CN203241545U - Airport runway foreign matter detection device - Google Patents
Airport runway foreign matter detection device Download PDFInfo
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- CN203241545U CN203241545U CN 201220656005 CN201220656005U CN203241545U CN 203241545 U CN203241545 U CN 203241545U CN 201220656005 CN201220656005 CN 201220656005 CN 201220656005 U CN201220656005 U CN 201220656005U CN 203241545 U CN203241545 U CN 203241545U
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Abstract
An airport runway foreign matter detection device is composed of a radar emission antenna, a radar receiving antenna, a radar transmitting-receiving front, a cantilever, a rotary mechanism, a signal processor and a display control terminal. The radar emission antenna and the radar receiving antenna are connected with the radar transmitting-receiving front through wave guides. The radar transmitting-receiving front is connected with the signal processor through the rotary mechanism. The signal processor is connected with the display control terminal. The airport runway foreign matter detection device points to a linear frequency modulation continuous wave system and achieves high distance resolution through wideband linear frequency modulation. The airport runway foreign matter detection device further achieves high azimuth resolution by realizing antenna semicircle locus rotation to construct synthetic apertures. The area of ground clutter units is reduced. Small runway fragment object detection is further achieved.
Description
Technical field:
The utility model belongs to the safety checking field, particularly a kind of airfield runway detection device for foreign matter.This system mainly adopts the synthetic aperture continuous wave frequency radar with rotating antenna to manifest, and realizes the high resolution detection to airfield runway surface target, can reduce ground clutter and disturb.
Background technology:
The automatic detection of the external legacy fragment in airfield runway surface is the important topic that is related to aviation safety.When aircraft on runway during high speed slide, on the runway these drop thing to aircraft and on every side the safety of personnel's vehicle all be serious threat, the accident that causes of annual runway fragment causes the loss of 4,000,000,000 dollars of aircraft industry according to estimates.The radar cross section of general consideration small size fragment only has-20dBm
2Below, these wisps are static on runway, the echo signal to noise ratio is extremely low, the radar return of fragment and ground radar angle echo mix, the intensity of radar ground clutter and radar are irradiated into firing angle, the area of irradiation surface units and the factor analysis such as attribute on ground over the ground, and wherein ground clutter cellar area (being determined by distance by radar and azimuthal resolution) is a key factor.If the resolution on distance and bearing of radar is not high enough, the area of ground clutter unit is large so, and its echo strength just may be more a lot of by force than the fragment echo that will detect, and the method that can not adopt moving-target to detect is eliminated the ground angle echo.The external method that adopts is the radar detection method of optical imaging method and 3mm wave band now, and the disturbing effect that the method for employing optical detection is subject to the factors such as light, shade, paper scrap is larger, and adopts the radar of 3mm wave band expensive, and maintenance cost is higher.
Summary of the invention:
The purpose of this utility model is in order to provide a kind of relative low price, can to realize to the airport fragment rotating antenna synthetic-aperture radar detection system of reliable detection.The utility model is for the linear frequency modulation continuous wave system, realize high range resolution by wide-band LFM, make up synthetic aperture by realizing the rotation of antenna semi arch track, thereby realize high azimuth discrimination, reduce the area of ground clutter unit, realize the detection to the little target of runway fragment.
As above design, the technical scheme that the utility model technical solution problem adopts is:
A kind of airfield runway detection device for foreign matter is characterized in that: be comprised of emission and receiving antenna, radar transmit-receive front end, cantilever, rotating mechanism, signal processor and display control terminal; Wherein: emission links to each other by waveguide with the radar transmit-receive front end with receiving antenna, and the radar transmit-receive front end links to each other with signal processor by rotating mechanism, and signal processor links to each other with display control terminal.
Above-mentioned transmitting radar antenna and receiving antenna adopt the wide-azimuth beam antenna.
