CN109612603A - A kind of fiber grating temperature sensor preparation method of the quick lens construction of star - Google Patents
A kind of fiber grating temperature sensor preparation method of the quick lens construction of star Download PDFInfo
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- CN109612603A CN109612603A CN201811646128.XA CN201811646128A CN109612603A CN 109612603 A CN109612603 A CN 109612603A CN 201811646128 A CN201811646128 A CN 201811646128A CN 109612603 A CN109612603 A CN 109612603A
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- 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
- G01K11/3206—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 at discrete locations in the fibre, e.g. using Bragg scattering
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K15/00—Testing or calibrating of thermometers
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Abstract
The present invention discloses a kind of fiber grating temperature sensor preparation method of quick lens construction of star, which comprises the steps of: 1) before the encapsulation of grating fibers temperature sensor, carries out mechanical simulation analysis to the grating fibers temperature sensor；2) the grating fibers temperature sensor strain measurement；3) the grating fibers temperature sensor encapsulation；4) the grating fibers calibration of sensor.The environmental requirement that can satisfy spacecraft work, reaches measurement purpose.Using novel packing forms, temperature measurement is realized.It realizes single branch sensor multi-point temperature measurement function, and grid region position arc routing and is suspended on substrate, so that the strain influence that substrate deformation generates greatly reduces, temperature measurement can be made more accurate.
Description
Technical field
The invention belongs to fibre optical sensor fields, and in particular to a kind of fiber grating temperature sensor of the quick lens construction of star
Preparation method.
Background technique
With the rapid development of China's aerospace industry, the performance parameter monitoring of spacecraft is more and more important.Wherein, temperature is
The physical quantity for indicating the cold and hot degree of object, there is important shadow to the working life of spacecraft, operating accuracy, working performance etc.
It rings.Traditional electronic temp measurement method has the methods of thermocouple temperature measurement, thermistor temperature detecting, but traditional temp measuring method exists
Anti- electromagnetic performance is poor, volume is big, weight is big, is difficult to the disadvantages of networking multiplexing.Compared with traditional electronic type temperature transducer, light
Research and application development of the fiber sensor in terms of parameter measurement are rapid, fiber grating have it is small in size, light-weight, not by electromagnetism
Interference, is easy to the features such as insert material is internal, flexible and convenient at the multiplexing of energy large-scale network-estabilishing, and because of the physics section of fiber grating
It is small with mechanical strength, it is pasting and is being embedded into spacecraft and its performance will not impacted with structure, be very suitable to space flight pole
Parameter measurement under end ring border is the hot spot of current spacecraft parameter monitoring Research on Sensing.
For the temperature monitoring of the quick lens construction of Satellite, traditional electronic temp is measured due to cable shielding line weight
Greatly, the disadvantages of anti-electromagnetic interference capability is not poor, and the further development of electronic temp measurement is limited, as fiber grating is got over
More to become the first choice of space flight performance parameter measurement, development speed in recent years also very rapidly, has great application prospect.
Due to bare fibre matter it is crisp very thin and it is easy to damage fracture, in optical fiber in use, place must be packaged to it
Reason, can not only shield in this way to fiber grating, moreover it is possible to realize temperature enhanced sensitivity, reduce strain interference etc. other
Function.Although the research that state, inside and outside researcher are applied to spacecraft parameter measurement to fiber-optic grating sensor has centainly
Progress, but current packaging technology is concentrated mainly on base chip package, metallization packaged, flush type encapsulation.For Satellite
The fiber-optic grating sensor of dependent sensor optical main mirror header structure is laid and temperature monitoring problem, the sensor of existing packing forms
The arcuate structure that camera lens is tested position cannot be fitted in completely, to influence the accuracy of temperature measurement.
Summary of the invention
The purpose of the present invention is to solve this problems, realize the accurate thermometric of fiber-optic grating sensor.A kind of star is provided
The fiber grating temperature sensor preparation method of quick lens construction, the temperature sensor use doughnut-shaped substrate encapsulating structure, energy
So that sensor perfection is fitted in star sensor optical main mirror header structure surface, reduces sensor to the thermometric shadow of specific structure
Ring, and concatenated multiple fiber gratings can be encapsulated in a sensor base, finally to the sensor of encapsulation carry out strain and
Temperature performance test.
