CN220636397U - Hole making device for aircraft assembly automatic drilling equipment - Google Patents
Hole making device for aircraft assembly automatic drilling equipment Download PDFInfo
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- CN220636397U CN220636397U CN202322352442.XU CN202322352442U CN220636397U CN 220636397 U CN220636397 U CN 220636397U CN 202322352442 U CN202322352442 U CN 202322352442U CN 220636397 U CN220636397 U CN 220636397U
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- 238000005553 drilling Methods 0.000 title claims abstract description 55
- 239000003638 chemical reducing agent Substances 0.000 claims description 12
- 230000001360 synchronised effect Effects 0.000 claims description 8
- 238000003754 machining Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Abstract
The utility model relates to a drilling equipment part, in particular to a hole making device for aircraft assembly automation drilling equipment, which comprises a B-axis swinging structure, an A-axis swinging structure, a clamping mechanism and a drilling mechanism which are sequentially arranged from top to bottom, wherein the B-axis swinging structure is rotationally connected with the A-axis swinging structure, the clamping mechanism is fixedly connected with the A-axis swinging structure, and the drilling mechanism is fixedly arranged at the lower part of the front end of the clamping mechanism; the B-axis swinging structure drives the A-axis swinging structure, the clamping mechanism and the drilling mechanism to swing in the horizontal plane, and the A-axis swinging structure drives the clamping mechanism and the drilling mechanism to swing in the vertical plane. The hole making device for the aircraft assembly automatic drilling equipment has the advantages of high precision, high efficiency, high reliability and automation, and is compact in structure, small in occupied area and easy to install and modulate.
Description
Technical Field
The utility model relates to a drilling equipment component, in particular to a hole making device for aircraft assembly automation drilling equipment.
Background
The connection of structural members such as wing plates of the aircraft is mainly riveting. The existing production means mainly uses manpower to process rivet holes of wing plates, and has low efficiency and low precision. The existing equipment with the automatic drilling function is complex in structure, large in weight, large in gravity deformation, and low in reliability, and can not be applied to riveting of structural members such as wing plates of an airplane due to the fact that the structure is complex, drilling accuracy is affected.
Disclosure of Invention
The utility model provides a hole making device for an aircraft assembly automatic drilling device, which has the advantages of high precision, high efficiency, high reliability and automation, and has the advantages of compact structure, small occupied area and easy installation and modulation.
The technical scheme of the utility model is as follows:
a hole making device for aircraft assembly automation drilling equipment comprises a B-axis swinging structure, an A-axis swinging structure, a clamping mechanism and a drilling mechanism which are sequentially arranged from top to bottom, wherein the B-axis swinging structure is rotationally connected with the A-axis swinging structure, the clamping mechanism is fixedly connected with the A-axis swinging structure, and the drilling mechanism is fixedly arranged at the lower part of the front end of the clamping mechanism; the B-axis swinging structure drives the A-axis swinging structure, the clamping mechanism and the drilling mechanism to swing in the horizontal plane, and the A-axis swinging structure drives the clamping mechanism and the drilling mechanism to swing in the vertical plane.
Further, the hole making device for the aircraft assembly automatic drilling equipment comprises a box body, a B-axis shell, a cycloid speed reducer and a first servo motor, wherein the box body and the B-axis shell are connected through the cycloid speed reducer to form a revolute pair, and the first servo motor is arranged on the box body and used for driving the cycloid speed reducer.
Further, the hole making device for the aircraft assembly automatic drilling equipment comprises an A-axis shell, a first bearing, a second bearing, a third bearing, a fourth bearing, a bearing seat, a first lead screw, a first nut, a second nut seat, a servo motor and a synchronous belt, wherein two sides of the A-axis shell are respectively provided with a first rotating shaft, and the first rotating shaft is in rotary connection with the B-axis shell through the first bearing; two sides of the bearing seat are respectively provided with a second rotating shaft, and the second rotating shaft is rotationally connected with the B-axis shell through a second bearing; the rotating shafts III are respectively arranged on two sides of the nut seat and are in rotary connection with the A-axis shell through bearings III; the screw rod I is rotationally connected with the bearing seat through a bearing IV, the screw nut I is in threaded connection with the screw rod I, and the screw nut I is fixedly arranged on the screw nut seat; the second servo motor is fixedly arranged on the bearing seat and drives the first screw rod through the synchronous belt.
A crank block mechanism is formed among the B shaft shell, the A shaft shell, the first screw rod, the bearing seat, the screw seat and the first screw rod, the first screw rod is driven to rotate by the second servo motor through the synchronous belt, and the first screw rod moves back and forth, so that the angle of the A shaft shell is changed, and the A shaft swing is realized.
