CN209689781U - A kind of optical fiber sensing system for aircraft overheat detection - Google Patents
A kind of optical fiber sensing system for aircraft overheat detection Download PDFInfo
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- CN209689781U CN209689781U CN201920577816.9U CN201920577816U CN209689781U CN 209689781 U CN209689781 U CN 209689781U CN 201920577816 U CN201920577816 U CN 201920577816U CN 209689781 U CN209689781 U CN 209689781U
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Abstract
The utility model relates to technical field of optical fiber sensing, refer specifically to a kind of optical fiber sensing system for aircraft overheat detection；Including sequentially connected light source, optical circulator, signal processing unit and computer, the first port of optical circulator is connect with light source, and the third port of optical circulator is connect with signal processing unit；It is connected with sensor fibre in the second port of the optical circulator, inscribes the antiradar reflectivity FBG array for there are several groups on sensor fibre, and the mode of several antiradar reflectivity FBG arrays at equidistant intervals is in turn distributed on the monitoring pipeline of aircraft；The utility model is structurally reasonable, Fibre Optical Sensor have high sensitivity, intrinsic safety, anti-electromagnetic interference capability it is strong, can distributed measurement advantage；Antiradar reflectivity FBG array is axially distributed on aircraft monitoring pipeline, and overheat position caused by capable of being revealed aircrafts exhaust by the demodulation to signal with analysis positions, and realizes the on-line real time monitoring of aircraft safety situation.
Description
Technical field
The utility model relates to technical field of optical fiber sensing, refer specifically to a kind of Fibre Optical Sensor system for aircraft overheat detection
System.
Background technique
Airplane air entraining pipeline belongs to high temperature pressure pipeline system, in aircraft operational process, bad environments, bleed air line by
The influence of the factors such as burn into external force, heat insulation layer aging, can generate leakage or problems of excessive heat.This not only will have a direct impact on
The adjusting of the parameters such as energy, the flow of bleed air system, at the same also can structure, equipment etc. to surrounding catheter region bring safety it is hidden
Suffer from.
In terms of aircraft pipeline fault monitoring, many experts both domestic and external achieve significant research achievement, actual
Thermal infrared radiation technology, transient pressure wave method, tracer method and acoustics leak hunting technology, but these sides are mainly used in engineer application
There are many deficiencies for method.For example traditional electric class temperature sensor thermistor poor linearity, reliability is low, it is inflammable and explosive to have
It is dangerous, be easy by electromagnetic interference to influencing measurement accuracy.
In terms of existing literature, Fibre Optical Sensor measurement at present mainly uses traditional FBG sensor, and FBG is a kind of quasi- distribution
The measurement of formula, difficult to realize leak space shuttle pipeline gas of existing FBG measuring technique carry out high spatial resolution, quickly ring
The monitoring answered.Existing fiber sensing health status measurement at present has certain technical bottleneck, existing Raman scattering and Brillouin
Scattering technology resolution ratio is low, and response speed is slow, the difficulty of distributed measurement；It is expensive there are also its system stability is poor, flying
Machine application above has difficulties.Irregular oscillation and cable temperature unevenness occur for body, so that letting out to space shuttle pipeline gas
Leakage is that temperature measurement is difficult.
Therefore, existing technology has much room for improvement and develops.
Utility model content
The purpose of this utility model is that in view of the drawbacks of the prior art and insufficient, provide that a kind of structure is simple, response speed
Spend fast, good security, high reliablity the optical fiber sensing system for aircraft overheat detection.
To achieve the goals above, the utility model uses following technical scheme:
A kind of optical fiber sensing system for aircraft overheat detection described in the utility model, including sequentially connected light
The first port of source, optical circulator, signal processing unit and computer, optical circulator is connect with light source, the third of optical circulator
Port is connect with signal processing unit；It is connected with sensor fibre in the second port of the optical circulator, is inscribed on sensor fibre
Have an antiradar reflectivity FBG array of several groups, and the mode of several antiradar reflectivity FBG arrays at equidistant intervals be in turn distributed in it is winged
On the monitoring pipeline of machine.
According to above scheme, the FBG grating in several antiradar reflectivity FBG arrays is respectively provided with different middle cardiac waves
Long, signal processing unit positions several antiradar reflectivity FBG arrays by the algorithm that is time-multiplexed.
According to above scheme, every group of antiradar reflectivity FBG array contains the different FBG grating of 10 wavelength, low
The layout pitch of adjacent FBG grating is 10cm in reflectivity FBG array and the wavelength interval of adjacent FBG grating is 4 μm；The letter
Number processing unit positions the FBG grating in antiradar reflectivity FBG array by wavelength-division multiplex algorithm.
According to above scheme, the sensor fibre is high temperature resistant organic coating optical fiber, and antiradar reflectivity FBG array uses femtosecond
Laser technology is scribed on sensor fibre.