For achieving the above object, the technical scheme is that
A kind of fiber grating temperature sensor preparation method of the quick lens construction of star, which comprises the steps of: 1) light
Before the encapsulation of grid fibre optic temperature sensor, mechanical simulation analysis is carried out to the grating fibers temperature sensor；
2) the grating fibers temperature sensor strain measurement；
3) the grating fibers temperature sensor encapsulation；
4) the grating fibers calibration of sensor.
Preferably as one kind of the invention, in the first step, the mechanical simulation analysis includes the following steps, 11) it uses
Ansys finite element analysis software carries out mechanical modeling to the temperature sensor substrate model；12) according to real sensor system
Sensor base material, packing colloid material and the dimensional parameters of standby situation setting mechanical modeling model.
Physical model is chosen, is modeled according to substrate material 7075T6 aluminum alloy materials and actual size；Use DP420
Fiber grating temperature sensor substrate is fixedly bonded to the part surface that is stretched by epoxide-resin glue；
Preferably as one kind of the invention, second step, the grating fibers temperature sensor strain measurement includes the following steps,
21) the temperature sensor substrate, epoxide-resin glue, fiber grating and tensioning member cut, combined, scanning grid stroke
Point；22) described tensioning member one end carries out constraint fixation, and the tensioning member other end X-direction is stretched, according to the quick mirror of Satellite
In-orbit thermometric requirement, so that the strain that tensioning member is transmitted to substrate reaches setting threshold value, obtains grating fibers temperature sensor
Strain cloud atlas.Strain is 500 μ.
Preferably as one kind of the invention, third step, the grating fibers temperature sensor encapsulation, includes the following steps,
31) it will be carved with multistage grating fibers concatenation forming fibre-optic grating string first, the fiber grating string will be fixed using epoxide-resin glue
It is encapsulated in the lower half portion of a doughnut-shaped substrate, and grid region position arc routing and is suspended on doughnut-shaped substrate；32) circular ring shape base
Bottom is placed on heating platform, and 60 DEG C of heating platform of setting is heating and curing；33) it after the completion of being heating and curing, places under room temperature；
34) silicon rubber is uniformly smeared in the ladder rooved face of doughnut-shaped substrate inner ring, outer ring, by doughnut-shaped substrate upper cover and circular ring shape
Substrate bottom is assembled, and temperature sensor overall package is completed；Then hole slot and substrate upper cover, substrate bottom outside substrate
Junction reuses silicon rubber and carries out sensor sealing, is fully cured at normal temperature.
Preferably as one kind of the invention, the 4th step, the grating fibers calibration of sensor includes the following steps,
41) temperature sensor is placed in high-low temperature chamber, and the temperature sensor passes through fiber annular using light source and (FBG) demodulator
Device is attached, and the (FBG) demodulator measures fiber grating reflection spectrum, by setting high-low temperature chamber temperature, to make in fiber grating
Cardiac wave length changes；42) setting high-low temperature chamber temperature range, setting are required according to the thermometric of satellite star sensor optical lens
It is -60 DEG C ~ 60 DEG C, every 10 DEG C are a stepping, carry out circulation experiment and are obtained by demodulating fiber bragg grating center wavelength variation
The relationship of temperature change.
Preferably as one kind of the invention, the fiber grating spectral width three dB bandwidth is 0.4nm, and grid region length is
The central wavelength of 10mm, the fiber grating string are respectively 1530nm, 1540nm, 1550nm.
Preferably as one kind of the invention, the light source is ASE wideband light source, and power is -55dB.
Preferably as one kind of the invention, the (FBG) demodulator is high speed optic fiber grating (FBG) demodulator, resolution ratio 1pm.
Preferably as one kind of the invention, the high-low temperature chamber uses the high-low temperature chamber of model GDW-100.
