CN107314840B - A kind of wing shearing method of real-time based on fiber grating actual measurement strain - Google Patents
A kind of wing shearing method of real-time based on fiber grating actual measurement strain Download PDFInfo
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- CN107314840B CN107314840B CN201710618765.5A CN201710618765A CN107314840B CN 107314840 B CN107314840 B CN 107314840B CN 201710618765 A CN201710618765 A CN 201710618765A CN 107314840 B CN107314840 B CN 107314840B
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- 239000000835 fiber Substances 0.000 title claims abstract description 54
- 238000005259 measurement Methods 0.000 title claims abstract description 46
- 238000010008 shearing Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000004744 fabric Substances 0.000 claims abstract description 21
- 238000012544 monitoring process Methods 0.000 claims abstract description 15
- 230000000694 effects Effects 0.000 claims abstract description 4
- 238000005452 bending Methods 0.000 claims description 41
- 239000013307 optical fiber Substances 0.000 claims description 15
- 238000013461 design Methods 0.000 claims description 7
- 238000009661 fatigue test Methods 0.000 claims description 7
- 230000005284 excitation Effects 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 238000012546 transfer Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 claims description 2
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- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims 1
- 230000007774 longterm Effects 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
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- 238000005457 optimization Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L1/00—Measuring force or stress, in general
- G01L1/24—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet
- G01L1/242—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet the material being an optical fibre
- G01L1/246—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet the material being an optical fibre using integrated gratings, e.g. Bragg gratings
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Abstract
The present invention provides a kind of wing shearing method of real-time based on fiber grating actual measurement strain, the specific steps of which are as follows: one: cloth pastes fiber-optic grating sensor on wing；Two: obtaining the strain of fiber-optic grating sensor actual measurement；Three: analysis wing shears state；Four: Wings shearing；Pass through above step, the present invention is attached to the strain data of the actual measurement of the fiber grating on wing using cloth, the shearing of wing is calculated, reach and has only utilized the strain data of fiber grating actual measurement, in the case where the other informations such as no wing loads and wing structure, the effect that wing shearing can be obtained solves the strain data for relying solely on fiber grating actual measurement and the practical problem of the shearing progress real-time monitoring to wing.
Description
Technical field:
The present invention provides a kind of wing shearing method of real-time based on fiber grating actual measurement strain, and in particular to utilizes
The actual measurement strain obtained measured by fiber grating obtains the shearing of wing, the real-time monitoring of wing shearing is realized, suitable for taking
Labour aircraft is strained using the actual measurement obtained measured by fiber grating to aircraft machine on the aircraft in the full machine fatigue test of aircraft
Shearing suffered by the wing carries out real-time monitoring, belongs to test field of measuring technique.
Background technique:
Aircraft wing is one of important feature component of aircraft, is the key factor for ensureing aircraft safety flight.In aircraft
Life cycle management in, aircraft wing can undergo specific load history, this load history be determine aircraft wing service life
Key factor, and the shearing of aircraft wing is then the important component of wing loads course.Therefore, to suffered by aircraft wing
Shearing carry out real-time monitoring, obtain single rack aircraft wing shearing load history, be the loaded log of reality for establishing aircraft
Key is advantageously implemented the health control of aircraft, while can further instruct the optimization design of aircraft wing.Currently, China
There are no long-term, the real time on-line monitoring of shearing suffered by the wing realized to military service aircraft, existing progress wing loads researchs
Method, be the monitoring method based on foil gauge, this method can only realize the Short-Term Monitoring of individual aircrafts, and measuring device
Complexity, calibration process is cumbersome, and reliability is low, cannot all demarcate to each frame military service aircraft, can not achieve it is long-term to aircraft,
The monitoring of real-time online.And fiber-optic grating sensor has high sensitivity, small in size, multimetering, corrosion-resistant, electromagnetism interference
The features such as ability is strong can realize long-term to aircraft wing institute bending moment, real-time online monitoring using fiber grating.
Summary of the invention:
One, purpose
By force using fiber-optic grating sensor high sensitivity, small in size, multimetering, corrosion-resistant, anti-electromagnetic interference capability etc.
