CN108007604A - Array fibre surveys metal/composite material interlayer temperature and the method and device of strain - Google Patents
Array fibre surveys metal/composite material interlayer temperature and the method and device of strain Download PDFInfo
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- CN108007604A CN108007604A CN201711386098.9A CN201711386098A CN108007604A CN 108007604 A CN108007604 A CN 108007604A CN 201711386098 A CN201711386098 A CN 201711386098A CN 108007604 A CN108007604 A CN 108007604A
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- 239000007769 metal material Substances 0.000 title claims abstract description 65
- 239000002131 composite material Substances 0.000 title claims abstract description 42
- 239000000835 fiber Substances 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 title claims abstract description 32
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 26
- 239000011229 interlayer Substances 0.000 title claims abstract description 25
- 239000013307 optical fiber Substances 0.000 claims abstract description 31
- 239000000463 material Substances 0.000 claims abstract description 21
- 238000002474 experimental method Methods 0.000 claims abstract description 6
- 238000005520 cutting process Methods 0.000 claims description 76
- 239000000758 substrate Substances 0.000 claims description 40
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 15
- 239000004917 carbon fiber Substances 0.000 claims description 15
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 14
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 12
- 230000007704 transition Effects 0.000 claims description 12
- 229910000838 Al alloy Inorganic materials 0.000 claims description 9
- 230000035945 sensitivity Effects 0.000 claims description 9
- -1 capillary Substances 0.000 claims description 6
- 229910045601 alloy Inorganic materials 0.000 claims description 5
- 239000000956 alloy Substances 0.000 claims description 5
- 239000004809 Teflon Substances 0.000 claims description 4
- 229920006362 Teflon® Polymers 0.000 claims description 4
- 230000000717 retained effect Effects 0.000 claims description 4
- 239000010935 stainless steel Substances 0.000 claims description 4
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 238000007731 hot pressing Methods 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 238000005553 drilling Methods 0.000 abstract description 16
- 230000008569 process Effects 0.000 abstract description 14
- 238000012544 monitoring process Methods 0.000 abstract description 9
- 238000005259 measurement Methods 0.000 abstract description 8
- 230000008859 change Effects 0.000 abstract description 4
- 238000011165 process development Methods 0.000 abstract description 4
- 238000011160 research Methods 0.000 abstract description 4
- 238000012827 research and development Methods 0.000 abstract description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 10
- 229910052799 carbon Inorganic materials 0.000 description 9
- XLOMVQKBTHCTTD-UHFFFAOYSA-N Zinc monoxide Chemical compound [Zn]=O XLOMVQKBTHCTTD-UHFFFAOYSA-N 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 6
- 239000002905 metal composite material Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000004918 carbon fiber reinforced polymer Substances 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 4
- 230000036541 health Effects 0.000 description 4
- 238000003475 lamination Methods 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 3
- 239000002648 laminated material Substances 0.000 description 3
- 239000010410 layer Substances 0.000 description 3
- 230000003287 optical effect Effects 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 239000011787 zinc oxide Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- VYFYYTLLBUKUHU-UHFFFAOYSA-N dopamine Chemical compound NCCC1=CC=C(O)C(O)=C1 VYFYYTLLBUKUHU-UHFFFAOYSA-N 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 239000002135 nanosheet Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 229960003638 dopamine Drugs 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005538 encapsulation Methods 0.000 description 1
- 230000009477 glass transition Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 229910021389 graphene Inorganic materials 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
- G01K11/32—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using changes in transmittance, scattering or luminescence in optical fibres
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
A kind of array fibre disclosed by the invention surveys metal/composite material interlayer temperature and the method and device of strain, it respectively can measure metal/composite material interlayer temperature and strain by the thermometric section and survey strain section of optical fiber in drilling is tested；Wherein, thermometric section will not be extruded by the protection of capillary, can keep free state, therefore can accurately measure the temperature change in drilling experiment；The temperature of thermometric section can be also used for compensating the temperature for surveying strain section, to eliminate temperature influence, obtain accurate strain value.It the composite can be widely applied to process monitoring and the measurement of aerospace, the new material of traffic and transport field related components, new product, the scientific research of new process and research and development.
