CN115945462B - Laser cleaning aircraft skin real-time monitoring method based on acoustic signal monitoring method - Google Patents
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 45
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- 238000001514 detection method Methods 0.000 claims abstract description 15
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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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, comprising the following steps: the object to be monitored is divided into: topcoats, primers, and metal substrates; the acoustic signal detection device monitors paint removal conditions; the sound signal is strong and weak when the laser cleans the paint; the intensity of the acoustic signal corresponding to the primer is increased; when the substrate is exposed, the acoustic signal intensity starts to decrease; when the substrate is cleaned, the acoustic signal intensity is increased along with the number of the applied pulses, and the signal intensity is lower and lower. The change of the special 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 signals to obtain a paint removal result. The invention has the advantages that: the paint removal device can monitor the paint removal of the multi-layer paint structure of the aircraft skin in real time, and has low delay, small error and high accuracy. When the signal indicates that the paint is removed, the point position can be replaced immediately so as to prevent the substrate from being damaged by the excessive irradiation of the laser. The method has real-time performance and accuracy 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 method based on an acoustic signal monitoring method.
Background
The performance integrity of the paint layer of the aircraft skin has a critical effect on the flight safety. As an emerging high-efficiency and rapid cleaning technology, the laser paint removing method has various advantages of high efficiency, small damage, less pollution and the like compared with the traditional paint removing method, and is widely applied in industry. To ensure the quality and the precision of paint removalThe 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. Wherein, the Laser Induced Breakdown Spectroscopy (LIBS) detection and the acoustic signal detection are favored by students at home and abroad by virtue of the advantages of high efficiency, accuracy, real time and the like [1,2] 。
In 2001, bregar [3] YAG lasers, which use excimer and Q-switched Nd, remove liquids or solids from the substrate, and are found to be accompanied by a detectable acoustic signal during cleaning. 2016 Villarreal-Villela [4] The laser ablation induced photo acoustic (PILA) signal fast fourier transform during laser paint removal to analyze the spectrum to identify paint components on the metal surface, and the method is proposed to be useful for monitoring the cleaning process. Papanikolaou 2020 [5] A hybrid Photo Acoustic (PA) and optical monitoring system for on-line monitoring of laser cleaning procedures is proposed by et al. This method allows the critical number of laser pulses required to eliminate the crust layer to be precisely determined. Researchers at home and abroad develop extensive researches aiming at the laser cleaning acousto-optic monitoring technology, and prove the effectiveness and real-time performance of the monitoring.
The prior art mainly focuses on the monitoring of single-layer paint cleaning, and the aircraft skin belongs to a multi-layer paint mechanism, and photoacoustic signals of the aircraft skin are more complex and various, so that the paint cleaning monitoring of the aircraft skin cannot be completed in the prior art.
The shock wave released by the laser breakdown air decays into an acoustic wave during transmission. The frequency of the sound wave is related to the parameters of the laser, and there will be a specific sound wave frequency at a specific laser parameter. Meanwhile, due to the fact that the materials of the paint layers of the paint absorb and reflect sound waves differently, pits are formed on the surfaces of the paint in the removing process to diffuse the sound waves and the like, 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 laser removal condition can be deduced by comparing the change of the amplitude intensity of the sound wave, so that the sound signal frequency monitoring method can also reflect the paint removal condition in real time.
Reference is made to:
[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] papanikolaou A, jtsereveleakis G, melesanaaki K, et al development of a hybrid photoacoustic and optical monitoring system for the study of laser abla tion processes upon the removal of encrustation from stonework [ J ]. Photoelectric progress (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 method based on an acoustic signal monitoring method.
