A quick-connect locking joint device for space trusses and its usage method

Abstract

This invention discloses a quick-connect locking joint device and its usage method for space trusses, relating to the field of space on-orbit assembly and space truss connection technology. It includes a first docking component, a second docking component, a first magnetic attraction unit, a second magnetic attraction unit, and a locking mechanism. The first docking component has a first docking end face, and the second docking component is fixed to a preset position on the space truss and has a second docking end face. The first magnetic attraction unit is mounted on the first docking end face, and the second magnetic attraction unit is mounted on the second docking end face and corresponds to the first magnetic attraction unit, generating magnetic attraction force during the docking approach phase to achieve pre-capture and posture correction. The locking mechanism is fitted onto the first docking component and can move axially and rotate circumferentially. After the docking surfaces reach the preset docking position, it moves axially to the locking position and rotates circumferentially to the locking position, forming an axial mechanical lock and a circumferential damping lock between the two docking components, improving assembly efficiency, reducing dependence on the absolute positioning accuracy of the robotic arm end effector, and improving connection reliability.

Description

Technical Field

[0001] This invention relates to the field of space on-orbit assembly and space truss connection technology, and in particular to a quick-connect locking joint device and its method of use for space trusses. Background Technology

[0002] With the development of large-scale space facilities such as space solar power stations, large-aperture space telescopes, and on-orbit service platforms, space truss structures have become important load-bearing frameworks for space infrastructure due to their lightweight, high specific stiffness, and strong scalability. Due to limitations in launch vehicle fairing size and launch capacity, large-volume space trusses are typically constructed using modular launch and on-orbit assembly methods. The connection links between members and joints are crucial to assembly efficiency, connection reliability, and structural stiffness.

[0003] Currently, space truss docking methods mostly rely on rigid alignment and mechanical insertion, which places extremely high demands on the positioning accuracy, attitude control accuracy, and initial alignment of the interface of the robotic arm. Any positional or attitude deviation can easily lead to collisions, jamming, and difficulty in fitting during the approach and contact phases, resulting in a reduced docking success rate. Although permanent magnet-assisted docking can generate adsorption, guide alignment, and attitude recovery during the approach phase, reducing the reliance on perfectly precise alignment, existing magnetic-assisted docking research is mostly geared towards interfaces for micro-spacecraft and has not fully considered the connection scenarios of space truss members and joints to develop a rapid-locking joint structure suitable for automated assembly.

[0004] Chinese patent CN114619219A discloses an on-orbit assembly platform for space trusses, and Chinese patent CN116374209A discloses an expandable triangular prism space truss unit structure. These patents provide a foundation for on-orbit assembly of space trusses from the perspectives of assembly execution platform and truss extension structure, respectively. However, specific structural solutions have not yet been developed for the specific connection details of truss members and joints during the docking process, such as magnetic pre-alignment, position and attitude correction, rapid locking, and stable locking.

[0005] Therefore, there is an urgent need to propose a rapid docking and locking joint device for connecting rods and joints, so as to improve the docking tolerance, connection reliability and automatic assembly adaptability of space trusses during on-orbit assembly. Summary of the Invention

[0006] The purpose of this invention is to provide a quick-connect locking joint device and method for use in space trusses, so as to solve the problems existing in the prior art, effectively improve assembly efficiency, effectively reduce the dependence of the robotic arm on the absolute positioning accuracy of the end effector, and effectively improve connection reliability.

[0007] To achieve the above objectives, the present invention provides the following solution: This invention provides a quick-connect locking joint device for a space truss, comprising: a first connecting member, a second connecting member, a first magnetic attraction unit, a second magnetic attraction unit, and a locking mechanism. The first connecting member has a first connecting end face; the second connecting member is fixedly disposed at a preset position on the space truss, and the second connecting member has a second connecting end face; the first magnetic attraction unit is installed on the first connecting end face; the second magnetic attraction unit is installed on the second connecting end face and is correspondingly disposed with the first magnetic attraction unit, and is used to generate magnetic attraction force during the approach phase of the first connecting end face and the second connecting end face to achieve pre-capture and posture correction of the first connecting member; the locking mechanism is sleeved on the first connecting member and can move axially and rotate circumferentially relative to the first connecting member, and can move axially to the locking position and rotate circumferentially to the locking position after the first connecting end face and the second connecting end face reach the preset connecting position under the action of magnetic attraction force, so that the first connecting member and the second connecting member form a mechanical lock in the axial direction and a damped lock in the circumferential direction.

