CN106054145B - A kind of scouting discrimination method of satellite-borne synthetic aperture radar operating mode - Google Patents
A kind of scouting discrimination method of satellite-borne synthetic aperture radar operating mode Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
- G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
- G01S13/9004—SAR image acquisition techniques
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/38—Jamming means, e.g. producing false echoes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
- G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
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Abstract
The invention discloses a kind of scouting discrimination methods of satellite-borne synthetic aperture radar operating mode.The present invention includes the following steps：1. writing dummy source generates signal；2. pair satellite-borne SAR signal obtains chirp rate K into row distance to parameter Estimationr, the parameters such as residual frequency Δ f；3. according to Kr, carry out Range compress, the range delay curve focused；4. compressed signal of adjusting the distance carries out Radon transformation and estimates range walk slope Kwalk, and according to KwalkCarry out range walk correction, the range delay curve corrected；5. obtaining orientation power diagram from the range delay curve after correction, the operating mode of satellite-borne SAR is adjudicated according to the form for receiving power.The present invention proposes the mode estimated satellite-borne SAR signal to differentiate the operating mode of satellite-borne SAR, has good distinguishing ability to common operating mode, can be applied to the fields such as the scouting, confrontation, test of satellite-borne SAR.
Description
Technical field
It is specifically a kind of to spaceborne synthesis the invention belongs to field of signal processing, more particularly to field of radar signal reconnaissance
The scouting discrimination method of aperture radar operating mode.
Background technology
Satellite-borne SAR is a kind of not climate and illumination effect, round-the-clock, round-the-clock Active Imaging Lidar, have it is long-range,
The advantages that wide cut, high-resolution.Longer wavelengths of SAR signals can also penetrate increased surface covering, to be hidden in earth's surface dummy load with
Under target be imaged.Therefore, satellite-borne SAR technology obtains in fields such as area monitoring, surface mapping and moving-target detections
Extensive use.So far, a large amount of critical facilities in China and vast territory are fully exposed to possess advanced Spaceborne SAR System
Under national surveillance.For this situation, China must actively develop the interference countermeasure techniques of satellite-borne SAR, to weaken and break
Performance advantage of the bad other side on satellite-borne SAR.
Satellite-borne SAR interferes the validity and reliability of countermeasure system, directly depends on to the basic of enemy's Spaceborne SAR System
The Grasping level of the information such as working method and signal parameter.When to run on band, pack, sliding pack etc. different for satellite-borne SAR
When operating mode, the signal parameter, processing method and the imaging algorithm that use all are very different, to the sensitivity of key parameter
Degree also has significant difference, also has very big difference to the SAR conflicting modes used, therefore carry out and detectd to SAR operating modes
It examines and has extremely important meaning with research is differentiated.
Currently, in terms of the scouting discriminating of SAR operating modes, common method be by the orbit parameters of SAR satellites or
The distance of SAR signals is measured to parameter (modulating bandwidth, centre frequency, distance resolution etc.) information, to judge to differentiate satellite-borne SAR
Operating mode.But with the fast development of SAR technologies, satellite-borne SAR has the work energy of multiband, multipolarization, multi-mode
Power so that conventional method can not effectively differentiate the real-time working pattern of satellite-borne SAR.In document " to the spaceborne conjunction of different working modes
Studied at the scouting of aperture radar " (《Computer engineering and application》, vol.49, no.12, pp.223-227,2013.) and document
" the side lobe reconnaissance comparative studies to satellite-borne synthetic aperture radar under pack and sliding beam bunching mode " (《Science and technology and engineering》,
Vol.20, no.8, pp.1785-1789,2012.) in, have studied satellite-borne SAR difference from the angle of theory analysis and emulation experiment
The orientation of operating mode receives power form, has shown that the orientation under satellite-borne SAR different working modes receives power form
Conclusion with bigger difference.The present invention is namely based on the conclusion, starts with from the satellite-borne SAR signal of intercepting and capturing, proposes to be based on score
The Processing Algorithm of rank Fourier transform and Radon transformation, the orientation that satellite-borne SAR is effectively estimated out receives power diagram, to reflect
The operating mode of other satellite-borne SAR.Flow that the present invention is handled and general Space-borne SAR Imaging flow there are prodigious difference, it
The demand characteristics that the estimation of power form is received according to orientation has carried out imaging flow and parameter Estimation flow organically
In conjunction with improvement, to design effective satellite-borne SAR pattern discrimination method.
