CN115945462A - Laser cleaning aircraft skin real-time monitoring device and method based on acoustic signal monitoring method - Google Patents
Laser cleaning aircraft skin real-time monitoring device and method based on acoustic signal monitoring method Download PDFInfo
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Abstract
The invention discloses a laser cleaning aircraft skin real-time monitoring device and method based on an acoustic signal monitoring method, which comprises the following steps: the objects to be monitored are divided into: a top coat, a primer and a metal substrate; monitoring the paint removal condition by an acoustic signal detection device; when the laser is used for cleaning the finish paint, the sound signal is strong and weak; the intensity of the acoustic signal corresponding to the primer is increased; when the substrate is exposed, the intensity of the acoustic signal begins to weaken; when the substrate is cleaned, the intensity of the acoustic signal is increased along with the number of the applied pulses, and the intensity of the acoustic signal is lower and lower. The change of the specific frequency of the sound wave can also distinguish different paint layers and substrates. And carrying out layered monitoring according to the intensity and frequency domain distribution of the acoustic signal to obtain a paint removing result. The invention has the advantages that: the paint removal of the multilayer paint structure of the aircraft skin can be monitored in real time, delay is low, errors are small, and accuracy is high. When the paint is completely removed at the moment, the point position can be immediately replaced to prevent the laser from over-irradiating to damage the substrate. The real-time performance and the accuracy are realized in the monitoring process.
Description
Technical Field
The invention relates to the technical field of aircraft skin monitoring, in particular to a laser cleaning aircraft skin real-time monitoring device and method based on an acoustic signal monitoring method.
Background
The integrity of the paint layer of the aircraft skin plays a crucial role in flight safety. As a new high-efficiency and rapid cleaning technology, laser paint removal has various advantages of high efficiency, small damage, less pollution and the like compared with the traditional paint removal mode, and is widely applied in industry. In order to ensure the quality and precision of paint removal, the cleaning process needs to be monitored and fed back in real time, and the current removal condition is known in time so as to realize closed-loop control. The main monitoring method at present is to invert the cleaning progress in real time by detecting signals generated by respective effects in the laser cleaning ablation process. Among them, laser Induced Breakdown Spectroscopy (LIBS) detection and acoustic signal detection are favored by scholars at home and abroad due to the advantages of high efficiency, accuracy, real time and the like [1,2] 。
In 2001, bremar [3] YAG laser from the substrate, and a detectable acoustic signal is found to accompany the cleaning process. In 2016, villarreal-Villela [4] The method is proposed to be used for monitoring the cleaning process by analyzing the spectrum by fast fourier transform of a photo acoustic (PILA) signal caused by laser ablation during the paint removal process by the et al, thereby identifying the paint composition on the metal surface. In 2020, papanikolaou [5] Et al propose a hybrid opto-acoustic (PA) and optical monitoring system for online monitoring of laser cleaning procedures. This method allows to precisely determine the critical number of laser pulses required to eliminate the crust layer. Researchers at home and abroad carry out extensive research on the laser cleaning acousto-optic monitoring technology, and the effectiveness and the real-time performance of the monitoring are proved.
The prior art mainly focuses on cleaning and monitoring single-layer paint, aircraft skins belong to a multi-layer paint mechanism, photoacoustic signals of the aircraft skins are more complex and various, and the prior art cannot finish the paint cleaning and monitoring of the aircraft skins.
The shock wave released by the laser breakdown of air is attenuated into sound wave during transmission. The frequency of the acoustic wave is related to the parameters of the laser, and the specific acoustic wave frequency exists under the specific laser parameters. Meanwhile, due to the fact that the material of the paint layer of the paint absorbs and reflects sound waves differently, and the fact that pits are formed on the surface of the paint in the removing process and diffuse reflection is conducted on the sound waves, the intensity of the sound waves in the removing process can change along with different parameters in the paint removing stage. According to the specific sound wave frequency, the removal condition of the laser can be inferred by comparing the change of the amplitude intensity, so that the sound signal frequency monitoring method can also reflect the paint removal condition in real time.
