Connecting device and spacecraft
By designing a connecting device including a lock body assembly and a magnetic component, the impact load and safety hazards existing in the spacecraft of the traditional compression and release device are solved, and the safe and reliable connection and separation between the module and the spacecraft body is achieved.
Patent Information
- Application Number
- CN202510156143.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-12
- Publication Date
- 2025-05-06
AI Technical Summary
During the launch and operation of spacecraft, traditional compression release devices have problems such as large impact loads and safety hazards after triggering.
A connecting device is designed, including a first connecting module and a second connecting module. Through the cooperation of the lock body assembly and the magnetic assembly, a safe and reliable connection and separation between the module and the spacecraft body is achieved.
It realizes safe and reliable connection and separation between the module and the spacecraft body, with almost no impact load, reduces safety hazards and improves the safety and reliability of the spacecraft.
Smart Images
Figure CN119929195A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of aerospace technology, and in particular to a connection device and a spacecraft. Background Art
[0002] In the design of spacecraft, especially during the launch and operation of satellites, it is crucial to ensure that some modules or auxiliary equipment that need to be deployed can be safely and reliably fixed on the spacecraft and can be accurately separated from the spacecraft when needed. This is accomplished by specially designed clamping and releasing devices. Traditional clamping and releasing devices mainly rely on pyrotechnic triggering. Although the separation is reliable and the actuation time is short, they also have the disadvantages of generating a large impact load after triggering and obvious safety hazards. Summary of the invention
[0003] The purpose of the present application is to provide a connection device and a spacecraft in view of at least one technical problem involved in the background technology.
[0004] In order to achieve the above objectives, this application adopts the following technical solutions:
[0005] One aspect of the present application provides a connection device, including a first connection module and a second connection module, the first connection module including a first connection block, a lock body assembly and a magnetic assembly, a receiving cavity is formed in the first connection block, the magnetic assembly is fixed to the inner wall of the receiving cavity, the lock body assembly is arranged in the receiving cavity, a socket connected to the receiving cavity is formed on the first connection block, the second connection module includes a second connection block and a pin fixed to the second connection block, the pin is used to be plugged into the socket in a first direction, the lock body assembly is used to lock the pin, and the magnetic assembly is used to drive the lock body assembly by magnetic force so that the pin can be separated from the first connection module.
[0006] Optionally, the lock body assembly includes a lock body, an elastic member and a locking unit, wherein the locking unit is installed on the inner wall of the accommodating cavity, the locking unit is arranged close to the insertion hole, the lock body is used to slide with the inner wall of the accommodating cavity in the first direction, and the elastic member is pressure-fitted with the lock body and the inner wall of the accommodating cavity, so that the lock body presses the locking unit toward the side of the insertion hole in the first direction, thereby causing the locking unit to lock the latch.
[0007] The beneficial effect of this technical solution is that the elastic member is a pressure spring, one end of the pressure spring is pressure-matched with the lock body in the first direction, and the other end of the pressure spring is pressure-matched with the inner wall of the accommodating cavity.
[0008] Optionally, the accommodating cavity includes a guide portion, which is coaxially arranged with the socket, the lock body and the inner wall of the guide portion are slidably matched in the first direction, the inner diameter of the guide portion is larger than the inner diameter of the socket, a limiting step is formed between the inner wall of the guide portion and the inner wall of the socket, and the locking unit is installed on the limiting step.
[0009] The beneficial effect of this technical solution is that by setting the guide part, the moving direction of the lock body can be limited by the inner wall of the guide part, thereby improving the accuracy of the lock body movement, thereby improving the reliability of the lock body locking and releasing the latch, and making the performance of the connecting device more reliable and stable.
[0010] Optionally, the locking unit includes a plurality of steel balls and a steel ball locking sleeve, the steel ball locking sleeve being coaxially arranged with the insertion hole, one end of the steel ball locking sleeve being fixed to the limiting step in the first direction, a plurality of steel ball limiting holes being formed on the steel ball locking sleeve, each of the steel ball limiting holes being evenly distributed in the circumferential direction of the steel ball locking sleeve, the diameter of the steel ball limiting holes being smaller than the diameter of the steel balls, each of the steel balls being arranged on the limiting step, each of the steel balls being located between the steel ball locking sleeve and the inner wall of the guide portion, each of the steel balls being matched with each of the steel ball limiting holes in a one-to-one manner, and the lock body being used to be inserted between the inner wall of the guide portion and each of the steel balls to squeeze each of the steel balls, so that each of the steel balls extends into the inner cavity of the steel ball locking sleeve and locks the latch.