[0008] Preferably, the first magnetic attraction unit includes a plurality of first permanent magnets and a plurality of second permanent magnets, the first permanent magnets and the second permanent magnets having opposite magnetic poles, and the first permanent magnets and the second permanent magnets being evenly spaced along the circumference of the first docking end face; the second magnetic attraction unit is correspondingly provided with a plurality of third permanent magnets and a plurality of fourth permanent magnets, the third permanent magnets and the fourth permanent magnets having opposite magnetic poles, the third permanent magnets and the fourth permanent magnets being evenly spaced along the circumference of the second docking end face, and the third permanent magnets being correspondingly provided with opposite magnetic poles to the first permanent magnets, and the fourth permanent magnets being correspondingly provided with opposite magnetic poles to the second permanent magnets.

[0009] Preferably, the locking mechanism includes a locking sleeve, at least one first elastic locking member, and at least one second elastic locking member. The locking sleeve is movably sleeved on the first docking member. The first and second elastic locking members are respectively disposed at both ends of the locking sleeve and can extend and retract along the radial direction of the locking sleeve. The outer periphery of the first docking member is provided with at least one first locking position, and the outer periphery of the second docking member is provided with at least one second locking position. When the locking sleeve rotates circumferentially to the locking position, the first elastic locking member engages with the first locking position of the first docking member, and the second elastic locking member engages with the second locking position of the second docking member, thereby achieving axial locking between the first docking member and the second docking member.

[0010] Preferably, there are multiple first elastic locking members, which are evenly arranged along the circumference of the locking sleeve. The number of first locking positions corresponds to the number of first elastic locking members, and the first locking positions are evenly arranged along the circumference of the first mating member. There are multiple second elastic locking members, which are evenly arranged along the circumference of the locking sleeve. The number of second locking positions corresponds to the number of second elastic locking members, and the second locking positions are evenly arranged along the circumference of the second mating member.

[0011] Preferably, the first elastic locking member includes a first spring seat, a plurality of first compression springs, a first slider, and a plurality of first screws. The locking sleeve is provided with a plurality of first sliding grooves, and the first locking position is a first axial locking groove that matches the first slider. The first spring seat is fixedly connected to the outside of the first sliding groove by the plurality of first screws. One end of the first compression spring is fixedly connected to the first spring seat, and the other end is fixedly connected to the first slider. The first slider is slidably connected to the first sliding groove along the radial direction of the locking sleeve, and can extend out of the first sliding groove under the action of the first compression spring and engage with the first axial locking groove. The second elastic locking element includes a second spring seat, multiple second compression springs, a second slider, and multiple second screws. The locking sleeve is provided with multiple second sliding grooves. The second locking position is a second axial locking groove that matches the second slider. The second spring seat is fixedly connected to the outside of the second sliding groove by multiple second screws. One end of the second compression spring is fixedly connected to the second spring seat, and the other end is fixedly connected to the second slider. The second slider is slidably connected to the second sliding groove along the radial direction of the locking sleeve, and can extend out of the second sliding groove under the action of the second compression spring and engage in the second axial locking groove.

[0012] Preferably, both ends of the first slider and both ends of the second slider are provided with a first smooth transition guide slope, and both ends of the first axial locking groove and both ends of the second axial locking groove are provided with a second smooth transition guide slope that cooperates with the first smooth transition guide slope.

[0013] Preferably, the locking mechanism further includes a first damping locking member and a second damping locking member. The first damping locking member is disposed on the outer periphery of the first docking member, and the second damping locking member is disposed on the inner wall of the locking sleeve. After the locking sleeve rotates to the locking position, the first damping locking member and the second damping locking member interact and generate a damping force in the circumferential direction, thereby restricting the locking sleeve from rotating circumferentially relative to the first docking member.

