CN103278567A - Ultrasonic nondestructive evaluation of early-stage fatigue damage of bonding interface - Google Patents
Ultrasonic nondestructive evaluation of early-stage fatigue damage of bonding interface Download PDFInfo
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Abstract
The invention relates to an ultrasonic nondestructive evaluation of the early-stage fatigue damage of a bonding interface, and relates to a method for evaluating the early-stage fatigue damage of the bonding interface by utilizing an ultrasonic detecting technology. The method comprises the following steps: selecting a test specimen with a bonding structure; measuring the initial nonlinear coefficient of the bonding interface by utilizing a nonlinear ultrasonic testing system; carrying out the tensile fatigue loading on the test specimen and performing nonlinear ultrasonic testing for every thirty times until the test specimen is damaged; dividing the number of the final fatigue loading times by the number of the fatigue loading times, so as to obtain the value of the relative fatigue life; dividing the initial nonlinear coefficient by the nonlinear coefficient, so as to perform normalization; then repeating the operations by selecting another four test specimens; and by taking the normalized nonlinear coefficient as the y-coordinate and the value of the relative fatigue life as the x-coordinate, expressing the normalized nonlinear coefficient values of the five test specimens in the coordinate, so as to obtain a fitting relationship curve chart of the normalized nonlinear coefficient and the relative fatigue life, wherein the greater the normalized nonlinear coefficient is, the more serious the fatigue damage degree of the bonding interface is.
Description
Technical field
The present invention relates to a kind of ultrasonic nonodestruction evaluation method of bonding interface incipient fatigue damage, belong to the ultrasonic non-destructive inspection techniques field.
Background technology
Bonding is to utilize bonding agent to produce the process that mechanical bond power, physisorption power and chemical bond link up two bonds with joint efforts at conjunction plane.The bonding same material that is not only applicable to also is applicable to foreign material, has a wide range of applications at numerous industrial circles.As the aircraft industry field, utilize technique for sticking after because the minimizing of metal coupling unit can make the riveted joint of parts weight ratio or welding alleviate 20～25%, the strength ratio riveted joint improves 30～35%, the fatigue ratio riveted joint improves 10 times.Thereby the fuselage of present generation aircraft, wing, rudder face etc. are all a large amount of adopts bonding metal plate structure and honeycomb sandwich construction, and the large transport airplane bonded structure that has reaches 3200m
2, the bomber bond area that has accounts for 85% of full machine surface area.Use so widely just because of adhesive technology, the assessment of bonding plane mechanical property in the bonded structure is just seemed particularly important.Early stage ultrasonic non-destructive inspection techniques is mainly used to detect hole, the crack in the bonding plane and gross imperfection such as come unstuck, but carries out direct, quantitative assessment and detect just helpless for the problems such as life prediction of bonding strength, bonding force, performance degradation situation and the bonding plane of bonding plane.
Ultrasonic non-destructive inspection techniques all has a wide range of applications in all fields as one of obligato detection means in Modern Industry Products manufacturing and the use.The ultrasonic non-destructive inspection techniques of comparative maturity is primarily aimed at defective initial sum accumulation stage and the ultimate failure stage of material or structure at present, as existence and the distribution of defectives such as the micropore in the detecting material, micro-crack.Wherein mainly be applied to the information such as time-histories, the velocity of sound, decay, impedance, scattering of ripple.But these parameters are very insensitive to the degeneration of material and the early stage mechanical property of structure.
In recent years, the non-linear ultrasonic technology has caused people's extensive attention.Studies show that more and more material property degradation and hyperacoustic nonlinear effect are closely related.Because the degeneration of material property, to make the ultrasound wave waveform of wherein propagating produce distortion, cause having in the ultrasound wave of single-frequency the generation of high-frequency harmonic, will produce the high-order harmonic wave of integer multiple frequencies such as two times, three times when namely the ultrasound wave of single-frequency is propagated in the medium with nonlinear characteristic or structure.Therefore by the measurement research to these high-frequency harmonics, find its acoustics nonlinear factor that is in different phase, just can make effective Non-Destructive Testing to early stage mechanical property degradation and the damage of material and structure.For this reason, the present invention carries out Nondestructive Evaluation by measuring hyperacoustic nonlinear transformations to the incipient fatigue damage of bonding interface.
