A circumferential axial double locking mechanism of a multi-body variable configuration satellite

Abstract

The application relates to a circumferential and axial double locking mechanism of a multi-body variable-configuration satellite, and belongs to the technical field of spacecrafts. The mechanism comprises a first frame, a second frame and a locking device, the first frame and the second frame are respectively installed on two variable-configuration satellite modules; a connecting hole is formed in the first frame, a connecting column matched with the connecting hole is fixedly connected to the second frame, the locking device comprises a fixing seat, a locking rod and a power assembly, the fixing seat is fixedly connected in the first frame, the locking rod is slidingly connected in the fixing seat, and the power assembly is used for driving the locking rod to move so that the end of the locking rod abuts against the side surface of the connecting column. The power assembly is used for driving the locking rod to move towards the connecting column, and the end of the locking rod is pressed against the side surface of the connecting column, so that the situation that the connecting column falls off from the connecting hole is reduced, the circumferential and axial locking between the two variable-configuration satellite modules is achieved, and the stability of docking is effectively improved.

Description

Technical Field

[0001] This application relates to the field of spacecraft technology, and in particular to a circumferential and axial double locking mechanism for a multibody deformable satellite. Background Technology

[0002] With the rapid development of microsatellites and related technologies, satellites with fixed structures are no longer sufficient to meet the requirements of various countries for multi-mission capabilities, strong environmental adaptability, and resilience. Therefore, attention has turned to self-reconfigurable satellites with on-orbit structural flexibility. Self-reconfigurable satellites consist of a varying number of structurally identical satellite modules that can autonomously change their configuration without external intervention or the addition or removal of any components. They can reconfigure multiple functional satellite modules from their original configuration to achieve the optimal configuration for different mission requirements. In the event of a local module failure, on-orbit reconfiguration can replace the faulty module with a spare, demonstrating self-repair capabilities. Furthermore, they can adjust to the optimal launch configuration based on launch conditions and, after entering orbit, restore their operational and functional state through on-orbit reconfiguration.

[0003] Due to these outstanding advantages, self-reconfigurable satellites, as a novel satellite concept, have received close attention and development from various countries in recent years. Since self-reconfigurable satellites consist of a varying number of structurally identical satellite modules, achieving circumferential and axial locking after docking is a crucial problem to solve. Currently, there are three main types of docking mechanisms on spacecraft: conical docking mechanisms, which use a series of transmission and telescopic devices to pull two satellites closer and lock them together; heterogeneous isomorphic peripheral docking mechanisms, which use identical mechanical structures to complete the satellite capture and docking task; and trident docking mechanisms, which utilize three hooks and three wedge-shaped openings to achieve strong capture and docking capabilities.

[0004] Although the aforementioned docking mechanisms can perform space capture and docking functions well, these docking mechanisms mainly serve large spacecraft and satellites, have complex structures, and are prone to docking instability. Summary of the Invention

[0005] To effectively improve docking stability, this application provides a circumferential and axial double locking mechanism for a multibody deformable satellite.

[0006] The purpose of this application is to provide a circumferential and axial dual locking mechanism for a multibody deformable satellite, which adopts the following technical solution:

[0007] A circumferential and axial double locking mechanism for a multibody variable-configuration satellite includes a first frame, a second frame, and a locking device. The first frame and the second frame are respectively mounted on two variable-configuration satellite modules. The first frame has a connection hole, and the second frame has a connecting post that is fixedly connected to the connection hole. The locking device includes a fixed base, a locking rod, and a power assembly. The fixed base is fixedly connected to the first frame, the locking rod is slidably connected to the fixed base, and the power assembly is used to drive the locking rod to move so that the end of the locking rod abuts against the side of the connecting post.

[0008] By adopting the above technical solution, when the two variable-structure satellite modules move to the designated locking position, the connecting post aligns with the connecting hole and passes through the connecting hole; then, the power component drives the locking rod to move towards the connecting post, and the end of the locking rod presses against the side of the connecting post, thereby reducing the possibility of the connecting post falling out of the connecting hole, so as to lock and fix the first frame and the second frame together, achieving the purpose of circumferential and axial locking between the two variable-structure satellite modules, and effectively improving the stability of docking.