[0014] Preferably, the first damping locking element is a plurality of fifth permanent magnets disposed on the outer periphery of the first docking element, and the second damping locking element is a plurality of sixth permanent magnets disposed on the inner wall of the locking sleeve, wherein the fifth permanent magnets and the sixth permanent magnets have opposite magnetic poles.

[0015] Preferably, the first connecting member is a connecting rod, and the second connecting member is a crossbeam joint.

[0016] The present invention also provides a method of using the quick-connect locking joint device for space trusses as described in any of the preceding claims, comprising the following steps: S1: Drive the first docking member to move toward the second docking member, so that the first docking end face is close to the second docking end face; S2: When the distance between the first docking end face and the second docking end face enters the effective range of the first magnetic attraction unit and the second magnetic attraction unit, the magnetic attraction force generated between the first magnetic attraction unit and the second magnetic attraction unit is used to pre-capture, guide centering and attitude correction of the first docking part, so that the first docking end face and the second docking end face automatically fit together. S3: The first mating end face and the second mating end face are kept in a close fit under the action of magnetic attraction, and the preset mating position is reached; S4: Drive the locking mechanism to move along the axial direction of the first docking member to the locking position; S5: Drive the locking mechanism to rotate circumferentially relative to the first docking member to the locking position, so that the locking mechanism forms a mechanical lock in the axial direction and a damped lock in the circumferential direction between the first docking member and the second docking member.

[0017] The present invention achieves the following technical effects compared to the prior art: This invention provides a quick-connection locking joint device and method for use in space trusses. By setting a first magnetic attraction unit and a second magnetic attraction unit, the device can automatically pre-capture, guide centering, and correct attitude of the first docking component during the docking approach phase. This effectively reduces the requirements for the positioning accuracy and initial alignment accuracy of the robotic arm end effector during the automatic on-orbit assembly of the space truss, and improves the tolerance of the docking process. At the same time, through a locking mechanism that can move axially and rotate circumferentially, the device can quickly achieve axial mechanical locking and circumferential damping locking of the first and second docking components after docking. The locking process does not require complex operations, adapts to the needs of automatic space assembly, and greatly improves assembly efficiency and structural reliability after connection. This invention solves the problem of the lack of a dedicated quick-connection locking structure for space truss member-joint connection scenarios in the prior art, and can provide a reliable connection foundation for the modular on-orbit assembly of large space trusses. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 A schematic diagram of the quick-connect locking joint device for space trusses provided by the present invention; Figure 2 This is a schematic diagram of the structure of the first docking member in the quick-connect locking joint device for space trusses provided by the present invention; Figure 3 This is a schematic diagram of the structure of the second docking member in the quick-connect locking joint device for space trusses provided by the present invention; Figure 4 A schematic diagram of the locking mechanism in the quick-connect locking joint device for space trusses provided by the present invention; Figure 5 This is a front sectional view of the locking mechanism in the quick-connect locking joint device for space trusses provided by the present invention. Figure 6 This is a schematic diagram of the quick-connect locking joint device for space trusses provided by the present invention installed in a space truss. In the figure: 1. First docking component; 11. First axial locking groove; 111. Second smooth transition guide slope; 12. Fifth permanent magnet; 13. First docking end face; 2. Second docking component; 21. Second axial locking groove; 22. Second docking end face; 3. Locking mechanism; 31. Locking sleeve; 32. First elastic locking component; 321. First spring seat; 322. First compression spring; 323. First slider; 3231. First smooth transition guide slope; 324. First screw; 33. Sixth permanent magnet; 4. First magnetic attraction unit; 5. Second magnetic attraction unit; 6. Space truss. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] The purpose of this invention is to provide a quick-connect locking joint device and method for use in space trusses, so as to solve the problems existing in the prior art, effectively improve assembly efficiency, effectively reduce the dependence of the robotic arm on the absolute positioning accuracy of the end effector, and effectively improve connection reliability.

