CN110261017A - Aircaft configuration load monitoring system based on optical fiber sensing technology - Google Patents
Aircaft configuration load monitoring system based on optical fiber sensing technology Download PDFInfo
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- CN110261017A CN110261017A CN201910342212.0A CN201910342212A CN110261017A CN 110261017 A CN110261017 A CN 110261017A CN 201910342212 A CN201910342212 A CN 201910342212A CN 110261017 A CN110261017 A CN 110261017A
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- 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
- G01B11/18—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge using photoelastic elements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0052—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to impact
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
- G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
- G01P15/03—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses by using non-electrical means
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- Length Measuring Devices By Optical Means (AREA)
Abstract
The invention discloses a kind of aircraft landing gear structures load on-line monitoring system based on optical fiber sensing technology, comprising: multiple optical fibre grating acceleration sensors are arranged on the C font bracket being arranged on landing gear shock strut；Multiple fiber Bragg grating strain sensors are arranged in the hound position of undercarriage；Fiber Bragg grating (FBG) demodulator is connect, for obtaining sensing data and being demodulated by optical fiber with multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors；Data processing module is connect with the fiber Bragg grating (FBG) demodulator, for the sensing data after the demodulation of storage and management fiber Bragg grating (FBG) demodulator output；Module is monitored on-line, for estimating the remaining life of undercarriage.
Description
Technical field
The present invention relates to a kind of health monitoring techniques applied to aircraft landing gear structures load in aviation field, specifically
Say it is a kind of aircraft landing gear structures load on-line monitoring system based on optical fiber sensing technology.
Background technique
Undercarriage is for taking off, landing, ground taxi and parks as aircraft important safety functional component
Important support system, function served as bridge is played between airframe and wheel brake system, the superiority and inferiority of structural behaviour is direct
Affect the performance and safety when taking off, landing.Since structure is complicated for undercarriage itself, there are many non-linear factor, rising
Fly to bear biggish shock loading in landing mission, is the main load-carrying member of aircraft, it is absorbed and dissipation aircraft is landing
And the impact energy formed in taxiing procedures with ground, guarantee aircraft during ground motion using safe, and by accidental
The influence of factor is bigger, therefore the use condition of undercarriage is more severe compared with other components of aircaft configuration.Undercarriage is once
Damage and failure will seriously jeopardize flight safety.Therefore, it is necessary to which the load to undercarriage carries out real-time monitoring, and with this
Judge the configuration state of undercarriage, estimates remaining life, provide maintenance foundation for maintenance personal.
It is extremely intensive for the use of various kinds of sensors in aerospace field.And the sensitivity to it, volume and again
Amount has higher requirement.The number of sensors needed for the landing gear structure load monitoring of a frame aircraft is huge, therefore
Size, the weight of sensor just become particularly important.Currently, the load monitoring method based on resistance strain gage is undercarriage
The important technical of structural loads monitoring.It is found during being directed to the load monitoring of undercarriage key position, resistance
Often structure is complicated for the strain region of foil gauge monitoring, narrow space.Which results in this region inner sensor conducting wires various, conducting wire
Between interfere with each other, and because of the various weight for increasing structure of conducting wire.Meanwhile system is taken up too much space, power supply is complicated, causes
Large volume, high energy consumption and it is complicated for operation the problems such as.In addition, undercarriage during takeoff and landing all can be by extremely tight
The influence of cruel environment.Existing tradition electrical sensor, being easy to be limited by environmental factor cannot be in extreme flying ring
It is worked normally under border, this necessarily will affect the accuracy of undercarriage load monitoring, lead to catastrophic failure.
Currently, existing monitoring method is mainly monitored using electrical sensor, due to electrical sensor itself vulnerable to
Electromagnetic interference does not have explosion prevention function and the operational difficulties in rugged environment, difficult using networking when multimetering, so that letter
Number timely processing it is limited.In addition, with sensitivity, not high, non-refractory, corrosion resistance are poor using electrical sensor measurement
The disadvantages of.