Further, the hole making device for the aircraft assembly automatic drilling equipment comprises a first linear guide rail, a clamping slide plate, a second screw rod, a second screw nut and a third servo motor, wherein the first linear guide rail is fixedly arranged on the lower end surface of the A-axis shell, and the clamping slide plate and the first linear guide rail are installed together in a sliding fit manner; the screw rod II is rotationally connected with the A-axis shell, the screw nut II is in threaded connection with the screw rod II, and the screw nut II is fixedly arranged on the clamping sliding plate; the servo motor III is fixedly arranged on the A-axis shell and is used for driving the screw rod II.
Further, the hole making device for the aircraft assembly automatic drilling equipment is characterized in that a searching sensor is arranged at the front end of the clamping sliding plate, and the searching sensor comprises an angle sensor and a force sensor.
Further, the hole making device for the aircraft assembly automatic drilling equipment is characterized in that a grating ruler is arranged at the front end of the clamping sliding plate.
Further, the hole making device for the aircraft assembly automatic drilling equipment comprises a main shaft, a main shaft box, a camera, a linear guide rail II, a screw rod III, a screw nut III and a servo motor IV, wherein the linear guide rail II is fixedly arranged on the lower end surface of the clamping slide plate, and the main shaft box and the linear guide rail II are installed together in a sliding fit manner; the screw rod III is rotationally connected with the clamping slide plate, the screw nut III is in threaded connection with the screw rod III, and the screw nut III is fixedly arranged on the spindle box; the servo motor IV is fixedly arranged on the clamping slide plate and used for driving the screw rod III; the main shaft is arranged in the main shaft box, and the camera is arranged at the lower part of the main shaft box.
Further, the hole making device for the aircraft assembly automatic drilling equipment is characterized in that the B-axis shell is provided with an angle sensor II and an angle encoder I, and the angle encoder I is used for realizing closed-loop feedback of the B-axis swinging structure.
Further, the hole making device for the aircraft assembly automatic drilling equipment is characterized in that a first rotating shaft on one side of an A-axis shell is provided with a second angle encoder for realizing closed-loop control of an A-axis swinging structure; the first bearing on the other side of the A-axis shell is provided with an adjusting pad for adjusting the gap of the first bearing.
The beneficial effects of the utility model are as follows:
1. the B shaft is driven by the servo motor connected with the cycloid speed reducer, and the cycloid speed reducer is directly connected with the box body and the B shaft shell, so that the requirement of structural rigidity can be met without using a bearing, and the structure is compact and the weight is light.
2. The A-axis driving of the utility model adopts the crank slide block mechanism, so that the width of the A-axis can be reduced, and the structure is compact; meanwhile, the crank slide block mechanism is driven by the screw rod and the screw nut, and converts rotation into movement, so that small errors are facilitated, and the precision is improved.
3. The clamping mechanism can realize automatic searching normal direction and automatic positioning for drilling; the clamping mechanism can perform telescopic movement, so that the searching sensor contacts the machining surface, automatically searches the normal direction of the machining surface, and performs feedback so that the drilling mechanism is positioned at the correct position.
4. The drilling mechanism can realize the axial feeding and rotation of the cutter to drill and cut. The camera on the drilling mechanism can realize an automatic positioning function.
Drawings
FIG. 1 is a schematic diagram of a hole maker for an aircraft assembly automated drilling apparatus;
FIG. 2 is a front view of a hole maker for an aircraft assembly automated drilling apparatus;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a cross-sectional view taken along B-B in FIG. 3;
FIG. 5 is a cross-sectional view taken along line C-C of FIG. 3;
in the figure, 1 is a box body, 2 is a B-axis shell, 3 is an A-axis shell, 4 is a clamping slide plate, 5 is a servo motor I, 6 is a servo motor II, 7 is a synchronous belt, 8 is a cycloid speed reducer, 9 is a servo motor III, 10 is a servo motor IV, 11 is a lead screw I, 12 is a spindle box, 13 is a spindle, 14 is a camera, 15 is a rotating shaft I, 16 is a bearing I, 17 is an angle encoder II, 18 is a grating ruler, 19 is a bearing seat, 20 is a nut seat, 21 is a nut I, 22 is a bearing II, and 23 is a bearing III.
Detailed Description
As shown in fig. 1-5, a hole maker for an aircraft assembly automation drilling device comprises a B-axis swinging structure, an A-Axis swinging structure, a clamping mechanism and a drilling mechanism which are sequentially arranged from top to bottom, wherein the B-axis swinging structure is rotationally connected with the A-Axis swinging structure, the clamping mechanism is fixedly connected with the A-Axis swinging structure, and the drilling mechanism is fixedly arranged at the lower part of the front end of the clamping mechanism.
