CN104374830A - Near field phased array structure health monitoring method based on piezoelectric array - Google Patents

Near field phased array structure health monitoring method based on piezoelectric array Download PDF

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CN104374830A
CN104374830A CN201410697078.3A CN201410697078A CN104374830A CN 104374830 A CN104374830 A CN 104374830A CN 201410697078 A CN201410697078 A CN 201410697078A CN 104374830 A CN104374830 A CN 104374830A
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signal
angle
damage
piezoelectric
piezoelectric patches
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孙亚杰
袁慎芳
张永宏
刘青山
季赛
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Nanjing University of Information Science and Technology
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Nanjing University of Information Science and Technology
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Abstract

The invention discloses a near field phased array structure health monitoring method based on a piezoelectric array. The method comprises the following steps: arranging a piezoelectric linear array on a monitoring structure so as to obtain a damage scattering signal of each excitation-sensing channel, adding time delay to a damage signal, and determining the damage direction; and finally, determining the damage position according to a signal arrival moment t. With the adoption of the near field phased array structure monitoring method disclosed by the invention, micro damage in a complex structure can be identified, and the limitation of a far field phased array on the monitoring distance is overcome.

Description

A kind of near-field phased array structure health monitoring method based on piezoelectric-array
Technical field
The invention belongs to engineering structure health monitoring technical field, particularly a kind of near-field phased array structure health monitoring method based on piezoelectric-array.
Background technology
Engineering structure health monitoring technology is used for monitoring, diagnosing and continuous state and the fault running engineering system of indication, ensure engineering equipment safe operation, promptly and accurately identification of damage will to the safe operation of guarantee engineering system, reduce or the sexual behavior therefore have very important significance of averting a calamity.The health monitoring technique of aptitude for flying structure needs the initial stage occurred in damage, real time on-line monitoring configuration state, damage in identification structure is also accurately located, but most of checkout equipment is complicated, and cost is high, time-consuming, to the material structure of some Performance comparision complexity, as composite structure, owing to affecting by noise etc., some little damages can't detect well.Phased array structures health monitoring technique is the time delay of transmitting and receiving by controlling each piezoelectric element and then controls Lamb wave beam scanning, realize the Multidirectional sweeping to structure, identify the damage existed in structure, the focusing of Lamb wave wave beam can improve the signal to noise ratio (S/N ratio) of signal greatly.Phased array theory calls monitoring target is positioned at sensor array far field, carries out the method for monitoring structural health conditions, and the method successfully can identify in structure and damage within the scope of its monitoring distance limited, and is very helpful to principle exploration work tool.But far field ultrasonic phase array, has certain restriction in monitoring distance, therefore study near-field ultrasound phased array structures health monitor method, the limitation of far field ultrasonic phase array in monitoring distance can be made up.
Summary of the invention
In order to solve the technical matters that above-mentioned background technology is mentioned, the present invention aims to provide a kind of near-field phased array structure health monitoring method based on piezoelectric-array, adopt near-field phased array structure monitoring method, the microlesion in labyrinth can be identified, and compensate for the limitation of far field phased array in monitoring distance.
In order to realize above-mentioned technical purpose, technical scheme of the present invention is:
Based on a near-field phased array structure health monitoring method for piezoelectric-array, comprise the following steps:
(1) in structure to be monitored, arrange the piezoelectricity linear array be made up of M piezoelectric patches, M piezoelectric patches defines sequence number 0 ~ M-1 successively;
(2) under structural health conditions, Lamb wave narrow band signal is put on successively M piezoelectric patches in piezoelectricity linear array, when Lamb wave narrow band signal is put on a certain piezoelectric patches, this piezoelectric patches inspires pumping signal in the structure as driver, and all the other M-1 piezoelectric patches all receives the response signal propagated in structure respectively as sensor, 1 driver and 1 sensor are collectively referred to as 1 excitation-sensing passage, then obtain altogether the response signal of the individual excitation-sensing passage of M × (M-1);
(3) under On Damage State, step (2) is repeated;
(4) response signal of the individual excitation-sensing passage of M × (M-1) step (2) obtained is as reference signal, the response signal of the individual excitation-sensing passage of M × (M-1) step (3) obtained is subtracted each other with corresponding reference signal, obtains the damage scattered signal of the individual excitation-sensing passage of M × (M-1);
(5) in the monitoring range of piezoelectricity linear array near field, the damage scattered signal of each excitation-sensing passage within the scope of angle monitor at interval of Δ θ, and corresponding time delay is carried out at interval of during Δ ε in distance monitoring range, this time delay is called and angle-apart from upper time delay obtains the damage scattered signal after the time delay of each excitation-sensing passage in monitoring range in each angle-distance; Wherein, described angle monitor scope is [0 °, 180 °], and distance monitoring range is [0, L], and i-th piezoelectric patches is as the angle-be apart from upper time delay of the excitation-sensing passage of driver:
Δ t i ( r , θ ) = r - r 2 + ( i · d ) 2 - 2 · r · i · d · cos θ c
In above formula, r is the distance between monitoring point and true origin, and θ is the angle that true origin line and x-axis are arrived in monitoring point, and c is Lamb wave velocity of wave in the structure, and d is the distance in piezoelectricity linear array between adjacent two piezoelectric patches;
(6) by the same angle of each excitation-sensing passage-carry out cumulative synthesis apart from the damage scattered signal after upper time delay, obtain each angle-apart from upper composite signal, and be normalized;
(7) more each angle-apart from upper normalization composite signal, the angle at the composite signal place of amplitude maximum is the direction at damage place, then calculated the radius of damage position by the due in of the composite signal of amplitude maximum and this direction Lamb wave wave-velocity meter, thus determine the position damaged.
