CN110320276A - A kind of composite panel impact injury based on ultrasound and impact force quantitative approach - Google Patents
A kind of composite panel impact injury based on ultrasound and impact force quantitative approach Download PDFInfo
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- CN110320276A CN110320276A CN201910668180.3A CN201910668180A CN110320276A CN 110320276 A CN110320276 A CN 110320276A CN 201910668180 A CN201910668180 A CN 201910668180A CN 110320276 A CN110320276 A CN 110320276A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0052—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to impact
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
- G01N29/06—Visualisation of the interior, e.g. acoustic microscopy
- G01N29/0654—Imaging
- G01N29/069—Defect imaging, localisation and sizing using, e.g. time of flight diffraction [TOFD], synthetic aperture focusing technique [SAFT], Amplituden-Laufzeit-Ortskurven [ALOK] technique
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
- G01N29/07—Analysing solids by measuring propagation velocity or propagation time of acoustic waves
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/44—Processing the detected response signal, e.g. electronic circuits specially adapted therefor
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- Acoustics & Sound (AREA)
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- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
Abstract
The invention discloses a kind of composite panel impact injury based on ultrasound and impact force quantitative approach, comprising the following steps: prepared by the sampling of S1. composite panel impact injury；S2. data are obtained using phased-array ultrasonic scanning；S3. the three-dimensional volumetric images of ultrasound data are constructed；S4. the regional area based on echo amplitude identification of damage, qualitative deficiency size；S5. step S4 is repeated, the corresponding flaw size of each test specimen is obtained；S6. it constructs between impact force and impact injury size and is associated with mathematical model；S7. composite panel to be measured is scanned using phased-array ultrasonic, according to step S2~S4, three-dimensional reconstruction is carried out to scan data, quantify as impact injury based on given echo amplitude predetermined threshold, and to flaw size, then solve impact force；The present invention is based on ultrasonic waves to carry out defect recognition to composite panel, and can obtain the relationship of impact injury and impact force, is effectively performed and is conducive to that impact injury is quantitative and the solution of impact force.
Description
Technical field
The present invention relates to ultrasound examinations, more particularly to a kind of composite panel impact injury based on ultrasound and punching
Hit power quantitative approach.
Background technique
Composite board has a wide range of applications in aerospace and auto industry field, but since composite board is forming
Process it is complicated, the defects of being easy to generate interlayer de- glutinous, fiber cracking, to guarantee its safe handling, to composite board
It is very necessary that situation, which carries out detection,.
For now, ultrasonic scanning is a kind of mode of plate defect detection, still, current to be detected
In the process, typically just the defect situation of composite board itself is detected, still, for composite board impact injury and phase
The quantitative there is also this some technological gap of impact force is answered, is unfavorable for accurately obtaining composite panel impact injury and impact force
Quantitative information.
Summary of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of composite panels based on ultrasound to impact
Damage and impact force quantitative approach, based on ultrasonic wave to composite panel carry out defect recognition, and can obtain impact injury and
The relationship of impact force is effectively performed and is conducive to that impact injury is quantitative and the solution of impact force.
The purpose of the present invention is achieved through the following technical solutions: a kind of composite panel impact based on ultrasound
Damage and impact force quantitative approach, comprising the following steps:
S1. the sampling preparation of composite panel impact injury:
Prepare N number of composite panel test specimen, to each test specimen, applies different size of power F1,F2,…,FN, cause test specimen
Damage, wherein FiIndicate the power applied to i-th of composite panel test specimen, i=1,2 ..., N；
S2. ultrasonic wave sampling scanning obtains data:
Scanning is carried out to the composite panel test specimen that each is damaged using phased-array ultrasonic and saves crude sampling number
According to obtaining the data file for corresponding to each test specimen, be denoted as D1,D2,…,DN, wherein DiIndicate the corresponding data text of i-th of test specimen
Part, i=1,2 ..., N；
S3. the three-dimensional volumetric images of ultrasound data are constructed:
According to ultrasonic wave acoustic speed of propagation, sampling time interval, ultrasonic wave initial data sampled point is mapped to each and is answered
Condensation material intralamellar part physical location constructs the three-dimensional volumetric images that each test specimen corresponds to ultrasound data, is denoted as V1,V2,…,VN；Its
Middle ViIndicate that i-th of test specimen corresponds to the three-dimensional volumetric images of ultrasound data, i=1,2 ..., N；
Each of three-dimensional volumetric images mesh point indicates the echo amplitude of the physical locations, according to three-D volumes
Image tentatively identifies the regional area of each test specimen damage；
S4. for any composite panel test specimen, based on the regional area of echo amplitude identification of damage, qualitative deficiency ruler
It is very little:
For any composite panel three-dimensional volumetric images, enabling the regional area of damage is region of interest ROI, is searched
Echo amplitude maximum point position is as defect center point in ROI；
It is connected Mesh expansion using obtained defect center point as starting point to surrounding, until echo amplitude is reduced to predetermined threshold
Stop, determining the defect area of test specimen as impact injury quantitative information, qualitative deficiency size；
S5. step S4 is repeated, the corresponding flaw size of each test specimen is obtained, is denoted as S1,S2,…,SN, wherein SiIndicate i-th
The flaw size of a test specimen, i=1,2 ..., N；
S6. with F={ F1,F2,…,FNIt is independent variable, S={ S1,S2,…,SNIt is dependent variable, building impact force and impact
Association mathematical model between lesion size.