Description
Technical field
The present invention relates to the health monitoring of metal/composite material lamination and Distributed Optical Fiber Sensing Techniques field, and in particular to
A kind of array fibre surveys metal/composite material interlayer temperature and the method and device of strain, can be widely applied to aerospace, hands over
The new materials of logical transport field related components, new product, process monitoring and the measurement of the scientific research of new process and research and development.
Background technology
Carbon fibre reinforced composite (Carbon fiber reinforced polymers, abbreviation CFRP) has very
High specific strength and specific modulus, and its designability is strong, anti-fatigue performance is good；Metal material, as titanium alloy also has higher ratio
Intensity, while also have the advantages that calorific intensity is high, corrosion stability is good, toughness is high, aboundresources.Based on above performance, metal material/
Composite laminate construction is widely used in aerospace field, can significantly mitigate structural member weight, improves structural reliability,
An important factor for being also considered as weighing a national scientific and technological level at the same time.
The module laminated body for the performance difference that carbon fibre composite is formed with metal material should in aircraft wing and tail vane
With extensive, largely riveting or bolt apertures are needed in module laminated body assembling process.In these aeronautical products assemble drilling, most preferably
Technique be on carbon fibre composite and metal material module laminated body while process required riveting or bolt apertures, this
It is to ensure that the main means of laminated material component product bonding strength, rigidity and security.Yet with carbon fibre composite
Interlayer structure feature and the difference of two kinds of material properties are huge, and drilling quality is difficult to ensure that and drilling process tool wear is acute
It is strong.It is exactly to require in particular with one of the development of aircraft flexible assembly technology and Digitized Manufacturing Technology, its key technology
Using a procedure, two kinds of highly-efficient processing carbon fibre composite and titanium alloy (aluminium alloy) are entirely different at the same time in assembling process
The difficult-to-machine material of property.Meanwhile metal material/composite laminate construction, such as space shuttle, delivers during military service
Rocket etc. in long-term flight course, can because fatigue of materials aging, adverse circumstances of corrosion and surrounding etc. it is unfavorable because
Element, continuous cumulative damage, or even the serious burst accident such as air crash can be caused, cause irremediable loss.Therefore need
The online damage check of in-service metal material/composite laminate construction and health monitoring are established, to extend the clothes of material structure
The service life is used as a servant, prevents material structure from catastrophic breaking-up occurs.It is bulky since space shuttle, carrier rocket etc. are complicated,
Need to use substantial amounts of sensor at the same time, and there is high requirement to sensing station and embedded mode etc..
Metal material/composite laminate construction is difficult-to-machine material, and boring procedure easily produces layering, tear, chipping
And the defects of burr, become the potential danger of metal material/composite structure service phase, in aircraft assembling because with layering damage
The component that wound is related and is refused is up to 60%.But the interlayer inside fibre reinforced composites occurs for lamination defect, is lacked with metal
Fall into compared to increasingly complex, when being layered smaller or occur when deeper internal, it is difficult to observe and identify.More generally acknowledged knot at present
By being that the increase of axial force will cause the lamination defect aggravation that drills, and strain and a kind of table on material is acted on as drill thrust
Existing, it can more embody influence of the drill thrust to material in the dynamic change of boring procedure.It is of special importance that drilling is semiclosed
Processing, the drilling heat that working angles produce is not easy to spread out of in time, especially in drilling CFRP- titanium alloy laminated plates, since titanium closes
The temperature of very low titanium alloy layer when causing drilling titanium alloy layer of the thermal conductivity of gold is very high, so that CFRP structure changes,
And the temperature of CFRP is no more than 120 DEG C.When temperature exceedes the glass transition temperature of resin matrix, the mechanical property of material
Steps decline is presented, causes material failure in process.Therefore, the temperature of On-line sampling system boring procedure, to drilling
Quality, which is controlled, seems particularly important and urgent.
