Integrated multi-beam device and method for laser preheating, polishing and strengthening of aircraft parts

Abstract

The invention discloses an integrated multi-beam device and method for aircraft part laser preheating, polishing and strengthening, and the device comprises a computer control system, a laser preheating device, a picosecond pulse laser device, an ultra-strong pulse laser device and a workbench, wherein the computer control system is used for controlling the movement of the laser preheating device, the ultra-strong pulse laser device, the picosecond pulse device and the workbench; the laser preheating device is used for focusing large-light-spot continuous laser beams on the surface of the aircraft part loaded on the surface of the workbench, and preheating of the surface of the aircraft part is achieved. The picosecond pulse device is used for forming small light spots which are focused on the preheated surface of the aircraft part to polish the surface of the aircraft part; the ultra-strong pulse laser device is used for forming high-energy small light spots which are focused on the polished surface of the aircraft part, and laser shock peening of the surface of the aircraft part is achieved. The machining efficiency and precision of aircraft parts can be effectively improved, and the manufacturing cost is reduced.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of laser composite processing of aviation manufacturing, and particularly relates to an integrated multi-beam device and method for laser preheating, polishing and strengthening of aircraft parts. BACKGROUND

[0002] In the field of aviation manufacturing, aircraft system functional parts or load-bearing components with high fatigue performance requirements are usually shaped into blanks by forging, casting or additive manufacturing, and then can reach the use precision and function of the parts after hand polishing or mechanical processing, polishing and strengthening, resulting in long processing procedures, multiple application devices, many operators and long manufacturing cycles. Laser polishing and impact strengthening are a new type of process method in recent years. Laser polishing is to irradiate the surface of a workpiece with a laser beam of a certain energy density and wavelength, so that the surface of the workpiece is melted or evaporated to obtain a smooth surface. Laser polishing has the advantages of non-contact complex curved surface / selected area polishing, small environmental pollution, no tool / milling consumption and high polishing efficiency. Laser impact strengthening is a new surface strengthening technology that uses high-intensity pressure stress shock waves generated by high-energy pulsed laser beams to irradiate metals for impact plastic deformation. It can form a deep pressure stress field, effectively improve the yield strength, fatigue strength and crack propagation resistance of metal materials, and has the advantages of high efficiency, flexibility, non-thermal and non-contact. At present, laser processing equipment is mainly used for single-process polishing or local area laser impact strengthening of aircraft parts after mechanical processing, without considering the processing efficiency and manufacturing cost of the parts. SUMMARY

[0003] The purpose of the application is to provide an integrated multi-beam device and method for laser preheating, polishing and strengthening of aircraft parts, so as to improve the processing efficiency and precision of aircraft parts and reduce the manufacturing cost.

[0004] In order to achieve the above-mentioned task, the application adopts the following technical solutions: The integrated multi-beam device for laser preheating, polishing and strengthening of aircraft parts comprises: a computer control system, a laser preheating device, a picosecond pulse laser device, an ultrastrong pulse laser device and a workbench, wherein: The computer control system is used to control the movement of the laser preheating device, the ultrastrong pulse laser device, the picosecond pulse device and the workbench; The surface of the workbench is used to load the aircraft parts to be processed and moves in a plane under the action of the computer control system; The laser preheating device comprises a continuous fiber laser, a first collimator, a first scanning galvanometer and a first field lens; the continuous fiber laser emits continuous laser, which is scanned at high speed by the first scanning galvanometer after passing through the first collimator with adjustable focus, and then is focused on the surface of the aircraft part as a large-spot continuous laser beam with positive and negative defocus under the action of the first field lens, thereby realizing the preheating of the surface of the aircraft part; The picosecond pulse device comprises a picosecond pulse laser, a second scanning galvanometer, a second collimator and a second field lens; the picosecond pulse laser generated by the picosecond pulse laser is controlled by the second scanning galvanometer after passing through the second collimator with adjustable focus, and is focused on the preheated surface of the aircraft part as a small spot under the action of the second field lens, thereby realizing the polishing of the surface of the aircraft part; The ultrastrong pulse laser device comprises an ultrastrong pulse laser, a third collimator, a third scanning galvanometer and a third field lens; the ultrastrong pulse laser emits high-energy pulse laser, which is controlled by the third scanning galvanometer after passing through the third collimator with adjustable focus, and is focused on the polished surface of the aircraft part as a small spot with high energy under the action of the third field lens, thereby realizing the laser shock peening of the surface of the aircraft part.

