Automatic screw locking device for aviation part shell

Abstract

The utility model discloses an aviation part shell automatic screw locking device which comprises a main installation assembly, two longitudinal movement control assemblies are arranged on the main installation assembly, auxiliary limiting assemblies are arranged at the output ends of the longitudinal movement control assemblies, and a screw storage assembly is arranged on the main installation assembly and located on one side of the longitudinal movement control assemblies. Side supporting assemblies are arranged on the two sides of the main mounting assembly, a transverse movement control assembly is arranged at the top ends of the side supporting assemblies, an auxiliary mounting assembly is arranged on the moving portion of the transverse movement control assembly, a lifting guide assembly is arranged on the auxiliary mounting assembly, and a lifting frame is arranged on the moving portion of the lifting guide assembly. The screw locking device is ingenious in structural design and high in practicability, manual screw locking and fixing operation on an aviation part shell and an aviation part is replaced with the screw locking device, the assembling and fixing efficiency of the aviation part shell and the aviation part is effectively improved, and the labor intensity of workers is reduced.

Description

Technical Field

[0001] This utility model relates to the field of aerospace component processing technology, and in particular to an automatic screw-locking device for aerospace component housings. Background Technology

[0002] In the production process of aerospace components, multiple aircraft shells need to be assembled with the aircraft components. After assembly, the aircraft shells are fixed with screws to secure them to the aircraft components. The existing screw fixing operation is done manually. Manual screw fixing results in long working hours, high labor intensity for workers, and low assembly and fixing efficiency of aircraft components and aircraft shells. Therefore, it is necessary to design an automatic screw fixing device for aircraft shells. Utility Model Content

[0003] The purpose of this invention is to solve the above-mentioned problems by designing an automatic screw-locking device for the outer shell of aircraft parts.

[0004] To achieve the above objectives, the technical solution of this utility model is an automatic screw-locking device for aircraft component shells, comprising a main mounting assembly, two longitudinal movement control assemblies on the main mounting assembly, an auxiliary limiting assembly at the output end of the longitudinal movement control assemblies, a screw storage assembly on one side of the longitudinal movement control assemblies on the main mounting assembly, side support assemblies on both sides of the main mounting assembly, a lateral movement control assembly at the top of the side support assemblies, an auxiliary mounting assembly on the moving part of the lateral movement control assembly, a lifting guide assembly on the auxiliary mounting assembly, a lifting frame on the moving part of the lifting guide assembly, a screw-locking assembly on the lifting frame, a lifting control assembly at the top of the auxiliary mounting assembly, and the lifting frame connected to the output end of the lifting control assembly.

[0005] As a further description of this technical solution, the main mounting assembly includes a main mounting platform, on which two longitudinal movement control components are disposed.

[0006] As a further description of this technical solution, the longitudinal movement control component includes a longitudinal movement control module disposed on the main mounting component, and the output end of the longitudinal movement control module is provided with an auxiliary limiting component.

[0007] As a further description of this technical solution, the auxiliary limiting component includes an auxiliary limiting frame disposed at the output end of the longitudinal movement control component, and the auxiliary limiting frame is provided with a main limiting groove.

[0008] As a further description of this technical solution, an adjustment groove is provided on one side of the main limiting groove on the auxiliary limiting frame, and an adjustment fixing block is provided in the adjustment groove.

[0009] As a further description of this technical solution, the screw storage assembly includes a screw storage box disposed on the main mounting assembly and located on one side of the longitudinal movement control assembly.

[0010] As a further description of this technical solution, the side support assembly includes side support columns disposed on both sides of the main mounting assembly, and a lateral movement control assembly is disposed at the top of the side support columns.

[0011] As a further description of this technical solution, the lateral movement control component includes a lateral movement control module disposed at the top of the side support component, and the moving part of the lateral movement control module is provided with an auxiliary installation component.

[0012] As a further description of this technical solution, the lifting guide assembly includes a lifting guide rail disposed on the auxiliary installation assembly, a movable slider disposed on the lifting guide rail, and a lifting frame disposed on the movable slider.

[0013] As a further description of this technical solution, the screw fastening assembly includes a screw fastening motor mounted on a lifting frame, and the output end of the screw fastening motor is provided with a screwdriver head.

[0014] Its beneficial effects are that the screw-locking device of this technical solution has a clever structural design and strong practicality. Using this screw-locking device, the manual operation of screw-locking and fixing of aircraft parts and shells is replaced, which effectively improves the assembly and fixing efficiency of aircraft parts and shells and aircraft parts, and also reduces the labor intensity of workers. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0016] Figure 2 This is a schematic diagram of the overall structure of this utility model from another perspective.

