Laser drilling and opening device for aviation composite material

Abstract

The invention discloses a laser drilling and opening device for an aviation composite material, which comprises a laser tapping machine for tapping the aviation composite material and a workbench for placing a material plate, and a multi-axis adjusting assembly is arranged in the middle of the workbench close to the laser tapping machine. The workbench is provided with a fixing assembly, a cleaning assembly and a synchronizing assembly connected with the fixing assembly and the cleaning assembly. The driving motor drives the rotating lead screw, the bevel gear set and the vertical lead screw to be linked, so that the pressing piece accurately moves downwards to abut against the aviation composite material plate. Particularly for flat plate pieces and large-area thin-wall pieces, hole forming position deviation caused by infirm material fixing can be effectively avoided, the hole forming dislocation problem of traditional equipment is solved, and material waste and rework loss caused by position errors are reduced.

Description

Technical Field

[0001] This invention relates to a laser drilling device for aerospace materials, specifically a laser drilling and opening device for aerospace composite materials, belonging to the technical field of aerospace material processing equipment. Background Art

[0002] The core structures of aviation equipment, such as fuselage, wings, tail, and engine nacelles, are all spliced ​​together from multiple composite material sub-components. Composite material components cannot be connected by welding like metal components; they must be fixed by drilling holes and then using "high-strength bolts" or "special rivets." Therefore, drilling holes in aviation composite materials is a very important step.

[0003] A search revealed Chinese patent CN116727900A, which discloses a laser-based hole-making method and apparatus for aerospace composite materials. This method achieves adaptive adjustment of the output beam direction, adaptive adjustment of the initial laser output power based on the characteristics of different materials, and strict control of the material temperature within the hole-making area. However, this patent only discloses the laser hole-making method. During the hole-making process, especially for flat or large-area thin-walled aerospace composite materials, if the material is not securely fixed, the hole position may shift, leading to incorrect opening locations and unnecessary losses. Summary of the Invention

[0004] The purpose of this invention is to provide a laser-based hole-forming and opening device for aerospace composite materials in order to solve the above-mentioned problems.

[0005] The present invention achieves the above-mentioned objective through the following technical solution: a laser hole-making and opening device for aerospace composite materials, comprising a laser hole-making machine for making holes in aerospace composite materials and a worktable for placing material plates, wherein a multi-axis adjustment component is provided in the middle of the worktable near the laser hole-making machine, and a fixing component, a cleaning component, and a synchronization component connecting the fixing component and the cleaning component are provided on the worktable; The fixing component mainly consists of a pressing component and a bevel gear set. The worktable is equipped with a horizontal rotating screw, and the two ends of the rotating screw are equipped with bevel gear sets. The top of the bevel gear set is connected to a vertical screw. The pressing component is located above the two vertical screws. The fixing component is arranged in multiple ways. The pressing component moves down with the screw and abuts against the top of the aerospace composite material plate to limit and fix it. The cleaning assembly consists of a vacuum pump and a cleaning roller. The top of the output end of the workbench is provided with two grooves, and a grid plate and a cleaning roller are respectively provided in the two grooves. The bottom end of the grid plate is provided with a vacuum pump. The synchronization component mainly consists of a driving component and a transmission component. A transmission component is provided between the bottom ends of the multiple fixed components and between the fixed components and the bottom end of the cleaning roller. When the driving component is started, it drives one of the connected rotating screws to rotate. The synchronous rotation of the multiple fixed components and the cleaning roller is realized through the transmission component.

[0006] Preferably, one end of the rotating lead screw is provided with a connecting rod, the connecting rod is provided with a gear disk, and a transmission belt is provided between two adjacent gear disks.

[0007] Preferably, a drive motor is connected to the connecting rod near the input end of the worktable, and a conveyor chain is provided between the connecting rod near the output end of the worktable and one end of the cleaning roller.

[0008] Preferably, the upper lead screw is connected to a lower pressure block, the lower pressure block has a pressing block at its bottom end, and the pressing block has multiple rubber pads at its bottom end.