[0011] The beneficial effect of this technical solution is that: in this way, when the pin is located in the socket and the steel ball locking sleeve, each steel ball extends from each steel ball limiting hole into the inner cavity of the steel ball locking sleeve under the extrusion of the lock body, locking the pin, making the first connection module and the second connection module unable to be separated; when magnetic force is generated between the lock body assembly and the magnetic assembly, the extrusion of the lock body on each steel ball fails, so that the lock pin can be pulled out of the steel ball locking sleeve and the socket, thereby realizing the separation of the first connection module and the second connection module.
[0012] Optionally, a hemispherical groove is formed on the lock body from the notch toward the socket, the hemispherical groove is coaxially arranged with the socket, an action portion is provided between the hemispherical groove and the outer wall of the lock body, and the action portion is used to be inserted between the inner wall of the guide portion and each of the steel balls.
[0013] The beneficial effect of this technical solution is that: in this way, the action part is a wedge-shaped structure with a thickness gradually increasing from the side close to the socket to the side away from the socket, and the wedge-shaped structure is inserted between the steel ball and the inner wall of the guide part to form an extrusion limit for the steel ball, thereby locking the pin inserted into the socket and the steel ball locking sleeve, and the hemispherical groove can be used to accommodate the part of the pin inserted into the accommodating cavity; in the process of inserting the pin into the socket, the pin will push each steel ball, so that each steel ball overcomes the pressure formed by the elastic member acting on the lock body and retracts into the steel ball limiting hole, and when the end of the pin enters the hemispherical groove, each steel ball is again extended into the inner cavity of the steel ball locking sleeve under the extrusion of the lock body, forming a limit for the pin, so that the pin cannot be pulled out of the socket.
[0014] Optionally, the lock body assembly further includes a buffering and limiting pad, which is fixed to the bottom of the hemispherical groove and is used for pressure contact with the latch.
[0015] The beneficial effect of this technical solution is that when the pin is inserted into the socket and the steel ball locking sleeve, it will elastically contact with the buffer limit pad, reducing the damage that may be caused by the collision. After each steel ball locks the pin, the pin and the buffer limit pad are pressure-contacted, so that the end of the pin is stably fixed between each steel ball and the buffer limit pad, thereby improving the stability of the connection between the first connecting module and the second connecting module.
[0016] Optionally, the latch includes an end and an insertion rod, one end of the insertion rod is fixed to the second connecting block, and the other end of the insertion rod is fixed to the end, the end and the insertion rod are both used to be coaxially arranged with the socket, and the diameter of the end is larger than the diameter of the insertion rod.
[0017] The beneficial effect of this technical solution is that when the end head is inserted into the steel ball locking sleeve and passes over each steel ball, each steel ball will extend into the L-shaped gap formed between the end head and the insertion rod, thereby forming a limit for the end head, making it difficult to pull the end head out of the socket.
[0018] Optionally, the lock body assembly further includes an iron core unit, the iron core unit includes a coil and an iron core, the iron core is fixed to the lock body, the coil is fixed to the iron core, the magnetic assembly includes a permanent magnet, the permanent magnet is fixed to the inner wall of the accommodating cavity, and the permanent magnet and the iron core unit are arranged in the first direction.
[0019] Optionally, the lock body assembly includes two core units, which are located on both sides of the lock body in the second direction, and the core units protrude from the lock body in the second direction. The permanent magnet is an annular structure coaxially arranged with the socket, and the permanent magnet is opposite to the two core units in the first direction, and the second direction is perpendicular to the first direction.
[0020] Another aspect of the present application provides a spacecraft, including a spacecraft body, a deployable module, and the connection device provided by the present application, wherein the spacecraft body has a mounting surface, the first connection module is fixed to the mounting surface, and the axial direction of the plug hole is perpendicular to the mounting surface;
[0021] The connecting device further comprises an extension bracket, the expandable module is hinged to the mounting surface, the extension bracket is mounted on the expandable module, the extension bracket extends outward from the expandable module in a direction parallel to the mounting surface, and the second connecting module is fixed to the extension bracket;
[0022] Alternatively, the expandable module includes a first functional unit and a second functional unit, the first functional unit and the second functional unit are stacked in sequence on the mounting surface, one end of the first functional unit is hinged to the mounting surface in a direction parallel to the mounting surface, the other end of the first functional unit is hinged to the second functional unit, the second connecting module is fixed to the second functional unit, and the first connecting module is used to pass through the first functional unit and connect to the second connecting module.
[0023] The technical solution provided by this application can achieve at least one of the following beneficial effects:
[0024] The connection device and spacecraft provided in the present application realize the connection between the module and the spacecraft body through the connection between the first connection module and the second connection module, or realize the pressing of the module onto the spacecraft body, and realize the separation between the module and the spacecraft body through the magnetic action between the lock body assembly and the magnetic assembly, or realize the deployment of the module from the spacecraft body, with almost no impact load and relatively small safety hazards, thereby improving the safety and reliability of the spacecraft.
