CN109323659A - A kind of airborne synthetic aperture radar baseline length measurement method and device - Google Patents
A kind of airborne synthetic aperture radar baseline length measurement method and device Download PDFInfo
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- CN109323659A CN109323659A CN201811146975.XA CN201811146975A CN109323659A CN 109323659 A CN109323659 A CN 109323659A CN 201811146975 A CN201811146975 A CN 201811146975A CN 109323659 A CN109323659 A CN 109323659A
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- 238000000691 measurement method Methods 0.000 title claims abstract description 21
- 238000005259 measurement Methods 0.000 claims abstract description 158
- 239000000758 substrate Substances 0.000 claims abstract description 117
- 239000013307 optical fiber Substances 0.000 claims abstract description 67
- 239000000835 fiber Substances 0.000 claims abstract description 46
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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
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
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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
- 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
- G01B11/24—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures
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Abstract
The present invention relates to synthetic aperture radar field of measuring technique, a kind of airborne synthetic aperture radar baseline length measurement method and device are disclosed.The measurement method is to be mounted on the measurement optical fiber for being carved with fiber bragg grating on measurement substrate, and the measurement substrate setting is connect on wing, and with airborne synthetic aperture radar submatrix；By measuring the strain and curvature of substrate, the shape function of measurement substrate is rebuild, to calculate the baseline length between radar submatrix.The present invention may be implemented not depending on wing motion modeling, it is not influenced by wing motion modeling accuracy, successfully solves the problems, such as the measurement of airborne synthetic aperture radar baseline length, measurement accuracy is high, and has the advantages that influence wing structure small, light-weight, weatherproof.
Description
Technical field
The present invention relates to synthetic aperture radar field of measuring technique, more particularly, to a kind of airborne synthetic aperture radar
Baseline length measurement method and device.
Background technique
For the carrier aircraft for the airborne synthetic aperture radar that submatrix is mounted on wing, the wing in flight course becomes
The baseline length that shape will lead to airborne synthetic aperture radar changes.Baseline length is that airborne synthetic aperture radar image is rebuild
An important parameter in the process, is directly related to the quality of the final reconstruction image of synthetic aperture radar.
Existing radar baseline length measuring system mainly have Germany FGSN-FHR Research Institute using single POS
System+laser/CCD combination sensor base line measurement system.System is to the measurement of baseline length dependent on the fortune to wing deformation
Dynamic modeling, and be easy to be influenced by weather environment.
And a kind of airborne Interference synthetic aperture radar is disclosed such as application number CN200510069053.X in the prior art
The combination metering device of baseline " installs a rigid platfor under the ventral of aircraft, two number of units code phases is fixedly mounted on platform
Machine, two laser range finders and an Inertial Measurement Unit, while disposing at least three apparent hairs respectively on two antennas
Optical diode mark；Two digital cameras, two laser range finders and Inertial Measurement Unit are all electrically connected with control processor,
And carry out signal communication.The instantaneous position and posture of digital camera and laser range finder measurement interference synthetic aperture radar antenna,
The position of platform and posture where Inertial Measurement Unit measures digital camera and laser range finder, three combine final realization
The dynamic of interference synthetic aperture radar double antenna measures." this measurement method needs additional device aboard, to aircaft configuration
It is affected, and its measurement accuracy is influenced by weather environment.
Fiber Bragg grating sensor has many advantages, such as that small in size, measurement accuracy is high, electromagnetism interference.
Summary of the invention
The present invention in order to overcome at least one of the drawbacks of the prior art described above, provides one kind and builds independent of wing motion
Mould, weatherproof airborne synthetic aperture radar baseline length measurement method.
In order to solve the above technical problems, technical scheme is as follows:
The measurement optical fiber for being carved with fiber bragg grating is mounted on measurement substrate, the measurement substrate is arranged in wing
On, and connect with airborne synthetic aperture radar submatrix；By measuring the strain and curvature of substrate, the shape letter of measurement substrate is rebuild
Number, to calculate the baseline length between radar submatrix.
In the present solution, fiber grating measurement obtains the curvature information of measurement substrate, and the location information of grating is also known
, it can carry out curve fitting to obtain coordinate of the substrate on two-dimensional surface to obtain base length using position and curvature information
Degree.In the present solution, strain and curvature of the fiber grating by measurement measurement substrate, and strain and the song of the indirect detection machine wing
Rate can measure the baseline length of airborne synthetic aperture radar without wing mechanical modeling, reduce inspection
While surveying difficulty, it is ensured that the precision of detection.
