CN105136086A - Composite structure interlayer contact state measurement sensor - Google Patents
Composite structure interlayer contact state measurement sensor Download PDFInfo
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- CN105136086A CN105136086A CN201510434136.8A CN201510434136A CN105136086A CN 105136086 A CN105136086 A CN 105136086A CN 201510434136 A CN201510434136 A CN 201510434136A CN 105136086 A CN105136086 A CN 105136086A
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- composite
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- induction core
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- 239000002131 composite materials Substances 0.000 title claims abstract description 59
- 239000011229 interlayers Substances 0.000 title claims abstract description 25
- 239000010410 layers Substances 0.000 claims abstract description 29
- 239000011257 shell materials Substances 0.000 claims abstract description 27
- 230000001939 inductive effects Effects 0.000 claims description 44
- 239000011888 foils Substances 0.000 claims description 16
- 238000007789 sealing Methods 0.000 claims description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 238000009434 installation Methods 0.000 abstract description 4
- 238000006073 displacement reactions Methods 0.000 description 14
- 230000000694 effects Effects 0.000 description 6
- 239000003365 glass fibers Substances 0.000 description 5
- 238000005516 engineering processes Methods 0.000 description 3
- 238000000034 methods Methods 0.000 description 3
- 238000010586 diagrams Methods 0.000 description 2
- 239000000463 materials Substances 0.000 description 2
- 210000003813 Thumb Anatomy 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000686 essences Substances 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000002905 metal composite materials Substances 0.000 description 1
- 239000002184 metals Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006011 modification reactions Methods 0.000 description 1
- 239000002245 particles Substances 0.000 description 1
- 230000003068 static Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Abstract
Description
Technical field
The present invention relates to a kind of structural mechanics field, particularly relate to a kind of sensor measuring composite structure interlayer contact state.
Background technology
Because composite structure can make full use of the physico mechanical characteristic of different materials, have that large, the anti-high pressure of rigidity, intensity are high, the advantage of good endurance, therefore composite structure is widely popular in fields such as building, machinery, Aero-Space, chemistry.
But large complex structure inevitably by the impact load, complicated mechanical behavior such as temperature load, environmental attack in daily military service, makes composite structure be in a kind of random multidimensional stress of continuous change under arms in process.The multidimensional stress of this complexity makes the time of day of composite structure unpredictable and calculate; Particularly in production, processing, transport and installation or work progress, composite structure is not only subject to static load, is also subject to more complicated dynamic load.Therefore, composite structure needs to monitor the contact condition of large complex structure interlayer in production and processing and operation process.
The existing displacement transducer for measuring composite structure has interior mode optical fibre displacement sensor and external regulation type optical fibre displacement sensor (Wang Guanghui, the blue or green application of the .FBG sensor on composite material structure health monitoring [A] of Yuan state. material engineering, 2010, increase 1:110-115; Shen Weiliang, Zhu Qirong, Xie Mingru. based on the experimental analysis [J] of the glass fiber compound material interlayer strain testing of fiber-optic grating sensor. mechanics quarterly, 2013,03:463-469).Interior mode optical fibre displacement sensor utilizes microbending effect to reflect the change of measured physical quantity, carrys out the change of quantitative description physical quantity according to the funtcional relationship between light intensity and measured physical quantity.The method system complex, the dynamic range of displacement measurement is little, high to requirement on machining accuracy, and mode is loaded down with trivial details, and engineer applied is less.External regulation type optical fibre displacement sensor identifies the change of physical quantity by luminous flux.Interior mode and external regulation type optical fibre displacement sensor are generally used for measuring displacement measurement between metal composite layer, need to do special processing in the composite structure be mingled with containing greater particle size, and measurement effect fluctuation is larger.