Feature obtains the actual measurement strain data of wing.Also, only using the strain data of fiber grating actual measurement, in no wing loads
In the case where the other informations such as wing structure, the shearing of wing is obtained.This method is simple and easy, may be implemented to fly to being on active service
The machine and shearing suffered by the wing of the aircraft in the full machine fatigue test of aircraft is long-term, monitoring of real-time online, is established each
The independent loaded log of airplane, provides for its life prediction and accurately enters, and realizes the health control to aircraft, on the one hand
Reference frame is provided for the determination in aircraft maintenance period, aircraft safety is ensured, on the other hand can further instruct the optimization of aircraft
Design.
Two, technical solution
A kind of wing based on fiber grating actual measurement strain of the present invention shears method of real-time, the specific steps are as follows:
Step 1: cloth pastes fiber-optic grating sensor on wing；
In aerofoil surface, perpendicular to the direction of fuselage along the rigid axis direction of wing or along wing, cloth pastes the optical fiber light of n point
Gate sensor measuring point；
Step 2: the strain of fiber-optic grating sensor actual measurement is obtained；
When aircraft is in practical flight or in the full machine fatigue test of aircraft, fiber-optic grating sensor demodulated equipment is utilized
Acquisition and record optical fiber grating signal, can obtain the peak wavelength signal λ of fiber-optic grating sensor, by this peak wavelength signal λ
Be converted to the strain value ε of measuring point, that is, the strain of fiber-optic grating sensor actual measurement；
Step 3: analysis wing shears state；
Wing can simplify to be fixed on the cantilever design on fuselage, the real load and aircraft that aircraft is awing subject to
The load for the multipoint excitation being subject in full machine fatigue test can be equivalent to the load p in the heart in wing pressure；Again by wing
It is reduced to paste the cantilever beam in direction along fiber-optic grating sensor cloth, presses the heart and load p in conjunction with wing, it is available along this direction
Wing bending moment is the straight line for having slope, and the shearing of wing is the slope of this skew lines of wing bending moment；
Step 4: Wings shearing；
It is different in the case where being the straight line with slope along fiber-optic grating sensor cloth patch direction wing bending moment
The wing bending moment in section has certain proportionate relationship, meanwhile, the actual measurement strain data measured is respectively multiplied by respective system
Proportionate relationship having the same after number, also, this proportionate relationship is related with point position.Using above mentioned proportionate relationship,
The slope of this skew lines of wing bending moment can be calculated, this slope is exactly the shearing of wing.
By above step, it is attached to the strain data of the actual measurement of the fiber grating on wing using cloth, wing is calculated
Shearing has reached only using the strain data of fiber grating actual measurement, in the other informations such as no wing loads and wing structure
In the case of, it will be able to obtain wing shearing effect, solve rely solely on fiber grating actual measurement strain data and to wing
Shearing carry out real-time monitoring practical problem.
Wherein, at " fiber-optic grating sensor " described in step 1, refer to one kind by extraneous strain variation to optical fiber
Bragg wavelength is modulated to obtain the wavelength modulation fiber sensor of sensor information.
Wherein, " the fiber-optic grating sensor demodulated equipment " described in step 2, refers to a kind of pair of optical fiber grating sensing
The equipment that device center reflection wavelength signal is resolved.
Wherein, " this peak wavelength signal λ is converted to the strain value ε of measuring point " described in step 2, it is specific to make
Method is as follows:
If the initial center wavelength of fiber-optic grating sensor is λ0, the central wavelength measured is λ, then has strainWherein β is the strain sensitive coefficient of optical fiber.
Wherein, " analysis wing shears state " described in step 3, the specific practice is as follows:
Wing is reduced to be fixed on the cantilever design on fuselage, by load-transfer mechanism suffered on wing be wing pressure in the heart
Load p, then wing can be regarded as to the cantilever beam structure by some concentrated forces in end；
So the shearing state of wing, so that it may which equivalent being seen as is shearing of the end by the cantilever beam of some concentrated forces
State, it is, wing bending moment is the straight line for having slope, shearing is equal to the invariable of wing pressure heart pulling force
Amount, meanwhile, shearing is also equal to the slope of wing bending moment skew lines.
Wherein, " the Wings shearing " described in step 4, the specific practice is as follows:
It is the straight line for having slope according to wing bending moment, wing bending moment and the strain measured have following relationship:
Mi=Kiεi
The proportionate relationship for establishing the wing bending moment between different cross section is as follows:
M1:M2:M3:……:Mn
=K1ε1: K2ε2: K3ε3: ...: Knεn
=(x+a1):(x+a2):(x+a3):……:x
Wherein, x is distance of the wing pressure heart to n-th of fiber grating measuring point, a1、a2、a3Deng being the 1st optical fiber light respectively
Grid measuring point is to the distance of n-th of fiber grating measuring point, the distance of the 2nd fiber grating measuring point to n-th of fiber grating measuring point,
3 fiber grating measuring points to n-th of fiber grating measuring point distance, and and so on；
The strain value obtained using measurement, the ratio equation of solution above, so that it may the value of n k-factor is obtained, to utilize
The wing bending moment at different interfaces can be calculated by measuring obtained strain, and the slope of wing bending moment skew lines, be sought to
The shear value arrived.