[0022] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0023] Example 1 This embodiment provides a quick-connect locking joint device for a space truss 6, such as... Figures 1-6 As shown, the assembly includes: a first docking component 1, a second docking component 2, a first magnetic attraction unit 4, a second magnetic attraction unit 5, and a locking mechanism 3. The first docking component 1 has a first docking end face 13; the second docking component 2 is fixedly installed at a preset position on the space truss 6, and the second docking component 2 has a second docking end face 22; the first magnetic attraction unit 4 is installed on the first docking end face 13; the second magnetic attraction unit 5 is installed on the second docking end face 22 and is correspondingly arranged with the first magnetic attraction unit 4, and is used to generate magnetic attraction force during the docking approach phase of the first docking end face 13 and the second docking end face 22, so as to achieve pre-capture and posture correction of the first docking component 1; the locking mechanism... Three magnetic units are mounted on the first docking member 1 and can move axially and rotate circumferentially relative to the first docking member 1. After the first docking end face 13 and the second docking end face 22 reach the preset docking position under the action of magnetic attraction, they can move axially to the locking position and rotate circumferentially to the locking position, so that the first docking member 1 and the second docking member 2 form a mechanical lock in the axial direction and a damped lock in the circumferential direction. By setting the first magnetic attraction unit 4 and the second magnetic attraction unit 5, the magnetic attraction is used to achieve pre-capture and posture correction of the first docking member 1 during the docking approach stage, reducing the dependence on high-precision initial alignment in the docking process and improving the fault tolerance of docking. The locking mechanism 3 can achieve axial mechanical locking and circumferential damped locking, ensuring that the structure has high stability in both the axial and circumferential directions after docking, meeting the reliability requirements of the docking of the space truss 6.

[0024] In a preferred embodiment, the first magnetic attraction unit 4 includes a plurality of first permanent magnets and a plurality of second permanent magnets, the first and second permanent magnets having opposite magnetic poles, and the first and second permanent magnets are evenly spaced along the circumference of the first docking end face 13; the second magnetic attraction unit 5 is correspondingly provided with a plurality of third permanent magnets and a plurality of fourth permanent magnets, the third and fourth permanent magnets having opposite magnetic poles, and the third and fourth permanent magnets are evenly spaced along the circumference of the second docking end face 22, and the third permanent magnets are opposite to the first permanent magnets. The four permanent magnets are set with opposite magnetic poles and are set with opposite magnetic poles. Multiple permanent magnets are evenly spaced on the docking end face with corresponding magnetic poles. The alternating magnetic poles can automatically adjust the position and posture of the first docking part 1 through the combined action of opposite poles attracting and like poles repelling when there is an initial position or attitude deviation. This pushes the first docking part 1 to rotate to the correct alignment posture, completes self-alignment and correction, and ensures that the two docking end faces can accurately fit together without the need for additional power to adjust the position and posture. This meets the requirements of automatic on-orbit assembly in space and greatly reduces the requirements for initial alignment accuracy during the docking process.

[0025] In a preferred embodiment, the locking mechanism 3 includes a locking sleeve 31, at least one first elastic locking member 32, and at least one second elastic locking member. The locking sleeve 31 is movably sleeved on the first docking member 1. The first elastic locking member 32 and the second elastic locking member are respectively disposed at both ends of the locking sleeve 31 and can extend and retract along the radial direction of the locking sleeve 31. The outer periphery of the first docking member 1 is provided with at least one first locking position, and the outer periphery of the second docking member 2 is provided with at least one second locking position. When the locking sleeve 31 rotates circumferentially to the locking position, the first elastic locking member 32 engages with the first locking position of the first docking member 1, and the second elastic locking member engages with the second locking position of the second docking member 2, thereby achieving axial locking of the first docking member 1 and the second docking member 2. This structural design achieves axial locking by rotating the locking sleeve 31 and utilizing the first elastic locking member 32 and the second elastic locking member to cooperate with the locking positions on the first docking member 1 and the second docking member 2, respectively. The structure is simple and easy to operate. The telescopic characteristic of the elastic locking element allows the locking sleeve 31 to automatically extend and engage with the corresponding locking position after rotating to the locking position. This eliminates the need for additional positioning and fixing operations, achieving axial locking and further enhancing the convenience of docking and locking. Simultaneously, the elastic force ensures that the locking element remains tightly fitted to the locking position, improving the stability of the connection structure.