Obtain between impact force and impact injury size be associated with mathematical model after, further include composite panel to be measured impact
Damage and impact force solution procedure S7:
In practical applications, composite panel to be measured is scanned using phased-array ultrasonic, according to step S2~S4, to sweeping
It retouches data and carries out three-dimensional reconstruction, based on given echo amplitude predetermined threshold, identify defect area, and determine flaw size
Amount is used as impact injury, is associated with mathematical model between impact force and impact injury size obtained in recycle step S6, right
Impact force is solved.
In embodiments herein, the predetermined threshold is for the absolute intensity of echo amplitude or relative to defect center point
The percentage of amplitude；The data file of each test specimen includes ultrasonic wave acoustic speed of propagation, sampling time interval, ultrasonic wave original number
According to sampled point echo amplitude corresponding with each sampled point.
Preferably, association mathematical model described in step S6 includes:
(1) linear model:
S=a+bF；
(2) log-linear model:
Log (S)=a+blog (F)；
(3) multinomial model:
S=a+bF+cF2。
Wherein, a, b, c are fitting parameter, by by F={ F1,F2,…,FN, S={ S1,S2,…,SNBring into model
It is calculated.
The beneficial effects of the present invention are: carrying out impact injury to composite panel the present invention is based on ultrasonic scanning information
It is quantitative, and the relationship of impact injury and impact force can be obtained, it is effectively performed and is conducive to that impact injury is quantitative and impact force
It solves.
Detailed description of the invention
Fig. 1 is flow chart of the method for the present invention；
Fig. 2 is the regional area schematic diagram of three-dimensional volumetric images test specimen damage in embodiment.
Specific embodiment
Technical solution of the present invention is described in further detail with reference to the accompanying drawing, but protection scope of the present invention is not limited to
It is as described below.
As shown in Figure 1, a kind of composite panel impact injury based on ultrasound and impact force quantitative approach, including it is following
Step:
S1. the sampling preparation of composite panel impact injury:
Prepare N number of composite panel test specimen, to each test specimen, applies different size of power F1,F2,…,FN, cause test specimen
Damage, wherein FiIndicate the power applied to i-th of composite panel test specimen, i=1,2 ..., N；
S2. ultrasonic wave sampling scanning obtains data:
Scanning is carried out to the composite panel test specimen that each is damaged using phased-array ultrasonic and saves crude sampling number
According to obtaining the data file for corresponding to each test specimen, be denoted as D1,D2,…,DN, wherein DiIndicate the corresponding data text of i-th of test specimen
Part, i=1,2 ..., N；
S3. the three-dimensional volumetric images of ultrasound data are constructed:
According to ultrasonic wave acoustic speed of propagation, sampling time interval, ultrasonic wave initial data sampled point is mapped to each and is answered
Condensation material intralamellar part physical location constructs the three-dimensional volumetric images that each test specimen corresponds to ultrasound data, is denoted as V1,V2,…,VN；Its
Middle ViIndicate that i-th of test specimen corresponds to the three-dimensional volumetric images of ultrasound data, i=1,2 ..., N；
Each of three-dimensional volumetric images mesh point indicates the echo amplitude of the physical locations, according to three-D volumes
Image tentatively identifies the regional area of each test specimen damage；Specifically, as shown in Fig. 2, in three-dimensional volumetric images (in dotted line frame)
Darker regions, as tentatively identify obtain test specimen damage regional area.