Wherein, in step (1), the piezoelectric patches number M of piezoelectricity linear array is 9.
Wherein, described in step (2), pumping signal is narrow band signal.
Wherein, in step (5), described angle intervals Δ θ is 1 °; Described L=3 λ, λ are the wavelength of Lamb wave, and distance interval delta ε is 1mm.
Wherein, the propagation group velocity when velocity of wave c of Lamb wave described in step (5) refers to that Lamb wave only inspires A0 pattern in the structure.
Adopt the beneficial effect that technique scheme is brought:
(1) the present invention can realize effective monitoring and evaluation of the structural damage to sensor array near field, overcomes the limitation of far field phased array structures health monitoring in monitoring distance, is conducive to the practical of Lamb wave phased array structures health monitoring;
(2) the present invention can realize the directional focusing of near-field phased array Lamb wave signal, damage scattered signal is focused at structural damage place, thus border can be suppressed to reflect and other noises, and then improve the signal to noise ratio (S/N ratio) of Lamb wave damage scattered signal;
(3) the present invention utilizes existing Lamb wave monitoring equipment to realize, without the need to increasing and decreasing equipment or amendment parameter in implementation procedure, simple.
Accompanying drawing explanation
Fig. 1 is the near-field phased array schematic diagram in the present invention;
Fig. 2 is method flow diagram of the present invention;
Fig. 3 is the structural representation of test specimen structure and sensor array in the embodiment of the present invention;
Fig. 4 is narrowband excitation signal time-domain diagram in the embodiment of the present invention;
Fig. 5 is typical sensors response signal and damage scattered signal time-domain diagram in the embodiment of the present invention, comprise (a), (b), (c) 3 width figure, be followed successively by the response signal of healthy structure when No. 0 piezoelectric patches is driver, No. 1 piezoelectric patches is sensor, the response signal of damaged structure and damage scattered signal;
Fig. 6 is typical time period inhibit signal time-domain diagram in the embodiment of the present invention, comprises (a) ~ (h) 8 width figure, represents No. 0 piezoelectric patches successively as driver, other piezoelectric patches as the damage scattered signal S of sensor 01~ S 08, at the schematic diagram that 0 ° of direction 10mm distance elapsed time postpones;
Fig. 7 is the ceiling capacity figure of each direction of scanning-distance composite signal in the embodiment of the present invention;
Fig. 8 is normalization composite signal absolute value envelope diagram in the embodiment of the present invention;
Fig. 9 is near-field ultrasound phased array surveillance map in the embodiment of the present invention.
Embodiment
Below with reference to accompanying drawing, technical scheme of the present invention is described in detail.