Summary of the invention
To solve the above-mentioned problems, the present invention proposes that a kind of aircraft landing gear structures load based on optical fiber sensing technology exists
Line monitoring system can work in harsh environment, and by the indirect measurement to load and deformation, damage in aircraft landing gear structures
Timely early warning when hurting serious, it is ensured that the purpose of flight safety.
The technical solution adopted by the present invention to solve the technical problems is:
A kind of aircraft landing gear structures load on-line monitoring system based on optical fiber sensing technology is provided, comprising:
Multiple optical fibre grating acceleration sensors are arranged on the C font bracket being arranged on landing gear shock strut；Record
Initial wavelength λ under the acceleration transducer light condition of each measuring point placement1, the real-time wavelength of real-time monitoring acceleration transducer
λ2；
Multiple fiber Bragg grating strain sensors are arranged in the hound position of undercarriage；Fiber Bragg grating strain sensor is empty
Initial wavelength λ under load state3, real-time monitoring fiber Bragg grating strain sensor real-time wavelength λ4；
Fiber Bragg grating (FBG) demodulator passes through with multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors
Optical fiber connection, for obtaining sensing data and being demodulated；Calculating real time acceleration size is λ2-λ1/ K, K add for fiber grating
The sensitivity coefficient of velocity sensor, calculating strain size in real time is λ4-λ3/ K', wherein K ' is fiber Bragg grating strain sensor
Sensitivity coefficient
Data processing module is connect with the fiber Bragg grating (FBG) demodulator, defeated for storage and management fiber Bragg grating (FBG) demodulator
The sensing data after demodulation out；
It monitors module on-line, for calculating Aircraft Load according to the sensing data after demodulation, and is established with flight parameter
Correlation connection, obtains the loading spectrum of undercarriage under different flight parameters, and bond material fatigue behaviour σ-N curve, and estimation flies
The remaining life of machine undercarriage.
Above-mentioned technical proposal is connect, fibre optic strain sensor is two-dimensional fiber bragg grating strain transducer, the two-dimensional fiber bragg grating
Strain transducer includes two strain arms in vertical direction.
Above-mentioned technical proposal is connect, optical fiber acceleration transducer is three-dimensional fiber grating acceleration transducer, three-dimensional acceleration
Sensor is to integrate three one-dimensional acceleration sensors on the basis of one-dimensional flexible hinge grating acceleration transducer structure
One, while obtaining the vibration signal in undercarriage position course, lateral, vertical three directions.
Above-mentioned technical proposal is connect, C font bracket is fixed on landing gear shock strut by epoxide-resin glue.
Above-mentioned technical proposal is connect, optical fibre grating acceleration sensor is fixed on C font by bolt or epoxide-resin glue
On bracket.
Above-mentioned technical proposal is connect, fiber Bragg grating strain sensor is pasted onto the hound of undercarriage by epoxy resin glue
On, and accurately it is fixedly mounted on according to measurement direction the surface at undercarriage hound position.
Above-mentioned technical proposal is connect, multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors are in array
Symmetry arrangement.
Connect above-mentioned technical proposal, the tail optical fiber of multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors
Picked out by a terminal box.
Above-mentioned technical proposal is connect, wherein the first, second one-dimensional grating acceleration transducer includes pedestal, two mass blocks
And fiber grating, it is connected by flexible hinge between two mass blocks, is carved with groove on two mass blocks, fiber grating is fixed
In groove, the perpendicular placement in the same plane of the fiber grating of the first, second one-dimensional grating acceleration transducer；3rd 1
Tieing up grating acceleration transducer includes two support bases and fiber grating, is all provided on two support bases fluted, and fiber grating is solid
It is scheduled in groove；The fiber grating of third one-dimensional grating acceleration transducer and the first, second one-dimensional grating acceleration transducer
Fiber grating in the same plane, and shape is at a certain angle.
Above-mentioned technical proposal is connect, the fiber grating series connection of three one-dimensional grating acceleration transducers is over the same fiber.