The B-axis swinging structure drives the A-axis swinging structure, the clamping mechanism and the drilling mechanism to swing in a horizontal plane, and the swinging angle range is +/-15 degrees; the B-axis swinging structure comprises a box body 1, a B-axis shell 2, a cycloid speed reducer 8 and a servo motor I5, wherein the box body 1 and the B-axis shell 2 are connected through the cycloid speed reducer 8 to form a revolute pair, and the servo motor I5 is arranged on the box body 1 and used for driving the cycloid speed reducer 8; the B-axis shell 2 is provided with an angle sensor II and an angle encoder I, and the angle encoder I is used for realizing closed-loop feedback of the B-axis swinging structure.
The A-axis swinging structure drives the clamping mechanism and the drilling mechanism to swing in a vertical plane, and the swinging angle range is +/-10 degrees; the A-axis swinging structure comprises an A-axis shell 3, a first bearing 16, a second bearing 22, a third bearing 23, a fourth bearing, a bearing seat 19, a first lead screw 11, a first nut 21, a first nut seat 20, a second servo motor 6 and a synchronous belt 7, wherein two sides of the A-axis shell 3 are respectively provided with a first rotary shaft 15, and the first rotary shaft 15 is in rotary connection with the B-axis shell 2 through the first bearing 16; two sides of the bearing seat 19 are respectively provided with a second rotating shaft, and the second rotating shaft is rotatably connected with the B-axis shell 2 through a second bearing 22; the two sides of the nut seat 20 are respectively provided with a third rotating shaft, and the third rotating shaft is rotatably connected with the A-shaft shell 3 through a third bearing 23; the first screw rod 11 is rotationally connected with the bearing seat 19 through a bearing IV, the first screw nut 21 is in threaded connection with the first screw rod 11, and the first screw nut 21 is fixedly arranged on the first screw nut seat 20; the second servo motor 6 is fixedly arranged on the bearing seat 19; the first rotary shaft 15 at one side of the A-axis housing 3 is provided with a second angle encoder 17 for realizing closed-loop control of the A-axis swing structure; the first bearing 16 on the other side of the A-axis housing 3 is provided with an adjusting pad for adjusting the gap of the first bearing 16; the servo motor II 6 drives the screw rod I11 to rotate through the synchronous belt 7, so that the screw nut I21 moves forwards and backwards, and the angle of the A-axis shell 3 is changed.
The clamping mechanism comprises a first linear guide rail, a clamping slide plate 4, a second screw rod, a second screw nut and a third servo motor 9, wherein the first linear guide rail is fixedly arranged on the lower end surface of the A-axis housing 3, and the clamping slide plate 4 and the first linear guide rail are installed together in a sliding fit manner; the screw rod II is rotationally connected with the A-axis shell 3, the screw nut II is in threaded connection with the screw rod II, and the screw nut II is fixedly arranged on the clamping slide plate 4; the servo motor III 9 is fixedly arranged on the A-axis shell 3, and the servo motor III 9 is used for driving the screw rod II to perform telescopic movement, and the telescopic travel is 400mm; the front end of the clamping slide plate 4 is provided with a searching sensor and a grating ruler 18, wherein the searching sensor comprises an angle sensor I and a force sensor; the force sensor is used for controlling the clamping force to avoid excessive deformation of the workpiece; the angle sensor is used for measuring the normal angle, and automatically controlling A, B shaft swing through a certain algorithm to realize automatic searching of the normal of the curved surface; the grating scale 18 is used to ensure positioning accuracy.
The drilling mechanism comprises a main shaft 13, a main shaft box 12, a camera 14, a linear guide rail II, a screw rod III, a screw nut III and a servo motor IV 10, wherein the linear guide rail II is fixedly arranged on the lower end surface of the clamping slide plate 4, and the main shaft box 12 and the linear guide rail II are installed together in a sliding fit manner; the screw rod III is rotationally connected with the clamping slide plate 4, the screw nut III is in threaded connection with the screw rod III, and the screw nut III is fixedly arranged on the spindle box 12; the servo motor IV 10 is fixedly arranged on the clamping slide plate 4, the servo motor IV 10 is used for driving a screw rod III, the stroke of the servo motor IV is 200mm, and the servo motor IV is used for manually changing a cutter; the main shaft 13 is arranged in the main shaft box 12, and the camera 14 is arranged at the lower part of the main shaft box 12 and is used for realizing the automatic positioning function of drilling. The drilling mechanism is used for realizing axial feeding and rotation of the cutter to conduct drilling cutting.