Near-field phased array schematic diagram as shown in Figure 1 in the present invention, puts on sequence number 0 ~ M-1 successively by M piezoelectric patches, and is linearly arranged in piezoelectricity linear array, using piezoelectricity linear array place straight line as x-axis, with the 0th piezoelectric patches position for initial point sets up rectangular coordinate system.P (r, signal θ) received is that the pumping signal that each piezoelectric patches inspires propagates the cumulative of rear signal in the structure, and r is the distance of P (r, θ) point to true origin, θ is the angle that true origin arrives beam position that P (r, θ) puts and x-axis.The signal that so P (r, θ) point receives is:
S P ( r , θ ) = k 1 Σ i = 0 M - 1 S e ( t - r i c ) = K 1 Σ i = 0 M - 1 S e ( t - r - Δr i c ) = K 1 Σ i = 0 M - 1 S e ( t - r c + Δ t i ( r , θ ) ) - - - ( 1 )
In formula (1), i is piezoelectric patches sequence number, i=0,1,2 .., M-1, K 1for the attenuation coefficient of amplitude after signal propagation certain distance in emission process; S et () represents pumping signal; r ibe that the i-th piezoelectric patches puts distance to P (r, θ); C is Lamb wave velocity of propagation in the structure; Δ r ibe the i-th piezoelectric patches pumping signal arrive P (r, θ) point with true origin arrive P (r, θ) put between range difference; Δ t i(r, θ) is the mistiming that the i-th piezoelectric patches arrival P (r, θ) point and true origin arrive between P (r, θ) point.
In order to make each pumping signal arrive P (r, θ) point simultaneously, then the pumping signal to each piezoelectric patches excites is needed to carry out certain compensation in time.If add corresponding time delay Δ t to the pumping signal that each piezoelectric patches excites i(r, θ), the signal energy that so P (r, θ) point receives reaches maximum, and the focus signal that now P (r, θ) point receives can be expressed as:
S P ( t ) = K 1 · M · S e ( t - r c ) - - - ( 2 )
By controlling the time delay of the pumping signal that each piezoelectric patches excites, controlling Lamb wave signal and deflecting by predetermined angle, realize monitoring the directional scanning of structure within the specific limits.
From reciprocity, under the same conditions, it is consistent for receiving with transmitting, and the time delay namely by controlling each sensor response signal can receive the target information on predetermined deflection angle direction.When piezoelectric patches receives P (r, θ) point reflection signal, the signal that the i-th piezoelectric patches receives P (r, θ) point reflection as sensor is:
S i ( r , θ ) = k 2 S P ( t - r c + Δ t i ( r , θ ) ) - - - ( 3 )
In formula (3), K 2for the attenuation coefficient of amplitude after signal propagation certain distance in receiving course; S pt focus signal that () receives for the place of P (r, θ) some formula (3) Suo Shi; Δ t i(r, θ) be the i-th piezoelectric patches as sensor Received signal strength time, some P (r, θ) is to the i-th piezoelectric patches and the mistiming of putting between P (r, θ) to true origin.
Δ t is added to the response signal in the θ direction that the i-th piezoelectric patches receives ithe time delay of (r, θ), its expression formula is:
S i ( t ) = K 2 S P ( t - r c ) - - - ( 4 )
The signal in beam position θ direction is the cumulative of the θ direction signal of each piezoelectric patches reception, that is:
S ( t ) = Σ i = 0 m - 1 K 2 S P ( t - r c ) = K 2 · M · S P ( t - r c ) = K 1 · K 2 · M 2 · S e ( t - 2 r c ) = K · M 2 · S e ( t - 2 r c ) - - - ( 5 )
In formula (5), K=K 1k 2for transmitting and receiving the attenuation coefficient that in two processes, signal amplitude is total.
In the near field of piezoelectricity linear array, the signal that array element excites forms the wave beam of a focus characteristics at space interference, when signal beam scans within the scope of certain angle, the echoed signal amplitude received is utilized to measure, when wave beam aims at the mark, echoed signal energy is the strongest, and when wave beam departs from target, echoed signal weakens.Beam position time the strongest according to reception echo, determines the direction of target.The ultimate principle of target angle measurement that Here it is.
