CN108333043A - A kind of composite repair structural crack method of real-time based on FBG sensor - Google Patents
A kind of composite repair structural crack method of real-time based on FBG sensor Download PDFInfo
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- CN108333043A CN108333043A CN201711339987.XA CN201711339987A CN108333043A CN 108333043 A CN108333043 A CN 108333043A CN 201711339987 A CN201711339987 A CN 201711339987A CN 108333043 A CN108333043 A CN 108333043A
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- 239000002131 composite material Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 29
- 230000008439 repair process Effects 0.000 title claims abstract description 24
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 16
- 230000008859 change Effects 0.000 claims abstract description 13
- 238000002474 experimental method Methods 0.000 claims abstract description 9
- 238000004088 simulation Methods 0.000 claims abstract description 8
- 238000012360 testing method Methods 0.000 claims abstract description 7
- 238000012544 monitoring process Methods 0.000 claims description 26
- 208000037656 Respiratory Sounds Diseases 0.000 claims description 21
- 238000009826 distribution Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 230000004044 response Effects 0.000 claims description 4
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 239000000835 fiber Substances 0.000 abstract description 9
- 230000008901 benefit Effects 0.000 abstract description 4
- 230000007797 corrosion Effects 0.000 abstract description 3
- 238000005260 corrosion Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 2
- 230000035945 sensitivity Effects 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000036541 health Effects 0.000 description 3
- 239000000956 alloy Substances 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 238000001228 spectrum Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 238000013524 data verification Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000013401 experimental design Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000003862 health status Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000010197 meta-analysis Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000000985 reflectance spectrum Methods 0.000 description 1
- 230000003595 spectral effect Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/006—Crack, flaws, fracture or rupture
- G01N2203/0062—Crack or flaws
- G01N2203/0066—Propagation of crack
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/0641—Indicating or recording means; Sensing means using optical, X-ray, ultraviolet, infrared or similar detectors
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention relates to a kind of composite repair structural crack method of real-time based on FBG sensor, includes the following steps, step 1：Selection experiment part；Step 2：Structure mechanics analysis, the stressing conditions at analysis sample coupon both ends are carried out to sample coupon；Step 3：According to FEM Numerical Simulation on aluminium alloy sheet (2A12 thin plates) paving FBG sensor；Step 4：The aluminium alloy sheet for posting FBG sensor after composite repair is mounted on fatigue tester and carries out fatigue crack propagation test；Step 5：It analyzes crack tip and wavelength situation of change after FBG sensor is installed；Step 6：Repeat step 15.The present invention is monitored in real time with On Crack Propagation process, more intuitive effective compared with other methods.In addition the fiber Bragg grating sensor that the present invention uses has many advantages, such as that small, high sensitivity, electromagnetism interference, corrosion-resistant, reliability is high and composite material good compatibility.
Description
Technical field
The invention belongs to structural health monitoring technology fields, and in particular to a kind of composite material based on FBG sensor is repaiied
Mend structural crack method of real-time.
Background technology
The use of aluminum alloy materials is very extensive in aeronautic structure metal material, the cracked carry out composite material of aluminium alloy
After repairing, crackle there is no disappearing, ask by the monitoring for crack propagation after aluminium alloy damaged structure composite repair at present
Topic, still without a kind of very ripe monitoring method.Once it is cracked to repair structure, if cannot carry out effectively monitoring meeting
Cause extremely serious consequence.
The Strain Distribution at composite repair structural crack tip has apparent uneven characteristic, when FBG sensor exists
When on its axial length direction by heterogeneous strain, the wavelength of reflectance spectrum can change.And strain gradient is different, light
Spectrum wavelength variation degree is different.Composite repair structure position to be monitored is simplified, and carries out finite element analysis and obtains difference
Strain Distribution under crack length determines therefrom that the layout of sensor, arranges that several sensors, extraction are anti-along direction of crack propagation
The characteristic parameter for penetrating spectrum change establishes wavelength change and the quantitative relationship of crack extending length, to realize in crack propagation
When crackle real-time monitoring.
Structural health monitoring technology is and traditional as a kind of technology by intelligence sensor monitoring of structures health status
The function that real time on-line monitoring may be implemented is compared in non-destructive testing.
Invention content
In view of the problems of the existing technology, the present invention propose a kind of function that real time on-line monitoring may be implemented based on
The composite repair structural crack method of real-time of FBG sensor.
The present invention is a kind of composite repair structural crack method of real-time based on FBG sensor, this crackle
Propagation direction it is vertical with the direction of principal stress.