Summary of the invention
The technical problem to be solved in the present invention:
Propose a kind of ultrasonic nonodestruction evaluation method of bonding interface incipient fatigue damage, provide the ultrasonic nonodestruction evaluation concrete operations step of estimating bonded structure bonding interface earlier damage under the fatigue load effect.
Technical scheme of the present invention:
A kind of ultrasonic nonodestruction evaluation method of bonding interface incipient fatigue damage, it comprises following steps:
The mensuration of the initial nonlinear factor of step 1 bonding interface
Choose a bonded structure test specimen (6), utilize signal specific to make ultrasonic transducer (5) excitation ultrasound ripple signal in a side of test specimen, utilize ultrasonic transducer (7) to receive the ultrasonic signal that sees through bonding interface at the opposite side of test specimen; The ultrasonic signal that receives is carried out Fourier transform, obtain the fundamental frequency amplitude A in the ultrasonic signal of computing machine (3) record
1With frequency multiplication amplitude A
2
Definition nonlinear factor: β=A
2/ A
1 2
Calculate the initial nonlinear factor of bonding interface, be designated as β
0
The fatigue of step 2 bonding interface loads
After utilizing testing machine that bonded structure (6) stretching is loaded into certain pulling force, unload again.After finishing unloading, again this bonded structure is loaded into same value of thrust, then unloading.Behind certain number of times, record fatigue loads number of times so repeatedly.Bonded structure is unloaded from experimental machine, carry out the mensuration of follow-up nonlinear factor;
The mensuration of step 3 bonding interface nonlinear factor
Utilize ultrasonic transducer (5) excitation ultrasound ripple signal in a side of bonded structure (6), utilize ultrasonic transducer (7) to receive the ultrasonic signal that sees through bonded structure at the opposite side of bonded structure; The ultrasonic signal that receives is carried out Fourier transform, obtain the fundamental frequency amplitude A in the ultrasonic signal of computing machine (3) record
1With frequency multiplication amplitude A
2According to the definition of nonlinear factor in the step 1, calculate corresponding nonlinear factor β; With this nonlinear factor β divided by the initial nonlinear factor β in the step 1
0Carry out regularization, obtain regularization nonlinear system numerical value;
Step 4 regularization nonlinear factor and the acquisition that concerns relative fatigue lifetime
Repeating step two destroys up to bonded structure to the operation of step 3, and the final fatigue of record loads number of times, measures final regularization nonlinear factor.Fatigue during with each repeating step two loads number of times divided by the final tired number of times that loads, and obtains the relative fatigue lifetime behind each repeating step two.According to the each repeating step three regularization nonlinear factor that obtains and relative fatigue lifetime that repeating step two obtains, obtain the regularization nonlinear factor of a test specimen and the relation of relative fatigue lifetime;
The acquisition of step 5 matched curve
Choose 3 to 5 bonded structure test specimen repeating steps one again to the operation of step 4, further obtain the regularization nonlinear factor of bonding interface in a plurality of bonded structure test specimens and the relation of relative fatigue lifetime; Experimental data to all test specimens carries out curve fitting, and obtains the relation curve of bonding interface regularization nonlinear factor and relative fatigue lifetime;
The ultrasonic nonodestruction evaluation of step 6 bonding interface incipient fatigue damage
According to the match graph of relation of regularization nonlinear factor with relative fatigue lifetime, the incipient fatigue damage of bonding interface is estimated: the regularization nonlinear factor is more big, and the fatigue damage degree of bonding interface is more big; More close to final regularization nonlinear factor, bonding interface is more close to its final service life for the regularization nonlinear factor.