Further, include the following steps
S1. the distance between length and the radar submatrix of measurement substrate are determined；
S2. measurement optical fiber is installed on measurement substrate；Measurement substrate is fixedly connected with radar submatrix, and makes to measure substrate guarantor
Hold flexion；
S3. the curvature information and location information obtained using fiber bragg grating, is carried out curve fitting, to obtain base
Line length.
Further, in the step S1, measure the position of each radar submatrix, obtain between each radar submatrix away from
From；If radar submatrix number is n, then measurement substrate is divided into n-1 sections；Wherein, the length for measuring every section of substrate is adjacent greater than two
The distance between radar submatrix.In the present solution, being divided into several segments by that will measure substrate, number of segment is fewer by 1 than radar submatrix number,
So that having measurement substrate between every two radars submatrix；And pass through the spacing of length and two radar submatrixs to every section of measurement substrate
From relationship setting so that measurement substrate is able to maintain flexion, further increasing measurement substrate, deformation occurs with wing
Matching.
Further, in the step S2, the end for measuring substrate and every section of separation are consolidated by the way of welding
It is scheduled in radar submatrix.In the present solution, using end and separation as fixed position, to be welded as fixed form, so that surveying
While amount substrate and radar submatrix are stably connected with, unnecessary connection is reduced, measurement substrate is further increased and occurs with wing
The matching of deformation improves measurement accuracy.
It further,, will by the wave length shift information of each grating of optical fibre interrogation instrument Real-time demodulation in the step S3
The wave length shift information of each grating uploads to host computer, establishes coordinate system at fuselage center, is surveyed using each fiber grating
The curvature information and location information measured, fits curve, further, calculates baseline length.
Further, in the step S3, the corresponding relationship of wavelength shift and curvature is calculated using formula
K is the curvature of optical fiber, Δ λ in formulaBFor center wavelength shift, λBFor the central wavelength of the grating, PeFor optical fiber
Valid elastic-optic constants, h are distance of the fiber optic hub to substrate center.
Further, the measurement substrate uses memorial alloy.In the present solution, can be using memory alloy material as survey
Substrate is measured, the deformation restorability of measurement substrate is improved.
Further, the measurement substrate uses continuous cross section for the substrate of trough of belt rectangle, and the measurement optical fiber is fixed
In the slot of measurement substrate.In this programme measure optical fiber be arranged in the measurement substrate groove of trough of belt rectangle, can substantially reduce because
Measure substrate torsional deflection bring precision measure error risk.
Another object of the present invention is to provide a kind of airborne synthetic aperture radar baseline length measuring devices, including measurement
Optical fiber, measurement substrate, fiber Bragg grating (FBG) demodulator, host computer；The measurement optical fiber is set to measurement substrate；Measurement substrate is mounted on
On wing, and it is fixedly connected with synthetic aperture radar submatrix；The head of the measurement optical fiber is connect with fiber Bragg grating (FBG) demodulator, institute
Grating demodulation instrument is stated to connect with host computer.
This programme carries out Multipoint strain gauging with the deformation of wing to measurement substrate by measurement optical fiber, by fiber grating solution
It adjusts instrument to demodulate the measurement parameter of measurement optical fiber, and is transmitted to host computer and carries out the resolving of radar baseline length.In this programme
Fiber Bragg grating (FBG) demodulator, host computer may be mounted at fuselage interior.Since measurement optical fiber and the optical fiber for measuring substrate composition are surveyed
It is very small to measure combined volume, it is small, light-weight on wing structure influence, and be protected from weather influences.
Further, fiber end reflections impact light source and demodulation in order to prevent, the tail portion of the measurement optical fiber
Connect optoisolator.
Compared with the existing technology, beneficial effects of the present invention are as follows:
The present invention is devised in a creative way comprising the high-precision strain sensing net based on fiber-optic grating sensor, measurement substrate
Network, be based on fiber Bragg grating (FBG) demodulator, host computer, and to measure substrate curvature, fiber grating position be input information base length
Spend resolving system.Measurement method of the present invention may be implemented not depending on wing motion modeling, not by the shadow of wing motion modeling accuracy
It rings, successfully solves the problems, such as the measurement of airborne synthetic aperture radar baseline length, measurement accuracy is high.
