Cabin plate butt-joint locking structure for mass production of micro-nano satellites and use method of cabin plate butt-joint locking structure

Abstract

The invention provides a cabin plate butt-joint locking structure for mass production of micro-nano satellites and a use method of the cabin plate butt-joint locking structure, and belongs to the field of satellite structures. The problems that a traditional screw connection mode is low in final assembly efficiency, poor in operation reliability, inconvenient to test and maintain quickly, difficult to meet the batch production requirement and the like are solved. The cabin comprises a cabin plate, locking execution units and lock seats, the cabin plate is divided into a bottom plate, a top plate and a plurality of side plates, the side plates are connected with the bottom plate through hinges, the locking execution units and the lock seats are arranged on the two butt joint edges of the adjacent side plates respectively, and the locking execution units and the lock seats are arranged on the two butt joint edges of the side plates and the top plate respectively. The adjacent side plates and the side plates and the top plate are locked in a butt joint mode through matching of the locking execution units and the lock seats. The method is mainly used for mass production of micro-nano satellites.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of satellite structure, in particular to a docking and locking structure of batch production of micro-nano satellites and a method of using the same. BACKGROUND

[0002] With the continuous development of space technology, micro-nano satellites have become an important development direction of space technology application due to their low cost, short development cycle, high functional density and networking application advantages, so high requirements are put forward for the batch production of micro-nano satellites.

[0003] In the traditional satellite structure, various types of cabin plates are usually connected by screw connection. This connection method is mature in technology, has high connection stiffness and reliability, and has been verified for a long time. However, in the development system of batch production of micro-nano satellites, the traditional method gradually exposes many inherent defects, such as low assembly efficiency, poor operation convenience, and high operation space requirement. When single machine testing, fault checking and other conditions are carried out, repeated screwing and unscrewing not only has low efficiency, but also is more likely to cause thread wear, thread slipping, and even metal debris, which poses a potential threat to the reliability and safety of the satellite. In addition, the consistency of the pre-tightening force of the screw cannot be guaranteed, and there may be problems such as missed screwing, insufficient torque or over-tightening, which introduces uncontrollable quality risks. SUMMARY

[0004] Therefore, the present application aims to provide a docking and locking structure of batch production of micro-nano satellites and a method of using the same to solve the problems of low assembly efficiency, poor operation reliability, inconvenience for rapid testing and maintenance, and difficulty in adapting to batch production requirements in the traditional screw connection method.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical scheme: a docking and locking structure of batch production of micro-nano satellites, comprising a cabin plate, a locking execution unit and a lock seat, the cabin plate is divided into a bottom plate, a top plate and a plurality of side plates, the plurality of side plates are connected to the bottom plate through hinges, locking execution units and lock seats are respectively arranged on the two docking edges of adjacent side plates, locking execution units and lock seats are respectively arranged on the two docking edges of the side plate and the top plate, the locking execution unit comprises a transmission device, a driving component and a locking point part, the transmission device comprises a housing, a gear and a transmission rod, the housing is connected to the cabin plate, the gear is rotatably arranged inside the housing, two transmission rods are slidably connected inside the housing, a gear structure is arranged on one side of the transmission rod, the other side of the transmission rod is connected to the locking point part, the gear is engaged with the gear rack, the gear is driven to rotate by the driving component, the locking point part is slidably connected to the cabin plate, a hook-shaped structure is arranged on the upper end of the locking point part, the lock seat is a stepped opening slot structure with a guide slope, the adjacent side plates and the side plate and the top plate are docked and locked through the cooperation of the locking execution unit and the lock seat.

[0006] Further, the plurality of cabin plates form a hexahedral configuration micro-nano satellite.

[0007] Further, the plurality of side plates are divided into a first side plate, a second side plate, a third side plate and a fourth side plate, the first side plate and the third side plate are provided with a locking execution unit on the abutting edge with the adjacent side plate, the first side plate, the second side plate, the third side plate and the fourth side plate are provided with a locking execution unit on the abutting edge with the top plate, the second side plate and the fourth side plate are provided with a lock seat on the edge abutting with the adjacent side plate, and the top plate is provided with a lock seat on the edge abutting with the side plate.

[0008] Further, the cabin plate adopts a structure of aluminum honeycomb core material and a peripheral metal force frame embedded part.