Above-mentioned radar transmit-receive front end is comprised of millimeter wave VCO, power splitter, power amplifier, emission polarizer, reception polarizer, low noise amplifier, orthogonal mixer, amplification channel and A/D analog to digital conversion; Wherein: millimeter wave VCO is connected with the interface of rotating mechanism by interface, is connected with the VCO gamma correction output of signal processor module by collector ring; The output of millimeter wave VCO is sent into power splitter and is divided into two-way, and one the tunnel is connected with power amplifier, and power amplifier is connected with the emission polarizer, and the emission polarizer is connected with emitting antenna by waveguide; Receiving polarizer is connected with receiving antenna by waveguide, the output that receives polarizer is connected with low noise amplifier, the output of low noise amplifier is connected with orthogonal mixer, the local oscillator of orthogonal mixer is provided by another road output of power splitter, the output of orthogonal mixer is connected with the amplification filtering channel, the amplification filtering channel is connected with the A/D analog to digital conversion, and the digital signal of A/D analog to digital conversion is connected with the interface of rotating mechanism by interface.
Above-mentioned emission polarizer and reception polarizer all adopt vertical polarization and the controlled polarizer of horizontal polarization.
Above-mentioned rotating mechanism is comprised of cantilever connector, speed reduction unit, direct current generator, photoelectric code disk, upper cable interface, collector ring and lower cable interface; Wherein the cantilever connector is connected with cantilever, the cantilever connector is connected with speed reduction unit, speed reduction unit is connected with direct current generator, direct current generator is connected with photoelectric code disk, collector ring is connected with direct current generator, upper cable interface is connected with collector ring respectively with lower cable interface; Collector ring plays the effect that the radar transmit-receive front end signal is connected with signal processing module.
The utility model is for the linear frequency modulation continuous wave system, realize high range resolution by wide-band LFM, make up synthetic aperture by realizing the rotation of antenna semi arch track, thereby realize high azimuth discrimination, reduce the area of ground clutter unit, realize the detection to the little target of runway fragment.
The course of work of the present utility model is:
Under airport environment, set up system of the present invention on the airfield runway limit, at first support and rotating mechanism are set up, cantilever and radar transmit-receive front end and emission and receiving antenna are installed, signal processor and display control terminal are put in place, connect receiving and transmitting front end to cable between signal controller, by the rotation of control rotating mechanism motor realization radar transmit-receive front end and emission and receiving antenna, signal processing module is stored and sent into to photoelectric code disk real time record rotational angle also.To airfield runway surveyed area radiated electromagnetic wave, the scope of antenna rotation will be centered by airfield runway in rotation for radar emission and receiving antenna, and the electromagnetic wave signal of generation is the microwave signal that has comprised the low phase noise of broadband distance measuring signal.In order to realize the broadband swept-frequency signal, the present invention adopts broadband VCO to realize the linear frequency sweep control of microwave signal, and in order to realize the linearity of frequency sweep, VCO control curve has carried out precorrection in signal processing module.The radar emission signal is sent into emitting antenna, the runway surf zone reflects back into radar receiving antenna after shining the runway target area, send into the low noise amplifier of receiving and transmitting front end, send in the orthogonal mixer through the signal after amplifying, the local oscillator of orthogonal mixer is produced by the shunting sign that transmits, orthogonal mixer output two-way quadrature vision signal is sent signal into the digitizing that the A/D analog to digital conversion realizes signal through the amplification filtering channel.Digitized echoed signal and rotating mechanism angle-data are sent into signal processing module through cable, signal processing module carries out Fast Fourier Transform (FFT) with the echoed signal of obtaining according to the frequency sweep sequential, the result of conversion arranges and buffer memory according to angle-data, in the data preparation module data are carried out arranging according to the distance measuring signal cycle (angle), form azimuth-range bidimensional matrix, data buffer storage is connected with the Azimuth Compression processing module, to carry out process of convolution along azimuth direction and orientation kernel function to the azimuth-range data matrix that forms in the data buffering in the Azimuth Compression module, through having obtained the compression result on the distance and bearing both direction behind the Azimuth Compression.The Azimuth Compression processing module is connected with the polarization information processing module, in the polarization information processing module, will utilize difference polarization data separation ground clutter and the artificial foreign matter of echo, the polarization information processing module with look change detection module more and be connected, in looking change detection module more by the data of azimuth scan sector are repeatedly compared, eliminate changeless ground return factor, keep the foreign matter factor that changes.Process and look more the realization of variation Check processing to the reliable detection of airport foreign matter by polarization information.
