Anti-floating and counter-force-eliminating fastening device for pressing plate type space station and locking method

Abstract

The invention discloses an anti-floating and counter-force-eliminating fastening device for a pressing plate type space station and a locking method. The anti-floating and counter-force-eliminating fastening device is used for a screw fastening use scene capable of preventing floating and eliminating tightening counter force in the space station. The electric screwing tool and the anti-floating screw are integrally designed, the electric screwing tool counter-force eliminating sleeve and the anti-floating screw shell have the regular hexagonal prism limiting characteristic, so that the influence of screwing counter-force is eliminated, and the anti-floating screw prevents an inner hexagon screw from driving a reset spring to rotate in the rotating process through the effect of a wing-shaped spring pressing plate. According to the method, the interface matching performance is improved, the screw on-orbit mounting process is optimized, and the on-orbit working efficiency of astronauts is improved.

Description

Technical Field

[0001] This invention relates to a pressure plate type anti-drift and anti-reaction fastening device and locking method for space stations, which is used in scenarios where anti-drift and anti-tightening reaction forces are required for fastening screws in space stations. Background Technology

[0002] Among the numerous on-orbit operations conducted for various experiments in space, screw tightening operations account for a significant proportion. Screw tightening operations currently face two main challenges:

[0003] 1) Weightlessness is a key characteristic of space stations, making it easy for screws and washers to float and form debris when astronauts disassemble them in orbit. Furthermore, securing screws and washers during reassembly is difficult. Currently, safety ropes are mainly used to prevent screws from drifting away and forming debris, but this method has limited effect on reducing the workload for astronauts.

[0004] 2) When tightening screws on the ground, the operator can apply tightening torque using their own weight. When tightening screws in orbit, the astronaut is in a floating state and cannot apply force using their own weight. The commonly used method is to install a handrail near the operating area, allowing the astronaut to use one hand to grasp the handle and apply force to overcome the reaction force.

[0005] The above method requires an extra hand to tighten the screws, which limits the efficiency of the operation. Summary of the Invention

[0006] The technical problem to be solved by this invention is to overcome the shortcomings of the prior art and meet the requirements for efficient on-orbit screw tightening.

[0007] The objective of this invention is achieved through the following technical solutions:

[0008] In a first aspect, the present invention provides a pressure plate type anti-drift and reaction force elimination fastening device for a space station, including an electric screwing tool and an anti-drift screw;

[0009] Electric screwdrivers include an electric drive assembly, bearings, screwdriver housing, hexagonal screw shaft, and anti-rebound sleeve; anti-drift screws include an internal hexagonal screw, wing spring pressure plate, return spring, anti-drift screw housing, anti-drift screw end cap, and mounting screw.

[0010] The screwdriver housing has a bearing mounting hole at the top and bottom, and the outer rings of the two bearings are fixed to the bearing mounting holes of the screwdriver housing respectively; the journals on the upper and lower sides of the hexagonal screw shaft are fixed to the inner rings of the two bearings respectively, thus forming a rotating pair between the hexagonal screw shaft and the screwdriver housing; the stator of the drive assembly is fixedly connected to the screwdriver housing, and the rotor of the drive assembly is fixedly connected to the upper side of the hexagonal screw shaft; the reaction force relief sleeve is a hollow structure, the upper side is fixedly connected to the screwdriver housing, the lower side is a regular hexagon, and the regular hexagon near the lower end face has an angled opening structure;

[0011] The anti-drift screw housing has a hollow cylindrical structure inside, with hollow sliding grooves on the left and right sides, and screw mounting lugs on the bottom left and right sides; the wing-shaped spring pressure plate has a hollow cylindrical structure with a symmetrical wing on each side. The hollow cylindrical structure of the wing-shaped spring pressure plate and the hollow cylindrical structure inside the anti-drift screw housing form a sliding pair.

[0012] The return spring is installed inside the anti-drift screw housing. The lower side of the return spring contacts the anti-drift screw end cap, and the upper side of the return spring contacts the lower end face of the wing spring pressure plate. The wing spring pressure plate is always subjected to the upward return force of the return spring. The anti-drift screw end cap is fixedly connected to the anti-drift screw housing. The cylindrical end face of the hexagon socket screw is a standard hexagon socket interface. From top to bottom, it consists of a flat cylindrical flange, a long cylinder, and a cylinder with a standard external thread. The diameter of the three cylinders decreases downwards. The hexagon socket screw is installed inside the anti-drift screw housing and passes through the center hole of the wing spring pressure plate, the center hole of the return spring, and the center hole of the anti-drift screw housing from top to bottom. The diameter of the flat cylindrical flange of the hexagon socket screw is larger than the diameter of the center hole of the wing spring pressure plate, and it is sandwiched between the upper end face of the wing spring pressure plate and the upper end face of the inner cavity of the anti-drift screw housing.