The beneficial effect comprise that: fibre optic strain sensor and optical fiber acceleration transducer are formed one by the present invention
A organic whole network settings are on undercarriage, by the indirect measurement to load and deformation, to undercarriage
The acceleration information of shock strut and the stress data of hound are surveyed when land, to judge the shape of aircraft landing gear structures
State, realization carry out real-time monitoring to the structural loads of undercarriage, the timely early warning when aircraft landing gear structures damage is serious,
Ensure the purpose of flight safety.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples, in attached drawing:
Fig. 1 is that the aircraft landing gear structures load on-line monitoring system based on optical fiber sensing technology of the embodiment of the present invention shows
It is intended to；
Fig. 2 is undercarriage of embodiment of the present invention Sensor layout drawing；
Fig. 3 is two dimensional optical fiber of embodiment of the present invention strain transducer structure chart；
Fig. 4 is three-dimensional fiber grating acceleration transducer of embodiment of the present invention structure chart；
Fig. 5 is C of embodiment of the present invention font supporting structure schematic diagram；
Fig. 6 is (FBG) demodulator of embodiment of the present invention working principle structure chart.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that described herein, specific examples are only used to explain the present invention, not
For limiting the present invention.
The present invention is based in the aircraft landing gear structures load on-line monitoring system of optical fiber sensing technology, due to Fibre Optical Sensor
Device itself has electromagnetism interference, intrinsic explosion-proof, can work in harsh environment, and measurement sensitivity height and precision are high, is easy to shape
The advantages that at distributed measurement.Strain can mutually be merged using this monitoring system with acceleration signal, aircraft landing is provided
True and reliable load and deformation data in journey are subtracted when landing to undercarriage by the indirect measurement to load and deformation
The stress data of the acceleration information and hound that shake pillar is surveyed, and to judge the state of aircraft landing gear structures, is realized
Real-time monitoring is carried out to the structural loads of undercarriage, the timely early warning when aircraft landing gear structures damage is serious, it is ensured that fly
The purpose of row safety.
The present invention relates to a kind of aircraft landing gear structures load on-line monitoring system based on optical fiber sensing technology, such as Fig. 1
Shown, the composition of this system mainly includes fibre optic strain sensor, optical fiber acceleration transducer, fiber Bragg grating (FBG) demodulator, data
Processing module and on-line checking module.By disposing sensor in undercarriage key structure, building is used for aircraft takeoffs and landings
The sensor network of frame structure monitoring realizes the real-time monitoring to operating conditions such as structural damage, fatigue, impacts；Utilize data processing
System is analyzed and processed collected data, and realization shows aircraft landing gear structures load and vibration data and structure is strong
The assessment of health state.Monitoring system realization flies in landing mission to aircraft landing gear structures integrality, stress deformation situation
Real-time monitoring is carried out, and carries out structural damage judgement, whether landing gear structure material pieces reach operating limit, and being reached with this ensures
The purpose of flight safety.Arranged in the embodiment of the present invention four strain transducers 1,2,3,4 and two acceleration transducers 5,
6.Fiber Bragg grating strain sensor is attached at left and right sides of undercarriage hound, monitors the stress variation of both direction, optical fiber respectively
Grating acceleration transducer is fixed on the maximum point of shock strut stress, it can monitor the acceleration of three loading directions simultaneously
Variation, as shown in Figure 1, sharing 6 monitoring points on undercarriage, they are connect between (FBG) demodulator with long range optical cable.
Further, optical fibre grating three-dimensional acceleration sensor arrangement is on the shock strut of undercarriage.When aircraft is in
When Asymmetric landing state, the main landing gear impact force suffered by that time of landing to make impact with the ground at first can gradually increase
Greatly, it not only will affect the center of gravity of airplane in the speed of vertical direction, also results in main landing gear and becoming around fuselage rotation occurs
Gesture.The trend is to receive lateral load when landing due to undercarriage.Main landing gear is around the generated rotation of the lateral force
Movement and the vertical load that is influenced by the center of gravity of airplane of vertical direction undercarriage, be all influence key factor that aircraft safety lands it
One.In addition to lateral load and vertical load, aircraft is from moment of landing to stopping, and entire motion process undercarriage is also subject to aircraft
Forward course load.As undercarriage primary load bearing component, shock strut is primarily subjected to the load in these three directions.Therefore to subtracting
The acceleration monitoring for shaking three directions of pillar becomes the main monitoring direction of this system.