[0009] Preferably, the bevel gear set consists of a first bevel gear and a second bevel gear, wherein the first bevel gear and the second bevel gear are meshed together in a perpendicular manner.

[0010] Preferably, the multi-axis adjustment assembly has a set of adjustment elements in each of the three directions: x-axis, y-axis, and z-axis.

[0011] Preferably, a water-cooling pipe is provided at the bottom of the workbench and at the location of the laser drilling machine. The water-cooling pipe is arranged in a snake shape, and a chiller is provided at one end of the water-cooling pipe.

[0012] Preferably, the cleaning roller is arranged horizontally in the groove, with the top of the cleaning roller higher than the surface of the workbench by 5-8 mm.

[0013] The present invention has the following beneficial effects: 1. The drive motor drives the rotating lead screw, bevel gear set, and vertical lead screw in a coordinated manner, allowing the pressing component to move precisely downwards and abut against the aerospace composite material plate. Especially for flat parts and large-area thin-walled parts, it can effectively avoid the displacement of the hole-making position caused by the material not being firmly fixed, solve the problem of hole misalignment in traditional equipment, and reduce material waste and rework losses caused by incorrect positioning; 2. With the help of the synchronization component, the cleaning component can work synchronously when the fixed component is in operation. On the one hand, the grid plate, together with the bottom dust pump, can adsorb the debris in the drilling area, reducing the impact of debris residue on subsequent processing or assembly; on the other hand, the cleaning roller with the top 5-8mm higher than the worktable can fully contact the bottom of the material plate, and wipe and clean the bottom of the material plate again after vacuum adsorption. 3. Only one drive motor needs to be started to drive the rotating screws and cleaning rollers of multiple fixed components to rotate synchronously through transmission components such as transmission belts and transmission chains. There is no need to control each component separately, which reduces the number of control nodes in the equipment, reduces the complexity of operation, improves the coordination of the actions of each component, and shortens the processing preparation and execution time. Attached Figure Description

[0014] Figure 1 This is a three-dimensional view of the overall structure of a laser-driven hole-making and opening device for aerospace composite materials proposed in this invention; Figure 2 This is a three-dimensional view of the overall structure of a laser-driven hole-making and opening device for aerospace composite materials proposed in this invention; Figure 3 This is a three-dimensional structural view of a laser hole-making and opening device for aerospace composite materials proposed in this invention. Figure 4 This is a three-dimensional structural view of a laser hole-making and opening device for aerospace composite materials proposed in this invention. Figure 5 This is a perspective view of a laser hole-making and opening device fixing component and a cleaning component for aerospace composite materials proposed in this invention; Figure 6 This is a perspective view of a laser hole-making and opening device fixing component and a cleaning component for aerospace composite materials proposed in this invention; Figure 7 This is a perspective view of a fixing component for a laser-driven hole-making and opening device for aerospace composite materials, as proposed in this invention. Figure 8 This is a perspective view of a fixing component for a laser-driven hole-making and opening device for aerospace composite materials, as proposed in this invention.

[0015] In the diagram: 1. Workbench; 2. Laser drilling machine; 3. Multi-axis adjustment assembly; 4. Fixing assembly; 401. Drive motor; 402. Rotating lead screw; 403. First bevel gear; 404. Second bevel gear; 405. Vertical lead screw; 406. Lower pressure block; 407. Pressing block; 408. Rubber pad; 5. Synchronization assembly; 501. Connecting rod; 502. First gear disc; 503. Second gear disc; 504. First conveyor belt; 505. Third gear disc; 506. Fourth gear disc; 507. Second conveyor belt; 508. Fifth gear disc; 509. Sixth gear disc; 6. Cleaning assembly; 601. Mesh plate; 602. Dust pump; 603. Cleaning roller; 604. Rotating rod; 605. Conveyor chain; 7. Water cooling pipe; 701. Chiller. Detailed Implementation

[0016] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Example 1:

[0017] Reference Figure 1-8 A laser hole-making and opening device for aerospace composite materials includes a laser hole-making machine 2 for making holes in aerospace composite materials and a worktable 1 for placing material plates. A multi-axis adjustment component 3 is provided in the middle of the worktable 1 near the laser hole-making machine 2. A fixing component 4, a cleaning component 6 and a synchronization component 5 connecting the fixing component 4 and the cleaning component 6 are provided on the worktable 1. The fixing component 4 is mainly composed of a pressing component and a bevel gear set. The worktable 1 is provided with a horizontal rotating screw 402. Both ends of the rotating screw 402 are provided with bevel gear sets. The top of the bevel gear set is connected to a vertical screw 405. The pressing component 406 is provided above the two vertical screws 405. The fixing component 4 is arranged in multiple ways. The pressing component 406 moves down with the screw 402 and abuts against the top of the aerospace composite material plate to limit and fix it. The cleaning component 6 consists of a vacuum pump 602 and a cleaning roller 603. The top of the output end of the workbench 1 is provided with two grooves, and a grid plate 601 and a cleaning roller 603 are respectively provided in the two grooves. The bottom end of the grid plate 601 is provided with a vacuum pump 602. The synchronization component 5 mainly consists of a driving component and a transmission component. A transmission component is provided between the bottom ends of multiple fixed components 4 and between the bottom ends of fixed components 4 and cleaning roller 603. When the driving component is started, it drives one of the connected rotating screws 402 to rotate. The synchronous rotation of multiple fixed components 4 and cleaning roller 603 is realized through the transmission component.

[0018] One end of the rotating lead screw 402 is provided with a connecting rod 501, and a gear disk is provided on the connecting rod 501. A transmission belt is provided between two adjacent gear disks. The connecting rod 501 near the input end of the worktable 1 is connected to a drive motor 401. A transmission chain 605 is provided between the connecting rod 501 near the output end of the worktable 1 and one end of the cleaning roller 603.

[0019] The upper nut of the vertical lead screw 405 is connected to a lower pressure block 406, and the bottom end of the lower pressure block 406 is provided with a pressing block 407, and the bottom end of the pressing block 407 is provided with multiple rubber pads 408.

[0020] The bevel gear set consists of a first bevel gear 403 and a second bevel gear 404, which are meshed vertically.

[0021] In this embodiment, it should be noted that when performing laser drilling on aerospace composite materials to facilitate subsequent bolt installation, especially for flat parts and large-area thin-walled parts (such as wing skin) aerospace composite material plates, the composite material plate is placed from the input end of the worktable 1 until the position to be drilled is close to the bottom of the laser drilling machine 2. The position of the hole is located according to the vision positioning system, coordinate control system and target positioning inside the laser drilling machine 2. According to the thickness of the composite material plate, the drilling depth, etc., the data is input through the control panel and the device is started. Through the cooperation of the multi-axis adjustment component 3, the laser drilling machine 2 is moved on the x-axis, y-axis and z-axis to achieve the positioning, quantitative and quantitative drilling operation.

[0022] The drive motor 401, multi-axis adjustment assembly 3, pressure sensor, dust pump and PLC controller model "S7-1200" are connected by telecommunications.

[0023] Before drilling, for larger composite material plates, when drilling on the workbench 1, in order to avoid misalignment and displacement of the drilling position, the fixing component 4 is activated, and the drive motor 401 is started, which drives the connected connecting rod 501 to rotate, that is, the rotating screw 402 rotates. The first bevel gear 403 located at both ends of the rotating screw 402 rotates, and the second bevel gear 404 meshing with the first bevel gear 403 rotates, which in turn drives the vertical screw 405 above the second bevel gear 404 to rotate.