[0009] Further, the gear is provided with a driving hole, the driving part is inserted into the driving hole, and the driving part drives the gear to rotate.

[0010] Further, the driving hole is a square hole structure, one end of the driving part is a handle, and the other end is a square shaft structure, and the square hole structure and the square shaft structure are matched in size.

[0011] Further, the transmission rod is provided with a connecting buckle, and the locking point part is provided with a matching hole connected with the connecting buckle.

[0012] Further, the shell is provided with a fixing hole, and the transmission rod is provided with an oval opening, and the transmission device is connected to the cabin plate by screwing through the fixing hole and the oval opening.

[0013] Further, the bottom plate and each side plate are connected through a plurality of hinges.

[0014] The application also provides a use method of the cabin plate abutting and locking structure of the batch-produced micro-nano satellite, specifically that the side plates are connected with the bottom plate through the hinges, the side plates are laid on the plane where the bottom plate is located, the cabin equipment installation and cable laying are carried out, when the cabin is closed, the top plate is placed after the side plates are sequentially erected, the operator drives the gear to rotate by using the driving part, the transmission rod is driven to move linearly through the meshing of the gear and the rack, the locking point part is driven to slide, the hook-shaped structure of the locking point part is slid into the stepped opening slot structure with a guide slope of the lock seat, the locking is realized, the cooperation of all the locking execution units and the lock seats is sequentially completed, and the adjacent cabin plates are tightly pressed together.

[0015] Compared with the prior art, the beneficial effects of the present application are that the present application provides a cabin plate docking and locking structure for batch production of micro-nano satellites and a use method thereof, which can significantly improve the assembly efficiency and reliability, the present application simplifies the cumbersome screw tightening operation into a quick rotating action, realizes multi-point synchronous locking, greatly shortens the operation time, and avoids the risk of human error such as torque inaccuracy, no metal debris is generated during the assembly process, and the reliability and safety of the satellite are improved, and it is particularly suitable for efficient assembly process of batch production of satellites.

[0016] The present application has excellent anti-vibration and mechanical properties, based on the mechanical self-locking effect generated by the locking point part and the inclined surface of the lock seat, and the uniform load distribution formed by the plurality of locking point parts, so that the system can maintain extremely high stability in the severe vibration environment of launch, effectively prevent the cabin plate from loosening, and improve the stress of the overall structure and reduce stress concentration.

[0017] The present application realizes the rapid and repeated opening and closing of the cabin plate, greatly facilitates the single machine test, inspection and replacement work in the satellite development process, reduces the physical damage to the cabin plate, and improves the convenience of testing and maintenance. The multi-hinge connection between the side plate and the bottom plate of the present application is combined with the docking and locking structure, which constitutes a distributed bearing structure and enhances the overall stiffness of the satellite. At the same time, the mechanism has compact structure and light weight, which meets the requirement of lightweight of spacecraft. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings, which form a part of this application, are used to provide a further understanding of the application, and the schematic embodiments of the application and their descriptions are used to explain the application, and do not constitute an improper limitation on the application. In the drawings: Figure 1 The side plate and bottom plate combination structure described in the present application is shown in the schematic diagram; Figure 2 The top plate locking seat arrangement structure described in the present application is shown in the schematic diagram; Figure 3 The locking execution unit structure described in the present application is shown in the schematic diagram; Figure 4 The transmission device explosion structure described in the present application is shown in the schematic diagram; Figure 5 The lock seat and locking point part cooperation explosion structure described in the present application is shown in the schematic diagram.

[0019] In the drawings: 1-First side plate, 2-Second side plate, 3-Third side plate, 4-Fourth side plate, 5-Bottom plate, 6-Locking execution unit, 7-Locking seat, 8-Hinge, 9-Top plate, 10-Transmission device, 11-Driving part, 12-Locking point part, 13-Driving hole, 14-Gear, 15-Rack, 16-Transmission rod, 17-Connecting buckle, 18-Housing, 19-Fixing hole. DETAILED DESCRIPTION

[0020] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only some of the embodiments of the present application, not all the embodiments.