[0005] Further, the first scanning galvanometer, the second scanning galvanometer and the third scanning galvanometer are fixed in parallel on an auxiliary scanning control platform, so as to ensure the same laser scanning moving speed of the first scanning galvanometer, the second scanning galvanometer and the third scanning galvanometer.

[0006] Further, the position of the auxiliary scanning control platform is adjustable and is controlled by a computer control system.

[0007] Further, baffles are installed between the first scanning galvanometer and the second scanning galvanometer and between the second scanning galvanometer and the third scanning galvanometer on the auxiliary scanning control platform, for separating the laser processing areas of the laser preheating device, the picosecond pulse laser device and the ultrastrong pulse laser device.

[0008] Further, the continuous fiber laser is a 1064 nm fiber laser; the picosecond pulse laser has a wavelength of 1030 nm and a pulse frequency of 1-2 MHz; and the ultrastrong pulse laser has a wavelength of 1064 nm and a pulse frequency of 1-10 Hz.

[0009] Further, the computer control system can control the Z-direction movement of the laser preheating device, the ultrastrong pulse laser device and the picosecond pulse device, and the X-direction and Y-direction movement of the workbench; wherein the Z-direction is perpendicular to the surface of the workbench; and the X-direction and the Y-direction are two directions perpendicular to each other in the plane of the workbench.

[0010] Further, the size of the large spot is 100-200 μm, and the size of the small spot is 20-100 μm.

[0011] A kind of the integrated multi-beam device aircraft part processing method, comprising: Step one, the surface of aircraft parts is ultrasonically cleaned, then it is fixed on the surface of workbench; Step two, the working position of auxiliary scanning control platform and the position of workbench are adjusted using computer control system, to determine the processing starting position of the surface of aircraft parts; Step three, set the working parameters of continuous fiber laser, picosecond pulse laser and ultrastrong pulse laser; Step four, laser preheating device, ultrastrong pulse laser device, picosecond pulse device are controlled using computer control system, so that the light path of the three devices is accurately focused on the surface of aircraft parts to be processed, and the maximum spot brightness is guaranteed, while ensuring that there is no polarization, light leakage; Step five, based on the preset numerical control program, automatically turn on continuous fiber laser, picosecond pulse laser and ultrastrong pulse laser, and move the workbench according to the program to carry out laser preheating, polishing and strengthening simultaneously; Step six, close the laser preheating device, ultrastrong pulse laser device and picosecond pulse device, unload the processed aircraft parts from the workbench, and carry out cleaning, drying treatment.

[0012] Further, the laser output wavelength of the continuous fiber laser is set to 1064 nm, and the spot diameter is 200 μm;The output wavelength of the picosecond pulse laser is set to 1030 nm, the pulse frequency is 2 MHz, and the spot diameter is 20 μm;The laser output wavelength of the ultrastrong pulse laser is 1064 nm, the pulse frequency is 10 Hz, the spot diameter is 50 μm, and the laser energy is 100 J.

[0013] Compared with the prior art, the present application has the following technical features: The present application provides an integrated multi-beam device for laser preheating, polishing and strengthening, and a corresponding process method for aircraft system functional parts, which can solve the problem of long-period manufacturing of aircraft system functional parts or load-bearing components with high fatigue performance requirements, thereby improving processing efficiency and precision;It can also reduce the number of operators, reduce the cost of cutting, polishing and strengthening tools and auxiliary consumables, and improve environmental friendliness. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 The structure diagram of the device of the present application.

[0015] Explanation of reference numerals in the figure: 1 computer control system, 2 continuous fiber laser, 3 picosecond pulse laser, 4 ultrastrong pulse laser, 5 third collimator, 6 auxiliary scanning control platform, 7 third scanning galvanometer, 8 third field lens, 9 aircraft part, 10 workbench, 11 baffle, 12 second scanning galvanometer, 13 second collimator, 14 second field lens, 15 first collimator, 16 first scanning galvanometer, 17 first field lens. DETAILED DESCRIPTION

[0016] Reference Figure 1 The present application first provides an integrated multi-beam device for laser preheating, polishing and strengthening of an aircraft part, which comprises a computer control system 1, a laser preheating device, a picosecond pulse laser device, an ultrastrong pulse laser device and a workbench 10, wherein: 1. The computer control system 1.