In order to achieve the above object, the present invention adopts the following technical scheme:
a laser cleaning aircraft skin real-time monitoring method based on an acoustic signal monitoring method is realized on the basis of a laser cleaning aircraft skin real-time monitoring device;
the laser cleaning aircraft skin real-time monitoring device comprises: the system 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, the laser is divided into two beams by a 2:8 spectroscope, and one beam of laser with lower power is transmitted into a power meter so as to monitor the laser power in real time; the laser beam with higher power is converged on the surface of a sample placed on the three-dimensional platform after passing through a condensing lens with the focal length of 150 mm; the sound signal detection device obtains the intensity and frequency of sound waves during paint removal;
the three-dimensional platform is controlled to move in real time through a computer, and 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, so that a graph of the sound wave signals is obtained in real time on the computer;
the laser cleaning aircraft skin real-time monitoring method comprises the following steps:
step 1, dividing the surface to be monitored into: topcoats, primers, and metal substrates;
step 2, monitoring paint removal conditions by an acoustic signal detection device;
step 3, the curve of the acoustic signal is smooth and weak when the finish paint is cleaned by laser, and no signal with characteristic frequency exists; the acoustic signal intensity increases when the primer is cleaned; when the primer is removed to expose the substrate, the acoustic signal strength begins to decrease 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 action pulses, and the signal is lower and lower;
step 4, adopting sound wave intensities of 3kHz, 4kHz and 7.5kHz as signals for detecting the paint layer, wherein the sound wave intensities of three frequencies are very small when the paint layer is cleaned by laser; the 2 nd to 15 th laser pulses are wash primers, where the signal increases rapidly and remains in a stable range; beginning to fade after the 16 th pulse, and reducing the acoustic signal frequency intensity to steady state by the 20 th pulse, which corresponds to the 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.
Preferably, the laser emits laser light at a frequency of 1Hz and a power density of 3.82J/cm 2 The spot size was 1200 μm.
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 multi-layer paint mechanism capable of monitoring the aircraft skin in real time can remove paint, and is low in delay, small in error and high in accuracy. When the signal indicates that the paint is removed, the point position can be replaced immediately so as to prevent the substrate from being damaged by excessive irradiation of laser. The method has real-time performance and accuracy in the monitoring process.
Drawings
FIG. 1 is a block diagram of a laser cleaning aircraft skin real-time monitoring device according to an embodiment of the invention;
FIG. 2 is a graph of the sound intensity signal corresponding to 1-20 laser pulses according to an embodiment of the present invention;
FIG. 3 is a graph showing the 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, and (g) 20 pulses;
FIG. 4 is a graph showing the intensity of the acoustic signals with different frequencies according to the number of pulses according to the embodiment of the present invention;
FIG. 5 is a graph of the acoustic spectrum of a laser ablated paint to produce a plasma in accordance with an embodiment of the present invention;
FIG. 6 is a graph of simulation results of acoustic rays of an embodiment of the present invention, in which the number of rays represents the intensity.
Detailed Description
The invention will be described in further detail below with reference to the accompanying drawings and by way of examples in order to make the objects, technical solutions and advantages of the invention more apparent.
1. Laser cleaning aircraft skin real-time monitoring device based on acoustic signal monitoring method
As shown in FIG. 1, the real-time monitoring device has a 532nm pulse laser 1 with a frequency of 1HZ and a power density of 3.82J/cm 2 After laser with the light spot size of 1200um, the laser is divided into two beams by a 2:8 spectroscope 2, and one beam of laser with lower power is input into a power meter 3 to monitor the laser power in real time; the laser beam with higher power is converged on the surface of the sample placed on the three-dimensional platform 5 after passing through the condensing lens 4 with the focal length of 150 mm. The sample substrate is made of a metal aluminum plate with the thickness of 1mmThe surface is 24 mu m red thermoplastic acrylic resin paint. And simultaneously, the RUBIX22 acoustic signal detection device 6 is used for obtaining the acoustic wave during paint removal. In the experiment, the computer 7 controls the three-dimensional platform to move the sample of the AL surface paint layer in real time, and the sample points under the action of the pulse times of 1,2,8 and the like are obtained, which correspond to different stages in the paint removal process respectively. Meanwhile, the acoustic wave probe receives the acoustic wave signal of the action point in real time during the action, and then the corresponding processing device obtains the graph of the acoustic wave signal on the computer in real time for real-time monitoring and subsequent research.
2. Laser cleaning aircraft skin real-time monitoring method based on acoustic signal monitoring method
FIG. 2 shows a laser energy density of 3.82J/cm 2 And the time domain distribution of the acoustic signals generated in the laser paint removal process changes along with the pulse number. It can be seen intuitively that the amplitude of the acoustic signal generated during the first pulse is lower, the amplitude of the acoustic signal generated during the 2-15 pulses becomes higher, the amplitude remains almost at the same level, the 16 th pulse starts to decrease in amplitude, and then decreases to a weak signal, until it becomes stable. The finishing paint is mainly characterized in that the contact surface of the finishing paint and the primer generates larger temperature gradient, the finishing paint and the primer deform and generate thermoelastic stress waves, the stress waves are transmitted out from the primer through the finishing paint, 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 acoustic signals acquired when the finishing paint is removed is smaller, and the corresponding strength is smaller. Compared with the top coat, the primer has high absorption to laser, mainly because ablation is removed, and the primer is ionized to generate shock waves in the ablation process, so that when the primer is not cleaned, the amplitude of an acoustic signal is high, and the intensity is increased. When the 16 th pulse is applied, the last thin primer is removed by thermal stress, so the signal amplitude is slightly reduced. After 16 pulses, the laser pulse directly acts on the metal substrate, and the reflectivity of the metal is higher, so that the absorption of the laser is less, the amplitude of the collected acoustic signal is smaller, and the corresponding intensity is reduced again.