The public technology of metal material/composite lay interlayer temperature and strain monitoring related fields is not yet found at present
Scheme, and the public technology scheme in terms of carbon fibre composite be concentrated mainly on the application and preparation of carbon fibre composite with
Special apparatus for working etc..Such as the Chinese patent document that disclosure of the invention number is 103496734B《A kind of Zinc oxide nano sheet ball/
The preparation method and applications of foamy graphite alkene composite material》It is compound to disclose a kind of Zinc oxide nano sheet ball/foamy graphite alkene
The preparation method of material, sensitivity is low when solving existing zinc oxide/graphene composite material applied to dopamine detection and detects
The higher technical problem of limit.Utility Model Publication No. is the Chinese patent document of 205091191U《One kind improves composite material power
Learn the detection fixture of fatigue behaviour》Be related to a kind of detection fixture for improving Compound Material Engineering fatigue behaviour, by the fixture and
The stability of test data can be further ensured that by the method for the fixture reinforcing material detection intensity.Utility Model Publication No. is
The Chinese patent document of 205183873U《Cutter for the laminated material Drilling operation of carbon fibre composite aluminium alloy》It is public
A kind of knife of the laminated material Drilling operation for carbon fibre composite aluminium alloy has been driven, can effectively reduce carbon fiber composite
There is the defects of material burn, layering, burr, tear in the bed of material.
Fibre optical sensor has the features such as small, light weight, electromagnetism interference, and current more and more scholars pass optical fiber
Sensor is embedded in the laminate structures of composite material, the health monitoring being used for.Optical fiber is that fibre core and overlay form outside diameter as 125
μm -9 μm of cylindrical filament.But due to fibre optical sensor pair at the same time temperature and strain sensitive, in practical engineering application, how
Optical fiber is subjected to embedment and is encapsulated into composite material, realizes temperature and the independent measurement always fibre optical sensor of strain for compound
Material structure health monitoring focus of attention.
Disclosure of the invention number is the Chinese patent document of 103076110B《Optical fibre raster package structure, temperature sensor and envelope
Dress method》Although describing the encapsulation to fiber grating, fiber grating body fragility and temperature strain cross sensitivity are overcome
Problem.But unresolved sensor on a large scale this to distribution type fiber-optic is packaged the temperature that need to be faced and intersects spirit with what is strained
Sensitivity problem.
Therefore, the prior art needs further development and improves.
The content of the invention
It is an object of the present invention to disclosing a kind of array fibre surveys metal/composite material interlayer temperature and the method for strain
And device, it can realize the accurate measurement to metal/composite material lamination interlayer temperature and strain.
Array fibre disclosed by the invention surveys metal/composite material interlayer temperature and the method for strain, comprises the following steps：
The metal material cutting substrate of the parallel cutting with predetermined array quantity is processed in alloy sheets；
The optical fiber of predetermined length is intercepted, thermometric section is reserved on the optical fiber of interception and surveys strain section；
The thermometric section is inserted in capillary, the strain section of surveying is retained in extracapillary；
Capillary is correspondingly placed in the cutting array of metal material cutting substrate, capillary is between adjacent cutting
U-shaped transition；
The survey strain section is correspondingly placed at the survey strain region in the cutting array between cutting, it is described to survey strain
Section U-shaped transition between adjacent survey strain region；
Capillary in the metal material cutting substrate and thereon and the overlying cured carbon fiber prepreg laying of optical fiber, make
Metal material cutting substrate, capillary, optical fiber and carbon fiber prepreg laying form integrally formed measuring device；
Drill experiment in the measuring device, measures the temperature of thermometric section respectively and surveys the temperature of strain section, Yi Jiji
Calculate the strain value for surveying strain section.
Further, the strain value calculating for surveying strain section is as follows：
Wherein, T1To survey the temperature value of strain section, T2For the temperature value of neighbouring thermometric section, K ε are fibre strain sensitivity
Coefficient, KTFor fiber optic temperature sensitivity coefficient.
Further, the alloy sheets are titanium alloy sheet or aluminium alloy plate.
Further, the carbon fiber prepreg laying passes through hot pressing or negative pressure of vacuum technique and the metal material cutting
Substrate, capillary, optical fiber form integrally formed measuring device.