Description of drawings:
Fig. 1 is the utility model airfield runway foreign matter detection system synoptic diagram;
Fig. 2 is the utility model radar transmit-receive front end composition frame chart;
Fig. 3 is the rotating mechanism composition frame chart;
Fig. 4 is that signal is processed composition frame chart;
Fig. 5 is the processing flow chart of display control terminal.
Embodiment:
The invention will be further described below in conjunction with drawings and Examples.
Fig. 1 has shown a kind of airfield runway detection device for foreign matter block diagram, and it adopts semi arch motion radar transmit-receive front end and antenna, and the method that forms by wide-band LFM and aperture realizes the high resolution detection to the airfield runway foreign matter.The airfield runway foreign matter detection system is comprised of 8mm band emission receiving antenna, radar transmit-receive front end 1, cantilever 5, rotating mechanism 2, support 6, signal processor 3 and display control terminal 4.Wherein emission and receiving antenna and radar transmit-receive front end 1 link to each other by waveguide, and supported by cantilever 5, cantilever 5 is connected with rotating mechanism on the support 6, and radar transmit-receive front end 1 links to each other with signal processor 3 by rotating mechanism 2, and signal processor 3 links to each other with display control terminal 4.Signal processor 3 can be put into Control Room with display control terminal 4.
Above-mentioned transmitting radar antenna and receiving antenna adopt the wide-azimuth beam antenna so that can shine all the time the airfield runway search coverage at radar antenna in the rotating mechanism rotary course.
The composition frame chart of above-mentioned radar transmit-receive front end is by shown in Figure 2, the radar transmit-receive front end is connected with radar transmit-receive antenna by waveguide, and the radar transmit-receive front end is comprised of millimeter wave VCO, power splitter, power amplifier, emission polarizer, reception polarizer, low noise amplifier, orthogonal mixer, amplification channel and A/D analog to digital conversion.Wherein millimeter wave VCO is connected with the interface 2-3 of rotating mechanism by interface 1-4, is connected with the VCO gamma correction output of signal processor module by collector ring; The output of millimeter wave VCO is sent into power splitter and is divided into two-way, and one the tunnel is connected with power amplifier, and power amplifier is connected with the emission polarizer, and the emission polarizer is connected with emitting antenna by waveguide; Receiving polarizer is connected with receiving antenna by waveguide, the output that receives polarizer is connected with low noise amplifier, the output of low noise amplifier is connected with orthogonal mixer, the local oscillator of orthogonal mixer is provided by another road output of power splitter, the output of orthogonal mixer is connected, amplifies channel with the amplification channel and is connected with the A/D analog to digital conversion, and the digital signal of A/D analog to digital conversion is connected with the interface 2-3 of rotating mechanism by interface 1-3.
Above-mentioned emission polarizer and reception polarizer all adopt vertical polarization and the controlled polarizer of horizontal polarization.
Signal form after the above-mentioned A/D analog to digital conversion as the formula (1)
S
m(mT
1,nT
2)=∑∑A(R)K
R
m=1,2,...,M.0<mT
1<T
2 (1)
S is the digital form of echoed signal in the formula, and m, n are respectively the data sampling sample sequence number on the distance and bearing direction, and α is chirp slope, τ
RThe delay time of target, T
1, T
2Be respectively sampling time and frequency sweep cycle, f
0Be the carrier frequency that transmits, A (R) is that echo signal amplitude changes K with polarization
RFor becoming the ring system number.
Above-mentioned rotating mechanism comprises that cantilever connector, speed reduction unit, direct current generator, photoelectric code disk, upper cable interface 2-3, collector ring and lower cable interface 2-2 form as shown in Figure 3.Wherein the cantilever connector is connected with cantilever, the cantilever connector is connected with speed reduction unit, speed reduction unit is connected with direct current generator, direct current generator is connected with photoelectric code disk, collector ring is connected with direct current generator, upper cable interface 2-3 is connected with collector ring respectively with lower cable interface 2-2.Collector ring plays the effect that receiving and transmitting front end Signal and Signal Treatment module is connected.