Specifically, the present invention by radar submatrix and measure substrate position relationship design, between radar submatrix
Design, the design to radar submatrix and measurement substrate fixed form that substrate length relationship is measured between length and radar submatrix, into
One step greatly reduces measurement error.
Meanwhile the present invention is by a certain range, improving measurement accuracy for optical fiber curvature limitation.Specifically, by light
Fibre measures combined length and is set greater than the distance between two radar submatrixs, ensure that optical fiber measurement group credit union is constantly in
Flexion；The length for selecting different optical fiber measurements to combine, the amount of curvature after can control optical fiber measurement combination installation, leads to
The length for crossing reasonably selection optical fiber measurement combination is realized optical fiber curvature limitation in a certain range, overcomes existing skill
The excessive too small caused measurement accuracy of the curvature of optical fiber declines problem in art.
Also, the present invention is excellent to the measurement shape of substrate, material and measurement substrate and the mounting means of measurement optical fiber
Change, further improves measurement accuracy.
Furthermore important device is mounted on interior of aircraft by the present invention, small on wing structure influence, and it is possible to prevente effectively from day
The influence of the factors such as gas, air-flow；It overcomes and needs in the prior art in engine body exterior attachment device, aircraft configuration and easily can be destroyed
The shortcomings that by external environmental interferences such as weather.
The shortcomings that measurement method of the invention, measuring device can effectively overcome the prior art is airborne synthetic aperture radar
Image reconstruction provides baseline length information, and improves airborne synthetic aperture radar image reconstruction precision, has important
Application value.
Detailed description of the invention
Fig. 1 is the scheme of installation of 1 airborne synthetic aperture radar baseline length measuring device of embodiment.
Fig. 2 is that 1 optical fiber measurement of embodiment combines the mounting means schematic three dimensional views on wing.
Fig. 3 is that 1 optical fiber measurement of embodiment combines the rearview being installed on wing.
Fig. 4 is that 1 optical fiber measurement of embodiment combines the deformation schematic diagram under wing bending state.
Fig. 5 is that 2 optical fiber measurement of embodiment combines the partial view on wing.
Fig. 6 is that embodiment 2 measures substrate cross sectional shape diagram.
Fig. 7 is that embodiment 2 measures optical fiber and measurement substrate in combination end view.
Fig. 8 is baseline method for reconstructing schematic diagram in embodiment 3.
Specific embodiment
The attached figures are only used for illustrative purposes and cannot be understood as limitating the patent；
In order to better illustrate this embodiment, the certain components of attached drawing have omission, zoom in or out, and do not represent actual product
Size；To those skilled in the art, the omitting of some known structures and their instructions in the attached drawings are understandable.
For the ordinary skill in the art, above-mentioned term can be understood in concrete meaning of the invention with concrete condition.Below
The following further describes the technical solution of the present invention in conjunction with the accompanying drawings and embodiments.
Embodiment 1
As shown in Figure 1, the present embodiment provides a kind of airborne synthetic aperture radar baseline length measuring device, including measurement light
Fine, measurement substrate, fiber Bragg grating (FBG) demodulator, host computer；The measurement optical fiber is set to measurement substrate；Measurement substrate is mounted on machine
On the wing, and it is fixedly connected with synthetic aperture radar submatrix；The head of measurement optical fiber is connect with fiber Bragg grating (FBG) demodulator, and measures light
Fine tail end is connected separately with optoisolator.The grating demodulation instrument is connect with host computer.
Specifically, the inscription of measurement inside of optical fibre has a series of fiber grating.Each grating has different middle cardiac waves
It is long, and all there is certain interval to guarantee in measurement process not occurrence frequency aliasing between central wavelength.In the present embodiment,
Measuring inside of optical fibre inscription is fiber bragg grating.In inside of optical fibre, a fiber bragg grating is inscribed every 10mm,
And the central wavelength of arranged rational these fiber bragg gratings.Specifically, fiber Bragg grating sensor can be used.
As a specific embodiment of the present embodiment, measures substrate and connect by welding manner with radar submatrix；Tool
Body, in addition to each radar submatrix coupling part, measure the rest part of substrate without welding.