Utilize ultrasonic phased array technology, the footpath, pole of damage position can be determined by the signal of target place angle, namely the signal on direction, known target place, then can know signal due in t, when measuring structure Lamb wave velocity of wave, can calculate monitoring objective (damage) to the distance of true origin is:
r * = c · t 2 - - - ( 6 )
According to above-mentioned theory, design a kind of near-field phased array structure health monitoring method based on piezoelectric-array of the present invention, comprise the following steps:
(1) in structure to be monitored, arrange the piezoelectricity linear array be made up of M piezoelectric patches;
(2) under structural health conditions, Lamb wave narrow band signal is put on successively M piezoelectric patches in piezoelectricity linear array, when Lamb wave narrow band signal is put on a certain piezoelectric patches, this piezoelectric patches inspires pumping signal in the structure as driver, and all the other M-1 piezoelectric patches all receives the response signal propagated in structure respectively as sensor, 1 driver and 1 sensor are collectively referred to as 1 excitation-sensing passage, then obtain altogether the response signal of the individual excitation-sensing passage of M × (M-1);
(3) under On Damage State, step (2) is repeated;
(4) response signal of the individual excitation-sensing passage of M × (M-1) step (2) obtained is as reference signal, the response signal of the individual excitation-sensing passage of M × (M-1) step (3) obtained is subtracted each other with corresponding reference signal, obtains the damage scattered signal of the individual excitation-sensing passage of M × (M-1);
(5) in the monitoring range of piezoelectricity linear array near field, the damage scattered signal of each excitation-sensing passage within the scope of angle monitor at interval of Δ θ, and corresponding time delay is carried out at interval of during Δ ε in distance monitoring range, this time delay is called and angle-apart from upper time delay obtains the damage scattered signal after the time delay of each excitation-sensing passage in monitoring range in each angle-distance; Wherein, described angle monitor scope is [0 °, 180 °], and distance monitoring range is [0, L], and i-th piezoelectric patches is as the angle-be apart from upper time delay of the excitation-sensing passage of driver:
Δ t i ( r , θ ) = r - r 2 + ( i · d ) 2 - 2 · r · i · d · cos θ c
In above formula, i represents the piezoelectric patches sequence number as driver (emission process) or sensor (receiving course), r is the distance between monitoring point and near-field phased array true origin, θ is the angle that near-field phased array true origin line and x-axis are arrived in monitoring point, c is Lamb wave velocity of wave in the structure, and d is the distance in piezoelectricity linear array between adjacent two piezoelectric patches;
(6) by the same angle of each excitation-sensing passage-carry out cumulative synthesis apart from the damage scattered signal after upper time delay, obtain each angle-apart from upper composite signal, and be normalized;
(7) more each angle-apart from upper normalization composite signal, the angle at the composite signal place of amplitude maximum is the direction at damage place, then calculated the radius of damage position by the due in of the composite signal of amplitude maximum and this direction Lamb wave wave-velocity meter, thus determine the position damaged.
Above-mentioned steps as shown in Figure 2.
This example adopts glass fibre reinforced composion plate conventional in engineering structure, is of a size of 2000mm × 1000mm × 3mm.In composite structure, arrange 9 PZT piezoelectric patches (sequence number 0 ~ 8) composition linear arrays, the distance between adjacent two piezoelectric patches is 12mm, and the diameter of each piezoelectric patches is 8mm, and thickness is 0.48mm.The present embodiment is using the 4th piezoelectric patches as the true origin of monitored area, and by load mass block simulation damage, mass loading position is (60 °, 50mm).The structural representation of experiment test specimen and piezoelectricity linear array as shown in Figure 3.
The pumping signal adopted in experiment is 5 crest sinusoidal modulation signals, and as shown in Figure 4, centre frequency is 40KHz, and peak-to-peak value is ± 10V, and in experiment, sample frequency is 1.6MHz.
Pick-up transducers response signal under structural health conditions and faulted condition, each array element in piezoelectric-array is in turn as driver, when one of them piezoelectric patches is as driver, other piezoelectric patches are then as sensor, therefore, the piezoelectricity linear array be made up of 9 piezoelectricity array elements obtains 9 × 8=72 transducing signal respectively at structural health conditions and faulted condition.
The sensor response signal gathered under structural health conditions is as reference signal, structure load after sensor response signal subtract each other with it obtain damage scattered signal, Fig. 5 comprises (a), (b), (c) 3 width figure, being followed successively by No. 0 piezoelectric patches is driver, the response signal of healthy structure when No. 1 piezoelectric patches is sensor, the response signal of damaged structure and damage scattered signal, damage scattered signal shown in figure (c) is because the existence damaged in structure causes, can see by damaging the damage scattered signal energy caused faint by figure (c), and it is less to damage the scattered signal energy caused, be aliasing in other signals.