Further, when measuring acceleration, acceleration transducer installs correctness, and can be not only directly related to obtain
True, valuable measurement data is taken, but also can avoid the incorrect damage installed and cause sensor.For three-dimensional fiber
Grating acceleration transducer, if be affixed directly on the shock strut of undercarriage, since the shock strut of undercarriage is a kind of
Round bar, may result in sensor mounting location has large error, and then measuring signal is caused to have error.So in order to accurately
Arrangement installation and upright placement sensor, as shown in figure 5, the invention patent installs acceleration transducer using C font bracket.
Sensor is installed on C font bracket using steel bolt first, then C font bracket is installed on the strut of undercarriage.In this way
Mounting means can fully ensure that the frequency range and temperature range of sensor, and its is fixed, and impact resistance ability is strong.It is logical
Often before bolt is tightened, a thin layer lubricating grease is coated on mounting surface, to increase installation rigidity.Due to the impact of undercarriage
Acceleration load is larger, so influence of the C font bracket to vibration transmitting is negligible.
As shown in Fig. 2, multiple optical fibre grating acceleration sensors, are arranged in the C font being arranged on landing gear shock strut
On bracket.C font bracket is as shown in figure 5, optical fibre grating acceleration sensor is placed on the top of C font bracket according to actual measurement
Portion position, and fixed by the way of steel bolt.It include in [fixed frame of type and being fixed on the fixed frame on C font bracket
On the support frame in C font.Multiple fiber Bragg grating strain sensors are arranged in the hound position of undercarriage.
As shown in figure 3, fibre optic strain sensor is two-dimensional fiber bragg grating strain transducer, including two in vertical direction
Strain arm.Fibre optic strain sensor can measure the strain signal of two orthogonal directions on undercarriage hound simultaneously.
Sensor structure is mainly made of FBG32 and pedestal 31, and the grid region of grating is affixed directly in the groove of base interior setting, base
Seat is fixed in measurand, and entire being made of one of sensor core structure, material is stainless steel.
Further, fiber Bragg grating strain sensor is mainly arranged on the hound of undercarriage, for the standard for guaranteeing measurement
True property, sensor should be two sides on hound and be arranged symmetrically, as shown in Figure 2.Hound is as connection airframe and rises and falls
The key component of frame.And aircraft landing is a dynamic impact process, as aero tyre is grounded undercarriage, landing load is to pass through
Tire touchdown point and two, wheel center position transmit the force to hound, and strut divides mainly by both direction power at this time
Be not shock strut to the support force of strut, the gravity of strut itself and pull rod to the pulling force of hound, these three are main
Power can make hound generate flexible deformation.The deformation is related with the size of different directions power when hound material itself, landing.When
When the deformation exceeds the elastic deformation of the hound, strut may be cracked, or even be broken, and cause the great peace of aircraft
Full accident.The actual measurement of strut stress when therefore, to aircraft landing is the important means for improving undercarriage service life.
Further, fiber Bragg grating strain sensor is pasted onto the two of undercarriage hound by epoxy resin glue
Fiber Bragg grating strain sensor is tightly attached in strut surfaces, wants before stickup after when stickup should be noted that determining good position by side
Remove oxide layer above as far as possible, simple grinding process is carried out to tested region surface.Secondly binder will adapt to undercarriage
The complex environment of landing lightly intersects polishing on surface with fine sandpaper, until the lines on its surface is uniform clear and legible is
Only, then with alcohol by surface clean for several times, then fiber Bragg grating strain sensor is accurately fixedly mounted according to measurement direction
On undercarriage hound surface.It comes into full contact with it with hound surface, reduces the slippages of ess-strain.