Reference documents:
[1]Binzowaimil,Ayed Mejwal.,and Mississippi State University.Physics Ast ronomy.Application of Laser-Induced Breakdown Spectroscopy(LIBS)to the Ex pansion of Strontium(Sr)Analysis Options and to Used Engine Oil.(2021):So urce:Dissertations Abstracts International,Volume:83-03,Section:B.Web；
[2]Song Yanxing,Wang Jing,Feng Qibo,Chen Shiqian.Influence of laser parameters and laser ultrasonic detection method on ultrasonic signals[J].Infraredand Laser Engineering,2014,43(5):1433-1437；
[3]Bregar V and Mozina J.Optodynamic characterization of a laser cleanin g process[M].2001；
[4]Villarreal-Villela A E and Cabrera L P.Monitoring the laser ablation pr ocess of paint layers by PILA technique[J].Open Journal of Applied Sciences,2016,6(9):626-635；
[5] papanicolaou A, jtserevelakis G, melessanaki K, et al, development of a hybrid photo-active and optical monitoring system for the study of laser ablation processes up the removal of photo from photo process [ J ]. Photoelectric evolution (English), 2020,3 (2): 11.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a laser cleaning aircraft skin real-time monitoring device and method based on an acoustic signal monitoring method.
In order to realize the purpose, the technical scheme adopted by the invention is as follows:
a laser washs aircraft skin real-time supervision device based on acoustic signal monitoring method includes: the device comprises a pulse laser, a spectroscope, a power meter, a condensing lens, a three-dimensional platform, an acoustic signal detection device and a computer;
after the laser emits laser, dividing the laser into two beams by a 2; the laser beam with higher power passes through a condenser lens with the focal length of 150mm and then is converged on the surface of a sample placed on the three-dimensional platform. The acoustic signal detection device obtains acoustic waves during paint removal.
The three-dimensional platform is controlled to move in real time through a computer, the sound wave signals of the action points on the surface of the sample can be received in real time through the sound signal detection device, and a curve graph of the sound wave signals is obtained in real time on the computer.
Further, the frequency of the laser emitted by the laser is 1Hz, and the power density is 3.82J/cm 2 The spot size was 1200 μm.
A laser cleaning aircraft skin real-time monitoring method based on an acoustic signal monitoring method comprises the following steps:
And 5, realizing layered monitoring according to the intensity distribution and the frequency domain distribution of the acoustic signals to obtain a paint removal result.
Preferably, the acoustic signal detection means sets the acoustic signal in the range of 1kHz-8 kHz.
Compared with the prior art, the invention has the advantages that:
the multilayer paint removing mechanism capable of monitoring the aircraft skin in real time is low in delay, small in error and high in accuracy. When the paint is completely removed at the moment, the point position can be immediately replaced to prevent the laser from excessively irradiating and damaging the substrate. The real-time performance and the accuracy are realized in the monitoring process.
Drawings
FIG. 1 is a structural diagram of a real-time monitoring device for laser cleaning of an aircraft skin according to an embodiment of the invention;
FIG. 2 is a graph of sound intensity signals corresponding to 1-20 laser pulses in accordance with one embodiment of the present invention;
FIG. 3 is a graph of frequency domain distribution of an acoustic signal as a function of the number of pulses according to an embodiment of the present invention; (a) 1 pulse, (b) 2 pulses, (c) 8 pulses, (d) 15 pulses, (e) 16 pulses, (f) 18 pulses, (g) 20 pulses;
FIG. 4 is a graph of the intensity versus number of pulses for acoustic signals of different frequencies according to an embodiment of the present invention;
FIG. 5 is a graph of the acoustic spectrum of a plasma generated by laser ablation of paint in accordance with an embodiment of the present invention;
FIG. 6 is a diagram of simulation results of acoustic rays according to an embodiment of the present invention, in which the number of beams of the rays is used to characterize the intensity.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings by way of examples.