[0013] Based on the first aspect, in one embodiment of the present invention, the lower side of the hexagonal screw shaft is a regular hexagonal prism, which can be used as a wrench for tightening internal hexagonal screws.

[0014] Based on the first aspect, in one embodiment of the present invention, under the action of the reset spring, the internal hexagonal screw is held at the top of the inner cavity of the anti-drift screw housing by the wing-shaped spring pressure plate.

[0015] Based on the first aspect, in one embodiment of the present invention, the drive assembly can provide power to rotate the hexagonal screw shaft relative to the screwing tool housing.

[0016] Based on the first aspect, in one embodiment of the present invention, the symmetrical wings of the wing-shaped spring pressure plate cooperate with the hollowed-out sliding grooves on the left and right sides of the anti-drift screw housing, so that the rolling and rotational degrees of freedom are eliminated during the sliding process of the wing-shaped spring pressure plate and the anti-drift screw housing.

[0017] Based on the first aspect, in one embodiment of the present invention, before the space equipment ascends, the anti-drift screw is fixed to the threaded hole of the space equipment lug by its own two left and right mounting screws. At this time, the anti-drift screw and the space equipment lug form a whole.

[0018] In a second aspect, the present invention provides a locking method based on the pressure plate type anti-drift and reaction force eliminating fastening device for space stations described in the first aspect, comprising:

[0019] The locking base of the space station workbench consists of multiple threaded holes. After the space equipment enters the space station, the astronauts perform the initial alignment of the center hole of the space equipment mounting lug with the threaded hole of the locking base. They then put the anti-reaction sleeve of the electric screwdriver onto the anti-drift screw housing and press down. The wing-shaped spring pressure plate drives the return spring to move downward, releasing the return force of the return screw on the hexagonal socket head cap screw. The hexagonal screw shaft is inserted into the standard hexagonal socket interface at the top of the hexagonal socket head cap screw. The electric drive assembly drives the hexagonal screw shaft to rotate, so that the hexagonal socket head cap screw is screwed into the threaded hole of the locking base, thereby achieving relative installation and locking between the space equipment and the locking base of the space station workbench.

[0020] Based on the second aspect, in one embodiment of the present invention, the reaction force during the thread tightening process is transmitted by the reaction force relief sleeve to the hexagonal shape feature of the anti-drift screw housing, thereby realizing the reaction force relief function and avoiding astronauts from bearing the thread tightening reaction force in a weightless environment.

[0021] Thirdly, the present invention provides a method for dismantling the anti-drift and reaction-eliminating fastening device for a space station based on the pressure plate type described in the first aspect, comprising:

[0022] The anti-reaction sleeve of the electric screw tightening tool is fitted onto the anti-drift screw housing. The hexagonal screw shaft is inserted into the standard hexagonal socket of the socket screw. The electric drive assembly drives the hexagonal screw shaft to rotate in the opposite direction, causing the socket screw to move upwards in the unlocking direction. The electric screw tightening tool moves upwards along with the socket screw, and the wing spring pressure plate moves upwards with the electric screw tightening tool under the action of the return spring. Finally, the space equipment mounting lug is removed from the locking base, and the anti-drift reset of the socket screw is achieved, facilitating the next installation operation.

[0023] Compared with the prior art, the present invention has the following advantages:

[0024] (1) The fastening device of the present invention eliminates the operational difficulties and risks of screws floating in the weightless environment of the space station by means of shell limiting and spring reset.

[0025] (2) The present invention eliminates the influence of tightening reaction force by using the reaction force elimination sleeve of the electric tightening tool and the hexagonal prism limiting feature of the anti-drift screw housing, thereby improving the efficiency of astronauts working in orbit.

[0026] (3) The anti-drift screw of the present invention can avoid the return spring from rotating during the rotation of the internal hexagon screw by the action of the wing spring pressure plate, thereby avoiding the performance degradation and life attenuation caused by the spring twisting along the axis.

[0027] (4) The electric screw tightening tool and the anti-drift screw of the present invention are integrated into one design, which improves the interface compatibility, optimizes the screw installation process in orbit, and improves the efficiency of astronauts working in orbit. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the composition of the pressure plate type anti-drift and reaction force elimination fastening device for space stations according to the present invention.

[0029] Figure 2 This is a schematic diagram showing the screw not being screwed in.