Optical fiber acceleration transducer is three-dimensional fiber grating acceleration transducer, and three dimension acceleration sensor includes three collection
Integral one-dimensional acceleration sensor, three one-dimensional acceleration sensors obtain simultaneously undercarriage position course, it is lateral,
The vibration signal in vertical three directions.Wherein the first, second one-dimensional grating acceleration transducer includes pedestal, two mass blocks
And fiber grating, it is connected by flexible hinge between two mass blocks, is carved with groove on two mass blocks, fiber grating is fixed
In groove, the perpendicular placement in the same plane of the fiber grating of the first, second one-dimensional grating acceleration transducer；3rd 1
Tieing up grating acceleration transducer includes two support bases and fiber grating, is all provided on two support bases fluted, and fiber grating is solid
It is scheduled in groove；The fiber grating of third one-dimensional grating acceleration transducer and the first, second one-dimensional grating acceleration transducer
Fiber grating in the same plane, and shape is at a certain angle.
Optical fiber acceleration transducer is three-dimensional fiber grating acceleration transducer, as shown in figure 4, three dimension acceleration sensor
It is made of three one-dimensional flexible hinge grating acceleration transducers, two of them one-dimensional flexible hinge grating acceleration transducer
Structure it is identical, include pedestal 41, flexible hinge 43, mass block 42 and FBG44, pass through flexible hinge between two mass blocks
Connection, pedestal are fixed on the object to be measured.Two one-dimensional flexible hinge grating acceleration transducers can share a pedestal,
One of mass block is shared, being entirely made of one structure.Groove is carved on mass block, FBG is placed in groove, and both ends are logical
Cementing agent is crossed to fix.The perpendicular placement of fiber grating of the two one-dimensional flexible hinge grating acceleration transducers.Another one
Tieing up acceleration transducer includes two support bases and FBG, and one of support base and other two sensor can share a base
It is carved with groove at the top of seat, pedestal and supporting block, FBG is fixed in two grooves.Three one-dimensional sensors share an optical fiber,
It is carved with grating in optical fiber corresponding position.That is three fiber grating series connection are over the same fiber.By three one-dimensional acceleration sensors
It is integrated in the way of Fig. 4, the vibration letter in undercarriage position course, lateral, vertical three directions can be obtained simultaneously
Number.The fiber grating of third one-dimensional flexible hinge grating acceleration transducer is put at an angle with other two fiber grating
It sets.
The tail optical fiber of fiber-optic grating sensor is connect with armored optical cable, then passes through a main cable and high speed fibre (FBG) demodulator
It is connected.High speed (FBG) demodulator converts collected optical signal by photoelectric conversion circuit, and output wavelength voltage signal can pass through
The voltage signal of acquisition is input in data processing module and on-line checking module by USB, and basis is corresponding after carrying out digital filtering
Sensor sensitivity factor strain data and acceleration information is calculated, then directly read in using data processing software
The data file for falling frame load derives the real load size for calculating and finally obtaining according to subsequent mathematical.
Further, aircraft landing gear structures key position load data, undercarriage are collected according to the sensor of deployment
Load measurement generally use the indirect method of measurement, when measuring the load parameter of undercarriage, do not measure directly, but pass through prediction
Correlation between value and strain, acceleration, pressure and the measured value of flight mechanics parameter determines.It is arranged in aircraft landing
Two kinds of signals of fiber-optic grating sensor output acceleration and strain on shock strut and strut, strain signal can be according to stress
Strain is converted into stress with the linear ratio relation of strain, and then obtains the stress spectra of hound；Acceleration signal can pass through
The mean stress and acceleration average energy in certain period of time are calculated, it is corresponding with acceleration average energy to establish mean stress
Relationship discloses the size of stress eventually by acceleration energy, and the stress intensity of undercarriage is finally obtained according to calculating.According to
Obtained stress and flight parameter measured data carries out correlation analysis to flight parameter and obtained stress loading, chooses phase
Load identification parameter of the significant parameter of closing property as dangerous position is established using polynomial function expression formula based on flight
The dangerous position loading spectrum of parameter, obtains the loading spectrum of dangerous position under different flight parameters, on this basis, in conjunction with Miner
Linear cumulative damage principle, and according to material broad sense σ-N surface equation, estimate remaining life.