1. Laser cleaning aircraft skin real-time monitoring device based on acoustic signal monitoring method
As shown in FIG. 1, the frequency of the 532nm pulse laser 1 is 1Hz, and the power density is 3.82J/cm 2 After the laser with the spot size of 1200um passes through a 2; the laser beam with higher power passes through a condenser lens 4 with the focal length of 150mm and then is converged on the surface of a sample placed on a three-dimensional platform 5. The sample substrate was a 1mm thick metal aluminum plate with a 24 μm surface of red thermoplastic acrylic paint. Meanwhile, the sound wave during paint removal is obtained through the RUBIX22 sound signal detection device 6. In the experiment, the three-dimensional platform is controlled by the computer 7 to move the sample with the substrate being the AL surface paint coating in real time, so that sample points under the action of 1,2,8 and other pulse times are obtained and respectively correspond to different stages in the paint removing process. Meanwhile, the sound wave probe receives the sound wave signals of the action point in real time through the action sound wave probe, and then the curve graphs of the sound wave signals are obtained on a computer in real time through the corresponding processing devices for real-time monitoring and follow-up research.
2. Real-time monitoring method for laser cleaning of aircraft skin based on acoustic signal monitoring method
FIG. 2 shows the laser energy density of 3.82J/cm 2 In the process, the time domain distribution of the acoustic signal generated in the laser paint removing process changes along with the pulse number. It can be seen from the figure that the amplitude of the sound signal generated by the action of the first pulse is lower, the amplitude of the sound signal generated by the action of 2-15 pulses is higher and is almost kept at the same level, the amplitude of the 16 th pulse is reduced, and then the amplitude of the sound signal is reduced to a weak signal gradually lower until the amplitude of the sound signal is stable. The finishing paint is mainly characterized in that a larger temperature gradient is generated on the contact surface of the finishing paint and the primer, so that the finishing paint and the primer are deformed and thermoelastic stress waves are generated, the stress waves penetrate through the finishing paint and are transmitted out of the primer, and when the stress is larger than the adhesion force of the primer of the finishing paint, the finishing paint is removed, so that the amplitude of an acquired acoustic signal is smaller when the finishing paint is removed, and the corresponding strength is smaller. Primer phaseCompared with the finish paint, the absorption of the finish paint to laser is high, mainly because ablation removal is carried out, and the primer is ionized in the ablation process to generate shock waves, so that when the primer is not cleaned, the amplitude of sound signals is high, and the intensity is increased. When applied to the 16 th pulse, the last thin layer of primer is removed by thermal stress, so the signal amplitude is now slightly reduced. After 16 pulses, the laser pulse directly acts on the metal substrate, and because the reflectivity of the metal is higher and the absorption of the laser is less, the amplitude of the collected acoustic signal is smaller, and the corresponding intensity becomes smaller again.
After Fourier transform is performed on the acoustic signal, a frequency domain distribution change diagram with the frequency range of 1kHz-20kHz is obtained when the 1 st to 20 th pulses are obtained, as shown in figure 3. The intensity change of the finish paint, the primer and the substrate in the frequency domain is similar to the time domain intensity change trend, and the overall intensity of the time domain signal is enhanced when the time domain signal is enhanced. It can be seen by comparing fig. 3 that there is a significant difference in the frequency spectrum when the topcoat, primer and substrate are laser cleaned. In a sectional view, signals are mainly distributed in a frequency range of 1kHz-8kHz, when the finish paint is cleaned (1 st pulse), a signal curve is smooth and weak, no signal with characteristic frequency exists, when the primer paint is cleaned (2 nd-15 th pulses), the signals in the range are increased, when the primer paint is removed and the substrate is exposed (16 th pulse), the signals begin to weaken and become flat as a whole without obvious peaks, and when the substrate is cleaned (17 th-20 th pulses), the signals in the range are increased along with the number of applied pulses, and the signals are lower and lower. Compared with the signal in the range of 1kHz-8kHz, the signal in the range of 8kHz-20kHz has only weak signal all the time, and has similar change trend with the signal in the range of 1kHz-8kHz, and the signal in the range is increased and then reduced in the process from cleaning the finish paint to the primer and finally to the substrate.