[0025] The additional technical features and advantages of the present application will be more clearly explained in the following description, or can be understood through the specific practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS
[0026] In order to more clearly illustrate the technical solutions of the specific implementation methods of the present application, the following is a brief introduction to the drawings required for the description of the specific implementation methods. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.
[0027] Figure 1 A schematic diagram of the internal structure of a connection device in one state according to an implementation mode of the present application;
[0028] Figure 2A schematic diagram of the internal structure of an implementation of a connecting device provided in an embodiment of the present application in another state;
[0029] Figure 3 A partial structural diagram of an implementation manner of a first connection module provided in an embodiment of the present application;
[0030] Figure 4 A partial structural schematic diagram of an implementation method of a spacecraft provided in an embodiment of the present application;
[0031] Figure 5 for Figure 4 A local enlarged schematic diagram of the A region;
[0032] Figure 6 A partial structural schematic diagram of another implementation manner of a spacecraft provided in an embodiment of the present application;
[0033] Figure 7 for Figure 6 A local enlarged schematic diagram of the B region;
[0034] Figure 8 A schematic diagram of a portion of the structure of a spacecraft in one state of an implementation mode provided in an embodiment of the present application;
[0035] Fig. 9 A schematic diagram of a portion of the structure of a spacecraft in another state according to an implementation mode of the present application;
[0036] Fig.10 A schematic diagram of the partial structure of a spacecraft in a third state according to an embodiment of the present application.
[0037] Reference numerals:
[0038] 01. Second connecting block; 02. Latch;
[0039] 03. Steel ball; 04. Steel ball locking sleeve;
[0040] 05. First connecting block; 06. Coil;
[0041] 07. Iron core; 08. Permanent magnet;
[0042] 09. Buffer washer; 10. Guide column;
[0043] 11. Pressure spring; 12. Guide sleeve;
[0044] 13. Lock body; 14. Action part;
[0045] 15. Buffer limit pad; 16. Limit step;
[0046] 17. Insertion rod; 18. End;
[0047] 19. Socket; 20. Steel ball limit hole;
[0048] 21. Spacecraft body; 22. Connecting device;
[0049] 23. First functional unit; 24. Second functional unit;
[0050] 25. Hinge; 26. Mounting bracket;
[0051] 27. A first connection module; 28. A second connection module;
[0052] 29. gland portion; 30. second SAR antenna array;
[0053] 31. First SAR antenna array; 32. Extension bracket;
[0054] 33. Column pad; 34. Accommodation cavity;
[0055] 35. Threaded rod. DETAILED DESCRIPTION
[0056] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present application.
[0057] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.
[0058] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.
[0059] like Figures 1 to 10 As shown, one aspect of the present application provides a connecting device 22, including a first connecting module 27 and a second connecting module 28, the first connecting module 27 including a first connecting block 05, a lock body assembly and a magnetic assembly, a receiving cavity 34 is formed in the first connecting block 05, the magnetic assembly is fixed to the inner wall of the receiving cavity 34, the lock body assembly is arranged in the receiving cavity 34, a socket 19 connected to the receiving cavity 34 is formed on the first connecting block 05, the second connecting module 28 includes a second connecting block 01 and a latch 02 fixed to the second connecting block 01, the latch 02 is used to be plugged into the socket 19 in a first direction, the lock body assembly is used to lock the latch 02, and the magnetic assembly is used to drive the lock body assembly by magnetic force so that the latch 02 can be separated from the first connecting module 27.
[0060] The connection device 22 provided in the present application is used for a detachable module separated from a spacecraft body 21, or for a deployable module deployed from a spacecraft body 21, when in use, to be fixed to the spacecraft body 21 through the connection device 22, the first connection module 27 is fixed to the spacecraft body 21, the second connection module 28 is fixed to the detachable module or the deployable module, or the second connection module 28 is fixed to the spacecraft body 21, the first connection module 27 is fixed to the detachable module or the deployable module, the latch 200 is inserted into the socket 19, and the latch 200 is inserted into the socket 19 through the lock body assembly The latch 02 is locked to fix the detachable module or the deployable module on the spacecraft body 21. When the detachable module needs to be separated from the spacecraft body 21, or the deployable module needs to be deployed from the spacecraft body 21, the lock body assembly is driven by the magnetic force between the magnetic assembly and the lock body assembly, so that the latch 02 can be separated from the first connecting module 27, and then the first connecting module 27 and the second connecting module 28 can be separated, thereby achieving the purpose of separating the detachable module from the spacecraft body 21, or deploying the deployable module from the spacecraft body 21.