Further, it according to obtained stress and flight parameter measured data, obtains undercarriage under different flight parameters and endangers
The stress spectra at dangerous position, then it is counted with rain flow method, so that stress spectra is separated into stress amplitude σaAnd stress
Mean value σmMatrix.Then broad sense σ-N surface equation is established, after completing rain-flow counting and establishing broad sense σ-N surface equation, meter
Two-dimentional Miner linear cumulative damage law is directlyed adopt when calculating the service life.Aircraft is determined using measured stress spectrum according to formula (1)
The equivalent service life that main hazard position is risen and fallen under load effect in each flight, is sentenced using determining equivalent service life
Whether the state of disconnected undercarriage is abnormal.
In formula: nijIt flies for one and acts on stress level (σ at different levels on component in rising and fallingai,σmj) recurring number；NijFor
In stress level (σ at different levelsai,σmj) destruction recurring number under independent role；T is that flight is risen and fallen the total (longevity in a typical mission
Life)；D is a constant, is usually taken to be 1.nijIt can directly be obtained from the equal amplitude matrix of rain flow way, NijIt can be from aircraft counter structure
It is acquired in part material broad sense σ-N surface equation.
Optical fiber sensing technology has an intrinsic explosion-proof characteristic with electromagnetism interference, and this system is by fiber Bragg grating strain sensor
It is cascaded with optical fibre grating acceleration sensor and carries out networking, to realize remote distributed on line monitoring.
Fiber Bragg grating (FBG) demodulator is high speed optic fiber grating (FBG) demodulator, has high demodulation speed, high stability, high reliability etc.
Feature, systemic resolution reach 1pm, and typical error is ± 1pm, and worst error is less than ± 2pm, are used for while demodulating 8 Lu Guangxin
Number, wavelength scanning range 50nm.Highest 2000Hz frequency may be implemented for single mode optical fiber grating acceleration transducer.By light
The reflecting light of fiber grating sensor carries out wavelength-division multiplex, makes the grating sensing array reflectance spectrum of different wave length in wavelength domain
Separation, and it is converted into electric signal, digital demodulation is carried out eventually by hardware and software.
Further, the composed structure of fiber grating signal (FBG) demodulator is as shown in Figure 6.Wide spectrum light source output light passes through the ring of light
Shape device is coupled to the bragg grating array of wavelength-division multiplex.The reflected light of bragg grating array is defeated by optical circulator
Exit port is coupled to Integrated Light demultiplexing module, and the narrowband that incident light is demultiplexed into multiple and different wavelength by Optical Demultiplexing module is defeated
Channel out.Each output channel is all coupled to progress photoelectric conversion processing on the detector all the way of photoelectronic detecting array, after conversion
Electric signal be input to multidiameter delay analog to digital conversion circuit with after amplification by filtering light intensity analog signal be converted into digital letter
Number, measured physical quantity, i.e. wavelength data are finally demodulated by digital signal processor.
Further, DC5V power supply is provided to ASE wideband light source first, the continuous spectrum warp issued after wideband light source work
Circulator is crossed, using photoswitch, if measurement one is to be measured can not to use photoswitch, photoswitch is to increase measurement
Channel, achieve the purpose that while measuring multiple FBG reflectance spectrums.The spectral signal for reaching FBG can be due to change to be measured
The drift for causing FBG reflection peak, the spectrum for meeting fiber-optic grating sensor phase-matching condition can be reflected back, be reflected back
The spectrum come enters FBGA, and FBGA converts optical signals into digital signal, is wavelength signals, warp by peak signal shift conversion
It is transferred on computer, the host computer test software that then application is write, is carried out corresponding to be measured by the USB interface on FBGA
Real-time display, the real-time display of device status information, sensor configuration etc..
Fibre optical sensor is connected to same demodulating system by the way of wavelength-division multiplex, convenient for the optical fiber to various different parts
The strain signal and acceleration signal of sensor acquisition distinguish, and facilitate the simplification for realizing digital information processing system.
Sensing probe is separated with signal processing system, and the optical signalling that optical fiber sensing network detects is passed in real time by optical fiber
It is sent to the monitoring control room far from each measuring point of undercarriage, signal processing is carried out, favorably guarantees the safe operation of system,
Optical sensing measures opposite electricity sensing measurement sensitivity with higher simultaneously.