The present invention discloses array fibre and surveys metal/composite material interlayer temperature and the device of strain, including integrally formed
Metal material cutting substrate, carbon fiber prepreg laying, capillary and optical fiber；
Wherein, there is the parallel cutting of some array quantity in the metal material cutting substrate；The capillary is located at
In the cutting array of metal material cutting substrate, capillary U-shaped transition between adjacent cutting；The optical fiber includes integrally connecting
The thermometric section and survey strain section, the thermometric section connect is sleeved in capillary, and the strain section of surveying is in extracapillary and described in
Survey strain region in cutting array between cutting, it is described to survey the U-shaped transition between adjacent survey strain region of strain section.
Further, the metal material cutting substrate is titanium alloy cutting substrate or aluminium alloy cutting substrate.
Further, the cutting in the metal material cutting substrate is square groove or V-shaped groove, naturally it is also possible to is other
Shape.
Further, the capillary is specially Stainless Steel capillary or Teflon pipe, or other capillaries.
The main of the present invention has the beneficial effect that：In drilling is tested, the thermometric section and survey strain section of optical fiber can be passed through respectively
Metal/composite material interlayer temperature and strain are measured；Wherein, thermometric section will not be extruded by the protection of capillary, can
Free state is kept, therefore the temperature change in drilling experiment can be accurately measured；The temperature of thermometric section can be also used for pair
The temperature for surveying strain section compensates, and to eliminate temperature influence, obtains accurate strain value.It the composite can be widely applied to aviation
Space flight, the new material of traffic and transport field related components, new product, the scientific research of new process and research and development process monitoring with
Measurement.
Brief description of the drawings
Fig. 1 is that array fibre disclosed in embodiment surveys metal/composite material interlayer temperature and the device decomposition texture of strain
Schematic diagram.
Fig. 2 is the structure diagram of metal material cutting substrate in Fig. 1.
Fig. 3 is the structure diagram that metal material cutting substrate places after capillary and optical fiber in Fig. 2.
Fig. 4 is will to form integrated apparatus structure schematic diagram after Fig. 3 curing carbon fiber prepreg overlays.
Fig. 5 is laser signal diagram when strain measurement is carried out using the device shown in Fig. 4.
In figure：1- optical fiber；2- capillaries；3- carbon fiber layings；4- metal material cutting substrates.
Embodiment
To make the purpose of the present invention, technical solution and effect clearer, clear and definite, develop simultaneously embodiment pair referring to the drawings
The present invention is further described.It should be appreciated that specific embodiment described herein is not used to only to explain the present invention
Limit the present invention.
Embodiment one
Please refer to Fig.1 to Fig.4, array fibre disclosed in embodiment one surveys metal/composite material interlayer temperature and strain
Method, gets out titanium alloy sheet or aluminium alloy plate and optical fiber, capillary (such as Stainless Steel capillary and Teflon pipe) and light
Fibre, performs following steps：
Step S101：The metal material cutting base of the parallel cutting with predetermined array quantity is processed in alloy sheets
Bottom.
For example, the metal material with certain tiny cutting of array quantity can be processed in the titanium alloy sheet of 80mm × 80mm
Expect cutting substrate 4, as shown in Figure 2.Size, the quantity of cutting and the interval of metal material cutting substrate 4 can as needed and
Design.
Step S102：The optical fiber of predetermined length is intercepted, thermometric section is reserved on the optical fiber of interception and surveys strain section.
Step S103：The thermometric section is inserted in capillary, the strain section of surveying is retained in extracapillary.
For example, intercepting the optical fiber 1 of 2m as needed, a part is packed into capillary 2, it is institute to pack into capillary 2
Thermometric section is stated, described survey that be used as being retained in outside capillary 2 strains section.Capillary 2 is used to protect thermometric section, is curing it
During will not be forced into, and the free state of non-tension and compression can be kept in pipe.Thermometric section can be used for temperature survey, and be used for
Survey in strain path and the temperature of neighbouring survey strain section is compensated.
Step S104：Capillary is correspondingly placed in the cutting array of metal material cutting substrate, capillary is adjacent
U-shaped transition between cutting.
Step S105：The survey strain region for straining section and being correspondingly placed in cutting array between cutting will be surveyed, survey strain section
The U-shaped transition between adjacent survey strain region.
Step S104 and step S105 are as shown in Figure 3.
Step S106：The overlying cured carbon fiber prepreg paving of capillary and optical fiber in metal material cutting substrate and thereon
Layer, makes metal material cutting substrate, capillary, optical fiber and carbon fiber prepreg laying form integrally formed measuring device.