Above-mentioned signal processor comprises Range compress processing module, data buffer storage, Azimuth Compression processing module, polarization information processing module VCO gamma correction, azimuth information reads and looks the variation detection more forming as shown in Figure 4.The Range compress processing module receives the front end signal that the collector ring port transmission is got off in the above-mentioned rotating mechanism by interface 3-3, and carry out Fast Fourier Transform (FFT) (FFT) and analyze the realization Range compress, the output of Range compress processing module is connected with data buffer storage, data buffer storage is arranged according to the orientation angles data that receive, form azimuth-range bidimensional matrix, the azimuth-range two-dimensional data can be represented by formula (2), data buffer storage is connected with the Azimuth Compression processing module, to carry out process of convolution along azimuth direction and orientation kernel function to the azimuth-range data matrix that forms in the data buffering in the Azimuth Compression module, the orientation kernel function can be by formula (3) expression, through having obtained the compression result on the distance and bearing both direction behind the Azimuth Compression.The Azimuth Compression processing module is connected with the polarization information processing module, in the polarization information processing module, will utilize difference polarization data separation ground clutter and the artificial foreign matter of echo, the polarization information processing module with look change detection module more and be connected, in looking change detection module more by the data of azimuth scan sector are repeatedly compared, eliminate changeless ground return factor, keep the foreign matter factor that changes.Process and look more the realization of variation Check processing to the reliable detection of airport foreign matter by polarization information.
S
m(m,n)=exp{jπk
c{-2R
0αm
+2f
0Lcos(ω(m+n)) (2)
+jπk
c{-2Lαcos(ω(m+n))m}}
Wherein L is jib-length, k
c=2/C;
Above-mentioned display control terminal treatment scheme as shown in Figure 5, realization to above-mentioned compression after the again processing of data, at first realize to detect separating of target and background, calculate target in the position on airport by the Azimuth ﹠ Range data, and carry out target mark in the airfield runway geography information, target information and airfield runway geography information are shown at terminal display.And make up the target that detects the detection of target data library storage, form daily record of work.
Claims (5)
1. an airfield runway detection device for foreign matter is characterized in that: be comprised of radar emission and receiving antenna, radar transmit-receive front end, cantilever, rotating mechanism, signal processor and display control terminal; Wherein: emission links to each other by waveguide with the radar transmit-receive front end with receiving antenna, and the radar transmit-receive front end links to each other with signal processor by rotating mechanism, and signal processor links to each other with display control terminal.
2. a kind of airfield runway detection device for foreign matter according to claim 1 is characterized in that: above-mentioned transmitting radar antenna and receiving antenna employing wide-azimuth beam antenna.
3. a kind of airfield runway detection device for foreign matter according to claim 1 is characterized in that: above-mentioned radar transmit-receive front end by millimeter wave VCO, power splitter, power amplifier, emission polarizer, receive polarizer, low noise amplifier, orthogonal mixer, amplification channel and A/D analog to digital conversion and form; Wherein: millimeter wave VCO is connected with the interface of rotating mechanism by interface, is connected with the VCO gamma correction output of signal processor module by collector ring; The output of millimeter wave VCO is sent into power splitter and is divided into two-way, and one the tunnel is connected with power amplifier, and power amplifier is connected with the emission polarizer, and the emission polarizer is connected with emitting antenna by waveguide; Receiving polarizer is connected with receiving antenna by waveguide, the output that receives polarizer is connected with low noise amplifier, the output of low noise amplifier is connected with orthogonal mixer, the local oscillator of orthogonal mixer is provided by another road output of power splitter, the output of orthogonal mixer is connected with the amplification filtering channel, the amplification filtering channel is connected with the A/D analog to digital conversion, and the digital signal of A/D analog to digital conversion is connected with the interface of rotating mechanism by interface.