The aircraft landing gear structures load monitoring system connects multiple fibre optical sensors by using wavelength-division multiplex technique
Together, the optical fiber sensing network of composition monitoring each key position structural loads of undercarriage body is to judge undercarriage
The faulted condition of structure, avoids the occurrence of major accident.
In the present embodiment, the data measured on undercarriage according to fiber-optic grating sensor judge landing gear structure
Faulted condition, if service life is reached, in order to prevent the generation of safety accident.For optical fibre grating acceleration sensor,
Record initial wavelength λ under the sensor light condition of each measuring point placement1, the wavelength value that the sensor of real-time monitoring is read is λ2,
So the acceleration magnitude of the measuring point is λ2-λ1/ K, K are the sensitivity of optical fiber raster vibration sensor.For fiber grating strain
Sensor measures its sensitivity coefficient K ' in Laboratory Calibration first, records the initial wavelength λ under sensor light condition3, real
When the wavelength value that reads of the sensor that monitors be λ4, so the strain size of the measuring point is λ4-λ3/ K' can acquire point strain
It is worth size.Thus the load data that fiber-optic grating sensor is exported in Real-time on undercarriage can be calculated out.
Data processing module is connected by the signal output end of signal input part and fiber Bragg grating (FBG) demodulator, for storing and
The signal of management fiber Bragg grating (FBG) demodulator output；The embodiment of the present invention passes through Enterprise Data library software MS SQL Sever-
2000 establish monitor database, and to the collected data of storage and provide data management, inquiry, analysis.
On-line monitoring system is connected by signal input part and the signal output end of data processing system, utilizes data processing
The data of system storage establish three-dimensional model to monitored aircraft landing gear structures, carry out stress, strain, acceleration to data
The monitoring of equal parameters simultaneously feeds back to operator.The structure that on-line monitoring system is combined using C/S and B/S, utilizes 3D modeling skill
Art monitors the real-time load and the health status such as damage and crackle, fatigue life of aircraft landing gear structures.
Fibre optic strain sensor and optical fiber acceleration transducer are formed an organic whole network by the present invention, are had anti-
It the features such as electromagnetic interference, anticorrosive, high temperature resistant, explosion-proof, bandwidth, low, precision is higher loss, successfully solves aircraft and is flying
Sensor big problem affected by environment in the process, by the variation of real time on-line monitoring aircraft landing gear structures load, so that
Operator can accurately observe and judge the state of aircraft landing gear structures damage, to effectively improve undercarriage knot
The safety of structure, avoids the occurrence of major accident.
It should be understood that for those of ordinary skills, it can be modified or changed according to the above description,
And all these modifications and variations should all belong to the protection domain of appended claims of the present invention.
Claims (10)
1. a kind of aircraft landing gear structures load on-line monitoring system based on optical fiber sensing technology characterized by comprising
Multiple optical fibre grating acceleration sensors are arranged on the C font bracket being arranged on landing gear shock strut；Record is each
Initial wavelength λ under the acceleration transducer light condition of measuring point placement1, the real-time wavelength λ of real-time monitoring acceleration transducer2；
Multiple fiber Bragg grating strain sensors are arranged in the hound position of undercarriage；Fiber Bragg grating strain sensor zero load shape
Initial wavelength λ under state3, real-time monitoring fiber Bragg grating strain sensor real-time wavelength λ4；
Fiber Bragg grating (FBG) demodulator passes through optical fiber with multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors
Connection, for obtaining sensing data and being demodulated；Calculating real time acceleration size is λ2-λ1/ K, K are optical fibre grating acceleration
The sensitivity coefficient of sensor, calculating strain size in real time is λ4-λ3/ K', wherein K ' is the sensitive of fiber Bragg grating strain sensor
Spend coefficient
Data processing module is connect with the fiber Bragg grating (FBG) demodulator, for the output of storage and management fiber Bragg grating (FBG) demodulator
Sensing data after demodulation；
Monitor module on-line, for calculating Aircraft Load according to the sensing data after demodulation, and it is related to flight parameter foundation
Property connection, obtain the loading spectrum of undercarriage under different flight parameters, and bond material fatigue behaviour σ-N curve, estimation aircraft rises
Fall the remaining life of frame.