[0017] In the diagram, 1. Main mounting assembly; 2. Longitudinal movement control assembly; 3. Auxiliary limit assembly; 4. Screw storage assembly; 5. Side support assembly; 6. Lateral movement control assembly; 7. Auxiliary mounting assembly; 8. Lifting guide assembly; 9. Lifting frame; 10. Screw tightening assembly; 11. Lifting control assembly; 12. Main mounting platform; 13. Longitudinal movement control module; 14. Auxiliary limit frame; 15. Main limit groove; 16. Adjustment groove; 17. Adjustment fixing block; 18. Screw storage box; 19. Side support column; 20. Lateral movement control module; 21. Lifting guide rail; 22. Moving slider; 23. Screw tightening motor; 24. Screwdriver head. Detailed Implementation

[0018] First, let me explain the design intention of this utility model. In the production process of aviation components, it is necessary to assemble multiple aviation component shells and aviation components. After assembly, the aviation component shells are fixed with screws to fix them to the aviation components. The existing screw fixing operation is done manually. Manual screw fixing is time-consuming and labor-intensive for workers, and the assembly and fixing efficiency of aviation components and aviation component shells is low. Therefore, this utility model designs an automatic screw fixing device for aviation component shells.

[0019] The present invention will now be described in detail with reference to the accompanying drawings, such as... Figures 1-2 As shown, an automatic screw-locking device for aircraft component housings includes a main mounting assembly 1. The main mounting assembly 1 will be described in detail below. The main mounting assembly 1 includes a main mounting platform 12, on which two longitudinal movement control components 2 are provided.

[0020] To facilitate the longitudinal movement of the auxiliary limiting component 3, two longitudinal movement control components 2 are provided on the main mounting component 1. The longitudinal movement control components 2 will be described in detail below. The longitudinal movement control components 2 include a longitudinal movement control module 13 provided on the main mounting component 1, and the output end of the longitudinal movement control module 13 is provided with the auxiliary limiting component 3.

[0021] To facilitate the positioning of aircraft components and their outer shells, an auxiliary positioning component 3 is provided at the output end of the longitudinal movement control component 2. The auxiliary positioning component 3 will be described in detail below. The auxiliary positioning component 3 includes an auxiliary positioning frame 14 provided at the output end of the longitudinal movement control component 2. The auxiliary positioning frame 14 is provided with a main positioning groove 15. An adjustment groove 16 is provided on one side of the main positioning groove 15 on the auxiliary positioning frame 14. An adjustment fixing block 17 is provided in the adjustment groove 16.

[0022] To facilitate screw storage, a screw storage assembly 4 is provided on the main mounting assembly 1 on one side of the longitudinal movement control assembly 2. The screw storage assembly 4 will be described in detail below. The screw storage assembly 4 includes a screw storage box 18 provided on the main mounting assembly 1 on one side of the longitudinal movement control assembly 2.

[0023] To facilitate the installation of the lateral movement control component 6, side support components 5 are provided on both sides of the main mounting component 1. The side support components 5 will be described in detail below. The side support components 5 include side support columns 19 provided on both sides of the main mounting component 1, and the lateral movement control component 6 is provided at the top of the side support columns 19.

[0024] To facilitate the control of the lateral movement of the auxiliary installation component 7, a lateral movement control component 6 is provided at the top of the side support component 5. The lateral movement control component 6 will be described in detail below. The lateral movement control component 6 includes a lateral movement control module 20 provided at the top of the side support component 5. The moving part of the lateral movement control module 20 is provided with the auxiliary installation component 7.

[0025] To facilitate the installation of the lifting guide assembly 8 and the lifting control assembly 11, an auxiliary installation assembly 7 is provided at the moving part of the lateral movement control assembly 6.

[0026] To facilitate the lifting and guiding of the lifting frame 9, a lifting guide component 8 is provided on the auxiliary installation component 7. The lifting guide component 8 will be described in detail below. The lifting guide component 8 includes a lifting guide rail 21 provided on the auxiliary installation component 7, a movable slider 22 provided on the lifting guide rail 21, and a lifting frame 9 provided on the movable slider 22.