4. a kind of airfield runway detection device for foreign matter according to claim 1 is characterized in that: above-mentioned rotating mechanism is comprised of cantilever connector, speed reduction unit, direct current generator, photoelectric code disk, upper cable interface, collector ring and lower cable interface; Wherein the cantilever connector is connected with cantilever, the cantilever connector is connected with speed reduction unit, speed reduction unit is connected with direct current generator, direct current generator is connected with photoelectric code disk, collector ring is connected with direct current generator, upper cable interface is connected with collector ring respectively with lower cable interface; Collector ring plays the effect that the radar transmit-receive front end signal is connected with signal processing module.
5. a kind of airfield runway detection device for foreign matter according to claim 3 is characterized in that: above-mentioned emission polarizer and receive polarizer and all adopt vertical polarization and the controlled polarizer of horizontal polarization.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220656005 CN203241545U (en) | 2012-12-03 | 2012-12-03 | Airport runway foreign matter detection device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220656005 CN203241545U (en) | 2012-12-03 | 2012-12-03 | Airport runway foreign matter detection device |
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| CN203241545U true CN203241545U (en) | 2013-10-16 |
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| CN 201220656005 Expired - Fee Related CN203241545U (en) | 2012-12-03 | 2012-12-03 | Airport runway foreign matter detection device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048694A (en) * | 2012-12-03 | 2013-04-17 | 天津职业技术师范大学 | Foreign body detection system for airfield runway |
| CN104374782A (en) * | 2014-11-18 | 2015-02-25 | 惠州硕贝德无线科技股份有限公司 | Foreign matter detection system based on antenna characteristic parameter monitoring |
| CN105204075A (en) * | 2015-09-22 | 2015-12-30 | 北京理工雷科电子信息技术有限公司 | Scene foreign matter detecting system based on millimeter wave radar |
| CN105510884A (en) * | 2015-12-08 | 2016-04-20 | 北京无线电计量测试研究所 | Method and device for processing image |
| CN109085539A (en) * | 2018-08-10 | 2018-12-25 | 湖南航天环宇通信科技股份有限公司 | A kind of double-reflecting face radar imagery antenna |
| CN110775753A (en) * | 2018-07-25 | 2020-02-11 | 奥的斯电梯公司 | Method and apparatus for elevator detection of hidden objects and notification of building management system |
-
2012
- 2012-12-03 CN CN 201220656005 patent/CN203241545U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048694A (en) * | 2012-12-03 | 2013-04-17 | 天津职业技术师范大学 | Foreign body detection system for airfield runway |
| CN103048694B (en) * | 2012-12-03 | 2017-09-08 | 天津职业技术师范大学 | A kind of foreign body detection system for airfield runway |
| CN104374782A (en) * | 2014-11-18 | 2015-02-25 | 惠州硕贝德无线科技股份有限公司 | Foreign matter detection system based on antenna characteristic parameter monitoring |
| CN105204075A (en) * | 2015-09-22 | 2015-12-30 | 北京理工雷科电子信息技术有限公司 | Scene foreign matter detecting system based on millimeter wave radar |
| CN105510884A (en) * | 2015-12-08 | 2016-04-20 | 北京无线电计量测试研究所 | Method and device for processing image |
| CN110775753A (en) * | 2018-07-25 | 2020-02-11 | 奥的斯电梯公司 | Method and apparatus for elevator detection of hidden objects and notification of building management system |
| CN110775753B (en) * | 2018-07-25 | 2022-04-26 | 奥的斯电梯公司 | Method and apparatus for elevator detection of hidden objects and notification of building management system |
| CN109085539A (en) * | 2018-08-10 | 2018-12-25 | 湖南航天环宇通信科技股份有限公司 | A kind of double-reflecting face radar imagery antenna |
| CN109085539B (en) * | 2018-08-10 | 2021-04-02 | 湖南航天环宇通信科技股份有限公司 | Double-reflector radar imaging antenna |
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| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131016 Termination date: 20151203 |
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| EXPY | Termination of patent right or utility model |