The paint removal process was analyzed by selecting the intensity of the acoustic signal at frequencies of 3kHz, 4kHz and 7.5kHz as a function of the pulsing, as shown in FIG. 4. The frequency intensity of the three positions changes almost uniformly along with the increase of the number of pulses. The intensity of the 2 nd pulse is increased rapidly, and the intensity of the 2 nd pulse to 14 th pulse is relatively stable, and begins to weaken after the 16 th pulse, and the intensity of the frequency of the acoustic signal is reduced to a stable state when the 20 th pulse acts. At pulse 16, the laser removes the last thin layer of primer by thermal stress effects, so that the 16 th pulse begins to decrease in intensity at all of these frequencies. After the 16 th pulse, the paint layer is gradually reduced and finally cleaned in the laser irradiation area, so that the intensity at the frequencies is gradually weakened until the intensity is stable. The incident laser light intensity is Gaussian distribution, the laser energy at the center of the facula is high, the energy at the edge is weak, the number of pulses required for cleaning the middle paint layer of the facula in the paint removing process is small, the paint layer at the edge needs more laser pulse action, along with the paint layer is less and less, the frequency intensity is lower and lower, and when the laser completely acts on the metal substrate, the intensity tends to be stable.
Theoretical analysis
The optical breakdown of air generates plasma to release shock waves, which become acoustic waves after propagation and attenuation. The mathematical model of a single laser acoustic signal is:
in the formula, P m Representing the sound wave peak sound pressure of the laser plasma; t is the attenuation coefficient of the laser plasma sound wave; u (t) represents a step function, P Bj Representing the peak sound pressure of the radiated sound wave when the laser cavitation bubble collapses for the jth time; tau is Bj Expressing the attenuation coefficient of the radiation sound wave when the laser cavitation collapses j times Bj The time interval of radiating the sound wave when the laser plasma sound wave and the laser cavitation bubble collapse for the jth time is shown. The Fourier transform is carried out on the sound wave to obtain an expression of the frequency spectrum of the sound wave, and under the ideal condition, the sound wave is formed by overlapping under the action of a plurality of lasers, so the expression of the frequency spectrum is as follows:
fig. 5 shows that the sound wave generated by the laser is mainly concentrated on 0-10 kHz, which includes the sound wave frequency bands 3, 4, and 7.5kHz that can be used for calibration in this embodiment, and it is proved that the significant amplitude variation of this band is because the sound wave generated by the laser plasma is also mainly concentrated on this band.
Meanwhile, comcol5.5 software is used for simulating acoustic rays in the paint removal process, and 5000 acoustic rays are emitted to the periphery by setting laser plasma to explode right above a paint layer and are absorbed and diffusely reflected in a certain proportion after contacting the paint layer. Meanwhile, with the increase of the pulse times, pits appear in the paint layer, and the diffuse reflection of sound waves is increased. And finally, receiving the number of the acoustic wave rays right above the plasma.
Below fig. 6 is a simulation diagram of 3 typical removal processes. When the first pulse removes the finish paint, the surface of the paint layer is smooth, so that the absorption and reflection of sound waves are uniform, and the receiving screen can only receive part of the sound waves; when the primer is removed by the pulse emitted by the 8 th emitter, a pit is formed in the paint layer due to the removal of the finish paint, sound waves are diffusely reflected in the pit, and the primer absorbs the sound waves less, so that rays of the substrate part are obviously reduced, a large number of rays are emitted in the positive direction after being reflected in the pit, and a large number of rays are received in the receiving screen; when the 18 th pulse damages the substrate, the main component of the substrate is aluminum, which is a metal and absorbs more sound waves, so that the number of rays penetrating through the paint layer is increased, and the number of rays received by the receiving screen is reduced. The upper graph of fig. 6 is obtained after counting the number of rays in different pulse situations. When the 1 st pulse is seen, the number of rays is less; then rapidly increases and maintains a stable trend; the number of rays decreased rapidly again until the primer was removed after the 16 th shot, damaging the substrate. Since the sound wave is a mechanical wave, the superposition principle of the sound wave follows linear superposition, the number of sound wave rays is in direct proportion to the amplitude of the total sound wave, and therefore the simulation result can be basically consistent with the amplitude change of the sound wave obtained by experiments.