The damage scattered signal of each excitation/sensing passage is θ ∈ [0 °, 180 °] in scope every 1 ° and r ∈ [0mm, 160mm] carry out corresponding time delay every 1mm in scope, obtain the damage scattered signal after the time delay of each excitation/sensing passage in each angle-distance.Time delay calculates according to following formula,
Δ t i ( r , θ ) = r - r 2 + ( i · d ) 2 - 2 · r · i · d · cos θ c
In above formula, i represents the piezoelectric patches sequence number as driver (emission process) or sensor (receiving course), i=0,1,2 ... 8, between adjacent array element, spacing d is 12mm, and the velocity of wave c of Lamb wave in glass fibre reinforced composion plate is 1.2km/s.Fig. 6 comprises (a) ~ (h) 8 width figure, represents No. 0 piezoelectric patches successively as driver, other piezoelectric patches as the damage scattered signal S of sensor 01~ S 08, at the schematic diagram that 0 ° of direction 10mm distance elapsed time postpones, the difference signal S of 0 ° of direction 10mm distance 01~ S 08time delay be: Δ t 01(r, θ)=0.007ms, Δ t 02(r, θ)=-0.003ms, Δ t 03(r, θ)=-0.013ms, Δ t 04(r, θ)=-0.023ms, Δ t 05(r, θ)=-0.033ms, Δ t 06(r, θ)=-0.043ms, Δ t 07(r, θ)=-0.053ms, Δ t 08(r, θ)=-0.063ms, in result of calculation, negative value represents and is moved to the left by signal, is moved right by signal on the occasion of expression, time delay is attached in damage scattered signal the damage scattered signal after namely obtaining the delay of respective angles-distance.
Each angle-carry out cumulative this angle of synthesis-apart from upper total composite signal apart from upper signal, Fig. 7 is the composite signal ceiling capacity corresponding diagram of each angle-distance correspondence.Then, in order to avoid the surveillance map after imaging is as spotting point-like, get the absolute value envelope postponing cumulative rear composite signal, and be planned to [0 to make the gray level of image, 1] between, be normalized each composite signal absolute value envelope, the amplitude that namely composite signal is often put obtains the relative magnitude of this point compared with the maximum amplitude of all signals, and Fig. 8 is normalization composite signal absolute value envelope diagram within the scope of corresponding 0 ° ~ 180 ° of ceiling capacity signal.Relatively all angles-apart from upper signal, the angle at the signal place that energy is stronger is the direction at damage place, then calculated the radius of damage position by the due in of the maximum composite signal of energy and this direction Lamb wave wave-velocity meter, thus finally determine the position at damage place.Within the scope of different scanning distance 0 ° ~ 180 °, the amplitude of normalization composite signal absolute value envelope is drawn on same figure according to its angle and obtains damage image, as shown in Figure 9.Coordinate in Fig. 9 represents the coordinate of monitored area, the normalization amplitude of this point in the pixel value respective signal of often, the gray scale of image from dark to bright corresponding energy from weak to strong.In the carbon fiber box section structure of near-field ultrasound phased array principle monitoring, load position is (60 °, 48mm), and compare with true loaded load position (60 °, 50mm), its angular error and distance error are (0 °, 2mm).
Above embodiment is only and technological thought of the present invention is described, can not limit protection scope of the present invention with this, and every technological thought proposed according to the present invention, any change that technical scheme basis is done, all falls within scope.

Claims (5)

1., based on a near-field phased array structure health monitoring method for piezoelectric-array, it is characterized in that, comprise the following steps:
(1) in structure to be monitored, arrange the piezoelectricity linear array be made up of M piezoelectric patches, M piezoelectric patches defines sequence number 0 ~ M-1 successively;
(2) under structural health conditions, Lamb wave narrow band signal is put on successively M piezoelectric patches in piezoelectricity linear array, when Lamb wave narrow band signal is put on a certain piezoelectric patches, this piezoelectric patches inspires pumping signal in the structure as driver, and all the other M-1 piezoelectric patches all receives the response signal propagated in structure respectively as sensor, 1 driver and 1 sensor are collectively referred to as 1 excitation-sensing passage, then obtain altogether the response signal of the individual excitation-sensing passage of M × (M-1);
(3) under On Damage State, step (2) is repeated;
(4) response signal of the individual excitation-sensing passage of M × (M-1) step (2) obtained is as reference signal, the response signal of the individual excitation-sensing passage of M × (M-1) step (3) obtained is subtracted each other with corresponding reference signal, obtains the damage scattered signal of the individual excitation-sensing passage of M × (M-1);
(5) in the monitoring range of piezoelectricity linear array near field, the damage scattered signal of each excitation-sensing passage within the scope of angle monitor at interval of Δ θ, and corresponding time delay is carried out at interval of during Δ ε in distance monitoring range, this time delay is called and angle-apart from upper time delay obtains the damage scattered signal after the time delay of each excitation-sensing passage in monitoring range in each angle-distance; Wherein, described angle monitor scope is [0 °, 180 °], and distance monitoring range is [0, L], described angle-be apart from upper time delay:
Δt i ( r , θ ) = r - r 2 + ( i · d ) 2 - 2 · r · i · d · cos θ c
In above formula, i represents the piezoelectric patches sequence number as driver or sensor, r is the distance between monitoring point and near-field phased array true origin, θ is the angle that near-field phased array true origin line and x-axis are arrived in monitoring point, c is the velocity of wave of Lamb wave, and d is the distance in piezoelectricity linear array between adjacent two piezoelectric patches;
(6) by the same angle of each excitation-sensing passage-carry out cumulative synthesis apart from the damage scattered signal after upper time delay, obtain each angle-apart from upper composite signal, and be normalized;
(7) more each angle-apart from upper normalization composite signal, the angle at the composite signal place of amplitude maximum is the direction at damage place, then calculated the radius of damage position by the due in of the composite signal of amplitude maximum and this direction Lamb wave wave-velocity meter, thus determine the position damaged.