Therefore, need to propose a kind of novel sensor being specifically designed to measurement large complex structure contact status between layers, the slippage of composite structure interlayer and disengaged condition can be reflected, can not only be used for measuring for measuring the interlayer state of composite structure in process of manufacture, the contact status between layers of composite structure in operation can also be monitored, especially, the 3 D stereo variable condition of large complex structure interlayer can be measured.
Summary of the invention
The shortcoming of prior art in view of the above, the technical problem to be solved in the present invention is to provide a kind of sensor being convenient to the measurement composite structure interlayer contact state of installing, and more adequately can measure disengagement and the slip state of composite structure interlayer.
For achieving the above object, the invention provides a kind of sensor measuring composite structure interlayer contact state, described composite structure comprises adjacent ground floor and the second layer, described sensor comprises induction core and a shell, described shell is positioned at the ground floor of composite structure, the body that described induction core has the first end be fixedly linked with the second layer of composite structure, the second end be fixedly connected with described shell and is positioned at described shell; The surface of described induction core is provided with multiple foil gauge, and described foil gauge is near described first end.
Preferably, the xsect of described induction core is square, and have four sides, the length of described induction core is L, and the length of side of xsect is that a, L/a are greater than 4.
Preferably, described foil gauge has 4, is pasted onto four sides of induction core respectively.
Preferably, described foil gauge is provided with wire, and described wire is drawn from described composite structure.
Preferably, be embedded with fixture in the second layer of described composite structure, the first end of described induction core is fixedly connected with described fixture.
Preferably, described fixture is nut, and the first end of described induction core is connected with described nut by screw thread.
Preferably, described shell is the thin cylinder of one end open.
Preferably, the openend of described shell is contacted with the second layer of composite structure by sealing gasket.
Preferably, the second end of described induction core is connected with at the bottom of the cylinder of described thin cylinder by nut.
As mentioned above, the sensor that the present invention relates to, there is following beneficial effect: described sensor, by arranging foil gauge at induction wicking surface, can measure slippage and the disengaged condition of large complex structure interlayer simultaneously, and the time of day of composite structure interlayer can be reflected multi-C stereo; Cost of manufacture is low, is convenient to install, and measures simple, is convenient to application.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is cut-open view of the present invention.
Fig. 3 is I-I cut-open view in Fig. 2.
Fig. 4 is the cut-open view of shell.
Fig. 5 is II-II cut-open view in Fig. 4.
Fig. 6 is the side view of sealing gasket.
Fig. 7 is composite structure interlayer changing of the relative positions schematic diagram.
Fig. 8 is Y-Z floor map in Fig. 7.
Fig. 9 is induction core cross section enlarged diagram.
Element numbers explanation
1 induction core
11 first ends
12 second ends
13 bodies
14 stationary installations
2 shells
3 foil gauges
31 wires
4 sealing gaskets
51 ground floors
52 second layers
Embodiment
By particular specific embodiment, embodiments of the present invention are described below, person skilled in the art scholar the content disclosed by this instructions can understand other advantages of the present invention and effect easily.
Notice, structure, ratio, size etc. that this instructions institute accompanying drawings illustrates, content all only in order to coordinate instructions to disclose, understand for person skilled in the art scholar and read, and be not used to limit the enforceable qualifications of the present invention, therefore the not technical essential meaning of tool, the adjustment of the modification of any structure, the change of proportionate relationship or size, do not affecting under effect that the present invention can produce and the object that can reach, still all should drop on disclosed technology contents and obtain in the scope that can contain.Simultaneously, quote in this instructions as " on ", D score, "left", "right", " centre " etc. term, also only for ease of understanding of describing, and be not used to limit the enforceable scope of the present invention, the change of its relativeness or adjustment, under changing technology contents without essence, when being also considered as the enforceable category of the present invention.