[0061] The connecting device 22 provided in the present application realizes the connection between the module and the spacecraft body 21, or realizes pressing the module on the spacecraft body 21, and realizes the separation between the module and the spacecraft body 21 through the magnetic force between the lock body assembly and the magnetic assembly, or realizes the deployment of the module from the spacecraft body 21, with almost no impact load and relatively small safety hazards, thereby improving the safety and reliability of the spacecraft; moreover, when the module is used to be deployed from the spacecraft body 21, when the module is folded or compressed again, the same connecting device 22 can still be used again. Compared with the compression and release devices that rely on pyrotechnics and are based on hot knives and can only be used once in the current field, the utilization rate of the connecting device 22 is higher, thereby reducing the use cost of the spacecraft; and, compared with the compression and release devices that are used during the release process, the connection device 22 can be used again. The compression and release devices that rely on pyrotechnics and the compression and release devices based on hot knives will generate smoke and dust pollution during the process. The connection device 22 provided in the present application does not generate smoke and dust and will not pollute the environment. At the same time, the compression and release devices commonly used in the field currently also include shape memory alloy compression and release devices driven by the shape memory effect of shape memory alloys. They do not generate separation shock and smoke and dust pollution, can be used repeatedly, overcome the defects of pyrotechnic devices, and have great advantages in the connection and separation of satellites. However, the release time of the shape memory alloy compression and release device is generally long, and it is not suitable for situations where synchronous release is required. However, the connection device 22 provided in the present application realizes the separation between the first connection module 27 and the second connection device 22 under the action of magnetic force, thereby achieving the purpose of releasing the module from the spacecraft body 21. The required implementation is short and the release efficiency is high, which is more suitable for situations where synchronous release is required.
[0062] Optionally, the lock body assembly includes a lock body 13, an elastic member and a locking unit, wherein the locking unit is installed on the inner wall of the accommodating cavity 34, and the locking unit is arranged close to the insertion hole 19. The lock body 13 is used to slide with the inner wall of the accommodating cavity 34 in the first direction, and the elastic member is pressure-fitted with the lock body 13 and the inner wall of the accommodating cavity 34, so that the lock body 13 squeezes the locking unit toward the side of the insertion hole 19 in the first direction, thereby causing the locking unit to lock the latch 02.
[0063] The elastic member is a pressure spring 11, one end of the pressure spring 11 is pressure-matched with the lock body 13 in the first direction, and the other end of the pressure spring 11 is pressure-matched with the inner wall of the accommodating chamber 34. In the embodiment of the present application, preferably, the pressure spring 11 is coaxially arranged with the jack 19 and the latch 02. Preferably, a guide post 10 extending in the first direction is fixed on the inner wall of the accommodating chamber 34, and a guide sleeve 12 is arranged on the lock body 13. The guide post 10 and the guide sleeve 12 are plugged and slidably matched in the first direction, and the pressure spring 11 is sleeved outside the guide sleeve 12, thereby improving the accuracy and stability of the movement of the lock body 13. Of course, the elastic member can also be a tension spring, and the tension spring and the locking unit are both located on the same side of the lock body 13, and the two ends of the tension spring are respectively fixedly connected to the lock body 13 and the inner wall of the accommodating chamber 34. Under the action of the tension of the tension spring, the lock body 13 is biased in a state of squeezing the locking unit.
[0064] Optionally, the accommodating cavity 34 includes a guide portion, the guide portion is coaxially arranged with the insertion hole 19, the lock body 13 and the inner wall of the guide portion are slidably matched in the first direction, the inner diameter of the guide portion is larger than the inner diameter of the insertion hole 19, a limiting step 16 is formed between the inner wall of the guide portion and the inner wall of the insertion hole 19, and the locking unit is installed on the limiting step 16. By providing the guide portion, the moving direction of the lock body 13 can be limited by the inner wall of the guide portion, the accuracy of the movement of the lock body 13 is improved, so as to improve the reliability of the lock body 13 locking and releasing the bolt 02, and make the performance of the connecting device 22 more reliable and stable.