As shown in figure 4, carbon fiber prepreg laying 3 by hot pressing or negative pressure of vacuum technique and metal material cutting substrate 4,
Capillary 2, optical fiber 1 form integrally formed measuring device.
Step S107：Drill experiment in measuring device, measures the temperature of thermometric section respectively and surveys the temperature of strain section, with
And calculate the strain value for surveying strain section.
The laser signal of step S107 measurement process is as shown in Figure 5.
In the present embodiment, for strain can use distribution type fiber-optic (FBG) demodulator (U.S. Luna, spatial resolution 2.6mm,
Temperature resolution is 0.2 DEG C, and strain resolution is 2 ε) subsidiary is carried out under temperature model, which calculates as follows：
Wherein, T1To survey the temperature value of strain section, T2For the temperature value of neighbouring thermometric section, K ε are fibre strain sensitivity
Coefficient, KTFor fiber optic temperature sensitivity coefficient.
In the calculating of strain value, the temperature of thermometric section is used to compensate the temperature for surveying strain section, to eliminate temperature
Influence, obtain accurate strain value.
Embodiment two
Fig. 1 to Fig. 4 equally is referred to, array fibre disclosed in embodiment surveys metal/composite material interlayer temperature and strain
Device, including integrally formed metal material cutting substrate 4, carbon fiber prepreg laying 3, capillary 2 and optical fiber 1.
Wherein, there is the parallel cutting of some array quantity in metal material cutting substrate 4；Capillary 2 is located at metal material
In the cutting array for expecting cutting substrate 4, the U-shaped transition between adjacent cutting of capillary 2；Optical fiber 1 includes the survey of integrally connected
Temperature section and survey strain section, thermometric section are sleeved in capillary 2, survey strain section in extracapillary and between cutting in cutting array
Survey strain region, survey strain section it is adjacent survey strain region between U-shaped transition.
Further, the metal material cutting substrate 4 is titanium alloy cutting substrate or aluminium alloy cutting substrate etc..Metal
Cutting in material cutting substrate 4 is square groove or V-shaped groove, naturally it is also possible to is other shapes.Capillary 2 is specially Stainless Steel
Capillary or Teflon pipe etc..
The introduction of the purposes reference implementation example one of implementation column two, which is not described herein again.
In conclusion the main of the present invention has the beneficial effect that：In drilling is tested, by thermometric section and strain can be surveyed respectively
Section measures metal/composite material interlayer temperature and strain；Wherein, thermometric section will not be extruded by the protection of capillary,
Free state can be kept, therefore the temperature change in drilling experiment can be accurately measured；The temperature of thermometric section can be also used for
The temperature for surveying strain section is compensated, to eliminate temperature influence, obtains accurate strain value.It the composite can be widely applied to navigate
Empty space flight, the new material of traffic and transport field related components, new product, the process monitoring of the scientific research of new process and research and development
With measurement.
It should be appreciated that for those of ordinary skills, can according to the above description be improved or converted,
And all these modifications and variations should all belong to the protection domain of appended claims of the present invention.
Claims (8)
1. a kind of array fibre surveys metal/composite material interlayer temperature and the method for strain, it is characterised in that including following step
Suddenly：
The metal material cutting substrate of the parallel cutting with predetermined array quantity is processed in alloy sheets；
The optical fiber of predetermined length is intercepted, thermometric section is reserved on the optical fiber of interception and surveys strain section；
The thermometric section is inserted in capillary, the strain section of surveying is retained in extracapillary；
Capillary is correspondingly placed in the cutting array of metal material cutting substrate, capillary is U-shaped between adjacent cutting
Transition；
The survey strain section is correspondingly placed at the survey strain region in the cutting array between cutting, the strain section of surveying exists
U-shaped transition between adjacent survey strain region；
Capillary in the metal material cutting substrate and thereon and the overlying cured carbon fiber prepreg laying of optical fiber, make metal
Material cutting substrate, capillary, optical fiber and carbon fiber prepreg laying form integrally formed measuring device；
Drill experiment in the measuring device, measures the temperature of thermometric section respectively and surveys the temperature of strain section, and calculates
Survey the strain value of strain section.