A kind of composite repair structural crack method of real-time based on FBG sensor of the present invention, steps are as follows：
Step 1：Selection experiment part prefabricated centre bore and is split in sample coupon central area in the prefabricated predetermined length in hole edge both sides
Line；
Step 2：Structure mechanics analysis carried out to sample coupon, the stressing conditions at analysis sample coupon both ends, and to sample coupon into
Row Finite Element Simulation Analysis determines the stress distribution situation of the crack tip region under the crack propagation to specific length；
Step 3：According to FEM Numerical Simulation on aluminium alloy sheet (2A12 thin plates) paving FBG sensor, specially
With paving FBG sensor in direction of crack propagation vertical direction, and composite panels paving solidification is carried out；
Step 4：It is enterprising that the aluminium alloy sheet for posting FBG sensor after composite repair is mounted on fatigue tester
Row fatigue crack propagation test acquires the original wavelength of FBG sensor as initial signal before fatigue tester load；
With the progress of fatigue loading, fatigue crack starts to extend, and observes crack propagation feelings by crack propagation instrument at this time
Condition, and crack extending length when recording different cycle-indexes, while the letter of FBG sensor acquisition is recorded by software in real time
Number；
Step 5：After completing experiment, the signal data of FBG sensor acquisition is handled, and is measured with crack propagation instrument
Crack extending length compared, analysis crack tip installation FBG sensor after wavelength situation of change；
Step 6：Step 1-5 is repeated, and is analyzed for the collected response signal of FBG sensor under various sample,
The method established in verification step 5；
Step 7：Realize the real-time monitoring of crackle；During actual monitoring, according to different location FBG sensor wavelength change
Situation is different, differentiates whether crackle expands to the sensing station, realizes the function of real-time monitoring crack spread scenarios.
Wherein, in step 1 it is described " Selection experiment part, and sample coupon is designed, it is pre- in sample coupon central area
Centre bore processed and in the prefabricated predetermined length crackle in hole edge both sides ", way is as follows：Aviation is selected often to use plank 2A12 aluminium alloy plates
For thin plate as test material, experimental design is small template, and specification 350mm*80mm*3mm sprouts in order to cracked faster
The phenomenon that raw and extension, in the centre bore of the centrally disposed certain 0.2mm~0.5mm diameters of plate, and using wire cutting
Crackle 15mm~25mm of the mode in the prefabricated certain length in centre bore both sides.
The method of real-time can extend and repair structure again by composite repair structural crack under loading conditions
Validity and sensor wavelength can mutate when passing through FBG sensor according to crackle when stand under load characteristic, become by wavelength
Change value carrys out monitoring crack extension length.Its major advantage is as follows：(1) since fiber Bragg grating sensor is with light, electric
It the advantages that insulation, corrosion-resistant and composite material compatibility, is used widely in monitoring structural health conditions field.We
The crackle of composite repair Al-alloy parts is monitored using fiber Bragg grating sensor, passes through reflectance spectrum center
Drift value monitoring crack expanding location/length of wavelength.Compared with other are to crackle monitoring method, which has better
Application prospect；(2) proposition is a kind of is changed based on FBG sensor reflection wavelength come the method for monitoring crack length/position, this side
Method can in real time be monitored with On Crack Propagation process, be a kind of more intuitively having based on optics itself compared with other methods
The physical monitoring method of effect.In addition fiber bragg grating (Fiber Bragg grating, the FBG) sensing that the present invention uses
Utensil has the advantages that small, high sensitivity, electromagnetism interference, corrosion-resistant, reliability is high and composite material good compatibility, extensively
It is general to be applied to the fields such as aerospace, naval vessel industry, ocean platform, civil engineering and engineering in medicine.
Description of the drawings
Fig. 1 is the method for the invention flow chart；
Fig. 2 is testpieces specification schematic diagram in the embodiment of the present invention；
Fig. 3 is fibre optical sensor arrangement schematic diagram in the embodiment of the present invention；
Fig. 4 is paving FBG sensor repair piece schematic diagram；
Fig. 5 is optical fiber wavelength change when crackle passes through fiber position.
Specific implementation mode
With reference to the accompanying drawings of the specification and embodiment present invention is further described in detail.