[0024] Uprights are provided on both sides of the workbench 1 near the vertical lead screw 405. One end of each upright is provided with a moving groove. When the vertical lead screw 405 rotates, the lower pressing block 406 connected to the nut of the vertical lead screw 405 is limited on both sides by the moving groove. Therefore, the lower pressing block 406 moves up and down with the rotation of the vertical lead screw 405, causing the pressing block 407 at the bottom of the lower pressing block 406 to approach the top of the aerospace composite material plate. The rubber pad 408 at the bottom of the pressing block 407 contacts the top of the aerospace composite material plate. A pressure sensor is also provided at the bottom of the pressing block 407. When the pressing block 407 is pressed, the pressure sensor detects that the pressure has reached a specified value and sends an electrical signal to the PLC controller. The PLC controller receives and processes the signal and sends it to the drive motor 401. The drive motor 401 stops rotating to avoid unnecessary damage to the aerospace composite material plate caused by excessive pressing.

[0025] like Figure 1-2 as well as Figure 5-7 As shown, the fixed components 4 are arranged in three groups, and the number of these groups can be varied according to the actual length of the workbench 1.

[0026] A first gear disk 502 is provided on the connecting rod 501 connected to the rotating lead screw 402 near the input end of the worktable 1. A second gear disk 503 is provided on the connecting rod 501 behind the connecting rod 501. A first conveyor belt 504 is provided between the first gear disk 502 and the second gear disk 503. A third gear disk 505 is provided on the connecting rod 501 with the second gear disk 503 on one side of the second gear disk 503. A fourth gear disk 506 is provided on the connecting rod 501 near the output end of the worktable 1 at a horizontal position with the third gear disk 505. A second conveyor belt 507 is provided on the third gear disk 505 and the fourth gear disk 506.

[0027] The cleaning roller 603 has a rotating rod 604 on its internal central shaft. One end of the rotating rod 604 is connected to a connecting rod 501 with a fourth gear disk 506 by a transmission chain 605. The connecting rod 501 and the rotating rod 604 are respectively equipped with a fifth gear disk 508 and a sixth gear disk 509. Example 2:

[0028] Unlike Example 1, referring to Figure 1-4 This embodiment also has the following further features: the multi-axis adjustment assembly 3 is provided with a set of adjustment components in the three directions of x-axis, y-axis and z-axis.

[0029] The cleaning roller 603 is horizontally positioned in the groove, with its top end higher than the surface of the worktable 1 by 5-8 mm.

[0030] In this embodiment, it should be noted that in some common aerospace composite material laser processing, the thickness of the material plate is mostly around 10mm. The cleaning roller 603 is 5-8mm higher than the table surface, which can ensure that the material plate is placed horizontally and that the bristles of the cleaning roller 603 can fully contact the bottom of the material plate for cleaning.

[0031] When the drive motor 401 starts and drives the lowering block 406 to press down, multiple conveyor belts rotate, so that the cleaning roller 603 rotates synchronously when the lowering block 406 presses down. When the lowering block 406 presses down, the cleaning roller 603 rotates from top to bottom toward the position of the laser drilling machine 2 to clean the bottom of the aerospace composite material plate at that position.

[0032] The grid plate 601 is set on the side of the worktable 1 near the laser drilling machine 2. After the front end of the material plate is drilled by the laser, the material plate is pushed to move along the worktable 1. The drilling position first passes through the grid plate 601, and the internal dust pump 602 adsorbs and cleans the debris inside the drilling position.

[0033] Since the cleaning roller 603 is 5-8mm higher than the table surface, as the material board moves horizontally, the opening position after being sucked by the dust pump 602 moves to the position of the cleaning roller 603 and is cleaned by the cleaning roller 603.

[0034] A connecting pipe is provided between the bottom end of the cleaning roller 603 and the bottom end of the grid plate 601 and the dust pump 602. When the pressing block 406 is pressed down, the transmission component rotates, causing the cleaning roller 603 to rotate and the top of the cleaning roller 603 to rotate into the interior of the workbench 1. The dust pump 602 uses this pipe to suction the cleaning roller 603 inside the workbench 2, thereby achieving self-cleaning of the cleaning roller 603. This avoids dust adhesion caused by wiping the bottom of the material board for a long time, which would cause secondary pollution to the subsequent material boards and improve the cleanliness. Example 3:

[0035] Reference Figure 1-4 Compared to Embodiment 1 and Embodiment 2, in this embodiment: a water-cooling pipe 7 is provided at the bottom of the workbench 1 and at the position of the laser drilling machine 2. The water-cooling pipe 7 is arranged in a snake shape, and a chiller 701 is provided at one end of the water-cooling pipe 7.