[0030] Figure 3 This is a schematic diagram of the screw-in process.

[0031] Figure 4 This is a partial structural diagram of an electric screwdriver.

[0032] Figure 5 This is a schematic diagram of the anti-drift screw structure.

[0033] Figure 6 This is a schematic diagram of the internal hexagon screw structure.

[0034] Figure 7 This is a schematic diagram of the ear plate structure for space equipment. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0036] A pressure plate type anti-drift and reaction force-eliminating fastening device for a space station includes an electric tightening tool 100 and an anti-drift screw 200. The electric tightening tool 100 includes an electric drive assembly 101, a bearing 102, a tightening tool housing 103, a hexagonal screw shaft 104, and a reaction force-eliminating sleeve 105, such as... Figure 2 , 3 As shown; the anti-drift screw 200 includes an internal hexagonal screw 201, a winged spring pressure plate 202, a return spring 203, an anti-drift screw housing 204, an anti-drift screw end cap 205, and a mounting screw 206, as shown. Figure 2 , 3 As shown.

[0037] The lower side of the hexagonal screw shaft 104 is a regular hexagonal prism, which can be used as a wrench for tightening hexagonal screws. The tightening tool housing 103 has a bearing mounting hole on both the top and bottom, and the outer rings of the two bearings 102 are fixed to these mounting holes. The journals on the upper and lower sides of the hexagonal screw shaft 104 are fixed relative to the inner rings of the two bearings 102, thus forming a rotating pair between the hexagonal screw shaft 104 and the tightening tool housing 103. The stator of the drive assembly 101 is fixedly connected to the tightening tool housing 103, and the rotor of the drive assembly 101 is fixedly connected to the upper side of the hexagonal screw shaft 104. The drive assembly 101 provides power, causing the hexagonal screw shaft 104 to rotate relative to the tightening tool housing 103. The reaction-absorbing sleeve 105 is a hollow structure, fixedly connected to the upper side of the tightening tool housing 103, and its lower interior has a regular hexagonal feature, with the regular hexagonal feature near the lower end face having an angled opening structure, such as... Figure 4 As shown.

[0038] The anti-drift screw housing 204 has an internal hollow cylindrical structure with hollowed-out grooves on both sides and screw mounting lugs on the bottom left and right sides. The wing-shaped spring pressure plate 202 is a hollow cylindrical structure with a symmetrical wing on each side. The hollow cylindrical structure and the internal hollow cylindrical structure of the anti-drift screw housing 204 form a sliding pair. The symmetrical wings of the wing-shaped spring pressure plate 202 engage with the hollowed-out grooves on the left and right sides of the anti-drift screw housing 204, eliminating the rolling and rotational degrees of freedom during the sliding process between the wing-shaped spring pressure plate 202 and the anti-drift screw housing 204. Figure 5 As shown.

[0039] The return spring 203 is installed inside the anti-drift screw housing 204. The lower side of the return spring 203 contacts the anti-drift screw end cap 205, and the upper side contacts the lower end face of the wing-shaped spring pressure plate 202. The wing-shaped spring pressure plate 202 is always subjected to an upward return force from the return spring 203. The anti-drift screw end cap 205 is fixedly connected to the anti-drift screw housing 204. The top cylindrical end face of the internal hexagon screw 201 has a standard internal hexagon interface, and from top to bottom, it features a flat cylindrical flange, a long cylindrical section, and a cylindrical section with standard external threads. The diameter of the three cylindrical sections decreases progressively downwards. Figure 6 As shown, the hex socket screw 201 is installed inside the anti-drift screw housing 204, passing through the central hole of the wing spring pressure plate 202, the central hole of the return spring 203, and the central hole of the anti-drift screw housing 204 from top to bottom. The diameter of the flat cylindrical flange of the hex socket screw 201 is larger than the diameter of the central hole of the wing spring pressure plate 202. It is sandwiched between the upper end face of the wing spring pressure plate 202 and the upper end face of the inner cavity of the anti-drift screw housing 204. That is, under the action of the return spring 203, the hex socket screw 201 is held at the top of the inner cavity of the anti-drift screw housing 204 along with the wing spring pressure plate 202.