Embodiment：
The present invention is a kind of Method for Cracks based on fiber Bragg grating sensor spectral signature, flow such as Fig. 1
It is shown, it is as follows：
Step 1：Selection experiment part, and sample coupon is designed, specification 350mm*80mm*3mm, material 2A12
Aluminium alloy plate thin plate, the phenomenon that for faster cracked germinating with extension, in the prefabricated 0.2mm centre bores in plate central area,
And the prefabricated predetermined length crackle in hole edge both sides be 20mm, by the way of wire cutting, as shown in Figure 2；
Step 2：Structure mechanics analysis carried out to sample coupon, the stressing conditions at analysis sample coupon both ends, and to sample coupon into
Row Finite Element Simulation Analysis determines the stress distribution situation of the crack tip region under the crack propagation to specific length；Limited
It needs to determine that extraneous loading environment, such as relevant parameters such as load type and sample coupon material, elasticity modulus are clearly supervised before meta analysis
The crack length etc. of survey；According to fixed experimental condition, Finite Element Simulation Analysis is carried out using ANSYS softwares to sample coupon,
Obtain crack propagation to crack tip enclosure region when different length stress value；
Step 3：According to FEM Numerical Simulation on aluminium alloy sheet paving FBG sensor, FBG sensor paving direction
It is vertical with direction of crack propagation, and composite panels paving solidification is carried out, FBG sensor is placed in composite panels and aluminium
Between alloy, this example selects 4 FBG sensors, and 4#FBG sensors and centre bore away from arranging outward successively for 15mm, 3#, 2#, 1#
Row, spacing 5mm, as shown in Figure 3；
Step 4：The aluminium alloy sheet for posting FBG sensor after the above progress composite repair is mounted on fatigue to try
It tests and carries out fatigue crack propagation test on machine, before fatigue tester load, acquire the signal of FBG sensor as initial letter
Number；With the progress of fatigue loading, fatigue crack starts to extend, and observes crack propagation situation by crack propagation instrument at this time, and
Crack extending length when different cycle-indexes is recorded, while recording the wavelength of FBG sensor acquisition in real time by software；
Step 5：After completing experiment, the wavelength of FBG sensor acquisition is handled；Main Analysis handles FBG sensor
Collected wavelength Value Data, and the crack extending length measured with crack propagation instrument is compared, analysis crack tip is just
Wavelength situation of change after FBG sensor；
Step 6：Step 1-5 is repeated, and is analyzed for the collected response signal of FBG sensor under various sample,
The method established in verification step 5；
Step 7：Realize the real-time monitoring of crackle；Determine crack tip just by FBG sensor position according to step 1-6
When, FBG sensor wavelength change threshold value, and by software, during actual monitoring, it is 5nm that corresponding wavelength threshold, which is arranged,
It is different according to different location FBG sensor wavelength change situation, differentiate whether crackle expands to the sensing station, realizes real-time
The function of monitoring crack spread scenarios, when crackle is by FBG sensor position, sensor wavelength value be original wavelength+
5nm。
Present case supervises the crackle of composite repair structure according to above-mentioned fiber Bragg grating sensor in real time
It surveys：The repair piece of paving FBG sensor is prepared using above-mentioned testpieces preparation process, as shown in Figure 4.
Determine cycle-index when crackle passes through fiber position when load, and cycle-index and cycle-index when is corresponding
Wavelength value corresponded to, only illustrate by taking 3# in Fig. 4 as an example, when crack tip just passes through FBG sensor, wavelength occur
Changing value is original wavelength+5nm, as shown in Figure 5.
The present invention can realize real time on-line monitoring of the technique for aircraft composite repairing aluminium alloy structure in stand under load, with experiment
Based on data, the relational model of crackle and FBG sensor response signal characteristic parameter is established by theory analysis, and passes through reality
Test the correctness of data verification method.The on-line monitoring that this method can be used for after aircraft repairing, can be assessed using FBG sensor
The validity of composite panels under loaded state ensures Airplane Structure Durability, damage tolerance quality and safe to use, use
The important means in service life.