[0065] Optionally, the locking unit includes a plurality of steel balls 03 and a steel ball locking sleeve 04, the steel ball locking sleeve 04 is coaxially arranged with the insertion hole 19, one end of the steel ball locking sleeve 04 is fixed to the limiting step 16 in the first direction, a plurality of steel ball limiting holes 20 are formed on the steel ball locking sleeve 04, each of the steel ball limiting holes 20 is evenly distributed in the circumferential direction of the steel ball locking sleeve 04, the diameter of the steel ball limiting hole 20 is smaller than the diameter of the steel ball 03, each of the steel balls 03 is arranged on the limiting step 16, each of the steel balls 03 is located between the steel ball locking sleeve 04 and the inner wall of the guide portion, each of the steel balls 03 is matched with each of the steel ball limiting holes 20 in a one-to-one manner, and the lock body 13 is used to be inserted between the inner wall of the guide portion and each of the steel balls 03 to squeeze each of the steel balls 03, so that each of the steel balls 03 extends into the inner cavity of the steel ball locking sleeve 04 and locks the latch 02. In this way, when the bolt 02 is located in the insertion hole 19 and the steel ball locking sleeve 04, each steel ball 03 extends from each steel ball limiting hole 20 into the inner cavity of the steel ball locking sleeve 04 under the extrusion of the lock body 13, locking the bolt 02, so that the first connection module 27 and the second connection module 28 cannot be separated. When the magnetic force is generated between the lock body assembly and the magnetic assembly, the extrusion of each steel ball 03 by the lock body 13 fails, so that the lock pin can be pulled out from the steel ball locking sleeve 04 and the insertion hole 19, and the first connection module 27 and the second connection module 28 are separated. In the embodiment of the present application, the number of steel balls 03 and steel ball limiting holes 20 can be more than 2, for example, 3, 4, 5 or 6, etc. Preferably, the number of steel balls 03 and steel ball limiting holes 20 is 4. Of course, the steel ball 03 can also be replaced by a cylinder, and correspondingly, the steel ball limiting hole 20 is a square hole.
[0066] Optionally, a hemispherical groove is formed on the lock body 13 from the notch toward the socket 19, and the hemispherical groove is coaxially arranged with the socket 19. An action portion 14 is provided between the hemispherical groove and the outer wall of the lock body 13, and the action portion 14 is used to be inserted between the inner wall of the guide portion and each of the steel balls 03. In this way, the action portion 14 is a wedge-shaped structure whose thickness gradually increases from the side close to the insertion hole 19 to the side away from the insertion hole 19. The wedge-shaped structure is inserted between the steel ball and the inner wall of the guide portion to form an extrusion limit for the steel ball 03, thereby locking the latch 02 inserted into the insertion hole 19 and the steel ball locking sleeve 04. The hemispherical groove can be used to accommodate the part of the latch 02 inserted into the accommodating cavity 34; in the process of the latch 02 being inserted into the insertion hole 19, the latch 02 will push each steel ball 03, so that each steel ball 03 overcomes the pressure formed by the elastic member acting on the lock body 13 and retracts into the steel ball limiting hole 20. When the end of the latch 02 enters the hemispherical groove, each steel ball 03 is squeezed into the inner cavity of the steel ball locking sleeve 04 again under the extrusion of the lock body 13, forming a limit for the latch 02, so that the latch 02 cannot be pulled out of the insertion hole 19. Of course, the hemispherical groove can also be replaced by a plurality of wedge-shaped blocks evenly distributed around the circumference of the insertion hole 19.
[0067] Optionally, the lock body assembly further includes a buffering and limiting pad 15, which is fixed to the bottom of the hemispherical groove and is used to be in pressure contact with the latch 02. In this way, when the latch 02 is inserted into the insertion hole 19 and the steel ball locking sleeve 04, it will be in elastic contact with the buffering and limiting pad 15, reducing the damage that may be caused by the collision. After each steel ball 03 locks the latch 02, the latch 02 is in pressure contact with the buffering and limiting pad 15, so that the end of the latch 02 is stably fixed between each steel ball and the buffering and limiting pad 15, thereby improving the stability of the connection between the first connection module 27 and the second connection module 28.
[0068] Optionally, the plug 02 includes an end 18 and a plug rod 17, one end of the plug rod 17 is fixed to the second connection block 01, and the other end of the plug rod 17 is fixed to the end 18, and the end 18 and the plug rod 17 are both used to be coaxially arranged with the insertion hole 19, and the diameter of the end 18 is larger than the diameter of the plug rod 17. In this way, when the end 18 extends into the steel ball locking sleeve 04 and passes over each steel ball 03, each steel ball 03 will extend into the L-shaped gap formed between the end 18 and the plug rod 17, thereby forming a limit on the end 18, making it difficult for the end 18 to be pulled out from the insertion hole 19. In the embodiment of the present application, preferably, the end head 18 is in the shape of a stepped shaft, and the diameter of the portion of the end head 18 close to the insertion rod 17 is smaller, and the diameter of the portion of the end head 18 away from the insertion rod 17 is larger. The portion of the end head 18 with a larger diameter is composed of two truncated cone structures, and the two truncated cone structures are coaxially arranged with the insertion rod 17. The end faces of the larger diameter ends of the two truncated cone structures overlap and are connected to each other. In this way, when the end head 18 is inserted into the insertion hole 19 and contacts each steel ball, the inclined surface of the truncated cone structure arranged away from the insertion rod 17 contacts each steel ball to form a guide, so that the end head 18 is easier to insert into the accommodating cavity 34. After the end head 18 enters the accommodating cavity 34, the inclined surface of the truncated cone structure arranged close to the insertion rod 17 fits better with each steel ball 03, thereby improving the stability of the fixation of the end head 18, and thereby improving the stability and reliability of the connection between the first connecting module 27 and the second connecting module 28.
