CN106404240B - A kind of undercarriage external applied load method of real-time based on fiber bragg grating sensor - Google Patents
A kind of undercarriage external applied load method of real-time based on fiber bragg grating sensor Download PDFInfo
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- CN106404240B CN106404240B CN201610847984.6A CN201610847984A CN106404240B CN 106404240 B CN106404240 B CN 106404240B CN 201610847984 A CN201610847984 A CN 201610847984A CN 106404240 B CN106404240 B CN 106404240B
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- 239000000835 fiber Substances 0.000 title claims abstract description 108
- 238000000034 method Methods 0.000 title claims abstract description 31
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- 238000004364 calculation method Methods 0.000 claims abstract description 10
- 238000001514 detection method Methods 0.000 claims abstract description 6
- 238000013178 mathematical model Methods 0.000 claims abstract description 6
- 238000005086 pumping Methods 0.000 claims description 15
- 229910052691 Erbium Inorganic materials 0.000 claims description 10
- UYAHIZSMUZPPFV-UHFFFAOYSA-N erbium Chemical compound [Er] UYAHIZSMUZPPFV-UHFFFAOYSA-N 0.000 claims description 10
- 239000013307 optical fiber Substances 0.000 claims description 9
- 230000003287 optical effect Effects 0.000 claims description 5
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- 238000012423 maintenance Methods 0.000 description 7
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Classifications
-
- 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
Abstract
The present invention provides a kind of undercarriage external applied load method of real-time based on fiber bragg grating sensor, the method for real-time is the following steps are included: a. builds grating fibers monitoring system；B. undercarriage external applied load mathematical model is established, universe Stress calculation is carried out to the Landing gear model, finds the external applied load stress concentration region of undercarriage；C. arrange that the grating fibers monitor system in undercarriage external applied load stress concentration region；D. external applied load is continuously applied to the undercarriage, the grating fibers monitoring system acquires the center wavelength shift amount data of grating fibers group by signal receiver, draw the relation curve of the center wavelength shift amount data of external applied load size and the grating fibers group, foil gauge is caused to strain by external applied load, so that the central wavelength of the grating fibers group be made to shift；E. the grating fibers detection system is mounted on undercarriage, is monitored by real-time load of the relation curve to undercarriage in flight course.
Description
The cross reference of patent
It is submitted this application claims on October 14th, 2015, the Chinese invention patent application of application number 201510662382.9
Preference.
Technical field
The present invention relates to field of aerospace technology, in particular to carried outside a kind of undercarriage based on fiber bragg grating sensor
Lotus method of real-time.
Background technique
Aircraft subjects the random load under various environment during practical flight, and structure destruction happens occasionally.To winged
Machine structure is monitored in real time, and the degree of impairment of itself is controlled in its flight course, strong using economy maintenance and structural life-time
Kang Guanli extends Aircraft life.
The external applied load that aircraft is subject in flight course be mainly 1) air force, 2) mass force, 3) other component transmits
Concentrfated load.In the flare maneuvers such as aircraft turn or sideslip, lateral load be will receive than smooth flight Shi Geng great air force
It influences；The quality of fuselage itself and the loading of interior of aircraft can generate mass force to aircraft, cause load to aircraft；Aircraft rises
The components such as wing, empennage and undercarriage can generate load to aircraft generation itself in winged, sliding race, descent.Outside aircraft
Load seriously affects airframe and aircraft components, will substantially reduce to airframe and aircraft components progress maintenance not in time winged
The service life of machine.It is all logical at present but for receiving influence of the load to fuselage and aircraft components in aircraft flight
It crosses experience or is repaired when airframe and component damage, maintenance at this moment produces Aircraft life
It influences, reduces the service life of aircraft.
The aircraft flight real time monitoring prior art is usually monitored by resistance sensor, is monitored
Effect and precision are not accurate enough, not strong to the maintenance directive significance of aircraft.