[0009] Optionally, the power assembly includes a screw, a nut, and a power component. The fixed base has a sliding groove. One end of the nut is fixedly connected to a sliding block that slides in conjunction with the sliding groove. The screw is threadedly engaged with the nut. The power component is used to drive the screw to rotate. The circumferential surface of the nut is a conical surface, and one end of the locking rod abuts against the conical surface of the nut.

[0010] By adopting the above technical solution, the screw is driven to rotate by the power component. The rotational torque of the screw will drive the nut to move axially. Then, the circumferential force of the nut will be transmitted to the locking rod through the conical surface, so that the end of the locking rod is pressed against the side of the abutment post, thereby locking and fixing the first frame and the second frame together.

[0011] Optionally, a locking groove is provided on the side of the connecting column, and the locking groove is inserted into the end of the locking rod.

[0012] By adopting the above technical solution, the locking groove and the end of the locking rod cooperate, further reducing the possibility of the connecting column detaching from the connecting hole, thereby making the locking and fixing of the first frame and the second frame more stable.

[0013] Optionally, an adjusting plate is slidably connected within the locking groove, and a limiting groove parallel to the locking groove is provided at the end of the connecting column, with a limiting plate slidably connected within the limiting groove; a rotating cavity is provided within the connecting column, communicating with both the locking groove and the limiting groove, and a telescopic rod is rotatably connected within the rotating cavity, with one end of the telescopic rod hinged to the adjusting plate and the other end hinged to the limiting plate; a limiting spring is provided within the locking groove, with one end fixed to the bottom of the locking groove and the other end fixed to the adjusting plate, and when the limiting spring is compressed, the surface of the limiting plate presses against the surface of the fixed seat away from the second frame.

[0014] By adopting the above technical solution, during the process of inserting the end of the locking rod into the locking groove, the locking rod will abut against the adjusting plate and move towards the bottom of the locking groove; then, the telescopic rod is used to make the limiting plate move in the opposite direction of the adjusting plate, so that the surface of the limiting plate presses against the surface of the fixed seat away from the second frame, further reducing the situation where the connecting column comes out of the connecting hole, thereby making the locking and fixing of the first frame and the second frame more stable.

[0015] Optionally, an anti-slip pad is fixedly connected to the end of the locking rod.

[0016] By adopting the above technical solution, the anti-slip pad can lock the rod out of the locking groove, thereby making the locking and fixing of the first frame and the second frame more stable.

[0017] Optionally, a winding wheel is rotatably connected inside the fixed base, a pull rope is wound on the winding wheel, and the other end of the pull rope is fixedly connected to the locking rod; a torsion spring is sleeved on the rotating shaft of the winding wheel, one end of the torsion spring is fixed to the winding wheel, and the other end of the winding wheel is fixed to the fixed base.

[0018] By adopting the above technical solution, the winding wheel, pull rope and torsion spring work together to make the end of the locking rod abut against the conical surface of the nut. When the power component drives the screw to rotate in the opposite direction, the other end of the locking rod can be easily retracted into the fixed seat, thereby disassembling and recombining multiple variable configuration satellite modules.

[0019] Optionally, a positioning block is fixedly connected to one side of the first frame, and a positioning hole is provided on one side of the second frame to engage with the positioning block.

[0020] By adopting the above technical solution, when the two variable-structure satellite modules move to the designated locking position, the positioning block and the positioning hole cooperate to position the first frame and the second frame to come together, making it easier for the connecting column to be inserted into the connecting hole, thus making it easier to lock and fix the first frame and the second frame.

[0021] Optionally, the positioning block is hemispherical in shape.

[0022] By adopting the above technical solution, the shape of the positioning block is designed to facilitate better insertion of the positioning block into the positioning hole, thereby improving the positioning effect of the first frame and the second frame.