[0017] The computer control system 1 is used to control the laser preheating device, the ultrastrong pulse laser device, the picosecond pulse device and the movement of the workbench 10.

[0018] The computer control system 1 can control the Z-direction movement of the laser preheating device, the ultrastrong pulse laser device and the picosecond pulse device and the X-direction and Y-direction movement of the workbench 10; see Figure 1 In this embodiment, the Z-direction is the direction perpendicular to the surface of the workbench 10; the X-direction and the Y-direction are two directions perpendicular to each other in the plane of the workbench 10.

[0019] 2. The laser preheating device.

[0020] The laser preheating device comprises a continuous fiber laser 2, a first collimator 15, a first scanning galvanometer 16 and a first field lens 17, wherein: The continuous fiber laser 2 emits continuous laser, which, after passing through the first collimator 15 with adjustable focus, becomes a parallel and stable light beam and further improves the laser output power and reduces the speckle of the laser beam; then the light beam is scanned at high speed by the first scanning galvanometer 16, and then the divergence angle of the light beam is further adjusted by the first field lens 17 to improve the spot quality, so that the surface of the aircraft part 9 is focused into a large spot continuous laser beam with positive and negative defocus, realizing efficient and stable preheating of the surface of the aircraft part 9.

[0021] 3. The picosecond pulse device.

[0022] The picosecond pulse device comprises a picosecond pulse laser 3, a second scanning galvanometer 12, a second collimator 13 and a second field lens 14, wherein: The picosecond pulsed laser generated by the picosecond pulsed laser 3 is controlled by the second scanning galvanometer 12 after passing through the second collimator 13 with adjustable focus, and under the action of the second field lens 14, a small spot is formed to focus on the preheated surface of the aircraft part 9 to implement the rough polishing and fine polishing of the surface of the aircraft part 9.

[0023] 3. The ultrastrong pulsed laser device.

[0024] The ultrastrong pulsed laser device comprises an ultrastrong pulsed laser 4, a third collimator 5, a third scanning galvanometer 7 and a third field lens 8, wherein: The ultrastrong pulsed laser 4 generates high-energy pulsed laser, which is controlled by the third scanning galvanometer 7 after passing through the third collimator 5 with adjustable focus, and under the action of the third field lens 8, a small spot with high energy is formed to focus on the polished surface of the aircraft part 9 to realize the laser shock strengthening of the surface of the aircraft part 9.

[0025] The functions of the collimators, scanning galvanometers and field lenses are similar, and will not be repeated here.

[0026] In an embodiment of the application, the continuous fiber laser 2 is a 1064 nm fiber laser; the picosecond pulsed laser 3 has a wavelength of 1030 nm and a pulse frequency of 1-2 MHz; and the ultrastrong pulsed laser 4 has a wavelength of 1064 nm and a pulse frequency of 1-10 Hz.

[0027] The size of the large spot is 100-200 microns, which is used for the preheating process of the surface of the aircraft part 9; and the size of the small spot is 20-100 microns, which is used for polishing and impact strengthening of the preheated surface of the aircraft part 9.

[0028] 4. The workbench 10.

[0029] The surface of the workbench 10 is used to load the aircraft part 9 to be processed, and moves in X and Y directions under the action of the computer control system 1. The aircraft part 9 can also be other workpieces.

[0030] 5. The auxiliary scanning control platform 6 and the baffle 11.

[0031] The first scanning galvanometer 16, the second scanning galvanometer 12 and the third scanning galvanometer 7 in the laser preheating device, the picosecond pulse laser device and the ultrastrong pulse laser device are fixed on the auxiliary scanning control platform 6 in parallel, so as to ensure the same laser scanning moving speed of the first scanning galvanometer 16, the second scanning galvanometer 12 and the third scanning galvanometer 7; meanwhile, the three are arranged in parallel and run at the same speed, so that a certain block of the to-be-processed area on the aircraft part 9 can be sequentially preheated, polished and impact strengthened under the movement control of the workbench 10, the integrated processing can be completed while the processing precision is effectively ensured, and the processing efficiency is effectively improved; meanwhile, the baffle 11 is installed between the first scanning galvanometer 16 and the second scanning galvanometer 12 and between the second scanning galvanometer 12 and the third scanning galvanometer 7 on the auxiliary scanning control platform 6, which is used for separating the laser processing areas of the laser preheating device, the picosecond pulse laser device and the ultrastrong pulse laser device, so as to avoid the influence of molten slag splashing on other laser processing areas.