Therefore, the acoustic signal in the range of 1kHz-8kHz can represent the process of laser cleaning the paint layer on the surface of the airplane skin compared with the intensity of the time domain signal, and the potential of the acoustic signal for online monitoring feedback of laser layered cleaning of the paint layer on the surface of the airplane skin is verified.
It will be appreciated by those of ordinary skill in the art that the examples described herein are intended to assist the reader in understanding the practice of the invention, and it is to be understood that the scope of the invention is not limited to such specific statements and examples. Those skilled in the art, having the benefit of this disclosure, may effect numerous modifications thereto and changes may be made without departing from the scope of the invention in its broader aspects.
Claims (4)
1. A laser washs aircraft skin real-time supervision device based on acoustic signal monitoring method includes: the device comprises a pulse laser, a spectroscope, a power meter, a condensing lens, a three-dimensional platform, an acoustic signal detection device and a computer;
after the laser emits laser, dividing the laser into two beams by a 2; the laser beam with higher power passes through a condenser lens with the focal length of 150mm and then is converged on the surface of a sample placed on a three-dimensional platform; the acoustic signal detection device obtains the intensity and frequency of acoustic waves during paint removal;
the three-dimensional platform is controlled to move in real time through a computer, the sound wave signals of the action points on the surface of the sample can be received in real time through the sound signal detection device, and a curve graph of the sound wave signals is obtained in real time on the computer.
2. The real-time monitoring device for the laser cleaning of the aircraft skin based on the acoustic signal monitoring method according to claim 1, is characterized in that: the laser frequency emitted by the laser is 1Hz, and the power density is 3.82J/cm 2 The spot size was 1200 μm.
3. A laser cleaning aircraft skin real-time monitoring method based on an acoustic signal monitoring method is characterized by comprising the following steps:
step 1, the surface to be monitored is divided into: a top coat, a primer and a metal substrate;
step 2, monitoring the paint removal condition by an acoustic signal detection device;
step 3, when the finish paint is cleaned by laser, the acoustic signal curve is smooth and weak, and no signal of characteristic frequency exists; the intensity of the acoustic signal is increased when the primer is cleaned; when the primer is removed to expose the substrate, the intensity of the acoustic signal begins to weaken and the whole becomes flat without obvious peaks; when the substrate is cleaned, the intensity of the acoustic signal is increased along with the number of the acting pulses, and the signal is lower and lower;
step 4, adopting sound wave intensities of 3kHz, 4kHz and 7.5kHz as signals of a detection paint layer, wherein when the finish paint is cleaned by laser, the first laser pulse is adopted, and the sound wave intensities of three frequencies are very small; the 2 nd to 15 th laser pulses are cleaning the primer, at which time the signal increases rapidly and remains in a stable range; the 16 th pulse is followed by a decay, and by the time about the 20 th pulse is applied, the acoustic signal frequency intensity is reduced to a steady state, corresponding to a thorough cleaning of the primer and irradiation of the substrate.
And 5, realizing layered monitoring according to the intensity distribution and the frequency domain distribution of the acoustic signals to obtain a paint removal result.
4. The real-time monitoring method for the laser cleaning of the aircraft skin based on the acoustic signal monitoring method according to claim 1, is characterized in that: the acoustic signal detection means sets the acoustic signal in the range of 1kHz to 8 kHz.
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| CN116484508A (en) * | 2023-04-26 | 2023-07-25 | 海目星激光智能装备(成都)有限公司 | Aircraft skin paint removal method, device, computer equipment and storage medium |
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