[0023] Optionally, the second frame includes a second connecting plate, a second mounting plate, and a second damper. The second mounting plate is for mounting the variable configuration satellite module. One end of the locking rod is fixedly connected to the side of the second mounting plate near the second connecting plate. The second connecting plate has a through hole for the locking rod to pass through. One end of the second damper is fixedly connected to the side of the second connecting plate near the second mounting plate. The second mounting plate has a damping hole for the second damper to pass through.

[0024] By adopting the above technical solution, and by using the second connecting plate, the second mounting plate, and the second damper in combination, the locking and fixing of the first frame and the second frame can be made more stable.

[0025] In summary, this application includes at least the following beneficial technical effects:

[0026] 1. When the two variable-structure satellite modules move to the designated locking position, the connecting post aligns with the connecting hole and passes through the connecting hole; then, the power component drives the locking rod to move towards the connecting post, and the end of the locking rod presses against the side of the connecting post, thereby reducing the possibility of the connecting post falling out of the connecting hole, so as to lock and fix the first frame and the second frame together, achieving the purpose of circumferential and axial locking between the two variable-structure satellite modules, effectively improving the stability of docking;

[0027] 2. During the process of inserting the end of the locking rod into the locking groove, the locking rod will abut against the adjusting plate and move towards the bottom of the locking groove; then the telescopic rod will be used to make the limiting plate move in the opposite direction of the adjusting plate, so that the surface of the limiting plate can press against the surface of the fixed seat away from the second frame, further reducing the possibility of the connecting column coming out of the connecting hole, thereby making the locking and fixing of the first frame and the second frame more stable. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the circumferential and axial double locking mechanism of a multibody deformable satellite according to an embodiment of this application;

[0029] Figure 2 This is a partial structural cross-sectional view of an embodiment of this application, mainly used to show the connection diagram of the first frame and the locking device;

[0030] Figure 3 This is a partial exploded view of the connection of an embodiment of this application, mainly used to show the connection diagram of the second frame;

[0031] Figure 4 This is a partial structural cross-sectional view of an embodiment of this application, mainly used to show the connection diagram of the connecting column.

[0032] Explanation of reference numerals in the attached drawings: 1. First frame; 101. First connecting plate; 102. First mounting plate; 103. First column; 2. Second frame; 201. Second connecting plate; 202. Second mounting plate; 203. Second damper; 3. Locking device; 31. Fixed base; 32. Locking rod; 33. Power component; 331. Screw; 332. Nut; 333. Power component; 334. Sliding groove; 335. Sliding block; 4. Connecting hole; 5. Connecting column; 6. Locking groove; 7. Adjusting plate; 8. Limiting groove; 9. Limiting plate; 10. Rotating cavity; 11. Telescopic rod; 12. Limiting spring; 13. Anti-slip pad; 14. Winding wheel; 15. Pull rope; 16. Torsion spring; 17. Positioning block; 18. Positioning hole; 19. Connecting hole; 20. Damping hole. Detailed Implementation

[0033] To make the purpose, technical solution, and advantages of this application clearer, the following description is provided in conjunction with the appendix. Figure 1-4 The present application will be further described in detail below with reference to embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the application.

[0034] This application discloses a circumferential and axial double locking mechanism for a multibody deformable satellite. (Refer to...) Figure 1 and Figure 2 The mechanism includes a first frame 1 and a second frame 2, which are respectively mounted on two variable-configuration satellite modules. The first frame 1 includes a first connecting plate 101, a first mounting plate 102, and a first column 103. The first connecting plate 101 and the first mounting plate 102 are parallel to each other, and the first column 103 is located between the first connecting plate 101 and the first mounting plate 102. There are three first columns 103, evenly distributed circumferentially on the first connecting plate 101. One end of each first column 103 is fixed to the first connecting plate 101 by a threaded connection, and the other end is fixed to the first mounting plate 102 by a threaded connection. The variable-configuration satellite module is fixedly mounted on the first mounting plate 102, away from the first connecting plate 101.

