Adjustable bracket for aircraft assembly

Abstract

The utility model discloses an adjustable bracket for aircraft assembly, and relates to the technical field of adjustable brackets. Comprising a positioning plate, a moving mechanism is installed at the bottom of the positioning plate, a first screw rod is rotatably installed in a first groove, one end of the first screw rod penetrates to one side of the positioning plate and is fixedly connected with a first servo motor, and a second screw rod is rotatably installed in a second groove. One end of the second screw rod penetrates to one side of the mounting plate and is fixedly connected with a second servo motor, a second threaded block is installed on the outer wall of the second screw rod in a threaded mode, and a bearing mechanism is installed at the top of the second threaded block. And meanwhile, the assembly precision can be improved, the aircraft assembly efficiency can be improved to a certain extent, airframes of different specifications can be borne by adjusting the radian of the bearing plate, and the use flexibility of the device can be improved.

Description

Technical Field

[0001] This utility model relates to the field of bracket technology, and in particular to an adjustable bracket for aircraft assembly. Background Technology

[0002] In aircraft assembly, ensuring coordination between parts and components, and thus guaranteeing assembly accuracy, is a crucial characteristic of aircraft manufacturing coordination. Aircraft assembly accuracy directly impacts aircraft performance and service life, making it the core of the entire assembly process. Currently, aircraft production sites often use component assembly trays to achieve coordinated fuselage assembly. However, existing assembly trays have complex structures, requiring multiple manual adjustments, increasing assembly complexity. Furthermore, manual adjustments result in poor assembly precision, low efficiency, and significant inconvenience, increasing the labor intensity for workers.

[0003] An adjustable assembly bracket is needed on the production site to improve the accuracy and efficiency of aircraft assembly. Summary of the Invention

[0004] This utility model provides an adjustable bracket for aircraft assembly, which solves the technical problems of poor assembly accuracy, low efficiency, and increased labor intensity caused by manual operation.

[0005] This utility model provides an adjustable bracket for aircraft assembly, including a positioning plate. A moving mechanism is installed at the bottom of the positioning plate, and a first groove is fixedly installed at the top of the positioning plate. Two first grooves are symmetrically arranged around the center line of the positioning plate. A first screw is rotatably installed inside the first groove. One end of the first screw passes through to one side of the positioning plate and is fixedly connected to a first servo motor. The first servo motor is fixedly installed on one side of the positioning plate. A first threaded block is threaded onto the outer wall of the first screw. An mounting plate is fixedly installed on the top of the first threaded block. A second groove is formed at the top of the mounting plate. A second screw is rotatably installed inside the second groove. One end of the second screw passes through to one side of the mounting plate and is fixedly connected to a second servo motor. The second servo motor is fixedly installed on one side of the mounting plate. A second threaded block is threaded onto the outer wall of the second screw. A bearing mechanism is installed on the top of the second threaded block.

[0006] Preferably, the moving mechanism includes a third groove, which is formed at the bottom of the positioning plate. An electric push rod is fixedly installed inside the third groove. A fixing plate is fixedly connected to the piston rod end of the electric push rod, and a caster wheel is installed at the bottom of the fixing plate.

[0007] Preferably, a fixing frame is fixedly installed on both sides of the fixing plate at the bottom of the positioning plate. A fourth groove is opened inside the fixing frame. A guide rod is fixedly installed inside the fourth groove. A slider is sleeved on the outer wall of the guide rod. The slider is fixedly installed on the side wall of the fixing plate.

[0008] Preferably, the bearing mechanism includes a bearing frame, which is fixedly installed on the top of the second threaded block. A plurality of first damping buffers are fixedly installed on the top of the bearing frame, and a bearing plate is fixedly connected to the piston rod end of each first damping buffer.

[0009] Preferably, a first rotating seat is fixedly installed on the outer wall of the cylinder of each of the first damping buffers, a second damping buffer is rotatably installed inside the first rotating seat, the piston rod end of the second damping buffer is rotatably connected to the second rotating seat, and the second rotating seat is fixedly installed on the bottom of the support plate.

[0010] Preferably, the first rotating seat, the second damping buffer, and the second rotating seat are all provided with through holes, and a pin is inserted into the through hole. Locking nuts are threaded onto the outer walls of both ends of the pin, and one side of the locking nut is respectively fitted to one side of the first rotating seat and the second rotating seat.

[0011] Compared with related technologies, the adjustable bracket for aircraft assembly provided by this utility model has the following advantages:

[0012] Beneficial effects:

[0013] The bracket provided by this utility model, through the cooperation of a first servo motor and a second servo motor, can realize the mechanized adjustment of the fuselage position, avoid manual operation, reduce the labor intensity of workers, improve assembly accuracy, and improve the efficiency of aircraft assembly to a certain extent. It solves the problem that manual operation and adjustment leads to poor assembly accuracy, low aircraft assembly efficiency, and increased labor intensity of workers.