The invention provides a kind of sensor measuring composite structure interlayer contact state, as shown in Figure 1, described composite structure comprises adjacent ground floor 51 and the second layer 52, under the impact of extraneous factor, between this ground floor 51 and second layer 52 occur throw off and slip state, described sensor measurement be namely this disengagement and slip state.As shown in Figure 2, described sensor comprises induction core 1 and a shell 2, described shell 2 is positioned at the ground floor 51 of composite structure, when there is disengagement and slip state between the ground floor 51 of composite structure and the second layer 52, induction core 1 meeting flexural deformation, therefore, should stay at regular intervals between the side of induction core 1 and the inwall of shell 2, guarantee to respond to the inwall that can not touch described shell 2 when core 1 is out of shape.
As shown in Figures 1 and 2, described induction core 1 body 13 that there is the first end 11 be fixedly linked with the second layer 52 of composite structure, the second end 12 be fixedly connected with described shell 2 and be positioned at described shell 2.Preferably, the material of described induction core 1 can adopt metal.The first end 11 of induction core 1 is fixedly connected with the following methods with the second layer 52 of composite structure is optional, as shown in Figure 1, embedded fixing component 14 in the second layer 52 of described composite structure, also fixture 14 can be pasted or be anchored in the second layer 52, the first end 11 of described induction core 1 is fixedly connected with described fixture 14, this fixture 14 can be nut, the first end 11 of described induction core 1 is connected with described nut by screw thread, also other connected modes can be adopted to connect first end 11 and the described fixture 14 of described induction core 1, as welding.As shown in Fig. 2, Fig. 4 and Fig. 5, preferably, described shell 2 is the thin cylinder of one end open, second end 12 of described induction core 1 is connected with at the bottom of the cylinder of described thin cylinder by nut, namely the second end 12 is provided with external thread, nut is positioned at the outside of shell 2, and the second end 12 of induction core 1 passes at the bottom of the cylinder of described thin cylinder, then by nut lock.As shown in Figure 6, preferably, the openend of described shell 2 is contacted with the second layer 52 of composite structure by sealing gasket 4, and described sealing gasket 4 can be elastic sealing gasket, guarantees the sealing property between sealing gasket 4 and the composite structure second layer 52.
As shown in Figure 1, the surface of described induction core 1 is provided with multiple foil gauge 3, described foil gauge 3 is near described first end 11, wire 31 can be provided with on foil gauge 3, described wire 31 is drawn from described composite structure, described wire generally should be located at the place that can not be interfered with by construction, accurately to measure the strained situation of induction core 1.As shown in Figure 3, preferably, the xsect of described induction core 1 is square, have four sides, correspondingly, shown foil gauge 3 also has four, be pasted onto four sides of induction core 1 respectively, the strain that the foil gauge 3 of four side stickups is up and down measured is followed successively by ε 1, ε 2, ε 3, ε 4(see Fig. 9), reflects the strain variation of each side of induction core 1.Less in order to ensure the strain error measured, the length of described induction core 3 is L, and the length of side of xsect is that a, L/a should be greater than 4.
Measure composite structure interlayer to the present invention below to throw off and the measuring principle of slip state and using method further illustrate, the distortion responding to core 1 in the present invention is divided into two parts, comprises transverse curvature and axial deformation.
For expressing clearly, to respond to the center of the end square sectional of core 1 for true origin, with the outer normal direction of the composite structure second layer 52 for Z axis, one of them is tangentially Y-axis, surface of contact between the ground floor 51 of Y-axis and composite structure and the second layer 52 overlaps (as shown in Figure 7 and Figure 8), in Fig. 7, M1 represents the original state of composite structure ground floor 51, and M2 shows the state after the disengagement of composite structure ground floor 51 and slippage.According to right-hand rule determination X-axis (as shown in Figure 9), wherein thumb is oriented to Z-direction.In Z-Y plane, assuming that distortion is to be just along coordinate axis forward, straining with tension is just, axial deformation causes strain for ε 0; The bending strain causing induction wicking surface is ε curved(ε curvedfor moment of flexure causes strain absolute value).Therefore, ε 1=ε 0-ε curved, ε 2=ε 0+ ε curved.