[0035] Reference Figure 1 and Figure 3The second frame 2 includes a second connecting plate 201, a second mounting plate 202, and a second damper 203. The second connecting plate 201 and the second mounting plate 202 are parallel to each other, and the second damper 203 is located between the second connecting plate 201 and the second mounting plate 202. There are six second dampers 203, which are evenly distributed in a circle on the second connecting plate 201. One end of the second damper 203 is fixed to the second connecting plate 201 by a threaded connection. The second mounting plate 202 has a damping hole 20, and the other end of the second damper 203 passes through the damping hole 20 and is fixed to the second mounting plate 202. The variable configuration satellite module is fixedly installed on the second mounting plate 202 away from the second connecting plate 201.

[0036] Reference Figure 2 and Figure 3 A positioning block 17 is integrally formed on the side of the first connecting plate 101 away from the first mounting plate 102. A positioning hole 18 is opened on one side of the second connecting plate 201 and the second mounting plate 202, and the positioning hole 18 is inserted into the positioning block 17. The positioning block 17 is hemispherical in shape. When the two variable structure satellite modules move to the designated locking position, the shape of the positioning block 17 makes it easier for the positioning block 17 to be inserted into the positioning hole 18. The positioning block 17 and the positioning hole 18 cooperate to position the first frame 1 and the second frame 2 to move closer together, which makes it easier for the connecting column 5 to be inserted into the connecting hole 4, thereby making it easier to lock and fix the first frame 1 and the second frame 2.

[0037] Reference Figure 2 and Figure 3 The first connecting plate 101 has three connecting holes 4, which are evenly distributed in a circle on the first connecting plate 101. A connecting post 5 is fixed to the second mounting plate 202 by welding. The second connecting plate 201 has a connecting hole 19 through which the connecting post 5 passes. The number of connecting holes 19 and connecting posts 5 corresponds to the number of connecting holes 4, and the connecting posts 5 are inserted into the connecting holes 4. That is, the connecting holes 4 are located on the first frame 1, and the connecting posts 5 are fixedly connected to the second frame 2. The second damper 203 is located inside the circle enclosed by the three connecting holes 19.

[0038] Reference Figure 2 and Figure 3A locking device 3 is installed on the first frame 1. The locking device 3 includes a fixed seat 31, a locking rod 32 and a power component 33. The fixed seat 31 is fixedly connected to the first connecting plate 101 by welding. The fixed seat 31 is cylindrical and has three square holes on its circumference. There are three locking rods 32, which are slidably connected in the square holes. When the connecting post 5 is inserted into the connecting hole 4, the power component 33 is used to drive the locking rod 32 to move so that the end of the locking rod 32 abuts against the side of the connecting post 5.

[0039] Reference Figure 2 and Figure 3 The power assembly 33 includes a screw 331, a nut 332, and a power component 333. A sliding groove 334 is provided on the fixed base 31. A sliding block 335 is fixedly connected to one end of the nut 332, and the sliding block 335 slides in conjunction with the sliding groove 334. The screw 331 and the nut 332 are threaded together. The power component 333 is a power motor. The housing of the power motor is bolted to the first mounting plate 102. The output shaft of the power motor is fixedly connected to the screw 331 by a key connection. The circumferential surface of the nut 332 is a conical surface, and one end of the locking rod 32 abuts against the conical surface of the nut 332. The power motor drives the screw 331 to rotate, and the rotational torque of the screw 331 drives the nut 332 to move axially. The circumferential force of the nut 332 is then transmitted to the locking rod 32 through the conical surface, achieving the purpose of pressing the end of the locking rod 32 against the side of the abutment post, thereby locking and fixing the first frame 1 and the second frame 2 together.