The beneficial effect of the invention is:
Bonded structure has a wide range of applications at numerous industrial circles.A kind of effective Dynamic Non-Destruction Measurement is to effective prediction of bonding interface earlier damage, and guarantees industrial security of operation and avoid great interruption of service significant.
Description of drawings
Fig. 1 is non-linear ultrasonic test macro synoptic diagram.
Fig. 2 is bonded structure test specimen synoptic diagram.
Fig. 3 be the regularization nonlinear factor with relative fatigue lifetime between graph of relation.
Among the figure: oscillograph 1, main frame 2, computing machine 3, preposition decay and low-pass filtering module 4, ultrasonic transducer 5, bonding test specimen 6, ultrasonic transducer 7.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The non-linear ultrasonic test macro, as shown in Figure 1, it comprises: oscillograph 1, main frame 2, computing machine 3, preposition decay and low-pass filtering module 4, ultrasonic excitation device 5, ultrasonic probe, ultrasonic receiver 7.The model of oscillograph 1 is TDS3034B, and the model of main frame 2 is Ritec SNAP-0.25-7-G2, and the model of preposition decay and low-pass filtering module 4 is RLP-2.Utilize concentric cable that the signal output part A of main frame 2 is connected with the input end of preposition decay and low-pass filtering module 4, the output terminal of preposition decay and low-pass filtering module 4 is connected with ultrasonic transducer 5, the signal of ultrasonic transducer inserts the receiving end B of main frame 2, and the signal monitoring port C of main frame 2 is connected with oscillograph 1.
A kind of ultrasonic nonodestruction evaluation method one of bonding interface incipient fatigue damage may further comprise the steps:
The mensuration of the initial nonlinear factor of step 1 bonding interface
Choose bonded structure test specimen 6 as shown in Figure 2, utilize signal specific to make ultrasonic transducer 5 excitation ultrasound ripple signals in a side of test specimen, utilize ultrasonic transducer 7 to receive the ultrasonic signal that sees through bonding interface at the opposite side of test specimen; The ultrasonic signal that receives is carried out Fourier transform, obtain the fundamental frequency amplitude A in the ultrasonic signal of computing machine 3 record
1With frequency multiplication amplitude A
2
Definition nonlinear factor: β=A
2/ A
1 2
Calculate the initial nonlinear factor of bonding interface, be designated as β
0
The fatigue of step 2 bonding interface loads
After utilizing testing machine that bonded structure 6 stretchings are loaded into 30kN, unload again.After finishing unloading, again this bonded structure is loaded into same value of thrust, then unloading.After loading 30 times so repeatedly, bonded structure is unloaded from experimental machine, carry out follow-up non-linear ultrasonic test;
The mensuration of step 3 bonding interface nonlinear factor
Utilize ultrasonic transducer 5 excitation ultrasound ripple signals in a side of bonded structure 6, utilize ultrasonic transducer 7 to receive the ultrasonic signal that sees through bonded structure at the opposite side of bonded structure; The ultrasonic signal that receives is carried out Fourier transform, obtain the fundamental frequency amplitude A in the ultrasonic signal of computing machine 3 record
1With frequency multiplication amplitude A
2According to the definition of nonlinear factor in the step 1, calculate corresponding nonlinear factor β; With this nonlinear factor β divided by the initial nonlinear factor β in the step 1
0Carry out regularization, obtain regularization nonlinear system numerical value;
Step 4 regularization nonlinear factor and the acquisition that concerns relative fatigue lifetime
Repeating step two destroys up to bonded structure to the operation of step 3, and the final fatigue of record loads number of times, measures final regularization nonlinear factor.Fatigue during with each repeating step two loads number of times divided by the final tired number of times that loads, and obtains the relative fatigue lifetime behind each repeating step two.The regularization relative nonlinear coefficient that each repeating step three obtains is respectively 1,1.46672,1.74364,2.61607, and be respectively 0,27.027,54.0541,99.0991 corresponding relative fatigue lifetime.Obtain the regularization nonlinear factor of a test specimen and the relation of relative fatigue lifetime thus;