2. array fibre according to claim 1 surveys metal/composite material interlayer temperature and the method for strain, its feature exists
In the strain value calculating for surveying strain section is as follows：
<mrow>
<mi>S</mi>
<mo>=</mo>
<mrow>
<mo>(</mo>
<mfrac>
<mrow>
<msub>
<mi>T</mi>
<mn>1</mn>
</msub>
<mo>-</mo>
<msub>
<mi>T</mi>
<mn>2</mn>
</msub>
</mrow>
<msub>
<mi>K</mi>
<mi>T</mi>
</msub>
</mfrac>
<mo>)</mo>
</mrow>
<mo>&times;</mo>
<mi>K</mi>
<mi>&epsiv;</mi>
</mrow>
Wherein, T1To survey the temperature value of strain section, T2For the temperature value of neighbouring thermometric section, k ε are fibre strain sensitivity coefficient,
KTFor fiber optic temperature sensitivity coefficient.
3. array fibre according to claim 2 surveys metal/composite material interlayer temperature and the method for strain, its feature exists
In the alloy sheets are titanium alloy sheet or aluminium alloy plate.
4. array fibre according to claim 3 surveys metal/composite material interlayer temperature and the method for strain, its feature exists
In the carbon fiber prepreg laying passes through hot pressing or negative pressure of vacuum technique and the metal material cutting substrate, capillary, light
Fibre forms integrally formed measuring device.
5. a kind of array fibre surveys metal/composite material interlayer temperature and the device of strain, it is characterised in that including being integrally formed
Metal material cutting substrate, carbon fiber prepreg laying, capillary and optical fiber；
Wherein, there is the parallel cutting of some array quantity in the metal material cutting substrate；The capillary is located at metal
In the cutting array of material cutting substrate, capillary U-shaped transition between adjacent cutting；The optical fiber includes integrally connected
Thermometric section and survey strain section, the thermometric section are sleeved in capillary, and the strain section of surveying in extracapillary and is located at the cutting
Survey strain region in array between cutting, it is described to survey the U-shaped transition between adjacent survey strain region of strain section.
6. array fibre according to claim 5 surveys metal/composite material interlayer temperature and the device of strain, its feature exists
In the metal material cutting substrate is titanium alloy cutting substrate or aluminium alloy cutting substrate.
7. array fibre according to claim 6 surveys metal/composite material interlayer temperature and the device of strain, its feature exists
In the cutting in the metal material cutting substrate is square groove or V-shaped groove.
8. array fibre according to claim 7 surveys metal/composite material interlayer temperature and the device of strain, its feature exists
In the capillary is specially Stainless Steel capillary or Teflon pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711386098.9A CN108007604A (en) | 2017-12-20 | 2017-12-20 | Array fibre surveys metal/composite material interlayer temperature and the method and device of strain |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711386098.9A CN108007604A (en) | 2017-12-20 | 2017-12-20 | Array fibre surveys metal/composite material interlayer temperature and the method and device of strain |
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|---|---|
| CN108007604A true CN108007604A (en) | 2018-05-08 |
Family
ID=62060015
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|---|---|---|---|
| CN201711386098.9A Pending CN108007604A (en) | 2017-12-20 | 2017-12-20 | Array fibre surveys metal/composite material interlayer temperature and the method and device of strain |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108955942A (en) * | 2018-08-29 | 2018-12-07 | 广州大学 | Silica gel covers Helical Fiber probe temperature measuring equipment and its production, application method |
| CN109297430A (en) * | 2018-12-07 | 2019-02-01 | 上海拜安传感技术有限公司 | Applied on strain gauge substrate and corresponding strain gauge |
| WO2022052724A1 (en) * | 2020-09-09 | 2022-03-17 | 山东科技大学 | Intelligent skin based on small-size distributed optical fiber sensing array |
| CN114324178A (en) * | 2021-12-07 | 2022-04-12 | 中北大学 | Metal-fiber cladding FBG sensor packaging structure based on low-temperature consolidation |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114324178A (en) * | 2021-12-07 | 2022-04-12 | 中北大学 | Metal-fiber cladding FBG sensor packaging structure based on low-temperature consolidation |
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