[0014] The bracket provided by this utility model uses a first damping buffer and a second damping buffer to cooperate in order to adjust the curvature of the bearing plate, thereby enabling it to support different sizes of machine bodies. This improves the flexibility of the device and solves the problem that existing devices have low flexibility and can mostly only support machine bodies of the same size. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0016] Figure 2 This is a three-dimensional schematic diagram of the first partial exploded structure of this utility model;

[0017] Figure 3 This is a partial three-dimensional structural schematic diagram of the present invention;

[0018] Figure 4 This is a schematic diagram of the second partial exploded three-dimensional structure of the present invention.

[0019] In the diagram: 101, positioning plate; 102, first screw; 103, first servo motor; 104, first threaded block; 105, mounting plate; 106, second screw; 107, second servo motor; 108, second threaded block; 200, moving mechanism; 201, electric push rod; 202, fixing plate; 203, caster wheel; 204, fixing frame; 205, guide rod; 206, slider; 300, bearing mechanism; 301, bearing frame; 302, first damping buffer; 303, bearing plate; 304, first rotating seat; 305, second damping buffer; 306, second rotating seat. Detailed Implementation

[0020] The technical solution of this utility model will be described in detail below with reference to the accompanying drawings.

[0021] This utility model includes a positioning plate 101. A moving mechanism 200 is installed at the bottom of the positioning plate 101, which facilitates the movement of the device. A first groove is fixedly installed on the top of the positioning plate 101. Two first grooves are symmetrically arranged around the center line of the axis of the positioning plate 101. A first screw 102 is rotatably installed inside the first groove. One end of the first screw 102 passes through to one side of the positioning plate 101 and is fixedly connected to a first servo motor 103. The first servo motor 103 is fixedly installed on one side of the positioning plate 101. A first threaded block 104 is threadedly installed on the outer wall of the first screw 102. The first servo motor 103 can control the rotation of the first screw 102, and the rotation of the first screw 102 can control the movement of the first threaded block 104.

[0022] A mounting plate 105 is fixedly installed on the top of the first threaded block 104. The movement of the first threaded block 104 can drive the mounting plate 105 to move. A second groove is opened on the top of the mounting plate 105. A second screw 106 is rotatably installed inside the second groove. One end of the second screw 106 passes through to one side of the mounting plate 105 and is fixedly connected to a second servo motor 107. The second servo motor 107 is fixedly installed on one side of the mounting plate 105. A second threaded block 108 is threaded on the outer wall of the second screw 106. A bearing mechanism 300 is installed on the top of the second threaded block 108. The second servo motor 107 can control the rotation of the second screw 106. The rotation of the second screw 106 can drive the movement of the second threaded block 108. The movement of the second threaded block 108 can control the movement of the bearing mechanism 300. The bearing mechanism 300 can support the machine body.

[0023] The moving mechanism 200 includes a third groove, which is located at the bottom of the positioning plate 101. An electric push rod 201 is fixedly installed inside the third groove. A fixed plate 202 is fixedly connected to the piston rod end of the electric push rod 201. A caster wheel 203 is installed at the bottom of the fixed plate 202. A fixed frame 204 is fixedly installed on both sides of the fixed plate 202 at the bottom of the positioning plate 101. A fourth groove is provided inside the fixed frame 204. A guide rod 205 is fixedly installed inside the fourth groove. A slider 206 is sleeved on the outer wall of the guide rod 205. The slider 206 is fixedly installed on the side wall of the fixed plate 202. The electric push rod 201 can control the lifting and lowering of the fixed plate 202. The lifting and lowering of the fixed plate 202 can control the lifting and lowering of the caster wheel 203. The guide rod 205 and the slider 206 cooperate to guide and limit the lifting and lowering of the fixed plate 202. The fixed frame 204 can conveniently support the device.

[0024] The bearing mechanism 300 includes a bearing frame 301, which is fixedly mounted on the top of the second threaded block 108. Multiple first damping buffers 302 are fixedly mounted on the top of the bearing frame 301. A bearing plate 303 is fixedly connected to the piston rod end of each first damping buffer 302. A first rotating seat 304 is fixedly mounted on the outer wall of the cylinder of each first damping buffer 302. A second damping buffer 305 is rotatably mounted inside the first rotating seat 304. A second rotating seat 306 is rotatably connected to the piston rod end of the second damping buffer 305. The second rotating seat 306 is fixedly mounted on the bottom of the bearing plate 303. The first rotating seat 304, the first... Both the second damping buffer 305 and the second rotating seat 306 have through holes, into which pins are inserted. Locking nuts are threaded onto the outer walls of both ends of the pins. One side of the locking nuts is respectively attached to one side of the first rotating seat 304 and the second rotating seat 306. The bearing plate 303 supports the machine body. The first damping buffer 302 can buffer the bearing plate 303 when it is subjected to the weight of the machine body. The first rotating seat 304, the second damping buffer 305 and the second rotating seat 306 cooperate with each other to adjust the curvature of the bearing plate 303, thereby enabling the bearing of machine bodies of different specifications.

