 can establish an electrical grounding circuit while realizing mechanical plugging.

[0055] As an optional implementation, when the plug-in component 2 is inserted into the fixing component 1, the metal shell of the plug-in component 2 and the mounting post 4-2 form a first grounding path, and the O-type terminal and the grounding post 5 form a second grounding path. Together, they constitute a redundant grounding system, further improving electrical safety and system reliability.

[0056] As an optional implementation, in specific use, astronauts can operate the grounding device in the following way: When it is necessary to connect the replaceable device 4 to the common grounding system of the spacecraft cabin, firstly, the fixing component 1 is pre-installed at a preset position on the mounting surface 3 of the equipment and fixing device. The fixing component 1 is fixed to the cabin plate through the mounting hole 4-3 on the fixing surface, and the mounting post 4-2 extends outward for subsequent insertion. Then, the astronaut holds the insertion component 2 and aligns the semi-enclosed docking channel of the insertion component 2 with the mounting post 4-2, and gradually inserts the insertion component 2 with the help of the guide groove. When the insertion component 2 is fully inserted to the designed depth, the top ball 5-4 automatically embeds into the ball socket groove 4-6 under the action of the spring, forming a preliminary self-locking connection. At this time, the astronaut can press down the threaded rod 5-2 with a manual tool or power tool, so that the threaded rod 5-2 moves in the screw sleeve 5-3, thereby driving the threaded rod 5-2 into the connection hole 4-4, realizing the secure locking of the insertion component 2 and the fixing component 1. After the plug-in assembly 2 is plugged in, the O-type terminal on the outside of the plug-in assembly 2 is reliably connected to the grounding post 5 of the replaceable equipment 4 via the grounding wire 5-5, thereby establishing a complete electrical grounding circuit and ensuring the electrical safety and anti-interference performance of the equipment during its on-rail operation.

[0057] When astronauts need to replace equipment or maintain the grounding device, they only need to rotate the threaded rod 5-2 in reverse to release the lock between the threaded rod 5-2 and the connecting hole 4-4. Then, by slightly pulling the insertion / removal assembly 2, the top ball 5-4 will automatically disengage from the ball socket groove 4-6 under the action of the spring, and the insertion / removal assembly 2 can be easily pulled out, achieving safe disassembly. Because this structure uses standardized dimensions, astronauts can directly replace the new insertion / removal assembly 2 and reinsert it into the fixing assembly 1 without replacing the entire fixing part, thus significantly improving on-orbit maintenance efficiency and reducing the weight and volume of spare parts.

[0058] The structure of this embodiment has been optimized in terms of both mechanical and electrical performance. The mating channel between the mounting post 4-2 and the plug-in assembly 2 uses direct metal contact for conductivity, and the contact surfaces are silver-plated or nickel-plated to reduce contact resistance and prevent corrosion. The elastic contact between the top bead 5-4 and the ball socket groove 4-6 not only provides mechanical positioning but also forms a second conductive path, improving the reliability of the grounding loop. The O-type terminal and the grounding post 5 are crimped using a standard aerospace-grade connector, capable of withstanding vibration and thermal cycling without loosening. This is achieved through multi-point contact and redundant design.

[0059] Furthermore, the fixing component 1 of the L-shaped structure 4-1 possesses high mechanical strength and torsional resistance, enabling it to withstand the high-load impacts during spacecraft launch. The hollow structure design of the mounting column 4-2 not only reduces weight but also achieves pressure balance through internal through-holes, preventing stress concentration caused by thermal expansion and contraction. The overall shell of the plug-in component 2 is made of lightweight, highly conductive aluminum alloy or nickel-plated copper alloy, ensuring both good conductivity and meeting the requirements for corrosion resistance and lightweight design.

[0060] Through the above design, the repairable grounding device of this application can complete a fast, safe, and reliable grounding connection under manual operation by astronauts, enabling efficient maintenance and replacement of spacecraft equipment in orbit. Compared with traditional fixed grounding terminals, this device has achieved significant improvements in structural strength, electrical performance, ease of operation, and maintenance cycle, effectively reducing on-orbit maintenance costs and improving the overall reliability and mission safety of the spacecraft system.