[0026] To a certain extent, it compensates for minor deviations during the docking process, improves the reliability and adaptability of axial locking, and ensures a stable connection in the axial direction after the space truss 6 is docked.

[0027] In a preferred embodiment, there are multiple first elastic locking elements 32, which are evenly arranged along the circumference of the locking sleeve 31. The number of first locking positions corresponds to the number of first elastic locking elements 32, and the first locking positions are evenly arranged along the circumference of the first mating member 1. There are multiple second elastic locking elements, which are evenly arranged along the circumference of the locking sleeve 31. The number of second locking positions corresponds to the number of second elastic locking elements, and the second locking positions are evenly arranged along the circumference of the second mating member 2. The multiple elastic locking elements and locking positions are evenly arranged in the circumference, which makes the axial locking force more evenly distributed in the circumference, avoiding the situation of excessive or insufficient local force, further enhancing the stability and reliability of the structure in the axial direction after docking, and improving the ability of the entire joint device to withstand complex loads.

[0028] In a preferred embodiment, the first elastic locking member 32 includes a first spring seat 321, a plurality of first compression springs 322, a first slider 323, and a plurality of first screws 324. The locking sleeve 31 is provided with a plurality of first sliding grooves, and the first locking position is a first axial locking groove 11 that matches the first slider 323. The first spring seat 321 is fixedly connected to the outside of the first sliding groove by a plurality of first screws 324. One end of the first compression spring 322 is fixedly connected to the first spring seat 321, and the other end is fixedly connected to the first slider 323. The first slider 323 is slidably connected to the first sliding groove along the radial direction of the locking sleeve 31, and can extend out of the first sliding groove under the action of the first compression spring 322 to engage the first... The axial locking groove 11 is located within the second elastic locking element, which includes a second spring seat, multiple second compression springs, a second slider, and multiple second screws. The locking sleeve 31 has multiple second sliding grooves, and the second locking position is the second axial locking groove 21 that matches the second slider. The second spring seat is fixedly connected to the outside of the second sliding groove by multiple second screws. One end of the second compression spring is fixedly connected to the second spring seat, and the other end is fixedly connected to the second slider. The second slider slides along the radial direction of the locking sleeve 31 in the second sliding groove and can extend out of the second sliding groove under the action of the second compression spring, engaging in the second axial locking groove 21. The detailed structural design makes the working principles of the first elastic locking element 32 and the second elastic locking element clear and explicit. The combination of the spring seat, compression spring, slider, and screws utilizes the elastic force of the compression spring to push the slider into the locking groove, achieving axial locking. This structure has good elasticity and reliability, can work stably under different docking conditions, and is easy to manufacture, install, and maintain.

[0029] In a preferred embodiment, both ends of the first slider 323 and both ends of the second slider are provided with first smooth transition guide slopes 3231, and both ends of the first axial locking groove 11 and both ends of the second axial locking groove 21 are provided with second smooth transition guide slopes 111 that cooperate with the first smooth transition guide slopes 3231. The smooth transition guide slopes help the sliders to engage and disengage from the locking grooves more smoothly, reducing the occurrence of jamming. During docking and unlocking, this design can improve the flexibility and efficiency of operation, while also reducing wear on components and extending the service life of the connector device.