[0021] Referring to Figures 1-5 In order to illustrate the present embodiment, a docking and locking structure of a batch-produced micro-nano satellite cabin plate is described, which comprises a cabin plate, a locking execution unit 6 and a lock seat 7. The cabin plate is divided into a bottom plate 5, a top plate 9 and a plurality of side plates. The plurality of side plates are connected to the bottom plate 5 through hinges 8. The locking execution unit 6 and the lock seat 7 are respectively arranged on the two docking edges of adjacent side plates. The locking execution unit 6 and the lock seat 7 are respectively arranged on the two docking edges of the side plate and the top plate 9. The locking execution unit 6 comprises a transmission device 10, a driving component 11 and a locking point part 12. The transmission device 10 comprises a housing 18, a gear 14 and a transmission rod 16. The housing 18 is connected to the cabin plate. The gear 14 is rotatably arranged in the housing 18. Two transmission rods 16 are slidably connected in the housing 18. The transmission rod 16 is provided with a rack 15 structure on one side. The transmission rod 16 is connected to the locking point part 12 on the other side. The rack 15 is engaged with the gear 14. The gear 14 is driven to rotate by the driving component 11. The locking point part 12 is slidably connected to the cabin plate. The locking point part 12 is provided with a hook-shaped structure on the upper end. The lock seat 7 is a stepped opening groove structure with a guide slope. The adjacent side plates and the side plate and the top plate 9 are docked and locked through the cooperation of the locking execution unit 6 and the lock seat 7.

[0022] The present embodiment is a hexahedral micro-nano satellite composed of a plurality of cabin plates.

[0023] The present embodiment takes four side plates as an example. The plurality of side plates are divided into a first side plate 1, a second side plate 2, a third side plate 3 and a fourth side plate 4. The first side plate 1 and the third side plate 3 are provided with the locking execution unit 6 on the docking edge with the adjacent side plate. The first side plate 1, the second side plate 2, the third side plate 3 and the fourth side plate 4 are provided with the locking execution unit 6 on the docking edge with the top plate 9. The second side plate 2 and the fourth side plate 4 are provided with the lock seat 7 on the edge docking with the adjacent side plate. The top plate 9 is provided with the lock seat 7 on the edge docking with the side plate.

[0024] The cabin plate in the present embodiment adopts a structure of aluminum honeycomb core material and peripheral metal load-bearing frame embedded parts. Excellent lightweight and structural strength are achieved.

[0025] The gear 14 is provided with a driving hole 13, and the driving component 11 is inserted into the driving hole 13 to rotate the driving component 11 to drive the gear 14 to rotate. The driving component 11 is an independent and movable operating tool. Preferably, the driving hole 13 is a square hole structure, and the driving component 11 has a handle at one end and a square shaft structure at the other end, and the square hole structure and the square shaft structure are matched in size. The driving component 11 is sequentially inserted into the driving hole 13 of each locking execution unit 6 and rotated. The power is transmitted to the gear 14 through the driving component 11, and the driving transmission rod 16 moves linearly to push the locking point part 12 to slide.

[0026] The transmission rod 16 is provided with a connecting buckle 17, and the locking point part 12 is provided with a matching hole connected with the connecting buckle 17. The housing 18 is provided with a fixing hole 19, and the transmission rod 16 is provided with an oval opening. The transmission device 10 is connected to the cabin plate by using a screw passing through the fixing hole 19 and the oval opening. The bottom plate 5 is connected with each side plate through a plurality of hinges 8. The oval opening on the transmission rod 16 is used to avoid the mounting screw of the transmission device 10.

[0027] The embodiment is a use method of a cabin plate docking locking structure of batch-produced micro-nano satellites. Specifically, each side plate is connected with the bottom plate 5 through the hinge 8, so that the side plate is laid on the plane where the bottom plate 5 is located, and the cabin equipment installation and cable laying are performed. When the cabin is closed, each side plate is sequentially erected and placed on the top plate 9. An operator drives the gear 14 to rotate by using the driving component 11, drives the transmission rod 16 to move linearly through the meshing of the gear 14 and the rack 15, and drives the locking point part 12 to slide, so that the hook-shaped structure of the locking point part 12 slides into the stepped opening slot structure with a guide slope of the lock seat 7, locking is realized, and the cooperation of all locking execution units 6 and lock seats 7 is sequentially completed, so that the adjacent cabin plates are tightly pressed together.