S4. for any composite panel test specimen, based on the regional area of echo amplitude identification of damage, qualitative deficiency ruler
It is very little:
For any composite panel three-dimensional volumetric images, enabling the regional area of damage is region of interest ROI, is searched
Echo amplitude maximum point position is as defect center point in ROI；
It is connected Mesh expansion using obtained defect center point as starting point to surrounding, until echo amplitude is reduced to predetermined threshold
Stop, determining the defect area of test specimen as impact injury quantitative information, qualitative deficiency size；
This step can be realized by some canonical algorithms, such as region increases (Seeded region growing)
Algorithm and its variant；In this way, can determine a connected domain centered on maximum echo strength position, the three of connected domain
Dimension size is denoted as the size of impact injury defect.
S5. step S4 is repeated, the corresponding flaw size of each test specimen is obtained, is denoted as S1,S2,…,SN, wherein SiIndicate i-th
The flaw size of a test specimen, i=1,2 ..., N；
S6. with F={ F1,F2,…,FNIt is independent variable, S={ S1,S2,…,SNIt is dependent variable, building impact force and impact
Association mathematical model between lesion size.
Obtain between impact force and impact injury size be associated with mathematical model after, further include composite panel to be measured impact
Damage and impact force solution procedure S7:
In embodiments herein, the predetermined threshold is for the absolute intensity of echo amplitude or relative to defect center point
The percentage of amplitude；The data file of each test specimen includes ultrasonic wave acoustic speed of propagation, sampling time interval, ultrasonic wave original number
According to sampled point echo amplitude corresponding with each sampled point.
In practical applications, composite panel to be measured is scanned using phased-array ultrasonic, according to step S2~S4, to sweeping
It retouches data and carries out three-dimensional reconstruction, based on given echo amplitude predetermined threshold, identify defect area, and determine flaw size
Amount is used as impact injury, is associated with mathematical model between impact force and impact injury size obtained in recycle step S6, right
Impact force is solved.
Preferably, association mathematical model described in step S6 includes:
(1) linear model:
S=a+bF；
(2) log-linear model:
Log (S)=a+blog (F)；
(3) multinomial model:
S=a+bF+cF2。
Wherein, a, b, c are fitting parameter, by by F={ F1,F2,…,FN, S={ S1,S2,…,SNBring into model
It is calculated: specific, by (F1,S1)、(F2,S2)、…、(FN,SN) bring any model (association mathematical model) into respectively
Obtain the corresponding fitting parameter of the model.
The above is a preferred embodiment of the present invention, it should be understood that the present invention is not limited to shape described herein
Formula should not be viewed as excluding other embodiments, and can be used for other combinations, modification and environment, and can be in this paper institute
It states in contemplated scope, modifications can be made through the above teachings or related fields of technology or knowledge.And what those skilled in the art were carried out
Modifications and changes do not depart from the spirit and scope of the present invention, then all should be within the scope of protection of the appended claims of the present invention.
Claims (5)
1. a kind of composite panel impact injury based on ultrasound and impact force quantitative approach, it is characterised in that: including following
Step:
S1. the sampling preparation of composite panel impact injury:
Prepare N number of composite panel test specimen, to each test specimen, applies different size of power F1,F2,…,FN, cause the damage of test specimen
Hurt, wherein FiIndicate the power applied to i-th of composite panel test specimen, i=1,2 ..., N；
S2. data are obtained using phased-array ultrasonic scanning:
Scanning is carried out to the composite panel test specimen that each is damaged using phased-array ultrasonic and saves original sampling data, is obtained
To the data file of each test specimen of correspondence, it is denoted as D1,D2,…,DN, wherein DiIndicate the corresponding data file of i-th of test specimen, i=
1,2,…,N；
S3. the three-dimensional volumetric images of ultrasound data are constructed:
According to ultrasonic wave acoustic speed of propagation, sampling time interval, ultrasonic wave initial data sampled point is mapped to each composite wood
Flitch internal physical position constructs the three-dimensional volumetric images that each test specimen corresponds to ultrasound data, is denoted as V1,V2,…,VN；Wherein Vi
Indicate that i-th of test specimen corresponds to the three-dimensional volumetric images of ultrasound data, i=1,2 ..., N；
Each of three-dimensional volumetric images mesh point indicates the echo amplitude of the physical locations, according to three-dimensional volumetric images
Tentatively identify the regional area of each test specimen damage；
S4. for any composite panel test specimen, based on the regional area of echo amplitude identification of damage, qualitative deficiency size:
For any composite panel three-dimensional volumetric images, enabling the regional area of damage is region of interest ROI, is searched in ROI
Echo amplitude maximum point position is as defect center point；
It is connected Mesh expansion using obtained defect center point as starting point to surrounding, stops until echo amplitude is reduced to predetermined threshold
Only, the defect area of test specimen, qualitative deficiency size are determined；
S5. step S4 is repeated, the corresponding flaw size of each test specimen is obtained, is denoted as S1,S2,…,SN, wherein SiIndicate i-th of examination
The flaw size of part is as impact injury quantitative information, i=1,2 ..., N；
S6. with F={ F1,F2,…,FNIt is independent variable, S={ S1,S2,…,SNIt is dependent variable, construct impact force and impact injury
Association mathematical model between size.