Compared with prior art, the beneficial effects of the present invention are:
The present invention has application prospect in the in-orbit temperature measurement of Satellite dependent sensor primary mirror header structure.Base is encapsulated in sensor
It is improved on bottom, using substrate formula packaging method, temperature sensor base material chooses space flight 7075T6 aluminum alloy materials,
The environmental requirement that can satisfy spacecraft work, reaches measurement purpose.When sensor encapsulates, multistage fiber grating string can be encapsulated
In a doughnut-shaped substrate, single branch sensor multi-point temperature measurement function is realized, and grid region position arc routing and be suspended on substrate,
So that the strain influence that substrate deformation generates greatly reduces, temperature measurement can be made more accurate.The sensor energy of the packing forms
It is enough to be preferably fitted in the quick primary mirror structure of star, it can accurately measure the temperature of satellite star sensor optical main mirror header structure.
Detailed description of the invention
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets implementation of the invention
Example, and be used to explain the principle of the present invention together with specification.
Fig. 1 is the main lens structural representation of the fiber grating temperature sensor preparation method of the quick lens construction of star of the present invention
Figure.
The fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of Fig. 2 a star of the present invention
Device substrate bottom and substrate perspective view.
The fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of Fig. 2 b star of the present invention
Device substrate bottom and substrate main view.
The fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of Fig. 2 c star of the present invention
Device substrate bottom and substrate bottom view.
The fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of Fig. 2 d star of the present invention
Device substrate bottom and substrate left view.
The fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of Fig. 2 e star of the present invention
Partial enlarged view at device substrate bottom and substrate A.
Fig. 2 f is the BB of Fig. 2 e to sectional view.
Fig. 2 g is partial enlarged view at D.
Fig. 2 h is the EE of Fig. 2 g to sectional view.
Fig. 3 is the fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of star of the present invention
Device substrate bottom and substrate upper cover three-dimensional figure.
Fig. 4 is the fiber grating temperature sensor of the fiber grating temperature sensor preparation method of the quick lens construction of star of the present invention
Device substrate bottom package and complete installation diagram.
The sensor and tensioning member of the fiber grating temperature sensor preparation method of the quick lens construction of Fig. 5 star of the present invention are illustrated
Figure.
The temperature calibration of Fig. 6 embodiment of the present invention tests schematic diagram.
Specific embodiment
Below in conjunction with attached drawing, technical scheme in the embodiment of the invention is clearly and completely described.
As shown in figures 1 to 6, the fiber grating temperature sensor preparation method of the quick lens construction of a kind of star, including walk as follows
It is rapid: 1) before the encapsulation of grating fibers temperature sensor, for verificating sensor feasibility, to the grating fibers temperature sensor
Carry out mechanical simulation analysis；
The mechanical simulation analysis, includes the following steps, 11) using Ansys finite element analysis software, to the temperature sensor
Substrate model carries out mechanical modeling；12) the sensor base material of situation setting mechanical modeling model is prepared according to real sensor
Matter, packing colloid material and dimensional parameters.Physical model is chosen, according to sensor base material 7075T6 aluminum alloy materials and reality
Border size is modeled；Using DP420 epoxide-resin glue, fiber grating temperature sensor substrate is fixedly bonded to the part that is stretched
Surface.
2) the grating fibers temperature sensor strain measurement；Include the following steps, 21) to the temperature sensor base
Bottom, epoxide-resin glue, fiber grating and tensioning member are cut, are combined, scan grid dividing；22) described tensioning member one end into
Row constraint is fixed, and the tensioning member other end X-direction is stretched, according to the in-orbit thermometric requirement of the quick camera lens of Satellite, so that drawing
Stretch part be transmitted to substrate strain reach setting numerical value be 500 μ, obtain grating fibers temperature sensor strain cloud atlas.
After the strain that the tensioning member is transmitted to substrate reaches 500 μ or so, size is strained caused by fiber grating
In 2 ~ 3 μ, strain very little is generated by substrate deformation and meets the in-orbit thermometric of satellite star sensor so that temperature measurement is more accurate
Requirement.The sensor of the packing forms can preferably be fitted in the quick primary mirror header structure 1 of star, can accurately measure Satellite
The temperature of sensor optical main mirror header structure.