Therefore, it is necessary to a kind of can effectively solve to be monitored to the external applied load in aircraft flight, fly to guidance
The undercarriage external applied load method of real-time based on fiber bragg grating sensor of machine maintenance shield.
Summary of the invention
The purpose of the present invention is to provide a kind of undercarriage external applied load method of real-time based on fiber bragg grating sensor,
The method of real-time the following steps are included:
A. grating fibers monitoring system is built, the monitoring system includes pumping source, the first Er-doped fiber, the second miserable erbium light
Fibre, wavelength division multiplexer, grating fibers group and signal receiver；Wherein
The grating fibers group is attached in series after being bonded by multistage grating fibers with foil gauge；
B. undercarriage external applied load mathematical model is established, universe Stress calculation is carried out to the Landing gear model, is found
The external applied load stress concentration region of undercarriage；
C. the grating fibers monitoring system is arranged in the undercarriage external applied load stress concentration region found in stepb；
D. external applied load is continuously applied to the undercarriage, the grating fibers monitoring system is adopted by signal receiver
Collect the center wavelength shift amount data of grating fibers group, draws the center wavelength shift of external applied load size and the grating fibers group
The relation curve of data is measured, wherein
Foil gauge is caused to strain by external applied load, so that the central wavelength of the grating fibers group be made to shift；
E. the grating fibers detection system is mounted on undercarriage, according to the relation curve to aircraft flight mistake
The real-time load of undercarriage is monitored in journey.
Preferably, first Er-doped fiber is identical with the second Er-doped fiber doping concentration.
Preferably, the pumping source is laser diode list pumping source.
Preferably, the pump light that the pumping source issues divides two-way to respectively enter the first Er-doped fiber and the second miserable erbium light
It is fine.
Preferably, welding isolator is arranged in the grating fibers group end, prevents influence of the edge echo to output signal.
Preferably, universe Stress calculation described in step b includes the calculating of the shearing of undercarriage, moment of flexure and torque.
Preferably, the grating fibers group is bonded by way of gluing with foil gauge.
Preferably, grating fibers monitoring system layout mode described in step c be by way of gluing by foil gauge with
It pastes undercarriage external applied load stress concentration region.
Preferably, the center wavelength shift amount data that grating fibers group is acquired in step d are handled, the processing method
Include the following steps:
D1. data prediction, the center wavelength shift amount data setup time course of collected grating fibers group；For
Data time course is detected, and underproof data of rising and falling are rejected；
D2. data secondary treatment, the data obtained to pretreatment are filtered and are segmented.
Present invention employs fiber bragg grating sensors to carry out real-time monitoring, monitoring process essence to undercarriage external applied load
Carefully, intelligent, accurate, effective maintenance to aircraft is instructed and realized, the bulk life time of aircraft is extended.
It should be appreciated that aforementioned description substantially and subsequent detailed description are exemplary illustration and explanation, it should not
As the limitation to the claimed content of the present invention.
Detailed description of the invention
With reference to the attached drawing of accompanying, the more purposes of the present invention, function and advantage are by the as follows of embodiment through the invention
Description is illustrated, in which:
Fig. 1 diagrammatically illustrates the structure chart of grating fibers monitoring system of the present invention；
Fig. 2 shows the present invention is based on the flow charts of the undercarriage external applied load method of real-time of fiber bragg grating sensor；
Fig. 3 shows the schematic diagram that the present invention carries out universe Stress calculation to undercarriage model；
Fig. 4 shows the process flow diagram of the center wavelength shift amount data of grating fibers group of the present invention；
Fig. 5 shows the relation curve of the center wavelength shift amount data of external applied load size of the present invention and grating fibers group.
Specific embodiment
By reference to exemplary embodiment, the purpose of the present invention and function and the side for realizing these purposes and function
Method will be illustrated.However, the present invention is not limited to exemplary embodiment as disclosed below；Can by different form come
It is realized.The essence of specification is only to aid in those skilled in the relevant arts' Integrated Understanding detail of the invention.