[0028] The embodiment is specifically described as follows. The cabin plate docking locking structure of batch-produced micro-nano satellites mainly includes a cabin plate, a locking execution unit 6 and a lock seat 7. The cabin plate includes a bottom plate 5, a top plate 9 and first, second, third and fourth side plates 1, 2, 3 and 4. The bottom plate 5 is connected with each side plate through a plurality of hinges 8, so that the side plate can rotate around the hinge 8. All the cabin plates adopt a structure of aluminum honeycomb core material and peripheral metal bearing frame embedded parts to realize light weight and sufficient structural strength.

[0029] Locking execution units 6 and lock seats 7 are arranged on the abutting edges of the cabin panels. Specifically, the first side panel 1 and the third side panel 3 are provided with locking execution units 6 on the edges abutting the adjacent side panels, and the first side panel 1, the second side panel 2, the third side panel 3 and the fourth side panel 4 are provided with locking execution units 6 on the edges abutting the top panel 9. The second side panel 2 and the fourth side panel 4 are provided with lock seats 7 on the edges abutting the adjacent side panels, and the top panel 9 is provided with a lock seat 7 on the edge abutting the side panel. The locking execution unit 6 comprises a transmission 10, a driving component 11 and a locking point 12. The transmission 10 is mounted on the metal bearing frame of the cabin panel through a fixing hole 19 on the housing 18 thereof. A gear 14 is rotatably arranged inside the transmission 10, and a driving hole 13 in the form of a square hole structure is formed in the center of the gear 14. Two transmission rods 16 are also slidably connected inside the transmission 10, one side of each transmission rod 16 is provided with a rack 15 structure to engage with the gear 14, and the other side thereof is connected to the locking point 12 through a connecting buckle 17. The locking point 12 is slidably arranged on the guide rail of the cabin panel frame, and a hook-shaped structure is provided on the upper end thereof. The driving component 11 is a separate tool, one end of which is a handle, and the other end thereof is a square shaft structure matching the driving hole 13 in size. The lock seat 7 is fixed to the edge of the passively abutting cabin panel by screws, and has a stepped opening slot structure with a guide slope.

[0030] When the structure is installed, first, the locking point 12 is placed in the guide rail of the metal bearing frame of the cabin panel. Then, the transmission 10 is positioned, the mating hole of the connecting buckle 17 and the locking point 12 is accurately abutted, and the transmission 10 is fastened to the frame through the fixing hole 19. The driving hole 13 of the transmission 10 is exposed to the outside of the cabin panel.

[0031] When the satellite is assembled, each side panel is laid flat on the plane where the bottom panel 5 is located through the hinge 8, which facilitates the installation of equipment in the cabin and the laying of cables. When the cabin is closed, the operator successively raises each side panel around the hinge 8, and then places the top panel 9. Subsequently, the square shaft end of the driving component 11 is inserted into the driving hole 13 of the locking execution unit 6, and the driving component 11 is rotated to drive the gear 14 to rotate. Through the engagement of the gear 14 and the rack 15, the transmission rod 16 moves linearly, and the locking point 12 is pushed along the guide rail through the connecting buckle 17. The hook-shaped structure of the locking point 12 slides into the stepped opening slot of the lock seat 7 under the guidance of the guide slope, realizing mechanical self-locking and tightly pressing the adjacent cabin panels. By successively operating all the locking execution units 6, the quick locking of the cabin panels of the whole satellite can be completed. When unlocking, the driving component 11 is rotated in the opposite direction to make the locking point 12 exit the lock seat 7, and the cabin panel can be opened.

[0032] The rotation is converted into linear motion by the gear 14 and the rack 15, and the lock point part 12 is driven to engage with the lock seat 7. The guide slope of the lock seat 7 ensures that the lock point part 12 is smoothly guided and pressed, and the connection reliability is ensured by the slope self-locking effect. The load distribution of the multiple lock point parts 12 improves the overall structure stress and reduces stress concentration. The quick and repeatable cabin plate locking and separation is realized, and the overall assembly efficiency and maintenance convenience are significantly improved.

[0033] The above disclosed embodiments of the present application are only used to help explain the present application. The embodiments do not describe all the details, nor limit the present application to the specific embodiments. According to the content of the present application, many modifications and changes can be made. The present application selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that those skilled in the art can well understand and utilize the present application.