[0069] Optionally, the lock body assembly also includes an iron core unit, which includes a coil 06 and an iron core 07, the iron core 07 is fixed to the lock body 13, the coil 06 is fixed to the iron core 07, the magnetic assembly includes a permanent magnet 08, the permanent magnet 08 is fixed to the inner wall of the accommodating cavity 34, and the permanent magnet 08 and the iron core 07 unit are arranged in the first direction.
[0070] Optionally, the lock body assembly includes two iron core 07 units, the two iron core 07 units are located on both sides of the lock body 13 in the second direction, the iron core 07 units protrude from the lock body 13 in the second direction, the permanent magnet 08 is an annular structure coaxially arranged with the jack 19, the permanent magnet 08 is directly opposite to the two iron core 07 units in the first direction, and the second direction is perpendicular to the first direction. In the embodiment of the present application, preferably, the iron core 07 is preferably made of silicon steel sheets, so that when the coil 06 is not energized, the permanent magnet 08 will not generate magnetic attraction with the iron core 07. Of course, as long as the distance between the permanent magnet 08 and the iron core 07 is large enough, other common iron-containing raw materials can also be used to make the iron core 07. In the embodiment of the present application, preferably, the permanent magnet 08 is arranged on the side of the lock body 13 away from the socket 19. When the coil 06 is energized, a magnetic attraction force is generated between the permanent magnet 08 and the iron core 07, causing the lock body 13 to move away from the socket 19, thereby releasing the latch 02; when the permanent magnet 08 is arranged on the side of the lock body 13 away from the socket 19, the magnetic assembly also includes a buffer washer 09, which is coaxially arranged with the socket 19, the buffer washer 09 is fixed to the inner ring of the permanent magnet 08, and in the first direction, the buffer washer 09 protrudes from the permanent magnet 08 toward the side of the socket 19. In the embodiment of the present application, preferably, the magnetic assembly includes two permanent magnets 08, and in the first direction, the iron core 07 unit is located between the two permanent magnets 08. When the coil 06 is energized, the iron core 07 generates a magnetic attraction force between the permanent magnets 08 arranged away from the socket 19, and the iron core 07 generates a repulsive force between the permanent magnets 08 arranged close to the socket 19. The arrangement of the two permanent magnets 08 can make the magnetic force more easily greater than the elastic force of the elastic member, thereby smoothly moving the lock body 13 and smoothly separating the first connecting unit from the second connecting unit.
[0071] Another aspect of the present application provides a spacecraft, including a spacecraft body 21, a deployable module, and a connecting device 22 provided in an embodiment of the present application, wherein the spacecraft body 21 has a mounting surface, the first connecting module 27 is fixed to the mounting surface, and the axial direction of the jack 19 is perpendicular to the mounting surface; preferably, the connecting device 22 further includes a mounting bracket 26, and the first connecting module 27 is fixed to the mounting surface through the mounting bracket 26;
[0072] The connecting device 22 further includes an extension bracket 32, the expandable module is hinged to the mounting surface, the extension bracket 32 is mounted on the expandable module, the extension bracket 32 extends outward from the expandable module in a direction parallel to the mounting surface, and the second connecting module 28 is fixed to the extension bracket 32; specifically, Figure 4 and Figure 5As shown, when the spacecraft includes two SAR antenna array surfaces stacked on the spacecraft body 21, one SAR antenna array surface is a second SAR antenna array surface 30 fixed to the spacecraft body 21, and the other is a first SAR antenna array surface 31 hinged to the second SAR antenna array surface 30 through a hinge 25. That is to say, in the embodiment of the present application, the first SAR antenna array surface 31 is used as a deployable module, and is hinged to the installation surface by being hinged to the second SAR antenna array surface 30. The first connecting module 27 is fixed to the installation surface, and the extension bracket 32 is installed on the first SAR antenna array surface 31. The extension bracket 32 extends outward from the first SAR antenna array surface 31 in a direction parallel to the installation surface. The second connecting module 28 is fixed to the extension bracket 32. When the first connecting module 27 is connected to the second connecting module 28, the first SAR antenna array surface 31 and the second SAR antenna array surface 30 are overlapped with each other. When the first connecting module 27 releases the second connecting module 28, the first SAR antenna array surface 31 can be gradually unfolded outward relative to the second SAR antenna array surface 30 and the installation surface.