Hereinafter, the embodiment of the present invention will be described with reference to the drawings.In the accompanying drawings, identical appended drawing reference represents identical
Or similar component or same or like step.A kind of rising and falling based on fiber bragg grating sensor provided by the present invention
Frame external applied load method of real-time is that system realization is monitored by grating fibers prepared by grating fibers to the real-time prison of undercarriage
It surveys, schematically provides the monitoring system of grating fibers described in one kind in the present embodiment, in one embodiment of the invention as shown in Figure 1
The structure chart of grating fibers monitoring system；The grating fibers detection system includes pumping source 101, the first miserable erbium optical fiber 102,
Two miserable erbium optical fiber 103, wavelength division multiplexer 105, grating fibers group 105 and signal receiver 106.Wherein, grating fibers group 105
Including multistage grating fibers 1052,4 sections of grating fibers are representatively illustrated in the present embodiment, 4 sections of grating fibers pass through concatenated
Mode is attached；In some embodiments, grating fibers can be multistage, specifically by the undercarriage to be monitored
Size is determined that similarly, the multistage grating fibers of setting are connected by concatenated mode.The grating fibers 1052 pass through glue
Viscous to paste on foil gauge 1051, when undercarriage is by external applied load, foil gauge 1051, which deforms, causes grating fibers
External load monitoring is realized in 1052 central wavelength drift.It should be understood that using multistage grating fibers structure in the present invention
At the entirety of grating fibers group 105 there is wave length shift so that the wavelength of the external applied load monitored and grating fibers group 105 floats
The relationship of shifting is more accurate.
In order to realize the spontaneous emission light of high flat C+L wave band amplification, the pumping source 101 that the present invention uses is laser two
Pole pipe list pumping source, and the first miserable erbium optical fiber 102 is identical with the doping concentration of the second miserable erbium optical fiber 103.
The optical path that pumping source 101 generates is divided into two-way and has respectively entered the first miserable erbium optical fiber 102 and the second miserable erbium optical fiber 103
In, processing is amplified by the optical signal that two-way optical path generates pumping source.Wavelength division multiplexer 104 is by amplified signal coupling
It closes in the grating fibers group 105 for entering and 4 sections of grating fibers being connected in series.Signal receiver 106 acquires optical path signal, preferably
Ground is arranged welding isolator in the end of grating fibers group 105, prevents influence of the edge echo to output signal.
The present embodiment illustrates the present invention using above-mentioned grating fibers monitoring system to undercarriage external applied load below
Method of real-time elaborates, and the present invention is based on the undercarriage external applied loads of fiber bragg grating sensor to supervise in real time as shown in Figure 2
The flow chart of survey method, shown undercarriage external applied load method of real-time should include the following steps:
Step 201: building grating fibers monitoring system；The monitoring system includes pumping source, the first Er-doped fiber, second
Miserable erbium optical fiber, wavelength division multiplexer, grating fibers group and signal receiver.
Step 202:: simulation calculation finds undercarriage stress concentration region；Establish undercarriage external applied load mathematical modulo
Type carries out universe Stress calculation to the Landing gear model, finds the external applied load stress concentration region of undercarriage.Specific emulation
Calculating process establishes aircraft mathematical model by finite element fraction analysis method, arranges grating fibers simultaneously in aircraft mathematical model
Boundary condition is set, and condition is to be simulated according to the external applied load in real aircraft flight course between the side.The present embodiment is adopted
The universe Stress calculation calculated with the simulation for including the shearing to undercarriage, moment of flexure and torque, so that calculated result is more
The case where close to during aircraft practical flight, thus more accurate to subsequent detection.
Pass through simulation calculation.The region of strain can most be generated in flight course by searching out aircraft, as shown in Figure 3 the present invention
The schematic diagram of universe Stress calculation, first connecting rod 301, the second connecting rod 302 of undercarriage are carried out to undercarriage model
And third connecting rod 303 strains in calculating process, while obtaining strain region 304, what calculated result obtained goes out
Existing strain region 304 is by the maximum region of external applied load.