According to above scheme, the sensor fibre is encapsulated in capillary metal tube, and capillary metal tube is mounted on aircraft
It monitors on pipeline.
According to above scheme, the computer is equipped with data processing software and outlet terminal.
The utility model has the beneficial effect that the utility model is structurally reasonable, and Fibre Optical Sensor has high sensitivity, intrinsic peace
Entirely, anti-electromagnetic interference capability it is strong, can distributed measurement advantage；Axially distributed monitor in aircraft of antiradar reflectivity FBG array is managed
On line, overheat position caused by capable of being revealed aircrafts exhaust by the demodulation to signal with analysis is positioned, and realizes aircraft
The on-line real time monitoring of safe condition.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the utility model.
In figure:
1, light source；2, optical circulator；3, sensor fibre；4, signal processing unit；5, computer；31, antiradar reflectivity FBG gusts
Column；32, FBG grating.
Specific embodiment
The technical solution of the utility model is illustrated with embodiment with reference to the accompanying drawing.
As shown in Figure 1, a kind of optical fiber sensing system for aircraft overheat detection described in the utility model, including successively
Light source 1, optical circulator 2, signal processing unit 4 and the computer 5 of connection, the first port of optical circulator 2 are connect with light source 1,
The third port of optical circulator 2 is connect with signal processing unit 4；Sense light is connected in the second port of the optical circulator 2
Fibre 3 inscribes the antiradar reflectivity FBG array 31 for having several groups on sensor fibre 3, and several antiradar reflectivity FBG arrays 31 are with equidistant
The mode at interval is in turn distributed on the monitoring pipeline of aircraft；Fibre Optical Sensor has high sensitivity, intrinsic safety, anti-electromagnetism dry
Disturb ability it is strong, can distributed measurement advantage；Antiradar reflectivity FBG array 31 is axially distributed on aircraft monitoring pipeline, passes through
Overheat position caused by capable of being revealed aircrafts exhaust with analysis the demodulation of reflection signal positions.The signal demodulation is single
Member 4 is based on wavelength-division multiplex and time-division multiplex technology demodulating algorithm, and the algorithm specifically based on wavelength positioning acquires not first
The FBG spectral signal being reflected back with time delay；Noise suppression preprocessing is filtered to the signal collected again；Obtained data are sieved
After choosing, obtained discrete data enters the peak-seeking algorithm stage, and discrete data progress Gauss curve fitting is obtained the peak value of Gaussian function
Point, then carry out asymmetric Gauss curve fitting；Temperature information finally is converted by wavelength signals, is shown by computer 5, is realized
The real-time monitoring of aircrafts exhaust pipe safety situation.
FBG grating 32 in several antiradar reflectivity FBG arrays 31 is respectively provided with different central wavelength, signal processing
Unit 4 positions several antiradar reflectivity FBG arrays 31 by the algorithm that is time-multiplexed；31 edge of antiradar reflectivity FBG array
It is axially distributed on aircraft monitoring pipeline, the concatenated mode of grating array improves monitoring point capacity；FBG array 1, FBG array
2 ..., FBG array n include the FBG grating 32 of different central wavelengths, and signal processing unit 4 can pass through time-division multiplex technology pair
Different FBG arrays are positioned.
Every group of antiradar reflectivity FBG array 31 contains the different FBG grating 32 of 10 wavelength, antiradar reflectivity FBG
The layout pitch of adjacent FBG grating 32 is 10cm in array 31 and the wavelength interval of adjacent FBG grating 32 is 4 μm；The signal
Processing unit 4 positions the FBG grating 32 in antiradar reflectivity FBG array 31 by wavelength-division multiplex algorithm.
Demodulating process mainly include signal acquisition, pretreatment, feature extraction and signal demodulation and etc.；Signal acquisition is to adjust
The spectral signal returned with the antiradar reflectivity FBG temperature sensor that acquisition method extracts different delay；Pretreatment includes to acquisition
Original spectrum signal first denoised Signal separator again, denoising purpose is to filter out high-frequency noise, improves signal-to-noise ratio, Signal separator
FBG sub-light spectrum is obtained from spectral signal；Feature extraction includes extracting Bouguer from sub-light spectrum to draw bragg wavelength；Signal demodulation
It is first to be converted to temperature value from bragg wavelength, algorithm determines current calibration curve according to temperature value.The signal demodulated is logical
Network interface transfers are crossed to main frame, the mode identificating software analysis system of computer basis first is preset temperature
Transducing signal distinguishes, and calculates different parts temperature information parameter on Airplane detection pipeline, realizes the temperature of entire chain road
Degree trend on-line monitoring guarantees that aircraft is in the operating status of health.