2. the aircraft landing gear structures load on-line monitoring system according to claim 1 based on optical fiber sensing technology,
It is characterized in that, fibre optic strain sensor is two-dimensional fiber bragg grating strain transducer, which includes
Two strain arms in vertical direction.
3. the aircraft landing gear structures load on-line monitoring system according to claim 1 based on optical fiber sensing technology,
It is characterized in that, optical fiber acceleration transducer is three-dimensional fiber grating acceleration transducer, and three dimension acceleration sensor includes three
Integrated one-dimensional acceleration sensor, three one-dimensional acceleration sensors obtain undercarriage position course, side simultaneously
To the vibration signal in, vertical three directions.
4. the aircraft landing gear structures load on-line monitoring system according to claim 1 based on optical fiber sensing technology,
It is characterized in that, C font bracket is fixed on landing gear shock strut by epoxide-resin glue.
5. the aircraft landing gear structures load on-line monitoring system according to claim 4 based on optical fiber sensing technology,
It is characterized in that, optical fibre grating acceleration sensor is fixed on C font bracket by bolt or epoxide-resin glue.
6. the aircraft landing gear structures load on-line monitoring system according to claim 1 based on optical fiber sensing technology,
It is characterized in that, fiber Bragg grating strain sensor is pasted on the hound of undercarriage by epoxy resin glue, and according to measurement
Direction is accurately fixedly mounted on the surface at undercarriage hound position.
7. the aircraft landing gear structures load according to claim 1 to 6 based on optical fiber sensing technology is supervised online
Examining system, which is characterized in that multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors are symmetrically arranged in array
Cloth.
8. the aircraft landing gear structures load on-line monitoring system according to claim 7 based on optical fiber sensing technology,
Be characterized in that, multiple fiber Bragg grating strain sensors, multiple optical fibre grating acceleration sensors tail optical fiber pass through a terminal box
It picks out.
9. the aircraft landing gear structures load on-line monitoring system according to claim 3 based on optical fiber sensing technology,
It is characterized in that, wherein the first, second one-dimensional grating acceleration transducer includes pedestal, two mass blocks and fiber grating, two
It being connected between a mass block by flexible hinge, is carved with groove on two mass blocks, fiber grating is fixed in groove, the
One, the fiber grating of the second one-dimensional grating acceleration transducer perpendicular placement in the same plane；Third one-dimensional grating accelerates
Spending sensor includes two support bases and fiber grating, is all provided on two support bases fluted, and fiber grating is fixed in groove；
The fiber grating of the fiber grating of third one-dimensional grating acceleration transducer and the first, second one-dimensional grating acceleration transducer exists
In same plane, and shape is at a certain angle.
10. the aircraft landing gear structures load on-line monitoring system according to claim 9 based on optical fiber sensing technology,
It is characterized in that, the fiber grating series connection of three one-dimensional grating acceleration transducers is over the same fiber.
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| CN114034261A (en) * | 2021-12-03 | 2022-02-11 | 中国航空工业集团公司北京长城计量测试技术研究所 | Miniaturized three-dimensional fiber grating strain sensor |
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| CN114199156A (en) * | 2021-12-15 | 2022-03-18 | 桂林航天工业学院 | Wing profile curved surface shape reconstruction method based on double FBG shape sensors |
| CN114199156B (en) * | 2021-12-15 | 2023-08-25 | 桂林航天工业学院 | Wing-shaped curved surface shape reconstruction method based on double FBG shape sensors |
| CN116306179A (en) * | 2023-05-22 | 2023-06-23 | 湖南云箭科技有限公司 | Load screening method and system for impact damage evaluation of airborne store lifting |
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| CN117033949A (en) * | 2023-10-08 | 2023-11-10 | 成都凯天电子股份有限公司 | Method for detecting, classifying and maintaining and guiding high-load landing event of airplane |
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