Step 203: arrangement grating fibers monitor system；The undercarriage external applied load stress collection found in step 202
Middle area arranges that the grating fibers monitor system.For the saving to grating elder generation material in the present embodiment, only to stress concentration region
Grating fibers group is arranged in domain 304.It should be understood that should be also to preferably be safeguarded to aircraft in some embodiments
The strain region of first connecting rod 301, second connecting rod 302 and third connecting rod 303 including undercarriage arranges grating fibers group.On
Arrangement grating fibers group is stated by the way of pasting by the straining concentration zone domain of the foil gauge of grating fibers group and undercarriage
Mutual gluing pastes fixation, it should be understood that the fixed form used in the present embodiment should further include other other than pasting
All thinkable fixed forms of field technical staff institute, such as: special gelatin is fixed or metal docking.
Step 204: drawing the relation curve of the center wavelength shift amount data of external applied load size and grating fibers group；To institute
It states undercarriage and is continuously applied external applied load, the grating fibers monitoring system acquires grating fibers group by signal receiver
Center wavelength shift amount data, the relationship for drawing the center wavelength shift amount data of external applied load size and the grating fibers group are bent
Line, wherein
Foil gauge is caused to strain by external applied load, so that the central wavelength of the grating fibers group be made to shift.
For undercarriage be continuously applied the process of external applied load using load machine to undercarriage from 6, space dimension
Loaded, make the external applied load applied as far as possible with the external applied load that is generated in aircraft flight.
Signal receiver connects the center wavelength shift amount data of acquisition grating fibers group, at collected data
Reason, the process flow diagram of the center wavelength shift amount data of grating fibers group as shown in Figure 4, specific data handling procedure include such as
Lower step
Step 401: data acquisition acquires the center of grating fibers group by the signal receiver that grating fibers monitor system
Wavelength shift；
Step 402: the center wavelength shift amount data setup time of data prediction, collected grating fibers group is gone through
Journey；It is detected for data time course, rejects underproof data of rising and falling；The data wherein rejected are collected pseudo- reading
Several and two-dimentional low load data.
Step 403: data secondary treatment carries out wave crest data to the data that pretreatment obtains and trough data is filtered
And segmentation.
The center wavelength shift amount data of treated grating fibers group and the load data of application are verified, and make to draw
The relation curve burst error of the center wavelength shift amount data of the external applied load size and grating fibers group of system reaches minimum.Such as figure
The relation curve of the center wavelength shift amount data of external applied load size shown in 5 and grating fibers group, external applied load are applied to limit point
Undercarriage is reappeared when 501 to be badly damaged.
Step 205: to landing-gear load real-time monitoring in aircraft flight；The grating fibers detection system is installed
In undercarriage, it is monitored according to real-time load of the relation curve to undercarriage in aircraft flight.It should manage
Control program is written in solution, described relation curve by way of programming, by control program in aircraft flight
Load is intuitively shown.The process of relation curve program of being write as should be those skilled in the art thinkable all volumes
Journey mode, such as: PLC logic control.
Present invention employs fiber bragg grating sensors to carry out real-time monitoring, monitoring process essence to undercarriage external applied load
Carefully, intelligent, accurate, effective maintenance to aircraft is instructed and realized, the bulk life time of aircraft is extended.
In conjunction with the explanation and practice of the invention disclosed here, the other embodiment of the present invention is for those skilled in the art
It all will be readily apparent and understand.Illustrate and embodiment is regarded only as being exemplary, true scope of the invention and purport are equal
It is defined in the claims.