[0061] In summary, all components in this embodiment work together to achieve a combination of functions including pluggable structure, mechanical self-locking, electrical conductivity, reusability, and on-orbit maintenance.

[0062] Finally, it should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the systems or apparatus disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the descriptions are relatively simple, and relevant parts can be referred to the method section.

[0063] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A maintainable grounding device for assisting astronauts in manually grounding in orbit, characterized in that, include: The plug-in assembly includes: a plug-in device located at the bottom of the plug-in assembly, capable of docking with the mounting post of the fixing assembly; a non-detachable fastening device located at the upper end of the plug-in assembly, allowing astronauts to lock the plug-in assembly to the fixing assembly using hand or power tools; a top ball mechanism disposed within the plug-in device to prevent the plug-in assembly from falling off; and a connecting mechanism for connecting to a replaceable device. A fixing assembly is disposed on the surface of a predetermined installation position on the compartment where the replaceable equipment is located. The fixing assembly includes a fixing plate and a mounting post disposed on the surface of the fixing plate. The plug-in component is positioned opposite to the fixed component, enabling a plug-in connection.

2. A maintainable grounding device for manual grounding of astronauts in orbit according to claim 1, characterized in that, The insertion and removal device is located at the bottom of the insertion and removal assembly. The insertion and removal device is a semi-enclosed docking channel. The outer surface of the docking channel is provided with a guide groove. The guide groove is used to guide the alignment of the docking parts when the insertion and removal assembly is inserted into the fixing assembly, so as to ensure smooth insertion.

3. A maintainable grounding device for on-orbit manual grounding assistance for astronauts according to claim 1, characterized in that, The non-disengaging fastening device includes an adjustable threaded rod and a threaded sleeve, the threaded sleeve being fitted onto the threaded rod, the threaded rod being movable within the threaded sleeve, and the threaded rod being located at the top center of the insertion / removal assembly.

4. A repairable grounding device for on-orbit assisted manual grounding by astronauts according to claim 2, wherein the top bead mechanism includes a top bead and a spring, the top bead mechanism is disposed inside the docking channel, and the spring is disposed behind the top bead, for providing elastic force to the top bead so that the top bead can be pushed into the fixing assembly to prevent the insertion and removal assembly from falling off.

5. The maintainable grounding device for on-orbit assisted manual grounding for astronauts according to claim 4, wherein the top of the docking channel and the mounting post of the fixing component are both provided with chamfered structures to guide the insertion and removal components to be smoothly inserted into the fixing component.

6. A maintainable grounding device for on-orbit assisted manual grounding by astronauts according to claim 1, characterized in that, The connection mechanism includes an O-type terminal and a grounding wire; the O-type terminal is fixedly disposed at one end of the grounding wire for connection to the grounding post of the replaceable device; the other end of the grounding wire is fixedly installed on one side surface of the plug-in assembly.

7. A maintainable grounding device for assisting astronauts in manual grounding in orbit according to claim 1, characterized in that, The fixing plate has an L-shaped structure, and the L-shaped structure includes a mounting surface and a fixing surface. Both the mounting surface and the fixing surface are provided with multiple mounting holes. The fixing component is fixedly mounted on the surface of the cabin plate through the fixing surface.

8. A maintainable grounding device for on-orbit manual grounding assistance for astronauts according to claim 7, characterized in that, The mounting post is vertically fixed at the center of the mounting surface and is used to engage with the plug-in assembly.

9. A repairable grounding device for on-orbit assisted manual grounding for astronauts according to claim 7, wherein the mounting post is a hollow cylindrical structure, and the mounting post is provided with a ball-and-socket groove that matches the top ball mechanism of the plug-in assembly for accommodating the top ball of the plug-in assembly.

10. A repairable grounding device for on-orbit assisted manual grounding for astronauts according to claim 9, wherein the top of the mounting post is provided with a connecting hole for accommodating the bottom of the threaded rod.

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