[0030] In a preferred embodiment, the locking mechanism 3 further includes a first damping locking member and a second damping locking member. The first damping locking member is disposed on the outer periphery of the first docking member 1, and the second damping locking member is disposed on the inner wall of the locking sleeve 31. After the locking sleeve 31 rotates to the locking position, the first damping locking member and the second damping locking member interact and generate a damping force in the circumferential direction, which restricts the circumferential rotation of the locking sleeve 31 relative to the first docking member 1. By setting the first damping locking member and the second damping locking member, a damping force is generated in the circumferential direction, which effectively restricts the circumferential rotation of the locking sleeve 31 relative to the first docking member 1, further enhancing the circumferential stability of the structure after docking, preventing the reliability of the entire space truss 6 structure from being affected by the circumferential loosening of the locking sleeve 31, and improving the working performance of the joint device in complex space environments.

[0031] In a preferred embodiment, the first damping locking element consists of a plurality of fifth permanent magnets 12 disposed on the outer periphery of the first mating member 1, and the second damping locking element consists of a plurality of sixth permanent magnets 33 disposed on the inner wall of the locking sleeve 31. The fifth permanent magnets 12 and the sixth permanent magnets 33 have opposite magnetic poles, and the attractive force generated by the opposite magnetic poles of the permanent magnets serves as the damping force, resulting in a simple and reliable structure. The arrangement of the permanent magnets can form a continuous and uniform damping force in the circumferential direction, effectively suppressing circumferential rotation. This design eliminates the need for additional complex mechanical structures, reduces the number of parts, lowers the weight and complexity of the device, and simultaneously improves the stability and reliability of circumferential locking.

[0032] In a preferred embodiment, the first connecting member 1 is a connecting rod, and the second connecting member 2 is a beam joint. This clarifies the specific application of the joint device in the space truss 6 structure, making the entire technical solution closely integrated with the actual connection requirements of the space truss 6. This approach is more targeted and practical, and helps to improve the docking efficiency and connection quality between the members of the space truss 6 and the beam joint.

[0033] Example 2 This embodiment also provides a method of using the quick-connect locking joint device for space truss 6 as described in any of Embodiment 1, including the following steps: 1. Docking process: Approach and Pre-capture: An external device (such as a robotic arm) is manipulated to grasp the first docking member 1 (dating rod), causing its first docking end face 13 to move toward the second docking end face 22 of the second docking member 2 (beam connector). When the first docking member 1 enters the effective range of the first magnetic attraction unit 4 and the second magnetic attraction unit 5, a magnetic attraction force is generated between them. Since the first permanent magnet, the second permanent magnet, the third permanent magnet and the fourth permanent magnet are evenly spaced circumferentially on the docking end face and their magnetic poles correspond, the magnetic attraction force acts evenly in the circumferential direction, achieving pre-capture of the first docking member 1 and correcting its posture, guiding the first docking member 1 toward the second docking member 2.

[0034] Reaching the preset docking position: Under the combined action of magnetic attraction and fine adjustment by external equipment, the first docking end face 13 of the first docking component 1 and the second docking end face 22 of the second docking component 2 gradually approach and finally fit together, reaching the preset docking position.

[0035] 2. Locking process: Axial movement locking sleeve 31: External equipment pushes the locking sleeve 31 of the locking mechanism 3, causing it to move axially along the first docking member 1 (docking rod) to the locking position. During this process, it is necessary to ensure that the locking sleeve 31 moves smoothly without any jamming.

[0036] Axial locking is achieved through circumferential rotation: The locking sleeve 31 continues to rotate via external equipment. When it reaches the locking position, the first elastic locking member 32 and the second elastic locking member located at both ends of the locking sleeve 31 extend radially under the action of their respective compression springs and engage with the first locking position (first axial locking groove 11) of the first mating member 1 and the second locking position (second axial locking groove 21) of the second mating member 2. Since the first elastic locking member 32 and the second elastic locking member are evenly arranged circumferentially at both ends of the locking sleeve 31, and their number matches the corresponding locking positions, this ensures stable mechanical locking of the first mating member 1 and the second mating member 2 in the axial direction. During this process, the first smooth transition guide slope 3231 at both ends of the first slider 323 and the second slider cooperate with the second smooth transition guide slope 111 at both ends of the first axial locking groove 11 and the second axial locking groove 21, guiding the slider smoothly into the locking groove and reducing the risk of jamming.