[0025] Working principle: In use, the user can fix one half of the machine body and place the other half on the support plate 303. Under the weight of the machine body, the curvature of the support plate 303 will change, and the first damping buffer 302 will buffer the descent of the support plate 303. At the same time, it will control the second damping buffer 305 to buffer the support plate 303. Then, the electric push rod 201 can be activated, which can push the fixed plate 202 to descend, thereby driving the caster wheel 203 to descend. When the caster wheel 203 contacts the ground, the caster wheel 203 can be controlled to rotate, thereby controlling the descent of the machine body. The device moves, and then the first servo motor 103 can be activated. The first servo motor 103 can control the rotation of the first screw 102. During the rotation of the first screw 102, the first threaded block 104 can be controlled to move. Through the movement of the first threaded block 104, the mounting plate 105 can be moved. At the same time, the second servo motor 107 can be activated. The second servo motor 107 can drive the second screw 106 to rotate. Through the rotation of the second screw 106, the second threaded block 108 can be moved, and the position of the machine body can be adjusted. After the two sections of the machine body are aligned, the machine body can be assembled.

Claims

1. An adjustable bracket for aircraft assembly, characterized in that, The system includes a positioning plate (101), which is fixedly connected to a first servo motor (103) via a first screw. A mounting plate (105) is fixedly mounted on the top of the positioning plate (101) via a first threaded block. A fixing plate (202) is fixedly connected to the bottom of the positioning plate (101). A caster wheel (203) is mounted on the bottom of the fixing plate (202), and fixing brackets (204) are fixedly mounted on both sides. A support frame is fixedly mounted on the mounting plate (105) via a second threaded block. (301) A plurality of first damping buffers (302) are fixedly installed on the top of the support frame (301). Each first damping buffer (302) has a support plate (303) fixedly connected to the piston rod end. Each first damping buffer (302) and the support plate (303) are connected through a first rotating seat (304) and a second rotating seat (306) and a second damping buffer (305) rotatably installed inside the first rotating seat (304) and the second rotating seat (306).

2. The adjustable bracket for aircraft assembly according to claim 1, characterized in that: A moving mechanism (200) is installed at the bottom of the positioning plate (101), and a first groove is fixedly installed at the top of the positioning plate (101). Two first grooves are symmetrically arranged around the center line of the positioning plate (101). A first screw (102) is rotatably installed inside the first groove. One end of the first screw (102) passes through to one side of the positioning plate (101) and is fixedly connected to a first servo motor (103). The first servo motor (103) is fixedly installed on one side of the positioning plate (101). A first threaded block (104) is threaded onto the outer wall of the first screw (102). A mounting plate (105) is fixedly installed on the top of the first threaded block (104). A second groove is provided on the top of the mounting plate (105). A second screw (106) is rotatably installed inside the second groove. One end of the second screw (106) passes through to one side of the mounting plate (105) and is fixedly connected to a second servo motor (107). The second servo motor (107) is fixedly installed on one side of the mounting plate (105). A second threaded block (108) is threaded on the outer wall of the second screw (106). A bearing mechanism (300) is installed on the top of the second threaded block (108).

3. An adjustable bracket for aircraft assembly according to claim 2, characterized in that, The moving mechanism (200) includes a third groove, which is located at the bottom of the positioning plate (101). An electric push rod (201) is fixedly installed inside the third groove. A fixing plate (202) is fixedly connected to the piston rod end of the electric push rod (201). A caster wheel (203) is installed at the bottom of the fixing plate (202).

4. An adjustable bracket for aircraft assembly according to claim 3, characterized in that, The bottom of the positioning plate (101) is fixedly installed with a fixing frame (204) on both sides of the fixing plate (202). The fixing frame (204) has a fourth groove inside. A guide rod (205) is fixedly installed inside the fourth groove. A slider (206) is sleeved on the outer wall of the guide rod (205). The slider (206) is fixedly installed on the side wall of the fixing plate (202).

5. An adjustable bracket for aircraft assembly according to claim 4, characterized in that, The bearing mechanism (300) includes a bearing frame (301), which is fixedly installed on the top of the second threaded block (108). A plurality of first damping buffers (302) are fixedly installed on the top of the bearing frame (301), and a bearing plate (303) is fixedly connected to the piston rod end of each first damping buffer (302).

6. An adjustable bracket for aircraft assembly according to claim 5, characterized in that, Each of the first damping buffers (302) has a first rotating seat (304) fixedly installed on the outer wall of the cylinder body. A second damping buffer (305) is rotatably installed inside the first rotating seat (304). The piston rod end of the second damping buffer (305) is rotatably connected to a second rotating seat (306). The second rotating seat (306) is fixedly installed on the bottom of the support plate (303).

7. An adjustable bracket for aircraft assembly according to claim 5, characterized in that, The first rotating seat (304), the second damping buffer (305) and the second rotating seat (306) are all provided with through holes. A pin is inserted into the through hole. Locking nuts are threaded on the outer walls of both ends of the pin. One side of the locking nut is respectively attached to one side of the first rotating seat (304) and the second rotating seat (306).

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