[0032] The position of the auxiliary scanning control platform 6 is adjustable and is controlled by the computer control system 1.

[0033] On the basis of the above technical scheme, the application further provides an aircraft part processing method based on the above integrated multi-beam device, which comprises the following steps: Step one: the surface of the aircraft part 9 is ultrasonically cleaned, and then the aircraft part 9 is fixed on the surface of the workbench 10 by means of a pressing plate or a bolt.

[0034] Step two: the working position of the auxiliary scanning control platform 6 and the position of the workbench 10 are adjusted by the computer control system 1, and the processing starting position of the surface of the aircraft part 9 is determined.

[0035] Step three: the laser output wavelength of the continuous fiber laser 2 is set to 1064 nm, and the spot diameter is 100-200 μm; the laser output wavelength of the picosecond pulse laser 3 is set to 1030 nm, the pulse frequency is 1-2 MHz, and the spot diameter is 20-100 μm; the laser output wavelength of the ultrastrong pulse laser 4 is 1064 nm, the pulse frequency is 1-10 Hz, the spot diameter is 20-100 μm, and the laser energy is 50-100 J.

[0036] For example, in an embodiment, the spot diameter of the continuous fiber laser 2 is 200 μm; the pulse frequency of the picosecond pulse laser 3 is set to 2 MHz, and the spot diameter is 20 μm; the pulse frequency of the ultrastrong pulse laser 4 is 10 Hz, the spot diameter is 50 μm, and the laser energy is 100 J.

[0037] Step four, the computer control system 1 is used to the laser preheating device, the super pulse laser device, the picosecond pulse device is regulated and controlled, makes three device light path accurate focus in the aircraft parts 9 to be processed surface, and guarantees the light spot brightness is maximum, guarantees not to appear the polarized light, the light leakage, completes the preparation work.

[0038] Step five, based on the preset numerical control program automatically opens the switch of the continuous fiber laser 2, the picosecond pulse laser 3 and the super pulse laser 4, and moves the workbench 10 according to the program and carries out laser preheating, polishing and strengthening simultaneously.

[0039] Step six, the laser preheating device, the super pulse laser device, the picosecond pulse device are closed, the processed aircraft parts 9 are unloaded from the workbench 10, and are washed, dried.

[0040] The above examples are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing examples, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. An integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts, characterized in that, include: The system comprises a computer control system (1), a laser preheating device, a picosecond pulse laser device, an ultra-intense pulse laser device, and a worktable (10), wherein: The computer control system (1) is used to control the movement of the laser preheating device, the ultra-intense pulse laser device, the picosecond pulse device, and the worktable (10); The surface of the worktable (10) is used to load the aircraft parts (9) to be processed and to move in a plane under the action of the computer control system (1); The laser preheating device includes a continuous fiber laser (2), a first collimator (15), a first scanning galvanometer (16), and a first field mirror (17). The continuous fiber laser (2) excites a continuous laser beam, which is then scanned at high speed by the first scanning galvanometer (16) after passing through the adjustable-focus first collimator (15). Then, under the action of the first field mirror (17), the laser beam is focused into a large spot of continuous laser beam with positive and negative defocus on the surface of the aircraft part (9) to achieve preheating of the surface of the aircraft part (9). The picosecond pulse device includes a picosecond pulse laser (3), a second scanning galvanometer (12), a second collimator (13), and a second field mirror (14). The picosecond pulse laser generated by the picosecond pulse laser (3) is controlled by the second scanning galvanometer (12) after passing through the adjustable second collimator (13), and under the action of the second field mirror (14), a small light spot is formed and focused on the preheated surface of the aircraft part (9) to carry out the polishing work on the surface of the aircraft part (9). The ultra-intense pulsed laser device includes an ultra-intense pulsed laser (4), a third collimator (5), a third scanning galvanometer (7), and a third field mirror (8). The ultra-intense pulsed laser (4) excites a high-energy pulsed laser, which is controlled by the third scanning galvanometer (7) after passing through the adjustable-focus third collimator (5). Under the action of the third field mirror (8), a high-energy small spot is formed and focused on the polished surface of the aircraft part (9) to achieve laser shock strengthening of the surface of the aircraft part (9).