Three, advantage and effect
(1) it the present invention is based on the shearing that fiber-optic grating sensor actual measurement strain carrys out real-time monitoring wing, may be implemented to clothes
It uses as a servant aircraft and the shearing suffered by the wing of the aircraft in the full machine fatigue test of aircraft carries out long-term, real-time online monitoring,
Solve the problems, such as that traditional foil gauge measurement method cannot long-term, real-time online measuring.It is advantageously implemented and establishes each airplane
The loaded log of independence, and further aircraft optimizing research.
(2) present invention only using fiber grating actual measurement strain data, no wing loads and wing structure etc. other
In the case where information, it will be able to obtain the shearing of wing.This method is simple and easy, can be on the aircraft that each frame actually uses
It is general, to realize that shearing suffered by the wing to each frame military service aircraft carries out long-term, real-time online monitoring.
Detailed description of the invention
Fig. 1 the method for the invention general flow chart.
Fig. 2 present invention pastes fiber-optic grating sensor schematic diagram along the rigid axis cloth of wing.
Fig. 3 present invention pastes fiber-optic grating sensor schematic diagram along vertical fuselage direction cloth.
Fig. 4 wing of the present invention presses heart position view 1.
Fig. 5 wing of the present invention presses heart position view 2.
Fig. 6 wing pressure heart of the present invention and equivalent pressure heart load p schematic diagram.
Fig. 7 present invention shearing and wing bending moment status diagram.
Serial number, symbol, code name are described as follows in figure:
The rigid axis X of wing refers to that the rigid heart line of wing is formed by the axis along wing.
Course refers to that aircraft flight direction is also the direction of airframe.
The wing pressure heart is the position of all load-transfer mechanisms on wing.
Wing pressure heart pulling force P refers to equivalent load of all load on wing at wing pressure heart position.
Specific embodiment
A kind of aircraft wing based on fiber grating actual measurement strain provided by the invention shears method of real-time, sees Fig. 1
It is shown, it is realized especially by following steps:
Step 1: cloth pastes fiber-optic grating sensor on wing；
In aerofoil surface, the fiber-optic grating sensor measuring point of n point is pasted along the rigid axis direction cloth of wing, cloth is attached to close always
In the end of wing, as shown in Figure 2；Alternatively, in aerofoil surface along the optical fiber grating sensing for pasting n point perpendicular to fuselage direction cloth
Device measuring point, cloth is attached to the end close to wing always, as shown in Figure 3；
Wherein, fiber-optic grating sensor either is pasted along the rigid axis direction of wing or along perpendicular to fuselage direction cloth, finally
The position of one or several fiber-optic grating sensor measuring points all can press heart position close to wing, as shown in Figure 4 and Figure 5；
Step 2: the strain of fiber-optic grating sensor actual measurement is obtained；
Firstly, on connection fiber-optic grating sensor to fiber-optic grating sensor demodulated equipment, the grating when not straining
The central wavelength of optical fiber is λ0, acquire and the peak wavelength of the fiber-optic grating sensor of record be λ；
Secondly, the peak wavelength of fiber-optic grating sensor depends on fiber grating periods lambda and effective refractive index neff, strain
It can cause fiber grating periods lambda and effective refractive index neffThe change of the two parameters, so as to cause fiber grating peak value wave
Long change has following relationship between them
ε=(λ-λ0)/1.22
Utilize above formula, so that it may which the λ for obtaining real-time measurement is converted to the actual measurement strain value ε of measuring point；
Step 3: analysis wing shears state；
Fuselage is seen as to the support of wing, that wing, which can simplify, regards the cantilever design being fixed on fuselage as；Fly
The load for the multipoint excitation that the real load and aircraft that machine is awing subject to are subject in full machine fatigue test, can be equivalent
For the load p in wing pressure in the heart, as shown in Figure 6；
Regard wing as cantilever beam structure by some concentrated forces in end, then the shear diagram of wing and wing bending moment figure be such as
Shown in Fig. 7；So wing bending moment state, is seen as being bending Moment of the end by the cantilever beam of some concentrated forces with regard to equivalent,
Be exactly, wing bending moment be one have slope straight line, shearing be it is invariable, equal to wing pressure the heart pulling force, while
Equal to the slope of this skew lines of wing bending moment；
Step 4: Wings shearing；
Wing bending moment is the straight line for having slope.The strain of wing bending moment and measurement has following relationship
Mi=Kiεi
The wing bending moment in i-th of section is equal to the strain in i-th of section multiplied by a coefficient；
After finding out wing bending moment by upper relation of plane, it can determine that shearing is
Formula above, molecule are the difference of two neighboring wing bending moment, and denominator is between two neighboring wing bending moment section
Distance.