The acquisition of step 5 matched curve
Choose 4 bonded structure test specimen repeating steps one again to the operation of step 4, the regularization nonlinear factor that obtains second bonded structure test specimen is respectively 1,1.37645,1.51807,3.02946, is respectively 0,32.967,65.9341,98.9011 fatigue lifetime relatively; The regularization nonlinear factor of the 3rd bonded structure test specimen is respectively 1,1.55236,1.99299,1.9896,2.20369,2.4099,2.44151,2.33157,2.66742, is respectively 0,9.677,19.355,29.032,38.71,48.387,58.064,80.645,96.774 fatigue lifetime relatively; The regularization nonlinear factor of the 4th bonded structure test specimen is respectively 1,1.39966,1.54367,2.36657, is respectively 0,29.412,58.823,88.235 fatigue lifetime relatively; The regularization nonlinear factor of the 5th bonded structure test specimen is respectively 1,1.42568,1.59604,1.7085,1.72219,1.75699,1.62131,2.15016, is respectively 0,10.714,21.429,32.143,42.857,53.571,64.286,82.143 fatigue lifetime relatively.According to test specimen 1 to the regularization nonlinear factor of test specimen 5 with relative fatigue lifetime of data, the experimental data of all test specimens is carried out curve fitting, obtain the relation curve of bonding interface regularization nonlinear factor and relative fatigue lifetime, as shown in Figure 3.
The ultrasonic nonodestruction evaluation of step 6 bonding interface incipient fatigue damage
According to the match graph of relation of regularization nonlinear factor with relative fatigue lifetime, the incipient fatigue damage of bonding interface is estimated: the regularization nonlinear factor is more big, and the fatigue damage degree of bonding interface is more big; More close to final regularization nonlinear factor, bonding interface is more close to its final service life for the regularization nonlinear factor.
Claims (1)
1. the ultrasonic nonodestruction evaluation method of a bonding interface incipient fatigue damage is characterized in that, comprises following steps:
The mensuration of the initial nonlinear factor of step 1 bonding interface
Choose a bonded structure test specimen (6), utilize signal specific to make ultrasonic transducer (5) excitation ultrasound ripple signal in a side of test specimen, utilize ultrasonic transducer (7) to receive the ultrasonic signal that sees through bonding interface at the opposite side of test specimen; The ultrasonic signal that receives is carried out Fourier transform, obtain the fundamental frequency amplitude A in the ultrasonic signal of computing machine (3) record
1With frequency multiplication amplitude A
2
Definition nonlinear factor: β=A
2/ A
1 2
Calculate the initial nonlinear factor of bonding interface, be designated as β
0
The fatigue of step 2 bonding interface loads
After utilizing testing machine that bonded structure (6) stretching is loaded into certain pulling force, unload again.After finishing unloading, again this bonded structure is loaded into same value of thrust, then unloading.Behind certain number of times, record fatigue loads number of times so repeatedly.Bonded structure is unloaded from experimental machine, carry out the mensuration of follow-up nonlinear factor;
The mensuration of step 3 bonding interface nonlinear factor
Utilize ultrasonic transducer (5) excitation ultrasound ripple signal in a side of bonded structure (6), utilize ultrasonic transducer (7) to receive the ultrasonic signal that sees through bonded structure at the opposite side of bonded structure; The ultrasonic signal that receives is carried out Fourier transform, obtain the fundamental frequency amplitude A in the ultrasonic signal of computing machine (3) record
1With frequency multiplication amplitude A
2According to the definition of nonlinear factor in the step 1, calculate corresponding nonlinear factor β; With this nonlinear factor β divided by the initial nonlinear factor β in the step 1