[0027] To facilitate the installation of the screw fastening assembly 10, a lifting frame 9 is provided on the moving part of the lifting guide assembly 8, and the screw fastening assembly 10 is provided on the lifting frame 9. The screw fastening assembly 10 will be described in detail below. The screw fastening assembly 10 includes a screw fastening motor 23 provided on the lifting frame 9, and a screwdriver head 24 is provided at the output end of the screw fastening motor.

[0028] In order to control the lifting and moving of the lifting frame 9, a lifting control component 11 is provided at the top of the auxiliary installation component 7, and the output end of the lifting control component 11 is connected to the lifting frame 9.

[0029] The specific structure of this utility model has been described in detail above. The working principle of this utility model will be explained below: In use, the aviation component is placed in the main limiting groove 15 on the auxiliary limiting frame 14. Then, the aviation component housing is placed on the aviation component. Next, the adjusting fixing block 17 is adjusted to the side of the aviation component housing in the adjusting groove 16 and fixed to the auxiliary limiting frame 14 by the fixing component. The screw in the screw storage assembly 4 is transported to the top of the aviation component housing by the external robotic arm. The lateral movement control module 20 drives the screw locking assembly 10 to move above the screw. The lifting control assembly 11 controls the screw locking assembly 10 to descend and contact the screw. The screw locking assembly 10 tightens the screw on the aviation component housing and the aviation component, thereby fixing the aviation component housing and the aviation component. The screw locking device of this technical solution has a clever structural design and strong practicality. Using this screw locking device, the manual screw fixing operation of the aviation component housing and the aviation component is replaced, which effectively improves the assembly and fixing efficiency of the aviation component housing and the aviation component and also reduces the labor intensity of workers.

[0030] The above technical solution only embodies the preferred technical solution of this utility model. Any changes that may be made by those skilled in the art to certain parts of it embody the principle of this utility model and fall within the protection scope of this utility model.

Claims

1. An automatic screw-locking device for the outer shell of an aircraft component, characterized in that, The system includes a main mounting component (1), on which two longitudinal movement control components (2) are provided. An auxiliary limit component (3) is provided at the output end of the longitudinal movement control component (2). A screw storage component (4) is provided on one side of the longitudinal movement control component (2) on the main mounting component (1). Side support components (5) are provided on both sides of the main mounting component (1). A transverse movement control component (6) is provided at the top of the side support component (5). An auxiliary mounting component (7) is provided at the moving part of the transverse movement control component (6). A lifting guide component (8) is provided on the auxiliary mounting component (7). A lifting frame (9) is provided at the moving part of the lifting guide component (8). A screw locking component (10) is provided on the lifting frame (9). A lifting control component (11) is provided at the top of the auxiliary mounting component (7). The lifting frame (9) is connected to the output end of the lifting control component (11).

2. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The main mounting assembly (1) includes a main mounting stand (12), on which two longitudinal movement control assemblies (2) are provided.

3. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The longitudinal movement control component (2) includes a longitudinal movement control module (13) disposed on the main mounting component (1), and an auxiliary limit component (3) is provided at the output end of the longitudinal movement control module (13).

4. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The auxiliary limiting component (3) includes an auxiliary limiting frame (14) disposed at the output end of the longitudinal movement control component (2), and the auxiliary limiting frame (14) is provided with a main limiting groove (15).

5. The automatic screw-locking device for the outer shell of an aircraft component according to claim 4, characterized in that, An adjustment groove (16) is provided on one side of the main limiting groove (15) on the auxiliary limiting frame (14), and an adjustment fixing block (17) is provided in the adjustment groove (16).

6. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The screw storage assembly (4) includes a screw storage box (18) disposed on the main mounting assembly (1) on one side of the longitudinal movement control assembly (2).

7. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The side support assembly (5) includes side support columns (19) arranged on both sides of the main mounting assembly (1), and a lateral movement control assembly (6) is provided at the top of the side support column (19).

8. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The lateral movement control assembly (6) includes a lateral movement control module (20) disposed at the top of the side support assembly (5), and the moving part of the lateral movement control module (20) is provided with an auxiliary installation assembly (7).

9. The automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The lifting guide assembly (8) includes a lifting guide rail (21) disposed on the auxiliary installation assembly (7), a movable slider (22) is disposed on the lifting guide rail (21), and a lifting frame (9) is disposed on the movable slider (22).

10. An automatic screw-locking device for the outer shell of an aircraft component according to claim 1, characterized in that, The screw-locking assembly (10) includes a screw-locking motor (23) mounted on a lifting frame (9), and the output end of the screw-locking motor is provided with a screwdriver head (24).

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