[0036] In this embodiment, it should be noted that the serpentine water-cooling pipe 7 is tightly fitted to the bottom of the worktable 1. The method of "milling groove inside the worktable 1 + embedding water-cooling pipe 7" is adopted. The aerospace composite material plate is in direct contact with the worktable 1. When the laser hole is opened, the heat of the overheated part of the material is transferred to the inside of the worktable 1 through the "material-worktable" contact. The heat is exchanged by the serpentine water-cooling pipe 7.

Claims

1. A laser-assisted hole-making device for aerospace composite materials, comprising a laser hole-making machine for making holes in aerospace composite materials and a worktable for placing material plates, characterized in that: A multi-axis adjustment component is provided in the middle of the worktable near the laser drilling machine. The worktable is provided with a fixing component, a cleaning component, and a synchronization component connecting the fixing component and the cleaning component. The fixing component mainly consists of a pressing component and a bevel gear set. The worktable is equipped with a horizontal rotating screw, and the two ends of the rotating screw are equipped with bevel gear sets. The top of the bevel gear set is connected to a vertical screw. The pressing component is located above the two vertical screws. The fixing component is arranged in multiple ways. The pressing component moves down with the screw and abuts against the top of the aerospace composite material plate to limit and fix it. The cleaning assembly consists of a vacuum pump and a cleaning roller. The top of the output end of the workbench is provided with two grooves, and a grid plate and a cleaning roller are respectively provided in the two grooves. The bottom end of the grid plate is provided with a vacuum pump. The synchronization component mainly consists of a driving component and a transmission component. A transmission component is provided between the bottom ends of the multiple fixed components and between the fixed components and the bottom end of the cleaning roller. When the driving component is started, it drives one of the connected rotating screws to rotate. The synchronous rotation of the multiple fixed components and the cleaning roller is realized through the transmission component.

2. The laser-assisted hole-making and opening device for aerospace composite materials according to claim 1, characterized in that: One end of the rotating lead screw is provided with a connecting rod, and a gear disk is provided on the connecting rod. A transmission belt is provided between two adjacent gear disks.

3. The laser-assisted hole-making and opening device for aerospace composite materials according to claim 2, characterized in that: A drive motor is connected to the connecting rod near the input end of the worktable, and a conveyor chain is provided between the connecting rod near the output end of the worktable and one end of the cleaning roller.

4. The laser-assisted hole-making and opening device for aerospace composite materials according to claim 1, characterized in that: The upper nut of the vertical lead screw is connected to a lower pressure block, and the bottom end of the lower pressure block is provided with a pressing block, and the bottom end of the pressing block is provided with multiple rubber pads.

5. A laser-assisted hole-making and opening device for aerospace composite materials according to claim 1, characterized in that: The bevel gear set consists of a first bevel gear and a second bevel gear, which are meshed perpendicularly.

6. The laser-assisted hole-making and opening device for aerospace composite materials according to claim 1, characterized in that: The multi-axis adjustment assembly has a set of adjustment components in each of the three directions: x-axis, y-axis, and z-axis.

7. The laser-assisted hole-making and opening device for aerospace composite materials according to claim 1, characterized in that: A water-cooling pipe is provided at the bottom of the workbench and at the location of the laser drilling machine. The water-cooling pipe is arranged in a snake shape, and a chiller is provided at one end of the water-cooling pipe.

8. The laser-assisted hole-making and opening device for aerospace composite materials according to claim 1, characterized in that: The cleaning roller is arranged horizontally in the groove, with its top end higher than the surface of the workbench by 5-8 mm.

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