0Carry out regularization, obtain regularization nonlinear system numerical value;
Step 4 regularization nonlinear factor and the acquisition that concerns relative fatigue lifetime
Repeating step two destroys up to bonded structure to the operation of step 3, and the final fatigue of record loads number of times, measures final regularization nonlinear factor.Fatigue during with each repeating step two loads number of times divided by the final tired number of times that loads, and obtains the relative fatigue lifetime behind each repeating step two.According to the each repeating step three regularization nonlinear factor that obtains and relative fatigue lifetime that repeating step two obtains, obtain the regularization nonlinear factor of a test specimen and the relation of relative fatigue lifetime;
The acquisition of step 5 matched curve
Choose 3 to 5 bonded structure test specimen repeating steps one again to the operation of step 4, further obtain the regularization nonlinear factor of bonding interface in a plurality of bonded structure test specimens and the relation of relative fatigue lifetime; Experimental data to all test specimens carries out curve fitting, and obtains the relation curve of bonding interface regularization nonlinear factor and relative fatigue lifetime;
The ultrasonic nonodestruction evaluation of step 6 bonding interface incipient fatigue damage
According to the match graph of relation of regularization nonlinear factor with relative fatigue lifetime, the incipient fatigue damage of bonding interface is estimated: the regularization nonlinear factor is more big, and the fatigue damage degree of bonding interface is more big; More close to final regularization nonlinear factor, bonding interface is more close to its final service life for the regularization nonlinear factor.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103713052A (en) * | 2014-01-03 | 2014-04-09 | 国家电网公司 | Method for measuring yield strength of Q345 low alloy steel by using nonlinear ultrasonic technique |
| CN103776902A (en) * | 2014-01-15 | 2014-05-07 | 北京交通大学 | Nonlinear ultrasound evaluating method for impact fatigue damage of metal bonding interface |
| CN108508091A (en) * | 2018-05-23 | 2018-09-07 | 国电锅炉压力容器检验有限公司 | Detect the method and device of article deterioration parameter |
| CN111257419A (en) * | 2020-02-03 | 2020-06-09 | 天津大学 | Extra-high voltage insulation pull rod interface defect detection device |
| CN111257417A (en) * | 2020-02-03 | 2020-06-09 | 天津大学 | Method for detecting interface defects of extra-high voltage insulating pull rod |
| CN113029773A (en) * | 2019-12-24 | 2021-06-25 | 深圳市富力达工业有限公司 | Method and system for detecting fatigue degree of material |
| JP2022142527A (en) * | 2021-03-16 | 2022-09-30 | 株式会社豊田中央研究所 | Deterioration measurement device and deterioration measurement method for adhesion junction |
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|---|---|---|---|---|
| CN103713052A (en) * | 2014-01-03 | 2014-04-09 | 国家电网公司 | Method for measuring yield strength of Q345 low alloy steel by using nonlinear ultrasonic technique |
| CN103776902A (en) * | 2014-01-15 | 2014-05-07 | 北京交通大学 | Nonlinear ultrasound evaluating method for impact fatigue damage of metal bonding interface |
| CN108508091A (en) * | 2018-05-23 | 2018-09-07 | 国电锅炉压力容器检验有限公司 | Detect the method and device of article deterioration parameter |
| CN113029773A (en) * | 2019-12-24 | 2021-06-25 | 深圳市富力达工业有限公司 | Method and system for detecting fatigue degree of material |
| CN111257419A (en) * | 2020-02-03 | 2020-06-09 | 天津大学 | Extra-high voltage insulation pull rod interface defect detection device |
| CN111257417A (en) * | 2020-02-03 | 2020-06-09 | 天津大学 | Method for detecting interface defects of extra-high voltage insulating pull rod |
| JP2022142527A (en) * | 2021-03-16 | 2022-09-30 | 株式会社豊田中央研究所 | Deterioration measurement device and deterioration measurement method for adhesion junction |
| JP7273375B2 (en) | 2021-03-16 | 2023-05-15 | 株式会社豊田中央研究所 | Deterioration measurement device and deterioration measurement method for adhesive joints |
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Application publication date: 20130904 |