[0073] Alternatively, the expandable module includes a first functional unit 23 and a second functional unit 24, the first functional unit 23 and the second functional unit 24 are sequentially stacked on the mounting surface, one end of the first functional unit 23 is hinged to the mounting surface in a direction parallel to the mounting surface, the other end of the first functional unit 23 is hinged to the second functional unit 24, the second connecting module 28 is fixed to the second functional unit 24, and the first connecting module 27 is used to pass through the first functional unit 23 and connect to the second connecting module 28; specifically, Figures 6 to 10As shown, when the deployable module is a solar power generation module including two solar panels, one of the solar panels can be a first functional unit 23, and the other solar panel can be a second functional unit 24. The two solar panels are hinged by a hinge 25. When the first connecting module 27 is connected to the second connecting module 28, the two solar panels are stacked and pressed against the spacecraft body 21. When the first connecting module 27 releases the second connecting module 28, the two solar panels are successively deployed relative to the spacecraft body 21. It can be understood that when the deployable module is deployed, the second connecting module 28 is also released. The second functional unit 24 makes an arc motion relative to the first functional unit 23. Due to the expandable module, the position of the connecting device 22 is far away from the hinge 25, and the release of the latch 02 will not interfere with the first connecting module 27 and affect its release process. If the distance between the connecting device 22 and the hinge 25 is close, a more slender latch 02 can be set or the diameter of the socket 19 can be increased, or a certain arc can be set on the inner wall of the socket 19 to avoid the latch 02. It can be made according to actual needs. In one embodiment of the present application, the first functional unit 23 can be made parallel to the second functional unit 24 (such as Figure 8 As shown), the first connection module 27 and the second connection module 28 are connected, and the angle between the first functional unit 23 and the second functional unit 24 is 1° (as shown Fig. 9 As shown), the plug 02 is located in the socket 19, the first connection module 27 and the second connection module 28 are in a state of neither being completely connected nor completely separated, so that the angle between the first functional unit 23 and the second functional unit 24 is 2° (as shown in FIG. Fig.10 As shown), the first connecting module 27 and the second connecting module 28 are in a separated state.
[0074] In the embodiment of the present application, the connecting device 22 can include a column pad 33, which is in a sleeve shape and has an internal thread, and the second connecting block 01 can include a threaded rod portion 35 and a pressure cover portion 29. The threaded rod portion 35 passes through the through hole on the second functional unit 24 and is threadedly connected to the column pad 33, so that the second functional unit 24 is clamped between the pressure cover portion 29 and the column pad 33, and the pin 02 is fixed to the threaded rod portion 35 so that the pin 02 can be plugged into the first connecting module 27.
[0075] Preferably, in the embodiment of the present application, at least two connecting devices 22 can be installed on one expandable module. For example, 3 to 6 connecting devices 22 can be installed on one expandable module, such as 4 or 5 connecting devices 22 can be installed.
[0076] The spacecraft provided by the present application adopts the connection device 22 provided by the present application, and realizes the connection between the module and the spacecraft body 21 through the connection between the first connection module 27 and the second connection module 28, or realizes pressing the module on the spacecraft body 21, and realizes the separation between the module and the spacecraft body 21 through the magnetic action between the lock body component and the magnetic component, or realizes the deployment of the module from the spacecraft body 21, with almost no impact load and relatively small safety hazards, thereby improving the safety and reliability of the spacecraft; moreover, when the module is used to be deployed from the spacecraft body 21, when the module is folded or compressed again, the same connection device 22 can still be used again. Compared with the compression and release devices that rely on pyrotechnics and are based on hot knives and can only be used once in the current field, the utilization rate of the connection device 22 is higher, thereby reducing the use cost of the spacecraft; and, Compared with the compression and release devices that rely on pyrotechnics and generate smoke and dust pollution during the release process, and the compression and release devices based on hot knives, the connection device 22 provided in the present application does not generate smoke and dust, and will not pollute the environment; at the same time, the commonly used compression and release devices in the field currently also include shape memory alloy compression and release devices driven by the shape memory effect of shape memory alloys, which do not generate separation shock and smoke and dust pollution, can be used repeatedly, overcome the defects of pyrotechnic devices, and have great advantages in the connection and separation of satellites. However, the release time of the memory alloy compression and release device is generally long, and it is not suitable for situations where synchronous release is required. However, the connection device 22 provided in the present application realizes the separation between the first connection module 27 and the second connection device 22 under the action of magnetic force, thereby achieving the purpose of releasing the module from the spacecraft body 21. The required implementation is short and the release efficiency is high, which is more suitable for situations where synchronous release is required.
[0077] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.