When aerofoil surface cloth paste n point fiber-optic grating sensor, as shown in Figures 2 and 3, in conjunction with wing bending moment with cut
Power state analysis, can establish following equation
M1:M2:M3:……:Mn
=K1ε1: K2ε2: K3ε3: ...: Knεn
=(x+a1):(x+a2):(x+a3):……:x
Wherein, x is distance of the wing pressure heart to n-th of fiber grating measuring point, a1、a2、a3Deng being the 1st optical fiber light respectively
Grid measuring point is to the distance of n-th of fiber grating measuring point, the distance of the 2nd fiber grating measuring point to n-th of fiber grating measuring point,
3 fiber grating measuring points to n-th of fiber grating measuring point distance, and and so on；
Above equation, since the value of x is unknown, so can not solve.
The analysis that data are carried out to the strain data for the n point that measurement obtains, when the wing pressure heart is in fiber grating point position
Near, the strain that the fiber grating measuring point measurement at this position obtains can be especially small compared with the strain value of other positions measuring point,
Close to 0；Fiber grating when the wing pressure heart is moved near optical fibre optical fibre grating point position, at this position at this time
The strain that measuring point measurement obtains can be especially small compared with the strain value of the measuring point at other moment at this position, close to 0.To measurement
Obtained n point strain is analyzed, and finds the measuring point m that data have such feature, then above equation becomes following form
M1:M2:M3:……:Mm
=K1ε1: K2ε2: K3ε3: ...: Kmεm
=a1:a2:a3:……:am
At this time, it is assumed that value be 1, then above equation can solve as the form of wing bending moment equation below
Wherein, K1、K2And K3Until Km-1It is the constant come out by above method solution；
After wing bending moment equation more than obtaining, so that it may which the strain data of fiber grating actual measurement strain is substituted into this
Equation can then find out the wing bending moment of real-time different cross section, recycle following formula
By the wing bending moment acquired between adjacent sections at a distance from substitute into above formula, then can find out real-time wing shearing.
Claims (6)
1. a kind of wing based on fiber grating actual measurement strain shears method of real-time, it is characterised in that: specific step is as follows:
Step 1: cloth pastes fiber-optic grating sensor on wing；
In aerofoil surface, perpendicular to the direction of fuselage along the rigid axis direction of wing or along wing, cloth pastes the fiber grating biography of n point
Sensor measuring point；
Step 2: the strain of fiber-optic grating sensor actual measurement is obtained；
When aircraft is in practical flight and in the full machine fatigue test of aircraft, the acquisition of fiber-optic grating sensor demodulated equipment is utilized
With record optical fiber grating signal, the peak wavelength signal λ of fiber-optic grating sensor can be obtained, this peak wavelength signal λ is converted
For the strain value ε of measuring point, that is, the strain of fiber-optic grating sensor actual measurement；
Step 3: analysis wing shears state；
Wing is reduced to be fixed on the cantilever design on fuselage, and the real load and aircraft that aircraft is awing subject to are tired in full machine
The load for the multipoint excitation being subject in labor test, is all equivalent to the load p in the heart in wing pressure；Wing is reduced to along optical fiber again
Grating sensor cloth pastes the cantilever beam in direction, presses the heart and load p in conjunction with wing, can obtain along the wing bending moment in this direction being one
Straight line with slope, and the shearing of wing is the slope of this skew lines of wing bending moment；
Step 4: Wings shearing；
In the case where being the straight line with slope along fiber-optic grating sensor cloth patch direction wing bending moment, different cross section
Wing bending moment have a scheduled proportionate relationship, meanwhile, the actual measurement strain data measured is respectively multiplied by respective coefficient
Proportionate relationship having the same afterwards, also, this proportionate relationship is related with point position；Utilize above mentioned proportionate relationship, energy
The slope of this skew lines of wing bending moment is calculated, this slope is exactly the shearing of wing；
By above step, it is attached to the strain data of the actual measurement of the fiber grating on wing using cloth, the shearing of wing is calculated,
Reach only using a strain data for fiber grating actual measurement, the no wing loads and wing structure and other information the case where
Under, it will be able to the effect for obtaining wing shearing solves the strain data for relying solely on fiber grating actual measurement and cuts to wing
The practical problem of power progress real-time monitoring.