2. a kind of composite panel impact injury based on ultrasound according to claim 1 and impact force quantitative approach,
It is characterized by: obtain between impact force and impact injury size be associated with mathematical model after, further include composite material to be measured
Plate impact injury and impact force solution procedure S7:
In practical applications, composite panel to be measured is scanned using phased-array ultrasonic, according to step S2~S4, to scanning number
According to three-dimensional reconstruction is carried out, based on given echo amplitude predetermined threshold, defect area is identified, and quantitative work is carried out to flaw size
For impact injury, it is associated with mathematical model between impact force and impact injury size obtained in recycle step S6, to impact
Power is solved.
3. a kind of composite panel impact injury based on ultrasound according to claim 1 and impact force quantitative approach,
It is characterized by: the predetermined threshold is the absolute intensity of echo amplitude or the percentage relative to defect center point amplitude.
4. a kind of composite panel impact injury based on ultrasound according to claim 1 and impact force quantitative approach,
It is characterized by: the data file of each test specimen includes ultrasonic wave acoustic speed of propagation, sampling time interval, ultrasonic wave initial data
Sampled point echo amplitude corresponding with each sampled point.
5. a kind of composite panel impact injury based on ultrasound according to claim 1 and impact force quantitative approach,
It is characterized by: association mathematical model described in step S6 includes:
(1) linear model:
S=a+bF；
(2) log-linear model:
Log (S)=a+blog (F)；
(3) multinomial model:
S=a+bF+cF2。
Wherein, a, b, c are fitting parameter, by by F={ F1,F2,…,FN, S={ S1,S2,…,SNBring into model and calculate
It obtains.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0701147A2 (en) * | 1994-09-08 | 1996-03-13 | Sonatech, Inc. | Method and apparatus for determining soil strength from Doppler-shifted acoustic signatures |
| CN102288684A (en) * | 2011-05-04 | 2011-12-21 | 北京理工大学 | Ultrasonic guided wave line scanning imaging method for debonding defect of carbon fiber reinforced epoxy resin-based composite plate |
| CN104237032A (en) * | 2014-10-10 | 2014-12-24 | 绍兴明透装甲材料有限责任公司 | Bullet impulse online detector |
-
2019
- 2019-07-23 CN CN201910668180.3A patent/CN110320276A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0701147A2 (en) * | 1994-09-08 | 1996-03-13 | Sonatech, Inc. | Method and apparatus for determining soil strength from Doppler-shifted acoustic signatures |
| CN102288684A (en) * | 2011-05-04 | 2011-12-21 | 北京理工大学 | Ultrasonic guided wave line scanning imaging method for debonding defect of carbon fiber reinforced epoxy resin-based composite plate |
| CN104237032A (en) * | 2014-10-10 | 2014-12-24 | 绍兴明透装甲材料有限责任公司 | Bullet impulse online detector |
Non-Patent Citations (2)
| Title |
|---|
| 何艳斌: "航空复合材料典型结构低能量冲击损伤及动力响应研究", 《中国博士学位论文全文数据库 工程科技Ⅰ辑》 * |
| 李海涛 等: "橡胶隔振器冲击特性的试验研究", 《噪声与振动控制》 * |
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Application publication date: 20191011 |