As a specific embodiment of the present embodiment, as shown in Figure 2 and Figure 3, measurement optical fiber and measurement substrate constitute light
Fibre measurement combination, is arranged along wing.Airborne synthetic aperture radar sub-antenna is arranged on wing.It is understood that due to light
Fibre measurement combination is very tiny, in order to indicate to understand its positional relationship, the non-reality of dimension scale of the optical fiber measurement combination in Fig. 2
Ratio is exaggerated display processing.
In the present embodiment, fiber Bragg grating (FBG) demodulator is connect with host computer by cable.Fiber Bragg grating (FBG) demodulator and host computer
It can be set in fuselage, can effectively avoid the adverse effect of the factors such as weather, air-flow.
As shown in figure 4, measurement substrate deformation with the deformation of wing in aircraft flight.It is understood that in order to
View, which is shown, to be become apparent from, and is easy to understand, the non-actual ratio of deformation of wing and measurement substrate in figure.
The working principle of the present embodiment is as follows: fiber Bragg grating sensor can be by way of wavelength-division multiplex one
It connects on root optical fiber multiple optical fibre Bragg optical grating strain sensors, realizes and strain measurements are surveyed to multiple points；The present embodiment passes through
Setting measurement substrate carries out Multipoint strain gauging to measurement substrate, according to theory of mechanics of materials, can go out survey by strain measurement
Measure the curvature of substrate.Further, it in conjunction with the location information of fiber bragg grating, carries out curve fitting, obtains measurement substrate
Shape function so that be not necessarily to direct survey aircraft wing deformation, the base length between two radar submatrixs can be obtained
Degree.And by the setting of optoisolator, fiber end reflections can be further prevented to impact light source and demodulation.
Wherein, the principle of optical fiber measurement substrate curvature is: when measurement substrate is bent with wing, surface can be strained, light
For fine grating together with measurement substrate sticking, the surface strain for measuring substrate also makes optical fiber occur to stretch or compress, so as to cause
The variation of the central wavelength of echo.Following formula can be released:
K is the curvature of optical fiber, Δ λ in formulaBFor center wavelength shift, λBFor the central wavelength of the grating, PeFor optical fiber
Valid elastic-optic constants, h are distance of the fiber optic hub to substrate center.Thus it is possible to which it is corresponding with curvature to obtain wavelength shift
Relationship.
By the wave length shift information of each grating of fiber Bragg grating (FBG) demodulator Real-time demodulation, by the wave length shift of each grating
Information uploads to host computer.Curvature information and location information are fitted by host computer, obtain matched curve, to calculate baseline
Length.
The present embodiment establishes high-precision strain sensing network by using fiber bragg grating, ingenious to be utilized at random
The measurement substrate of wing change, measurement optical fiber are formd can demodulate the fiber Bragg grating (FBG) demodulator of grating wavelength drift information, upper
Machine is the baseline length resolving system of core, realizes the high-acruracy survey of radar baseline length.The airborne synthesis of the present embodiment
Aperture radar baseline length measuring device overcomes the prior art and needs in engine body exterior attachment device, destroys aircraft configuration and easily
The shortcomings that by external environmental interferences such as weather, device is mounted on interior of aircraft, it is possible to prevente effectively from the factors such as weather, air-flow
It influences.
Embodiment 2
The present embodiment difference from example 1 is that, it is as shown in Figures 5 to 7, specific as one of the present embodiment
Embodiment, it can be specifically the base that cross section is concave that measurement substrate, which is the substrate that continuous cross section is trough of belt rectangle,
Plate.The material of measurement substrate can use memorial alloy.It is understood that the length of measurement substrate can be according to specific machine
Borne synthetic aperture radar submatrix length is adjusted.Fiber bragg grating is mounted on the state of the bottom of measurement substrate groove such as
Shown in Fig. 7, lower section is the measurement substrate being processed into memorial alloy, and measurement optical fiber is precisely mounted to the groove of measurement substrate
In interior right angle.
The measurement substrate of the present embodiment has the characteristics that be not easy torsional deflection, the present embodiment overcome because measurement substrate from
The resultant error that body factor deformation generates, the measurement accuracy of measuring device instrumentation radar baseline length are higher.