After the acoustic signal is subjected to Fourier transform, a frequency domain distribution change diagram with the frequency range of 1kHz-20kHz is obtained when the 1 st to 20 th pulse is obtained, and is shown in figure 3. The intensity changes of the finish paint, the primer and the base frequency domain are similar to the trend of the time domain intensity change, and the integral intensity of the time domain signal enhanced time-frequency domain signal is also enhanced. As can be seen by comparing fig. 3, there is a significant difference in the spectra of the laser cleaned topcoat, primer and applied to the substrate. In terms of segmentation, the signals are mainly distributed in the frequency range of 1kHz-8kHz, the signal curve is smooth and weak when the finishing paint is cleaned (1 st pulse), no signal with characteristic frequency exists, the signal in the range is increased when the primer is cleaned (2 nd pulse-15 th pulse), the signal starts to be weakened and the whole becomes flat without obvious peak when the primer is removed and exposed out of the substrate (16 th pulse), and the signal is lower and lower when the primer is cleaned to the substrate (17 th pulse-20 th pulse) along with the increase of the number of the action pulses. The frequency range of 8kHz-20kHz is always only weak compared with the signal range of 1kHz-8kHz, and the signal range is increased and then reduced in the process from the finish paint cleaning to the primer finishing to the substrate, similar to the signal change trend in the range of 1kHz-8 kHz.
The paint removal process was analyzed by selecting the intensity versus pulse of the acoustic signal frequencies at 3kHz, 4kHz and 7.5kHz, as shown in fig. 4. The frequency intensity of the three points is almost consistent with the change trend of the increase of the pulse number. The 2 nd pulse strength increases rapidly and begins to decrease after the 16 th pulse, with the 2 nd-14 th pulse being relatively stable, to about 20 th pulse, and the acoustic signal frequency strength decreases to steady state. The 16 th pulse acts to remove the last thin primer layer by thermal stress effects, so the 16 th pulse starts to decrease in intensity at all of these frequencies. After the 16 th pulse, the paint layer is gradually reduced in the laser irradiation area and finally cleaned, so that the intensity at the frequencies gradually reduces until the paint layer tends to be stable. The light intensity of the incident laser is Gaussian, the laser energy in the center of a facula is high, the energy at the edge is weak, the number of pulses required for cleaning a facula middle paint layer in the paint removal process is small, the paint layer at the edge needs more laser pulse action, the frequency intensity is lower and lower along with the fact that the paint layer is smaller and smaller, and when the laser completely acts on a metal substrate, the intensity tends to be stable.
Theoretical analysis
The optically broken air produces a plasma-releasing shock wave that propagates and decays to become an acoustic wave. The mathematical model of a single laser acoustic signal is:
in which P is m Representing the peak sound pressure of the laser plasma sound wave; t is the attenuation coefficient of the laser plasma sound wave; u (t) represents a step function P Bj The peak sound pressure of the radiation sound wave when the j-th collapse of the laser cavitation bubble is shown; τ Bj The attenuation coefficient T of the radiation sound wave when the jth laser cavitation is collapsed Bj The time interval of radiating the sound wave at the j-th collapse of the laser plasma sound wave and the laser cavitation is represented. The method is characterized in that the method is subjected to Fourier transformation to obtain an expression of a frequency spectrum, and under ideal conditions, sound waves are overlapped under the action of multiple lasers, so that the expression of the frequency spectrum is as follows:
as can be seen from FIG. 5, the sound wave generated by the laser is mainly concentrated at 0-10 kHz, which includes the sound wave bands 3, 4 and 7.5kHz which can be used for calibration in the embodiment, and the obvious amplitude change of the band is proved to be just because the sound wave generated by the laser plasma is mainly concentrated at the band.