Claims (7)
1. a kind of undercarriage external applied load method of real-time based on fiber bragg grating sensor, which is characterized in that the real-time prison
Survey method the following steps are included:
A. build grating fibers monitoring system, the monitoring system include pumping source, the first Er-doped fiber, the second Er-doped fiber,
Wavelength division multiplexer, grating fibers group and signal receiver；Wherein
The grating fibers group is attached in series after being bonded by multistage grating fibers with foil gauge,
The pump light that the pumping source issues divides two-way to respectively enter the first Er-doped fiber and the second Er-doped fiber, passes through two-way light
The optical signal that road generates pumping source amplifies processing, and amplified signal is coupled into grating fibers by wavelength division multiplexer
In group；
B. undercarriage external applied load mathematical model is established, universe stress is carried out to the undercarriage external applied load mathematical model
It calculates, finds the external applied load stress concentration region of undercarriage；
C. the grating fibers monitoring system is arranged in the undercarriage external applied load stress concentration region found in stepb；
D. external applied load is continuously applied to the undercarriage, the grating fibers monitoring system acquires light by signal receiver
The center wavelength shift amount data of grid optical fiber group draw the center wavelength shift amount number of external applied load size and the grating fibers group
According to relation curve, wherein
Foil gauge is caused to strain by external applied load, so that the central wavelength of the grating fibers group is made to shift,
The center wavelength shift amount data of acquisition grating fibers group are handled, and the treating method comprises following steps:
D1. data prediction, the center wavelength shift amount data setup time course of collected grating fibers group；For data
Time history is detected, and underproof data of rising and falling are rejected；
D2. data secondary treatment, the data obtained to pretreatment are filtered and are segmented, in treated grating fibers group
The long offset data of cardiac wave and the load data of application are verified；
E. the grating fibers detection system is mounted on undercarriage, according to the relation curve in aircraft flight
The real-time load of undercarriage is monitored.
2. method of real-time according to claim 1, which is characterized in that first Er-doped fiber and described second is mixed
Erbium optical fiber doping concentration is identical.
3. method of real-time according to claim 1, which is characterized in that the pumping source is the pumping of laser diode list
Source.
4. method of real-time according to claim 1, which is characterized in that grating fibers group end setting welding every
From device, influence of the edge echo to output signal is prevented.
5. method of real-time according to claim 1, which is characterized in that universe Stress calculation packet described in step b
Include the calculating of the shearing of undercarriage, moment of flexure and torque.
6. method of real-time according to claim 1, which is characterized in that the grating fibers group and foil gauge pass through glue
Viscous mode is bonded.
7. method of real-time according to claim 1, which is characterized in that grating fibers described in step c monitor system
Arrangement is to be pasted foil gauge and undercarriage external applied load stress concentration region by way of gluing.
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| CN201510662382 | 2015-10-14 | ||
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| CN107560767A (en) * | 2017-08-30 | 2018-01-09 | 陕西千山航空电子有限责任公司 | A kind of airborne structural stress monitoring device |
| CN108216584B (en) * | 2017-12-14 | 2021-07-16 | 中航(成都)无人机系统股份有限公司 | Aircraft grounding state monitoring method |
| CN108931324A (en) * | 2018-09-20 | 2018-12-04 | 四川腾盾科技有限公司 | A kind of strain wheel load and real-time heavy condition measuring system |
| CN109506819B (en) * | 2018-12-13 | 2020-06-05 | 贵州贵航飞机设计研究所 | Method for monitoring impact load of undercarriage during landing of airplane |
| CN110261017A (en) * | 2019-04-26 | 2019-09-20 | 武汉理工大学 | Aircaft configuration load monitoring system based on optical fiber sensing technology |
| CN112134358A (en) * | 2020-09-22 | 2020-12-25 | 国家电网有限公司 | Overhead power transmission insulator insulation performance monitoring and analyzing method |
| CN112013908A (en) * | 2020-09-22 | 2020-12-01 | 国家电网有限公司 | Method for monitoring state of key stress point of overhead transmission line |
| CN113624152B (en) * | 2021-06-22 | 2022-06-07 | 成都凯天电子股份有限公司 | Grating-based wheel-load signal detection method |
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