3) the grating fibers temperature sensor encapsulation；Include the following steps, 31) it will be carved with multistage grating fibers 7 first
Forming fibre-optic grating string is concatenated, the fiber grating string is used into the fixed lower half for being encapsulated in a doughnut-shaped substrate of epoxide-resin glue 8
Part, and grid region position arc routing and it is suspended on doughnut-shaped substrate, epoxy resin is DP420 epoxy resin；32) circular ring shape base
Bottom is placed on heating platform, and 60 DEG C of heating platform of setting is heating and curing；33) it after the completion of being heating and curing, places under room temperature；
34) silicon rubber is uniformly smeared in the ladder rooved face of doughnut-shaped substrate inner ring, outer ring, by doughnut-shaped substrate upper cover and circular ring shape
Substrate bottom is assembled, and temperature sensor overall package is completed；Then hole slot and substrate upper cover, substrate bottom outside substrate
Junction reuses silicon rubber and carries out sensor sealing, is fully cured at normal temperature.
As shown in fig. 6, elementary proving principle.4) the grating fibers calibration of sensor, includes the following steps, 41)
The temperature sensor is placed in high-low temperature chamber 2, and the temperature sensor 3 passes through fiber annular using light source 4 and (FBG) demodulator 5
Device is attached, and is incident on fiber grating through coupler 6 (insertion loss), and the (FBG) demodulator measures fiber grating reflection spectrum, is led to
Setting high-low temperature chamber temperature is crossed, so that fiber bragg grating center wavelength be made to change；42) according to satellite star sensor optical lens
Thermometric require setting high-low temperature chamber temperature range, be set as -60 DEG C ~ 60 DEG C, every 10 DEG C are a stepping, and it is real to carry out circulation
It tests, by demodulating fiber bragg grating center wavelength variation, obtains the relationship of temperature change.
Fiber grating spectral width three dB bandwidth described in 4th step is 0.4nm, and grid region length is 10mm, the optical fiber light
The central wavelength of grid string is respectively 1530nm, 1540nm, 1550nm.The light source is ASE wideband light source, and power is -55dB.Institute
Stating (FBG) demodulator is high speed optic fiber grating (FBG) demodulator, resolution ratio 1pm.The high-low temperature chamber uses the height of model GDW-100
Incubator.
Experiment shows: measurement temperature is at -60 DEG C ~ 60 DEG C, the optical fiber grating temperature of designed circular ring type packing forms
Transducer sensitivity reaches 8.74pm/ DEG C, and Linear Quasi is right to reach 0.998.When loop test, under same temperature, optical fiber light
Grid center wavelength variation amount is up to 2pm.Meet the thermometric requirement of satellite star sensor optical main mirror structure.
The present invention uses novel packing forms, and substrate formula packaging method realizes temperature measurement.Base material chooses boat
It uses 7075T6 aluminum alloy materials, can satisfy the environmental requirement of spacecraft work, reaches measurement purpose.When sensor encapsulates,
Fiber grating string can be encapsulated in an annulus substrate, realize single branch sensor multi-point temperature measurement function, and grid region position arc
Cabling is simultaneously suspended on substrate, so that the strain influence that substrate deformation generates greatly reduces, temperature measurement can be made more accurate.
Embodiments described above is only a part of the embodiment of the present invention, instead of all the embodiments.Based on this
Embodiment in invention, every other reality obtained by those of ordinary skill in the art without making creative efforts
Example is applied, shall fall within the protection scope of the present invention.
Claims (9)
1. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, which comprises the steps of: 1)
Before the encapsulation of grating fibers temperature sensor, mechanical simulation analysis is carried out to the grating fibers temperature sensor；
2) the grating fibers temperature sensor strain measurement；
3) the grating fibers temperature sensor encapsulation；
4) the grating fibers calibration of sensor.
2. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 1
In in the first step, the mechanical simulation analysis includes the following steps, 11) using Ansys finite element analysis software, to the temperature
It spends sensor base model and carries out mechanical modeling；12) sensing of situation setting mechanical modeling model is prepared according to real sensor
Device substrate material, packing colloid material and dimensional parameters.
3. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 1
In second step, the grating fibers temperature sensor strain measurement includes the following steps, 21) to the temperature sensor base
Bottom, epoxide-resin glue, fiber grating and tensioning member are cut, are combined, scan grid dividing；22) described tensioning member one end into
Row constraint is fixed, and the tensioning member other end X-direction is stretched, so that the strain that tensioning member is transmitted to substrate reaches setting threshold
Value obtains grating fibers temperature sensor strain cloud atlas.
4. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 1
In third step, the grating fibers temperature sensor encapsulation includes the following steps, 31) it will be carved with multistage grating fibers string first
It is connected into fiber grating string, the fiber grating string is used into the fixed lower half for being encapsulated in a doughnut-shaped substrate of epoxide-resin glue
Point, and grid region position arc routing and it is suspended on doughnut-shaped substrate；32) doughnut-shaped substrate is placed on heating platform, setting heating
60 DEG C of platform are heating and curing；33) it after the completion of being heating and curing, places under room temperature；34) in doughnut-shaped substrate inner ring, outer ring
Ladder rooved face uniformly smears silicon rubber, and doughnut-shaped substrate upper cover and doughnut-shaped substrate bottom are assembled, and completes temperature and passes
After sensor overall package；Hole slot and substrate upper cover, substrate bottom junction, reuse silicon rubber and are sensed outside substrate
Device sealing, is fully cured at normal temperature.
5. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 1
In the 4th step, the grating fibers calibration of sensor includes the following steps, 41) temperature sensor is placed in height
In incubator, the temperature sensor is attached using light source and (FBG) demodulator by optical fiber circulator, and the (FBG) demodulator measures light
Fine optical grating reflection spectrum, by setting high-low temperature chamber temperature, so that fiber bragg grating center wavelength be made to change；42) according to satellite
The thermometric of star sensor optical lens requires setting high-low temperature chamber temperature range, and every 10 DEG C are a stepping, carries out circulation experiment,
By demodulating fiber bragg grating center wavelength variation, the relationship of temperature change is obtained.
6. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 5
In the fiber grating spectral width three dB bandwidth is 0.4nm, and grid region length is 10mm, the central wavelength of the fiber grating string
Respectively 1530nm, 1540nm, 1550nm.
7. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 5
In the light source is ASE wideband light source, and power is -55dB.
8. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 5
In the (FBG) demodulator is high speed optic fiber grating (FBG) demodulator, resolution ratio 1pm.
9. a kind of fiber grating temperature sensor preparation method of the quick lens construction of star, feature exist according to claim 5
In the high-low temperature chamber uses the high-low temperature chamber of model GDW-100.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112084584A (en) * | 2020-07-30 | 2020-12-15 | 航天东方红卫星有限公司 | Manufacturing method of star sensor support capable of monitoring deformation and deformation measuring method |
| CN112556874A (en) * | 2020-12-29 | 2021-03-26 | 广东精铟海洋工程股份有限公司 | Assembly method of fiber bragg grating distributed sensing device for measuring bearing temperature |
| CN114383736A (en) * | 2021-12-23 | 2022-04-22 | 北京市遥感信息研究所 | Method and device for evaluating temperature resolution of infrared remote sensing satellite based on intersection |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112084584A (en) * | 2020-07-30 | 2020-12-15 | 航天东方红卫星有限公司 | Manufacturing method of star sensor support capable of monitoring deformation and deformation measuring method |
| CN112084584B (en) * | 2020-07-30 | 2024-03-15 | 航天东方红卫星有限公司 | Manufacturing method of star sensor bracket capable of monitoring deformation |
| CN112556874A (en) * | 2020-12-29 | 2021-03-26 | 广东精铟海洋工程股份有限公司 | Assembly method of fiber bragg grating distributed sensing device for measuring bearing temperature |
| CN114383736A (en) * | 2021-12-23 | 2022-04-22 | 北京市遥感信息研究所 | Method and device for evaluating temperature resolution of infrared remote sensing satellite based on intersection |
| CN114383736B (en) * | 2021-12-23 | 2023-10-24 | 北京市遥感信息研究所 | Infrared remote sensing satellite temperature resolution assessment method and device based on intersection |
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