Embodiment 3
The present embodiment provides a kind of airborne synthetic aperture radar baseline length measurement methods.Measurement optical fiber is mounted on measurement
On substrate, the measurement optical fiber is the optical fiber for being carved with fiber bragg grating；The measurement substrate is arranged on wing, and and machine
The connection of borne synthetic aperture radar submatrix；By the strain and curvature of measurement measurement substrate, the shape function of measurement substrate is rebuild, from
And calculate the baseline length between radar submatrix.
Embodiment 1 can be used in this measurement method or the device of embodiment 2 measures.
Specifically, measurement method the following steps are included:
S1. the distance between length and the radar submatrix of measurement substrate are determined.
Under surface condition, the position of each radar submatrix is measured, obtains the distance between each radar submatrix.If thunder
It is n up to submatrix number, then measurement substrate is divided into n-1 sections.The length of every section of substrate of measurement is slightly over adjacent two radars submatrix
The distance between.The separation between every section of substrate of measurement can be indicated with coloring agent.This line of demarcation and measurement substrate
End is exactly the mark for measuring the fixed point of substrate and radar submatrix.
S2. measurement optical fiber is installed on measurement substrate；Measurement substrate is fixedly connected with radar submatrix, and makes to measure substrate guarantor
Hold flexion.
Substrate is measured in the present embodiment can use groove structure as shown in Figure 5, and measurement optical fiber can pass through stickup
Mode is installed on measurement substrate.When the cross section for measuring substrate is concave, measurement optical fiber be may be mounted in the slot of concave.It surveys
Amount optical fiber and measurement substrate collectively form optical fiber measurement combination.Optical fiber measurement combination settings are on wing.
Position of the fiber grating relative to measurement substrate can be measured by graduated scale, obtain each grating relative to measurement
The one-dimensional coordinate of substrate first section: x1, x2 ... xn.Optical fiber measurement combination is divided into 4 sections in the present embodiment, with dyeing between section and section
Agent makes marks.
The end for measuring substrate and every section of line of demarcation are fixed in radar submatrix.In the present embodiment, it can will measure
Base ends and every section of line of demarcation are connect by the way of welding with radar submatrix；Measure substrate in addition to each radar submatrix
Coupling part, rest part is without welding.
In the present embodiment, the measurement substrate length between each radar submatrix is more slightly longer than the distance between radar submatrix, makes
The state that substrate keeps buckling must be measured, it is ensured that the deformation for measuring substrate is corresponding with the deformation of wing, to further increase
The measurement accuracy of baseline.
Two tail portions for measuring optical fiber connect the optoisolator that upper central wavelength is 1550nm, to prevent fiber end reflections
Light source and demodulation are impacted.Two optical fiber head portions are connected respectively on fiber Bragg grating (FBG) demodulator.Fiber Bragg grating (FBG) demodulator
It is connected with host computer by cable.So complete the building of measurement network.
S3. the curvature information and location information obtained using fiber bragg grating, is carried out curve fitting, to obtain base
Line length.
Measurement optical fiber is connected on fiber Bragg grating (FBG) demodulator and is demodulated.Obtain the real-time central wavelength of each grating
Information uploads to these information on host computer by cable.
On host computer, by the corresponding relationship of central wavelength drift value and curvature, each light is calculated according to formula (1)
The corresponding curvature of grid.Have been obtained location information of each grating on substrate before, the location information of each grating and each
The curvature information of a grating corresponds, and coordinate of the substrate both ends on two-dimensional surface can be obtained by curve matching, in
It is the length that can be obtained by baseline.
Specifically, after the carrier aircraft of airborne synthetic aperture radar reaches area to be observed, fiber Bragg grating (FBG) demodulator starts work
Make.The wave length shift information of each grating is uploaded to host computer by the wave length shift information of each grating of Real-time demodulation.Upper
In machine, the curvature information and location information obtained using fiber Bragg grating sensor is carried out curve fitting, as shown in figure 8,
Coordinate system is established at fuselage center, the curvature information and location information obtained using each fiber grating measurement fits song
Line further calculates baseline length.
Baseline information can be carried out storing and baseline information is sent to radar computer by host computer, can be tied in observation
Radar image reconstruction is carried out after beam, can also carry out real-time radar image reconstruction.
The measurement method of the present embodiment overcomes and needs existing for existing airborne synthetic aperture radar base line measurement technology pair
The deficiency that wing is modeled can measure airborne synthetic aperture radar baseline length, and measurement accuracy is high.