[0037] Circumferential damping locking: After the locking sleeve 31 rotates to the locking position, the first damping locking element (multiple fifth permanent magnets 12) set on the outer periphery of the first docking member 1 interacts with the second damping locking element (two rows of sixth permanent magnets 33) set on both ends of the inner wall of the locking sleeve 31. Since the magnetic poles of the fifth permanent magnets 12 and the sixth permanent magnets 33 are opposite, a damping force will be generated in the circumferential direction, which restricts the circumferential rotation of the locking sleeve 31 relative to the first docking member 1, thereby realizing circumferential damping locking and further enhancing the stability of the docking structure.

[0038] 5. Disassembly process (if necessary): Unlocking circumferential damping: By applying a certain torque through an external device, the damping force between the first damping locking member and the second damping locking member is overcome, so that the locking sleeve 31 can rotate circumferentially relative to the first docking member 1.

[0039] Unlocking the axial lock: Rotate the locking sleeve 31 in the opposite direction. With the cooperation of the first smooth transition guide slope 3231 and the second smooth transition guide slope 111, the first elastic locking member 32 and the second elastic locking member retract radially respectively, disengaging from the first locking position of the first docking member 1 and the second locking position of the second docking member 2, thereby releasing the axial lock.

[0040] Separate the docking parts: retract the locking sleeve 31 along the axial direction of the first docking part 1, and then separate the first docking part 1 (dock rod) from the second docking part 2 (beam joint) using external equipment to complete the disassembly process.

[0041] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A quick-connect locking joint device for space trusses, characterized in that: include: A first mating component, the first mating component having a first mating end face; The second docking member is used to be fixedly installed at a preset position on the space truss, and the second docking member has a second docking end face; A first magnetic attraction unit is mounted on the first docking end face; The second magnetic attraction unit is installed on the second docking end face and is correspondingly arranged with the first magnetic attraction unit. It is used to generate magnetic attraction force during the docking approach stage of the first docking end face and the second docking end face to achieve pre-capture and posture correction of the first docking part. The locking mechanism is sleeved on the first docking member and can move axially and rotate circumferentially relative to the first docking member. After the first docking end face and the second docking end face reach the preset docking position under the action of magnetic attraction, the locking mechanism can move axially to the locking position and rotate circumferentially to the locking position, so that the first docking member and the second docking member form a mechanical lock in the axial direction and a damping lock in the circumferential direction.

2. The quick-connect locking joint device for space trusses according to claim 1, characterized in that: The first magnetic attraction unit includes multiple first permanent magnets and multiple second permanent magnets, the first permanent magnets and the second permanent magnets having opposite magnetic poles, and the first permanent magnets and the second permanent magnets are evenly spaced along the circumference of the first docking end face; the second magnetic attraction unit is correspondingly provided with multiple third permanent magnets and multiple fourth permanent magnets, the third permanent magnets and the fourth permanent magnets having opposite magnetic poles, the third permanent magnets and the fourth permanent magnets are evenly spaced along the circumference of the second docking end face, and the third permanent magnets are correspondingly provided with opposite magnetic poles to the first permanent magnets, and the fourth permanent magnets are correspondingly provided with opposite magnetic poles to the second permanent magnets.

3. The quick-connect locking joint device for space trusses according to claim 1, characterized in that: The locking mechanism includes a locking sleeve, at least one first elastic locking member, and at least one second elastic locking member. The locking sleeve is movably sleeved on the first docking member. The first and second elastic locking members are respectively disposed at both ends of the locking sleeve and can extend and retract along the radial direction of the locking sleeve. The outer periphery of the first docking member is provided with at least one first locking position, and the outer periphery of the second docking member is provided with at least one second locking position. When the locking sleeve rotates circumferentially to the locking position, the first elastic locking member engages with the first locking position of the first docking member, and the second elastic locking member engages with the second locking position of the second docking member, thereby achieving axial locking of the first docking member and the second docking member.