Following equation is set up according to structural mechanics beam with both ends built-in Deformation Theory:
h/L＝ε 0(2)
ε 1=ε 0-ε curved, ε 2=ε 0+ ε curved(3)
Solve an equation:
The displacement (slippage) of the tangential Y-direction in interlayer contact face:
The displacement (disengagement) of interlayer contact face normal direction Z-direction:
In like manner can calculate:
The displacement (slippage) of the tangential X-direction in interlayer contact face:
In formula, L is induction core effective length; A is the square-section length of side of induction core; ε 1, ε 2, ε 3, ε 4be respectively the strain value of four sides up and down of induction core 1; v xfor composite structure interlayer contact face displacement in X direction under slip state; v yfor the displacement of the tangential Y-direction in composite structure interlayer contact face under slip state; H is the displacement of composite structure interlayer contact face normal direction Z-direction under disengaged condition.
Concrete using method and step as follows:
1) pre-buried stationary installation 14 in the second layer 52 of composite structure, is then connected sensor with stationary installation 14, installs sealing gasket 4 between shell 2 and the second layer 52 of composite structure, and wire 31 is drawn composite structure be convenient to connect acquisition instrument.
2) described sensor is connected with general strain acquirement instrument, before testing instrument is carried out rezero operation.
3) strain value of four sides up and down of record induction core 1 is respectively ε 1, ε 2, ε 3, ε 4.
3) by ε 1and ε 2be updated to respectively in formula (4) and formula (5), obtain v yand h, by ε 3and ε 4be brought in formula (6), obtain v x.
Clearer for describing, below provide one embodiment of the present of invention
The bendind rigidity EI=7.78Nm of induction core used in the present invention 2; L=0.04m; A=0.006m.The strain being recorded four foil gauges 3 by strain instrument is respectively ε 1=-100 μ ε; ε 2=500 μ ε; ε 3=800 μ ε; ε 4above-mentioned data are brought in formula (4), (5) and (6), calculate v by=-400 μ ε y=6.67e -4m, v x=1.33e -3m; H=8e -6m
In sum, the present invention effectively overcomes various shortcoming of the prior art and tool high industrial utilization.
Above-described embodiment is illustrative principle of the present invention and effect thereof only, but not for limiting the present invention.Any person skilled in the art scholar all without prejudice under spirit of the present invention and category, can modify above-described embodiment or changes.Therefore, such as have in art usually know the knowledgeable do not depart from complete under disclosed spirit and technological thought all equivalence modify or change, must be contained by claim of the present invention.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510434136.8A CN105136086B (en) | 2015-07-22 | 2015-07-22 | Measure the sensor of composite construction contact status between layers |
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| CN201510434136.8A CN105136086B (en) | 2015-07-22 | 2015-07-22 | Measure the sensor of composite construction contact status between layers |
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| CN105136086A true CN105136086A (en) | 2015-12-09 |
| CN105136086B CN105136086B (en) | 2018-02-09 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564217A (en) * | 2016-10-26 | 2017-04-19 | 东南大学 | Intelligent sandwich panel |
| CN109708563A (en) * | 2018-12-28 | 2019-05-03 | 重庆交通大学 | Strain-type structure section changing of the relative positions test device |
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2015
- 2015-07-22 CN CN201510434136.8A patent/CN105136086B/en active IP Right Grant
Patent Citations (8)
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| EP0410910A1 (en) * | 1989-07-27 | 1991-01-30 | SEXTANT Avionique | Membrane deformation measuring device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564217A (en) * | 2016-10-26 | 2017-04-19 | 东南大学 | Intelligent sandwich panel |
| CN109708563A (en) * | 2018-12-28 | 2019-05-03 | 重庆交通大学 | Strain-type structure section changing of the relative positions test device |
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| Publication number | Publication date |
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| CN105136086B (en) | 2018-02-09 |
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