[0040] Space device 300 typically includes multiple lugs. For ease of description, this article only describes the locking connection of a single lug. The space device lug includes a central aperture and two threaded holes on the left and right sides, such as... Figure 7 As shown. Before the space equipment 300 ascends, the anti-drift screw 200 is fixed to the threaded hole of the lug of the space equipment 300 by its two mounting screws 206 on the left and right sides. At this time, the anti-drift screw 200 and the lug of the space equipment 300 form a whole. The locking base 400 of the space station workbench is composed of multiple threaded holes. When the space equipment 300 enters the space station, as shown... Figure 1 As shown, the astronauts complete the initial alignment of the center hole of the mounting lug of the space equipment 300 with the threaded hole of the locking base 400, and then put the anti-reaction sleeve 105 (internal hexagonal shape) of the electric screw tightening tool 100 onto the anti-drift screw housing 204 (external hexagonal shape) of the anti-drift screw 200, and then press down. The wing-shaped spring pressure plate 202 drives the return spring 203 to move downward, releasing the return force of the return screw on the internal hexagonal screw 201. The hexagonal screw shaft 104 is inserted into the internal hexagonal standard interface at the top of the internal hexagonal screw 201, and the electric drive assembly 101 drives the hexagonal screw shaft 104 to rotate, so that the internal hexagonal screw 201 is screwed into the threaded hole of the locking base 400, thereby realizing the relative installation and locking between the space equipment 300 and the locking base 400 of the space station workbench. During the thread tightening process, the reaction force is transmitted from the reaction force relief sleeve 105 to the hexagonal shape of the anti-drift screw housing 204, thereby achieving the reaction force relief function and preventing astronauts from experiencing thread tightening reaction force in a weightless environment. After tightening is completed, the electric tightening tool 100 is removed.

[0041] When it is necessary to remove the space device 300 from the locking base 400, the electric tightening tool 100's reaction-absorbing sleeve 105 (internal hexagonal shape) is fitted onto the anti-drift screw housing 204 (external hexagonal shape) of the anti-drift screw 200. The hexagonal screw shaft 104 is inserted into the standard internal hexagonal interface of the internal hexagonal screw 201. The electric drive assembly 101 drives the hexagonal screw shaft 104 to rotate in the opposite direction, realizing the movement of the internal hexagonal screw 201 in the unlocking upward direction. The electric tightening tool 100 moves upward along with the internal hexagonal screw 201, and the wing-shaped spring pressure plate 202 moves upward with the electric tightening tool 100 under the action of the return spring 203. Finally, the space device mounting lugs are removed from the locking base, and the anti-drift reset of the internal hexagonal screw 201 is achieved, facilitating the next installation operation.

[0042] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0043] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A pressure plate type anti-drift and reaction force absorbing fastening device for a space station, characterized in that, Includes an electric screwdriver (100) and anti-drift screws (200); The electric screwdriver (100) includes an electric drive assembly (101), a bearing (102), a screwdriver housing (103), a hexagonal screw shaft (104), and a reaction sleeve (105); the anti-drift screw (200) includes an internal hexagonal screw (201), a wing spring pressure plate (202), a return spring (203), an anti-drift screw housing (204), an anti-drift screw end cap (205), and a mounting screw (206); The screw-twisting tool housing (103) has a bearing mounting hole on the top and bottom, and the outer rings of the two bearings (102) are fixed to the bearing mounting holes of the screw-twisting tool housing (103) respectively; the journals on the top and bottom sides of the hexagonal screw shaft (104) are fixed to the inner rings of the two bearings (102) respectively, thereby forming a rotating pair between the hexagonal screw shaft (104) and the screw-twisting tool housing (103); the stator of the drive assembly (101) is fixedly connected to the screw-twisting tool housing (103), and the rotor of the drive assembly (101) is fixedly connected to the upper side of the hexagonal screw shaft (104); the reaction force relief sleeve (105) is a hollow structure, the upper side is fixedly connected to the screw-twisting tool housing (103), the lower side is a regular hexagon, and the regular hexagon near the lower end face is a beveled opening structure; The anti-drift screw housing (204) has a hollow cylindrical structure inside, with hollow sliding grooves on the left and right sides, and screw mounting lugs on the left and right sides at the bottom; the wing-shaped spring pressure plate (202) has a hollow cylindrical structure with a symmetrical wing on each side. The hollow cylindrical structure of the wing-shaped spring pressure plate (202) and the hollow cylindrical structure inside the anti-drift screw housing (204) cooperate to form a sliding pair; The return spring (203) is installed inside the anti-drift screw housing (204). The lower side of the return spring (203) contacts the anti-drift screw end cap (205), and the upper side of the return spring (203) contacts the lower end face of the wing-shaped spring pressure plate (202). The wing-shaped spring pressure plate (202) is always subjected to the upward return force of the return spring (203). The anti-drift screw end cap (205) is fixedly connected to the anti-drift screw housing (204). The cylindrical end face of the internal hexagon screw (201) is a standard internal hexagon interface, which consists of a flat cylindrical flange, a long cylindrical flange, and a flange with a tapered end. The cylinder features a standard external thread, and the diameter of the three cylindrical sections decreases sequentially downwards. The internal hexagonal screw (201) is installed inside the anti-drift screw housing (204), passing through the central hole of the wing spring pressure plate (202), the central hole of the return spring (203), and the central hole of the anti-drift screw housing (204) sequentially from top to bottom. The diameter of the flat cylindrical flange of the internal hexagonal screw (201) is larger than the diameter of the central hole of the wing spring pressure plate (202), and it is sandwiched between the upper end face of the wing spring pressure plate (202) and the upper end face of the inner cavity of the anti-drift screw housing (204).