Claims (4)
1. a kind of composite repair structural crack method of real-time based on FBG sensor, it is characterised in that including as follows
Step：
Step 1：Selection experiment part, the prefabricated centre bore and in the prefabricated predetermined crackle in hole edge both sides in sample coupon central area；
Step 2：Structure mechanics analysis, the stressing conditions at analysis sample coupon both ends are carried out to sample coupon, and are had to sample coupon
The first simulation analysis of limit, determines the stress distribution situation of the crack tip region under the crack propagation to specific length；
Step 3：According to FEM Numerical Simulation on aluminium alloy sheet paving FBG sensor, specially and direction of crack propagation
Paving FBG sensor in vertical direction, and carry out composite panels paving solidification；
Step 4：By the aluminium alloy sheet for posting FBG sensor after composite repair be mounted on fatigue tester on carry out it is tired
Labor crack expansion test acquires the original wavelength of FBG sensor as initial signal before fatigue tester load；
With the progress of fatigue loading, fatigue crack starts to extend, and observes crack propagation situation by crack propagation instrument at this time, and
Crack extending length when different cycle-indexes is recorded, while recording the signal of FBG sensor acquisition in real time by software；
Step 5：After completing experiment, the signal data of FBG sensor acquisition is handled, and is split with what crack propagation instrument measured
Line extension length is compared, wavelength situation of change after analysis crack tip installation FBG sensor；
Step 6：Step 1-5 is repeated, and is analyzed for the collected response signal of FBG sensor under various sample, is verified
The method established in step 5；
Step 7：Realize the real-time monitoring of crackle；
It is different according to different location FBG sensor wavelength change situation during actual monitoring, differentiate whether crackle expands to this
Sensing station realizes the function of real-time monitoring crack spread scenarios.
2. the composite repair structural crack method of real-time according to claim 1 based on FBG sensor, special
Sign is：Prefabricated centre bore aperture is 0.2mm~0.5mm in step 1.
3. the composite repair structural crack method of real-time according to claim 1 based on FBG sensor, special
Sign is：Precrack length is 15mm~25mm in step 1.
4. the composite repair structural crack method of real-time according to claim 1 based on FBG sensor, special
Sign is：Aluminum alloy thin material is 2A12 in step 2.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711339987.XA CN108333043A (en) | 2017-12-14 | 2017-12-14 | A kind of composite repair structural crack method of real-time based on FBG sensor |
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| CN201711339987.XA CN108333043A (en) | 2017-12-14 | 2017-12-14 | A kind of composite repair structural crack method of real-time based on FBG sensor |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109916741A (en) * | 2019-01-18 | 2019-06-21 | 昆明理工大学 | A kind of composite impact crack detection algorithm based on optical fiber grating sensing |
| CN110807250A (en) * | 2019-10-22 | 2020-02-18 | 扬州大学 | Crane health monitoring method based on sensitivity vector compromise and competition relationship |
| CN113514545A (en) * | 2021-04-14 | 2021-10-19 | 芜湖创联新材料科技有限公司 | Aircraft composite structure health monitoring system |
| CN114923420A (en) * | 2022-05-18 | 2022-08-19 | 中南大学 | Crack diagnosis method and system based on fiber Bragg grating and storage medium |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105842345A (en) * | 2016-04-15 | 2016-08-10 | 重庆邮电大学 | Method for positioning structural multiple cracks through fiber Bragg grating sensor network |
| CN106596255A (en) * | 2016-11-18 | 2017-04-26 | 北京航空航天大学 | Hole-edge crack diagnosis method based on optical fiber spectrum image analysis |
-
2017
- 2017-12-14 CN CN201711339987.XA patent/CN108333043A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105842345A (en) * | 2016-04-15 | 2016-08-10 | 重庆邮电大学 | Method for positioning structural multiple cracks through fiber Bragg grating sensor network |
| CN106596255A (en) * | 2016-11-18 | 2017-04-26 | 北京航空航天大学 | Hole-edge crack diagnosis method based on optical fiber spectrum image analysis |
Non-Patent Citations (1)
| Title |
|---|
| 袁慎芳 等: "基于FBG反射谱特征的修补结构裂纹扩展监测", 《光谱学与光谱分析》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109916741A (en) * | 2019-01-18 | 2019-06-21 | 昆明理工大学 | A kind of composite impact crack detection algorithm based on optical fiber grating sensing |
| CN110807250A (en) * | 2019-10-22 | 2020-02-18 | 扬州大学 | Crane health monitoring method based on sensitivity vector compromise and competition relationship |
| CN110807250B (en) * | 2019-10-22 | 2023-08-22 | 扬州大学 | Crane health monitoring method based on sensitivity vector compromise and competition relationship |
| CN113514545A (en) * | 2021-04-14 | 2021-10-19 | 芜湖创联新材料科技有限公司 | Aircraft composite structure health monitoring system |
| CN114923420A (en) * | 2022-05-18 | 2022-08-19 | 中南大学 | Crack diagnosis method and system based on fiber Bragg grating and storage medium |
| CN114923420B (en) * | 2022-05-18 | 2022-12-27 | 中南大学 | Crack diagnosis method and system based on fiber Bragg grating and storage medium |
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Application publication date: 20180727 |