Claims
1. A connecting device, characterized in that The invention comprises a first connection module and a second connection module, wherein the first connection module comprises a first connection block, a lock body assembly and a magnetic assembly, wherein a receiving cavity is formed in the first connection block, the magnetic assembly is fixed to the inner wall of the receiving cavity, the lock body assembly is arranged in the receiving cavity, a plug hole connected to the receiving cavity is formed on the first connection block, the second connection module comprises a second connection block and a pin fixed to the second connection block, the pin is used to be plugged into the plug hole in a first direction, the lock body assembly is used to lock the pin, and the magnetic assembly is used to drive the lock body assembly by magnetic force so that the pin can be separated from the first connection module.
2. The connection device according to claim 1, characterized in that: The lock body assembly includes a lock body, an elastic member and a locking unit, wherein the locking unit is installed on the inner wall of the accommodating cavity, and the locking unit is arranged close to the insertion hole. The lock body is used to slide with the inner wall of the accommodating cavity in the first direction, and the elastic member is pressure-fitted with the lock body and the inner wall of the accommodating cavity, so that the lock body presses the locking unit toward the side of the insertion hole in the first direction, thereby causing the locking unit to lock the latch.
3. The connection device according to claim 2, characterized in that: The accommodating cavity includes a guide portion, which is coaxially arranged with the insertion hole. The lock body and the inner wall of the guide portion are slidably matched in the first direction. The inner diameter of the guide portion is larger than the inner diameter of the insertion hole. A limiting step is formed between the inner wall of the guide portion and the inner wall of the insertion hole, and the locking unit is installed on the limiting step.
4. The connection device according to claim 3, characterized in that: The locking unit includes a plurality of steel balls and a steel ball locking sleeve, the steel ball locking sleeve being coaxially arranged with the insertion hole, one end of the steel ball locking sleeve being fixed to the limiting step in the first direction, a plurality of steel ball limiting holes being formed on the steel ball locking sleeve, each of the steel ball limiting holes being evenly distributed in the circumferential direction of the steel ball locking sleeve, the diameter of the steel ball limiting holes being smaller than the diameter of the steel balls, each of the steel balls being arranged on the limiting step, each of the steel balls being located between the steel ball locking sleeve and the inner wall of the guide portion, each of the steel balls being matched with each of the steel ball limiting holes in a one-to-one correspondence, and the lock body being used to be inserted between the inner wall of the guide portion and each of the steel balls to squeeze each of the steel balls, thereby allowing each of the steel balls to extend into the inner cavity of the steel ball locking sleeve and lock the latch.
5. The connection device according to claim 4, characterized in that: A hemispherical groove is formed on the lock body from the notch toward the insertion hole. The hemispherical groove is coaxially arranged with the insertion hole. An action part is between the hemispherical groove and the outer wall of the lock body. The action part is used to be inserted between the inner wall of the guide part and each of the steel balls.
6. The connection device according to claim 5, characterized in that: The lock body assembly further comprises a buffering and limiting pad, which is fixed to the bottom of the hemispherical groove and is used for pressure contact with the latch.
7. The connection device according to claim 4, characterized in that: The latch includes an end and a rod, one end of the rod is fixed to the second connecting block, and the other end of the rod is fixed to the end, the end and the rod are both used to be coaxially arranged with the socket, and the diameter of the end is larger than the diameter of the rod.
8. The connection device according to any one of claims 2 to 7, characterized in that: The lock body assembly also includes an iron core unit, which includes a coil and an iron core. The iron core is fixed to the lock body, and the coil is fixed to the iron core. The magnetic assembly includes a permanent magnet, which is fixed to the inner wall of the accommodating cavity. The permanent magnet and the iron core unit are arranged in the first direction.
9. The connection device according to claim 8, characterized in that: The lock body assembly includes two core units, which are located on both sides of the lock body in the second direction. The core units protrude from the lock body in the second direction. The permanent magnet is an annular structure coaxially arranged with the socket. The permanent magnet is opposite to the two core units in the first direction, and the second direction is perpendicular to the first direction.
10. A spacecraft, characterized in that It comprises a spacecraft body, a deployable module and a connection device as claimed in any one of claims 1 to 9, wherein the spacecraft body has a mounting surface, the first connection module is fixed to the mounting surface, and the axial direction of the socket is perpendicular to the mounting surface; The connecting device further comprises an extension bracket, the expandable module is hinged to the mounting surface, the extension bracket is mounted on the expandable module, the extension bracket extends outward from the expandable module in a direction parallel to the mounting surface, and the second connecting module is fixed to the extension bracket; Alternatively, the expandable module includes a first functional unit and a second functional unit, the first functional unit and the second functional unit are stacked in sequence on the mounting surface, one end of the first functional unit is hinged to the mounting surface in a direction parallel to the mounting surface, the other end of the first functional unit is hinged to the second functional unit, the second connecting module is fixed to the second functional unit, and the first connecting module is used to pass through the first functional unit and connect to the second connecting module.