Claims

1. A panel docking and locking structure for mass-produced micro / nano satellites, characterized in that: It includes cabin plate, locking execution unit (6) and lock seat (7), the cabin plate is divided into bottom plate (5), top plate (9) and multiple side plates, the multiple side plates are connected with bottom plate (5) through hinge (8), locking execution unit (6) and lock seat (7) are respectively arranged on the two butt joint edges of adjacent side plates, locking execution unit (6) and lock seat (7) are respectively arranged on the two butt joint edges of side plate and top plate (9), the locking execution unit (6) includes transmission (10), driving part (11) and locking point part (12), the transmission (10) includes shell (18), gear (14) and transmission rod (16), the shell (18) is connected with cabin plate, the gear (14) is rotatably arranged in the shell (18), the shell (18) is slidably connected with two transmission rods (16), one side of the transmission rod (16) is provided with rack (15) structure, the other side of the transmission rod (16) is connected with locking point part (12), the rack (15) is engaged with gear (14), the gear (14) is driven to rotate by driving part (11), the locking point part (12) is slidably connected with cabin plate, the upper end of the locking point part (12) is provided with hook structure, the lock seat (7) is ladder type opening groove structure with guide inclined plane, the adjacent side plates and the side plate and top plate (9) are locked by the cooperation of locking execution unit (6) and lock seat (7).

2. The docking and locking structure of the cabin panel of the batch-produced micro-nano satellite according to claim 1, characterized in that: Multiple cabin plates form a hexahedral micro-nano satellite.

3. The docking and locking structure of the cabin panel of the batch-produced micro-nano satellite according to claim 1, characterized in that: The multiple side plates are divided into first side plate (1), second side plate (2), third side plate (3) and fourth side plate (4), the first side plate (1) and third side plate (3) are provided with locking execution unit (6) on the butt joint edge with adjacent side plate, the first side plate (1), second side plate (2), third side plate (3) and fourth side plate (4) are provided with locking execution unit (6) on the butt joint edge with top plate (9), the second side plate (2) and fourth side plate (4) are provided with lock seat (7) on the edge butted with adjacent side plate, and the top plate (9) is provided with lock seat (7) on the edge butted with side plate.

4. The docking and locking structure of a batch-produced micro-nano satellite cabin panel according to claim 1, characterized in that: The cabin plate adopts the structure of aluminum honeycomb core material and peripheral metal force frame embedded part.

5. The docking and locking structure of the cabin panel of the batch-produced micro-nano satellite according to claim 1, characterized in that: The gear (14) is provided with driving hole (13) in the center, the driving part (11) is inserted into the driving hole (13), and the driving part (11) is driven to rotate the gear (14).

6. The docking and locking structure of a batch-produced micro-nano satellite cabin panel according to claim 5, characterized in that: The driving hole (13) is square hole structure, one end of the driving part (11) is handle, and the other end is square shaft structure, and the square hole structure and the square shaft structure are matched in size.

7. The docking and locking structure of a batch-produced micro-nano satellite cabin panel according to claim 1, characterized in that: The transmission rod (16) is provided with connecting buckle (17), and the locking point part (12) is provided with matching hole connected with the connecting buckle (17).

8. The docking and locking structure of a batch-produced micro-nano satellite cabin panel according to claim 1, characterized in that: The shell (18) is provided with fixing hole (19), and the transmission rod (16) is provided with oval opening, and the transmission (10) is connected to the cabin plate by screwing through the fixing hole (19) and the oval opening.

9. The docking and locking structure of a batch-produced micro-nano satellite cabin panel according to claim 1, characterized in that: The bottom plate (5) is connected with each side plate through multiple hinges (8).

10. The use of the docking and locking structure of the cabin panel of the batch-produced micro-nano satellites according to claim 1, characterized in that: Each side plate is connected with the bottom plate (5) through a hinge (8), so that the side plate is laid on the plane where the bottom plate (5) is located, and the installation of cabin equipment and the laying of cables are carried out; when the cabin is closed, each side plate is placed on the top plate (9) after being erected in sequence; an operator drives the gear (14) to rotate by using a driving component (11); the gear (14) is engaged with the rack (15), the transmission rod (16) is driven to move linearly, the locking point part (12) is driven to slide, the hook-shaped structure of the locking point part (12) slides into the stepped opening slot structure with a guide slope of the lock seat (7), locking is realized, the cooperation of all locking and closing execution units (6) and lock seats (7) is completed in sequence, and the adjacent cabin plates are tightly pressed and combined.

Images