[0040] Reference Figure 2 and Figure 3 A winding wheel 14 is rotatably connected inside the fixed base 31, and a pull rope 15 is wound on the winding wheel 14. The other end of the pull rope 15 is fixedly connected to the locking rod 32. A torsion spring 16 is sleeved on the rotating shaft of the winding wheel 14. One end of the torsion spring 16 is fixed to the winding wheel 14, and the other end of the winding wheel 14 is fixed to the fixed base 31. Through the cooperation of the winding wheel 14, the pull rope 15, and the torsion spring 16, the end of the locking rod 32 can abut against the conical surface of the nut 332. When the power component 333 drives the screw 331 to rotate in the opposite direction, the other end of the locking rod 32 can be retracted into the fixed base 31, thereby disassembling and recombining multiple variable configuration satellite modules.

[0041] Reference Figure 2 and Figure 4A locking groove 6 is provided on the side of the connecting post 5, and the locking groove 6 is inserted into the end of the locking rod 32; an anti-slip pad 13 is fixedly connected to the end of the locking rod 32. By engaging the locking groove 6 with the end of the locking rod 32, the possibility of the connecting post 5 disengaging from the connecting hole 4 is further reduced, thereby making the locking and fixing of the first frame 1 and the second frame 2 more secure; the anti-slip pad 13 prevents the locking rod 32 from disengaging from the locking groove 6, thereby making the locking and fixing of the first frame 1 and the second frame 2 more secure.

[0042] Reference Figure 2 and Figure 4 An adjusting plate 7 is slidably connected inside the locking groove 6. A limiting groove 8 is provided at the end of the connecting column 5. The limiting groove 8 is parallel to the locking groove 6. A limiting plate 9 is slidably connected inside the limiting groove 8. A rotating cavity 10 is provided inside the connecting column 5. The rotating cavity 10 is connected to the locking groove 6 and the limiting groove 8 respectively. A telescopic rod 11 is rotatably connected inside the rotating cavity 10. One end of the telescopic rod 11 is hinged to the adjusting plate 7, and the other end of the telescopic rod 11 is hinged to the limiting plate 9. A limiting spring 12 is installed inside the locking groove 6. One end of the limiting spring 12 is fixed to the bottom of the locking groove 6, and the other end of the limiting spring 12 is fixed to the adjusting plate 7. When the limiting spring 12 is in a compressed state, the surface of the limiting plate 9 presses against the surface of the fixed seat 31 away from the second frame 2.

[0043] In this embodiment, during the process of inserting the end of the locking rod 32 into the locking groove 6, the locking rod 32 will move against the adjusting plate 7 towards the bottom of the locking groove 6; then the telescopic rod 11 is used to move the limiting plate 9 in the opposite direction of the moving direction of the adjusting plate 7, so that the surface of the limiting plate 9 can press against the surface of the fixing seat 31 away from the second frame 2, further reducing the possibility of the connecting column 5 disengaging from the connecting hole 4, thereby making the locking and fixing of the first frame 1 and the second frame 2 more stable.

[0044] The implementation principle of the circumferential and axial double locking mechanism of a multi-body variable-structure satellite according to the embodiments of this application is as follows: when the two variable-structure satellite modules move to the designated locking position, the connecting post 5 is aligned with the connecting hole 4, and the connecting post 5 passes through the connecting hole 4; then the power component 33 drives the locking rod 32 to move towards the connecting post 5, and the end of the locking rod 32 presses against the side of the connecting post 5, thereby reducing the possibility of the connecting post 5 falling out of the connecting hole 4, so as to lock and fix the first frame 1 and the second frame 2 together, achieving the purpose of circumferential and axial locking between the two variable-structure satellite modules, and effectively improving the stability of docking.

[0045] The above are all preferred embodiments of this application and are not intended to limit the scope of protection of this application. Any feature disclosed in this specification (including the abstract and drawings) may be replaced by other equivalent or similar features unless specifically stated otherwise. Therefore, all equivalent changes made to the structure, shape, and principle of this application should be covered within the scope of protection of this application.