2. a kind of near-field phased array structure health monitoring method based on piezoelectric-array according to claim 1, is characterized in that: described in step (1), the piezoelectric patches number M of piezoelectricity linear array is 9.
3. a kind of near-field phased array structure health monitoring method based on piezoelectric-array according to claim 1, is characterized in that: described in step (2), pumping signal is narrow band signal.
4. a kind of near-field phased array structure health monitoring method based on piezoelectric-array according to claim 1, it is characterized in that: in step (5), described angle intervals Δ θ is 1 °; Described L=3 λ, λ are the wavelength of Lamb wave, and distance interval delta ε is 1mm.
5. a kind of near-field phased array structure health monitoring method based on piezoelectric-array according to claim 1, is characterized in that: the propagation group velocity when velocity of wave c of Lamb wave described in step (5) refers to that Lamb wave only inspires A0 pattern in the structure.
CN201410697078.3A 2014-11-26 2014-11-26 Near field phased array structure health monitoring method based on piezoelectric array Pending CN104374830A (en)

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CN105527345A (en) * 2016-01-15 2016-04-27 北京工业大学 Defect positioning method for condensed laser sensor array based Lamb corrugated plate structure
CN105806949A (en) * 2016-03-07 2016-07-27 杭州华新检测技术股份有限公司 Correcting method for radial travel time in ultrasonic CT detection
CN104406901B (en) * 2014-11-07 2017-02-01 北京奥科瑞检测技术开发有限公司 Concrete internal steel bar corrosion monitoring sensor based on Lamb wave principle
CN106404911A (en) * 2016-11-15 2017-02-15 哈尔滨工业大学 True-time-delay single-mode Lamb wave phased array control system used for platy structure detection
CN110789731A (en) * 2019-10-11 2020-02-14 中国直升机设计研究所 System and method for monitoring health of helicopter tail boom structure based on Lamb wave
WO2023163653A3 (en) * 2022-02-25 2023-11-23 Agency For Science, Technology And Research Computer-implemented method for determining depth and location of localised thinning in plate structure

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104406901B (en) * 2014-11-07 2017-02-01 北京奥科瑞检测技术开发有限公司 Concrete internal steel bar corrosion monitoring sensor based on Lamb wave principle
CN105527345A (en) * 2016-01-15 2016-04-27 北京工业大学 Defect positioning method for condensed laser sensor array based Lamb corrugated plate structure
CN105527345B (en) * 2016-01-15 2018-12-25 北京工业大学 The defect positioning method of Lamb wave plate structure based on intensive laser sensor array
CN105806949A (en) * 2016-03-07 2016-07-27 杭州华新检测技术股份有限公司 Correcting method for radial travel time in ultrasonic CT detection
CN105806949B (en) * 2016-03-07 2019-04-02 杭州华新检测技术股份有限公司 A kind of ray traveltime bearing calibration in ultrasound computed tomography detection
CN106404911A (en) * 2016-11-15 2017-02-15 哈尔滨工业大学 True-time-delay single-mode Lamb wave phased array control system used for platy structure detection
CN106404911B (en) * 2016-11-15 2019-01-08 哈尔滨工业大学 True time delay single mode Lamb wave phased array system for plate structure detection
CN110789731A (en) * 2019-10-11 2020-02-14 中国直升机设计研究所 System and method for monitoring health of helicopter tail boom structure based on Lamb wave
WO2023163653A3 (en) * 2022-02-25 2023-11-23 Agency For Science, Technology And Research Computer-implemented method for determining depth and location of localised thinning in plate structure

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