2. The integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts according to claim 1, characterized in that, The first scanning galvanometer (16), the second scanning galvanometer (12), and the third scanning galvanometer (7) are fixed in parallel on an auxiliary scanning control platform (6) to ensure that the first scanning galvanometer (16), the second scanning galvanometer (12), and the third scanning galvanometer (7) have the same laser scanning movement speed.

3. The integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts according to claim 1, characterized in that, The position of the auxiliary scanning control platform (6) is adjustable and is controlled by the computer control system (1).

4. The integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts according to claim 1, characterized in that, On the auxiliary scanning control platform (6), baffles (11) are installed between the first scanning galvanometer (16), the second scanning galvanometer (12), the second scanning galvanometer (12), and the third scanning galvanometer (7) to separate the laser processing areas of the laser preheating device, the picosecond pulse laser device, and the ultra-intense pulse laser device.

5. The integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts according to claim 1, characterized in that, The continuous fiber laser (2) is a 1064 nm fiber laser; the picosecond pulse laser (3) has a wavelength of 1030 nm and a pulse frequency of 1~2 MHz; the ultra-intense pulse laser (4) has a wavelength of 1064 nm and a pulse frequency of 1~10 Hz.

6. The integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts according to claim 1, characterized in that, The computer control system (1) can regulate the Z-axis movement of the laser preheating device, the ultra-intense pulse laser device, and the picosecond pulse device, as well as the X-axis and Y-axis movement of the worktable (10); wherein the Z-axis is the direction perpendicular to the surface of the worktable (10); and the X-axis and Y-axis are two mutually perpendicular directions of the worktable (10) in the plane.

7. The integrated multi-beam device for laser preheating, polishing, and strengthening of aircraft parts according to claim 1, characterized in that, The large light spot has a size of 100~200μm, and the small light spot has a size of 20~100μm.

8. A method for processing aircraft parts based on the integrated multi-beam device according to any one of claims 1-7, characterized in that, include: Step 1: Perform ultrasonic cleaning on the surface of the aircraft part (9) and then fix it on the surface of the worktable (10). Step 2: Use the computer control system (1) to adjust the working position of the auxiliary scanning control platform (6) and the position of the worktable (10) to determine the starting position for processing the surface of the aircraft part (9); Step 3: Set the operating parameters of the continuous fiber laser (2), picosecond pulse laser (3), and ultra-intense pulse laser (4); Step 4: Use the computer control system (1) to adjust the laser preheating device, the ultra-intense pulse laser device, and the picosecond pulse device so that the optical paths of the three devices are accurately focused on the surface of the aircraft part (9) to be processed, and ensure that the brightness of the spot is maximized, while ensuring that there is no polarization or light leakage. Step 5: Based on the preset CNC program, the continuous fiber laser (2), picosecond pulse laser (3) and ultra-intense pulse laser (4) are automatically turned on, and the worktable (10) is moved according to the program to carry out laser preheating, polishing and strengthening simultaneously. Step 6: Turn off the laser preheating device, the ultra-intense pulse laser device, and the picosecond pulse device. Unload the processed aircraft parts (9) from the worktable (10) and clean and dry them.

9. The aircraft parts processing method according to claim 7, characterized in that, The laser output wavelength of the continuous fiber laser (2) is set to 1064 nm, and the spot diameter is set to 200 μm; the output wavelength of the picosecond pulse laser (3) is set to 1030 nm, the pulse frequency is set to 2 MHz, and the spot diameter is set to 20 μm; the laser output wavelength of the ultra-intense pulse laser (4) is set to 1064 nm, the pulse frequency is set to 10 Hz, the spot diameter is set to 50 μm, and the laser energy is set to 100 J.

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