Obviously, the above embodiment of the present invention be only to clearly illustrate example of the present invention, and not be pair
The restriction of embodiments of the present invention.For those of ordinary skill in the art, may be used also on the basis of the above description
To make other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all this
Made any modifications, equivalent replacements, and improvements etc., should be included in the claims in the present invention within the spirit and principle of invention
Protection scope within.
Claims (10)
1. a kind of airborne synthetic aperture radar baseline length measurement method, which is characterized in that fiber bragg grating will be carved with
Measurement optical fiber is mounted on measurement substrate, and the measurement substrate is arranged on wing, and is connected with airborne synthetic aperture radar submatrix
It connects；By measuring the strain and curvature of substrate, the shape function of measurement substrate is rebuild, to calculate the base length between radar submatrix
Degree.
2. airborne synthetic aperture radar baseline length measurement method according to claim 1, which is characterized in that including step
S1. the distance between length and the radar submatrix of measurement substrate are determined；
S2. measurement optical fiber is fixed on measurement substrate；Measurement substrate is fixedly connected with radar submatrix, and measurement substrate is made to keep bending
Curved state；
S3. the curvature information and location information obtained using fiber bragg grating, is carried out curve fitting, to obtain base length
Degree.
3. airborne synthetic aperture radar baseline length measurement method according to claim 2, which is characterized in that the step
In S1, the position of each radar submatrix is measured, obtains the distance between each radar submatrix；If radar submatrix number is n, then will survey
Amount substrate is divided into n-1 sections；Wherein, the length for measuring every section of substrate is greater than the distance between two adjacent radar submatrixs.
4. airborne synthetic aperture radar baseline length measurement method according to claim 3, which is characterized in that the step
In S2, the end for measuring substrate and every section of separation are fixed in radar submatrix by the way of welding.
5. airborne synthetic aperture radar baseline length measurement method according to claim 2, which is characterized in that the step
It, will be in the wave length shift information of each grating by the wave length shift information of each grating of optical fibre interrogation instrument Real-time demodulation in S3
Host computer is passed to, establishes coordinate system at fuselage center, the curvature information obtained using each fiber grating measurement and position letter
Breath, fits curve, calculates baseline length.
6. being existed according to airborne synthetic aperture radar baseline length measurement method, feature described in claim 2 to 5 any one
In in the step S3, using the corresponding relationship of formula calculating wavelength shift and curvature
K is the curvature of optical fiber, Δ λ in formulaBFor center wavelength shift, λBFor the central wavelength of the grating, PeFor the effective of optical fiber
Elasto-optical coefficient, h are distance of the fiber optic hub to measurement substrate center.
7. existing according to claim 1 to airborne synthetic aperture radar baseline length measurement method, feature described in 5 any one
In the measurement substrate uses memorial alloy.
8. airborne synthetic aperture radar baseline length measurement method according to claim 7, which is characterized in that the measurement
Substrate uses continuous cross section for the substrate of trough of belt rectangle, and the measurement optical fiber is fixed in the slot of measurement substrate.
9. a kind of airborne synthetic aperture radar baseline length measuring device, which is characterized in that including measurement optical fiber, measurement substrate,
Fiber Bragg grating (FBG) demodulator, host computer；The measurement optical fiber is set to measurement substrate；Measurement substrate be mounted on wing, and with conjunction
It is fixedly connected at aperture radar submatrix；The head of the measurement optical fiber is connect with fiber Bragg grating (FBG) demodulator, the grating demodulation instrument
It is connect with host computer.
10. airborne synthetic aperture radar baseline length measuring device according to claim 9, which is characterized in that the survey
The tail portion for measuring optical fiber connects optoisolator.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110068817A (en) * | 2019-05-07 | 2019-07-30 | 中国科学院电子学研究所 | A kind of topographic mapping method, instrument and system based on laser ranging and InSAR |
| CN111288912A (en) * | 2020-03-24 | 2020-06-16 | 北京航空航天大学 | Fiber bragg grating deformation measurement method for airborne distributed POS |
| WO2020186970A1 (en) * | 2019-03-18 | 2020-09-24 | 东南大学 | Measurement method for dynamic position of aerofoil base line based on ifem and rzt |
| CN111854621A (en) * | 2020-06-05 | 2020-10-30 | 北京航空航天大学 | Fiber bragg grating sensor data fitting method and device for airborne distributed POS |
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