Meanwhile, the Comcol5.5 software is used for simulating the sound wave rays in the paint removal process, laser plasmas are set to explode right above the paint layer, 5000 sound wave rays are emitted to the periphery, and a certain proportion of absorption and diffuse reflection exist after the sound wave rays contact the paint layer. Meanwhile, as the pulse times increase, pits appear in the paint layer to increase the diffuse reflection of sound waves. And finally, receiving the number of acoustic ray lines right above the plasma.
Below fig. 6 are simulated views of 3 typical removal processes. When the first impulse removes the top paint, the paint layer surface is smooth and flat, so that the absorption and reflection of sound waves are uniform, and the receiving screen can only receive part of sound waves; when the 8 th pulse is used for removing the primer, a pit is formed in the paint layer due to the removal of the finish paint, sound waves are diffusely reflected in the pit, meanwhile, the absorption of the primer to the sound waves is smaller, so that the rays of a substrate part are obviously reduced, a large number of rays are emitted forward after being reflected in the pit, and a large number of rays are received in a receiving screen; when the 18 th pulse damages the substrate, the main component of the substrate is aluminum, and the substrate absorbs more sound waves, so that the quantity of rays transmitted through the paint layer is increased, and the quantity of rays received by the receiving screen is reduced. The graph above in fig. 6 is obtained by counting the number of rays in the case of different pulses. When the 1 st pulse can be seen, the number of rays is small; then increases rapidly and maintains a steady trend; the number of rays decreased rapidly until the primer was removed after 16 th shot, damaging the substrate. Because the sound wave is used as a mechanical wave, the superposition principle of the sound wave is 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 is basically consistent with the amplitude change of the sound wave obtained through 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 aircraft skin compared with the time domain signal intensity, and the potential of the acoustic signal for on-line monitoring feedback of laser layering cleaning of the paint layer on the surface of the aircraft skin is verified.
Those of ordinary skill in the art will appreciate that the embodiments described herein are intended to aid the reader in understanding the practice of the invention and that the scope of the invention is not limited to such specific statements and embodiments. Those of ordinary skill in the art can make various other specific modifications and combinations from the teachings of the present disclosure without departing from the spirit thereof, and such modifications and combinations remain within the scope of the present disclosure.
Claims (3)
1. A real-time monitoring method for laser cleaning aircraft skin based on an acoustic signal monitoring method is characterized by comprising the following steps of: the laser cleaning aircraft skin real-time monitoring method is realized on the basis of a laser cleaning aircraft skin real-time monitoring device;
the laser cleaning aircraft skin real-time monitoring device comprises: the system 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, the laser is divided into two beams by a 2:8 spectroscope, and one beam of laser with lower power is transmitted into a power meter so as to monitor the laser power in real time; the laser beam with higher power is converged on the surface of a sample placed on the three-dimensional platform after passing through a condensing lens with the focal length of 150 mm; the sound signal detection device obtains the intensity and frequency of sound waves during paint removal;
the three-dimensional platform is controlled to move in real time through a computer, and 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, so that a graph of the sound wave signals is obtained in real time on the computer;
the laser cleaning aircraft skin real-time monitoring method comprises the following steps:
step 1, dividing the surface to be monitored into: topcoats, primers, and metal substrates;
step 2, monitoring paint removal conditions by an acoustic signal detection device;
step 3, the curve of the acoustic signal is smooth and weak when the finish paint is cleaned by laser, and no signal with characteristic frequency exists; the acoustic signal intensity increases when the primer is cleaned; when the primer is removed to expose the substrate, the acoustic signal strength begins to decrease 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 action pulses, and the signal is lower and lower;
step 4, adopting sound wave intensities of 3kHz, 4kHz and 7.5kHz as signals for detecting the paint layer, wherein the sound wave intensities of three frequencies are very small when the paint layer is cleaned by laser; the 2 nd to 15 th laser pulses are wash primers, where the signal increases rapidly and remains in a stable range; beginning to fade after the 16 th pulse, and reducing the acoustic signal frequency intensity to steady state by the 20 th pulse, which corresponds to the 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.
2. The method for monitoring the skin of the laser cleaning aircraft in real time based on the acoustic signal monitoring method according to claim 1, wherein the method comprises the following steps: the laser emitted by the laser has the frequency of 1Hz and the power density of 3.82J/cm 2 The spot size was 1200 μm.
3. The method for monitoring the skin of the laser cleaning aircraft in real time based on the acoustic signal monitoring method according to claim 1, wherein the method comprises the following steps: the acoustic signal detection means sets the acoustic signal in the range of 1kHz-8 kHz.
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