Claims (8)
1. The hole making device for the aircraft assembly automatic drilling equipment is characterized by comprising a B-axis swinging structure, an A-axis swinging structure, a clamping mechanism and a drilling mechanism which are sequentially arranged from top to bottom, wherein the B-axis swinging structure is rotationally connected with the A-axis swinging structure, the clamping mechanism is fixedly connected with the A-axis swinging structure, and the drilling mechanism is fixedly arranged at the lower part of the front end of the clamping mechanism; the B-axis swinging structure drives the A-axis swinging structure, the clamping mechanism and the drilling mechanism to swing in the horizontal plane, and the A-axis swinging structure drives the clamping mechanism and the drilling mechanism to swing in the vertical plane.
2. The hole maker for the aircraft assembly automatic drilling device according to claim 1, wherein the B-axis swinging structure comprises a box body, a B-axis shell, a cycloid speed reducer and a first servo motor, wherein the box body and the B-axis shell are connected through the cycloid speed reducer to form a revolute pair, and the first servo motor is arranged on the box body and used for driving the cycloid speed reducer.
3. The hole maker for the aircraft assembly automatic drilling equipment according to claim 2, wherein the A-Axis swinging structure comprises an A-Axis housing, a first bearing, a second bearing, a third bearing, a fourth bearing, a bearing seat, a first screw, a second screw seat, a servo motor and a synchronous belt, wherein two sides of the A-Axis housing are respectively provided with a first rotating shaft, and the first rotating shaft is rotatably connected with the B-axis housing through the first bearing; two sides of the bearing seat are respectively provided with a second rotating shaft, and the second rotating shaft is rotationally connected with the B-axis shell through a second bearing; the rotating shafts III are respectively arranged on two sides of the nut seat and are in rotary connection with the A-axis shell through bearings III; the screw rod I is rotationally connected with the bearing seat through a bearing IV, the screw nut I is in threaded connection with the screw rod I, and the screw nut I is fixedly arranged on the screw nut seat; the second servo motor is fixedly arranged on the bearing seat and drives the first screw rod through the synchronous belt.
4. A hole maker for an aircraft assembly automated drilling apparatus according to claim 3, wherein the clamping mechanism comprises a first linear guide rail, a clamping slide plate, a second screw rod, a second screw nut and a third servo motor, the first linear guide rail is fixedly arranged on the lower end surface of the A-Axis housing, and the clamping slide plate is mounted together with the first linear guide rail in a sliding fit; the screw rod II is rotationally connected with the A-axis shell, the screw nut II is in threaded connection with the screw rod II, and the screw nut II is fixedly arranged on the clamping sliding plate; the servo motor III is fixedly arranged on the A-axis shell and is used for driving the screw rod II.
5. The hole maker for an aircraft assembly automated drilling apparatus according to claim 4, wherein the front end of the clamping slide is provided with a seek sensor comprising an angle sensor and a force sensor.
6. The hole maker for an aircraft assembly automated drilling apparatus according to claim 4, wherein the front end of the clamping slide is provided with a grating ruler.
7. The hole maker for the aircraft assembly automatic drilling equipment according to claim 4, wherein the drilling mechanism comprises a main shaft, a main shaft box, a camera, a linear guide rail II, a lead screw III, a screw III and a servo motor IV, wherein the linear guide rail II is fixedly arranged on the lower end surface of the clamping slide plate, and the main shaft box and the linear guide rail II are installed together in a sliding fit manner; the screw rod III is rotationally connected with the clamping slide plate, the screw nut III is in threaded connection with the screw rod III, and the screw nut III is fixedly arranged on the spindle box; the servo motor IV is fixedly arranged on the clamping slide plate and used for driving the screw rod III; the main shaft is arranged in the main shaft box, and the camera is arranged at the lower part of the main shaft box.
8. A hole maker for an aircraft assembly automation drilling device according to claim 2, wherein the B-axis housing is provided with an angle sensor two and an angle encoder one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322352442.XU CN220636397U (en) | 2023-08-31 | 2023-08-31 | Hole making device for aircraft assembly automatic drilling equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322352442.XU CN220636397U (en) | 2023-08-31 | 2023-08-31 | Hole making device for aircraft assembly automatic drilling equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220636397U true CN220636397U (en) | 2024-03-22 |
Family
ID=90269464
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322352442.XU Active CN220636397U (en) | 2023-08-31 | 2023-08-31 | Hole making device for aircraft assembly automatic drilling equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220636397U (en) |
-
2023
- 2023-08-31 CN CN202322352442.XU patent/CN220636397U/en active Active
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