Claims

1. A circumferential and axial double locking mechanism for a multibody variable-structure satellite, characterized in that, The system includes a first frame (1), a second frame (2), and a locking device (3). The first frame (1) and the second frame (2) are respectively mounted on two variable-structure satellite modules. The first frame (1) has a connecting hole (4), and the second frame (2) has a connecting post (5) that is inserted into the connecting hole (4). The locking device (3) includes a fixing seat (31), a locking rod (32), and a power component (33). The fixing seat (31) is fixedly connected to the first frame (1), and the locking rod (32) is slidably connected to the fixing seat (31). The power component (33) is used to drive the locking rod (32) to move so that the end of the locking rod (32) abuts against the side of the connecting post (5). The side of the connecting column (5) is provided with a locking groove (6), and the locking groove (6) is inserted into the end of the locking rod (32); An adjusting plate (7) is slidably connected inside the locking groove (6). A limiting groove (8) parallel to the locking groove (6) is opened at the end of the connecting column (5). A limiting plate (9) is slidably connected inside the limiting groove (8). A rotating cavity (10) is opened inside the connecting column (5). The rotating cavity (10) is connected to the locking groove (6) and the limiting groove (8) respectively. A telescopic rod (11) is rotatably connected inside the rotating cavity (10). One end of the telescopic rod (11) is hinged. The telescopic rod (11) is attached to the adjustment plate (7), and the other end of the telescopic rod (11) is hinged to the limiting plate (9). A limiting spring (12) is provided in the locking groove (6). One end of the limiting spring (12) is fixed to the bottom of the locking groove (6), and the other end of the limiting spring (12) is fixed to the adjustment plate (7). When the limiting spring (12) is in a compressed state, the surface of the limiting plate (9) presses against the surface of the fixed seat (31) away from the second frame (2).

2. The circumferential and axial double locking mechanism for a multibody variable-structure satellite according to claim 1, characterized in that, The power assembly (33) includes a screw (331), a nut (332), and a power component (333). The fixed base (31) has a sliding groove (334). One end of the nut (332) is fixedly connected to a sliding block (335) that slides in cooperation with the sliding groove (334). The screw (331) and the nut (332) are threaded together. The power component (333) is used to drive the screw (331) to rotate. The circumferential surface of the nut (332) is a conical surface, and one end of the locking rod (32) abuts against the conical surface of the nut (332).

3. The circumferential and axial double locking mechanism for a multibody variable-structure satellite according to claim 1, characterized in that, An anti-slip pad (13) is fixedly connected to the end of the locking rod (32).

4. A circumferential and axial double locking mechanism for a multibody variable-structure satellite according to claim 1 or 2, characterized in that, A winding wheel (14) is rotatably connected inside the fixed base (31). A pull rope (15) is wound on the winding wheel (14), and the other end of the pull rope (15) is fixedly connected to the locking rod (32). A torsion spring (16) is sleeved on the shaft of the winding wheel (14). One end of the torsion spring (16) is fixed to the winding wheel (14), and the other end of the winding wheel (14) is fixed to the fixed base (31).

5. The circumferential and axial double locking mechanism for a multibody variable-structure satellite according to claim 1, characterized in that, A positioning block (17) is fixedly connected to one side of the first frame (1), and a positioning hole (18) is provided on one side of the second frame (2) to engage with the positioning block (17).

6. The circumferential and axial double locking mechanism for a multibody variable-structure satellite according to claim 5, characterized in that, The positioning block (17) is hemispherical in shape.

7. The circumferential and axial double locking mechanism for a multibody variable-structure satellite according to claim 5, characterized in that, The second frame (2) includes a second connecting plate (201), a second mounting plate (202), and a second damper (203). The second mounting plate (202) is for mounting the variable configuration satellite module. One end of the connecting post (5) is fixedly connected to the side of the second mounting plate (202) near the second connecting plate (201). The second connecting plate (201) has a through hole (19) for the connecting post (5) to pass through. One end of the second damper (203) is fixedly connected to the side of the second connecting plate (201) near the second mounting plate (202). The second mounting plate (202) has a damping hole (20) for the second damper (203) to pass through.

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