2. The pressure plate type anti-drift and reaction force absorbing fastening device for space stations according to claim 1, characterized in that, The lower side of the hexagonal screw shaft (104) is a regular hexagonal prism, which can be used as a wrench for tightening internal hexagonal screws.

3. The pressure plate type anti-drift and reaction force absorbing fastening device for space stations according to claim 1, characterized in that, Under the force of the return spring (203), the internal hexagon screw (201) is held at the top of the cavity of the anti-drift screw housing (204) along with the wing spring pressure plate (202).

4. The pressure plate type anti-drift and reaction force absorbing fastening device for space stations according to claim 1, characterized in that, The drive assembly (101) provides power to rotate the hexagonal screw shaft (104) relative to the screwdriver housing (103).

5. The pressure plate type anti-drift and reaction force absorbing fastening device for space stations according to claim 1, characterized in that, The symmetrical wings of the wing-shaped spring pressure plate (202) cooperate with the hollowed-out sliding grooves on the left and right sides of the anti-drift screw housing (204), so that the rolling and rotational degrees of freedom are eliminated during the sliding process of the wing-shaped spring pressure plate (202) and the anti-drift screw housing (204).

6. The pressure plate type anti-drift and reaction force absorbing fastening device for space stations according to claim 1, characterized in that, Before the space device (300) ascends, the anti-drift screw (200) is fixed to the threaded hole of the lug of the space device (300) by its two mounting screws (206) on the left and right. At this time, the anti-drift screw (200) and the lug of the space device (300) form a whole.

7. A locking method based on the anti-drift and reaction force-eliminating fastening device for a space station using a pressure plate as described in claim 6, characterized in that, include: The locking base (400) of the space station workbench consists of multiple threaded holes. After the space equipment (300) enters the space station, the astronauts perform the initial alignment of the center hole of the mounting lug of the space equipment (300) with the threaded hole of the locking base (400), and put the anti-reaction sleeve (105) of the electric screw tightening tool (100) onto the anti-drift screw housing (204) of the anti-drift screw (200), and then press down. The wing-shaped spring pressure plate (202) drives the return spring ( 203) Move downwards to release the reset force of the reset screw on the internal hexagonal screw (201); the hexagonal screw shaft (104) is inserted into the internal hexagonal standard interface at the top of the internal hexagonal screw (201), and the electric drive assembly (101) drives the hexagonal screw shaft (104) to rotate, so that the internal hexagonal screw (201) is screwed into the threaded hole of the locking base (400), thereby realizing the relative installation and locking between the space equipment (300) and the space station workbench locking base (400).

8. The locking method according to claim 7, characterized in that, The reaction force during the thread tightening process is transmitted from the reaction force relief sleeve (105) to the hexagonal shape feature of the anti-drift screw housing (204), thereby realizing the reaction force relief function and avoiding the astronauts from bearing the thread tightening reaction force in a weightless environment.

9. A method for dismantling the anti-drift and reaction-eliminating fastening device for a space station based on the pressure plate type as described in claim 1, characterized in that, include: The anti-reaction sleeve (105) of the electric screw tightening tool (100) is fitted onto the anti-drift screw housing (204) of the anti-drift screw (200). The hexagonal screw shaft (104) is inserted into the standard internal hexagonal interface of the internal hexagonal screw (201). The electric drive assembly (101) drives the hexagonal screw shaft (104) to rotate in the opposite direction, so that the internal hexagonal screw (201) moves in the unlocking upward direction. The electric screw tightening tool (100) moves upward along with the internal hexagonal screw (201). The wing-shaped spring pressure plate (202) moves upward with the electric screw tightening tool (100) under the action of the return spring (203). Finally, the space equipment mounting lug is disassembled relative to the locking base (400), and the anti-drift reset of the internal hexagonal screw (201) can be realized, which is convenient for the next installation operation.

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