4. The quick-connect locking joint device for space trusses according to claim 3, characterized in that: The number of first elastic locking elements is multiple and they are evenly arranged along the circumference of the locking sleeve. The number of first locking positions corresponds to the number of first elastic locking elements and the first locking positions are evenly arranged along the circumference of the first mating member. The number of second elastic locking elements is multiple and they are evenly arranged along the circumference of the locking sleeve. The number of second locking positions corresponds to the number of second elastic locking elements and the second locking positions are evenly arranged along the circumference of the second mating member.

5. The quick-connect locking joint device for space trusses according to claim 4, characterized in that: The first elastic locking member includes a first spring seat, a plurality of first compression springs, a first slider and a plurality of first screws. The locking sleeve is provided with a plurality of first sliding grooves. The first locking position is a first axial locking groove that matches the first slider. The first spring seat is fixedly connected to the outside of the first sliding groove by a plurality of first screws. One end of the first compression spring is fixedly connected to the first spring seat and the other end is fixedly connected to the first slider. The first slider is slidably connected to the first sliding groove along the radial direction of the locking sleeve and can extend out of the first sliding groove under the action of the first compression spring and engage in the first axial locking groove. The second elastic locking element includes a second spring seat, a plurality of second compression springs, a second slider, and a plurality of second screws. The locking sleeve is provided with a plurality of second sliding grooves. The second locking position is a second axial locking groove that matches the second slider. The second spring seat is fixedly connected to the outside of the second sliding groove by a plurality of second screws. One end of the second compression spring is fixedly connected to the second spring seat, and the other end is fixedly connected to the second slider. The second slider is slidably connected to the second sliding groove along the radial direction of the locking sleeve, and can extend out of the second sliding groove under the action of the second compression spring and engage in the second axial locking groove.

6. The quick-connect locking joint device for space trusses according to claim 5, characterized in that: Both ends of the first slider and both ends of the second slider are provided with a first smooth transition guide slope, and both ends of the first axial locking groove and both ends of the second axial locking groove are provided with a second smooth transition guide slope that cooperates with the first smooth transition guide slope.

7. The quick-connect locking joint device for space trusses according to claim 6, characterized in that: The locking mechanism further includes a first damping locking member and a second damping locking member. The first damping locking member is disposed on the outer periphery of the first docking member, and the second damping locking member is disposed on the inner wall of the locking sleeve. After the locking sleeve rotates to the locking position, the first damping locking member and the second damping locking member interact and generate a damping force in the circumferential direction, thereby restricting the locking sleeve from rotating circumferentially relative to the first docking member.

8. The quick-connect locking joint device for space trusses according to claim 7, characterized in that: The first damping locking element is a plurality of fifth permanent magnets disposed on the outer periphery of the first docking element, and the second damping locking element is a plurality of sixth permanent magnets disposed on the inner wall of the locking sleeve, wherein the fifth permanent magnets and the sixth permanent magnets have opposite magnetic poles.

9. The quick-connect locking joint device for space trusses according to claim 1, characterized in that: The first connecting member is a connecting rod, and the second connecting member is a crossbeam joint.

10. A method of using the quick-connect locking joint device for space trusses as described in any one of claims 1 to 9, characterized in that: Includes the following steps: S1: Drive the first docking member to move toward the second docking member, so that the first docking end face is close to the second docking end face; S2: When the distance between the first docking end face and the second docking end face enters the effective range of the first magnetic attraction unit and the second magnetic attraction unit, the magnetic attraction force generated between the first magnetic attraction unit and the second magnetic attraction unit is used to pre-capture, guide centering and attitude correction of the first docking part, so that the first docking end face and the second docking end face automatically fit together. S3: The first mating end face and the second mating end face are kept in a close fit under the action of magnetic attraction, and the preset mating position is reached; S4: Drive the locking mechanism to move along the axial direction of the first docking member to the locking position; S5: Drive the locking mechanism to rotate circumferentially relative to the first docking member to the locking position, so that the locking mechanism forms a mechanical lock in the axial direction and a damped lock in the circumferential direction between the first docking member and the second docking member.

Images