The sensor fibre 3 is high temperature resistant organic coating optical fiber, and antiradar reflectivity FBG array 31 is carved using femtosecond laser technology
It writes on sensor fibre 3；Femtosecond laser, which inscribes fiber bragg grating, to be scribed with extraordinary infrared femtosecond laser (800nm)
FBG grating 32 makes sensor-based system still can be with steady operation in severe and extraordinary environment.
The sensor fibre 3 is encapsulated in capillary metal tube, and capillary metal tube is mounted on the monitoring pipeline of aircraft, hair
Thin metal pipe packaged type can be convenient for the installation of sensor fibre 3, while not influence its sensitivity to temperature-responsive.
The computer 5 is equipped with data processing software and outlet terminal.
The above description is only a preferred embodiment of the present invention, therefore all according to described in the utility model patent application range
The equivalent change or modification done of structure, feature and principle, be included in the scope of the utility model patent application.
Claims (6)
1. a kind of optical fiber sensing system for aircraft overheat detection, it is characterised in that: including sequentially connected light source (1), light
The first port of circulator (2), signal processing unit (4) and computer (5), optical circulator (2) is connect with light source (1), the ring of light
The third port of shape device (2) is connect with signal processing unit (4)；Sensing is connected in the second port of the optical circulator (2)
Optical fiber (3) inscribes the antiradar reflectivity FBG array (31) for having several groups, and several antiradar reflectivity FBG arrays on sensor fibre (3)
(31) mode at equidistant intervals is in turn distributed on the monitoring pipeline of aircraft.
2. the optical fiber sensing system according to claim 1 for aircraft overheat detection, it is characterised in that: described several low
FBG grating (32) in reflectivity FBG array (31) is respectively provided with different central wavelength, when signal processing unit (4) passes through
Multiplexing algorithm is divided to position several antiradar reflectivity FBG arrays (31).
3. the optical fiber sensing system according to claim 2 for aircraft overheat detection, it is characterised in that: described every group low
Reflectivity FBG array (31) contains the different FBG grating (32) of 10 wavelength, adjacent in antiradar reflectivity FBG array (31)
The layout pitch of FBG grating (32) is 10cm and the wavelength interval of adjacent FBG grating (32) is 4 μm；The signal processing unit
(4) the FBG grating (32) in antiradar reflectivity FBG array (31) is positioned by wavelength-division multiplex algorithm.
4. the optical fiber sensing system according to claim 1 for aircraft overheat detection, it is characterised in that: the sense light
Fine (3) are high temperature resistant organic coating optical fiber, and antiradar reflectivity FBG array (31) is scribed at sensor fibre using femtosecond laser technology
(3) on.
5. the optical fiber sensing system according to claim 4 for aircraft overheat detection, it is characterised in that: the sense light
Fine (3) are encapsulated in capillary metal tube, and capillary metal tube is mounted on the monitoring pipeline of aircraft.
6. the optical fiber sensing system according to claim 1 for aircraft overheat detection, it is characterised in that: the computer
(5) data processing software and outlet terminal are equipped with.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201920577816.9U CN209689781U (en) | 2019-04-25 | 2019-04-25 | A kind of optical fiber sensing system for aircraft overheat detection |
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| CN201920577816.9U CN209689781U (en) | 2019-04-25 | 2019-04-25 | A kind of optical fiber sensing system for aircraft overheat detection |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110220611A (en) * | 2019-04-25 | 2019-09-10 | 武汉理工大学 | A kind of optical fiber sensing system for aircraft overheat detection |
| CN111780790A (en) * | 2020-06-03 | 2020-10-16 | 华南师范大学 | Device and method for demodulating dense fiber bragg grating array |
| CN111830626A (en) * | 2020-07-29 | 2020-10-27 | 武汉理工大学 | Method for preparing wavelength division and time division multiplexing low-reflectivity high-temperature fiber grating array |
| CN113588119A (en) * | 2021-06-29 | 2021-11-02 | 中国船舶重工集团公司第七一五研究所 | Method for measuring wall temperature of high-temperature part of aircraft engine based on femtosecond fiber bragg grating sensing |
-
2019
- 2019-04-25 CN CN201920577816.9U patent/CN209689781U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110220611A (en) * | 2019-04-25 | 2019-09-10 | 武汉理工大学 | A kind of optical fiber sensing system for aircraft overheat detection |
| CN111780790A (en) * | 2020-06-03 | 2020-10-16 | 华南师范大学 | Device and method for demodulating dense fiber bragg grating array |
| CN111830626A (en) * | 2020-07-29 | 2020-10-27 | 武汉理工大学 | Method for preparing wavelength division and time division multiplexing low-reflectivity high-temperature fiber grating array |
| CN113588119A (en) * | 2021-06-29 | 2021-11-02 | 中国船舶重工集团公司第七一五研究所 | Method for measuring wall temperature of high-temperature part of aircraft engine based on femtosecond fiber bragg grating sensing |
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