2. a kind of wing based on fiber grating actual measurement strain according to claim 1 shears method of real-time, special
Sign is: in fiber-optic grating sensor described in step 1, referring to one kind by extraneous strain variation to optical fiber Bragg wave
Long modulates to obtain the wavelength modulation fiber sensor of sensor information.
3. a kind of wing based on fiber grating actual measurement strain according to claim 1 shears method of real-time, special
Sign is: the fiber-optic grating sensor demodulated equipment described in step 2, refers to that a kind of pair of fiber-optic grating sensor center is anti-
Penetrate the equipment that wavelength signals are resolved.
4. a kind of wing based on fiber grating actual measurement strain according to claim 1 shears method of real-time, special
Sign is: the strain value ε that this peak wavelength signal λ is converted to measuring point described in step 2, the specific practice are as follows: setting
The initial center wavelength of fiber-optic grating sensor is λ0, the central wavelength measured is λ, then has strainWherein
β is the strain sensitive coefficient of optical fiber.
5. a kind of wing based on fiber grating actual measurement strain according to claim 1 shears method of real-time, special
Sign is: the analysis wing described in step 3 shears state, and the specific practice is as follows:
Wing is reduced to be fixed on the cantilever design on fuselage, is the load in wing pressure in the heart by load-transfer mechanism suffered on wing
Wing is then regarded as the cantilever beam structure by some concentrated forces in end by lotus P；
So the shearing state of wing, is seen as being shearing state of the end by the cantilever beam of some concentrated forces, also with regard to equivalent
It is that wing bending moment is the straight line for having slope, shearing is equal to the invariable amount of wing pressure heart pulling force, meanwhile, it cuts
Power is also equal to the slope of wing bending moment skew lines.
6. a kind of wing based on fiber grating actual measurement strain according to claim 1 shears method of real-time, special
Sign is: the Wings shearing described in step 4, the specific practice are as follows:
It is the straight line for having slope according to wing bending moment, wing bending moment and the strain measured have following relationship:
Mi=Kiεi
The proportionate relationship for establishing the wing bending moment between different cross section is as follows:
M1:M2:M3:……:Mn
=K1ε1: K2ε2: K3ε3: ...: Knεn
=(x+a1):(x+a2):(x+a3):……:x
Wherein, x is distance of the wing pressure heart to n-th of fiber grating measuring point, a1、a2、a3It is the 1st fiber grating measuring point respectively
Distance, the distance of the 2nd fiber grating measuring point to n-th of fiber grating measuring point, the 3rd light to n-th of fiber grating measuring point
Fine grating measuring point to n-th of fiber grating measuring point distance, and and so on；Using the obtained strain value of measurement, solution is above
Ratio equation just obtains the value of n k-factor, thus curved using the wing that the strain that measurement obtains can calculate different interfaces
Square, and the slope of wing bending moment skew lines, the shear value sought to.
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| CN113219894B (en) * | 2021-04-12 | 2022-12-13 | 成都飞机工业（集团）有限责任公司 | Aircraft tool state real-time monitoring method based on three-dimensional force sensor |
| CN116388859B (en) * | 2022-10-31 | 2023-08-18 | 广东电网有限责任公司中山供电局 | Optical fiber state monitoring data acquisition device, method, equipment and medium |
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| CN106477070A (en) * | 2015-10-14 | 2017-03-08 | 北京信息科技大学 | A kind of wing external applied load method of real-time based on fiber bragg grating sensor |
| CN105352444A (en) * | 2015-10-26 | 2016-02-24 | 南京航空航天大学 | Plate structure deformation distributed optical fiber calculation method based on double integrating principle and application thereof |
| CN205537696U (en) * | 2016-04-06 | 2016-08-31 | 江苏建筑职业技术学院 | Steel construction strategic locations stress and strain monitoring and early warning system |
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