Invention content
The purpose of the present invention is starting with from the satellite-borne SAR signal spied out, based on fraction Fourier conversion (FrFT) with
Radon transformation proposes a kind of satellite-borne SAR operating mode mirror that the orientation reception power form to echo-signal is estimated
Other method.
The technical solution adopted in the present invention specifically comprises the following steps：
S1：Satellite-borne SAR signal is intercepted and captured using ground reconnaissance plane, it is assumed that the docking collection of letters number has carried out reception power azimuth to figure
Compensation and range attenuation power back-off, the satellite-borne SAR signal that receiver output end exports are：
Wherein A0It is distance including scattering coefficient to overall gain, τ is distance to the fast time, when t is that orientation is slow
Between, t0Deviate time, w for beam centerrg() and waz() be respectively distance to orientation envelope function, KrFor distance to
Frequency modulation rate, R (t) are instantaneous distance, and c is the light velocity, and Δ f is residual frequency, and λ is wavelength；J indicates plural number；
S2：To the satellite-borne SAR signal of receiver output end into row distance to parameter Estimation, to obtain distance to frequency modulation rate
Kr, the equidistant descriscent parameter informations of residual frequency Δ f, eliminate residual frequency.It is as follows：
S21：If the satellite-borne SAR signal received is s (t), then the p rank fraction Fourier conversions of s (t) are a lines
Property integral operation：
Wherein, p is the exponent number of FrFT, and α is coordinate system rotation angle, wherein α=p pi/2s, Kp(t, u) is the core letter of FrFT
Number, i.e.,：
(3) are substituted into (2), then the p ranks FrFT of signal s (t) can be expressed as：
S22：The distance for detecting satellite-borne SAR is exactly scanned using rotation angle α as variable to signal, and satellite-borne SAR is asked to believe
Number s0FrFT from the distance of (τ, t) to signal, to form Two dimensional Distribution of the signal energy in parameter { α, u } plane, herein
The two-dimensional search for carrying out peak point in plane by threshold value obtains
Satellite-borne SAR distance is to the distance of signal to frequency modulation rate KrWith residual frequency Δ f and parameterRelationship be：
Distance is estimated to the distance of signal to frequency modulation rate K using above-mentioned formularWith frequency difference Δ f；
S23：Utilize the frequency difference Δ f structure residual frequency filters H estimated1(Δf)：
H1(Δ f)=exp {-j2 π Δ f τ } (7)
By satellite-borne SAR signal s0(τ, t) and residual frequency filter H1(Δ f) is multiplied, the satellite-borne SAR for the frequency difference that is eliminated
Signal s1(τ,t)：
S3：According to distance to the distance of parameter Estimation to frequency modulation rate KrDistance is built to matched filter H2(fτ)：
Wherein fτIt is distance to frequency.Eliminate residual frequency.Then the satellite-borne SAR signal s except frequency difference is offseted1(τ, t) is carried out
Range compress is as follows：
S31：To SAR signals s1(τ, t) obtains S into row distance to Fourier transform1(fτ,t)；
S32：Then by S1(fτ, t) with distance to matched filter H2(fτ) be multiplied；
S33：The satellite-borne SAR after Range compress is obtained into row distance to inverse fourier transform to the signal that is handled in S32 again
Signal s2(τ, t) is
The two-dimensional distance delay curve just focused by above-mentioned processing.
S4：Method of estimation is converted using Radon, range walk correction is carried out to the two-dimensional distance delay curve of focusing：
SAR signals s after Range compress2The range migration amount of (τ, t) is by the oblique distance R (t) of sinc functions in formula (10)
It determines.No matter under which kind of imaging pattern, the instantaneous oblique distance R (t) of reconnaissance plane to satellite is all identical, is expressed as：
Wherein ts=R0tan(θs)/v, R0It is satellite to reconnaissance plane minimum distance, θsIt is angle of squint, v is the flight speed of satellite
Degree.
Instantaneous oblique distance R (t) can be indicated with following formula
R (t)=R (t0)+RL(t)+RC(t) (12)
Wherein, R (t0) be the beam center moment instantaneous oblique distance, RL(t) be instantaneous oblique distance linear component (also referred to as away from
From walking about), RC(t) be instantaneous oblique distance high order component.Range walk RL(t) it is range walk slope KwalkWith multiplying for time t
Product, i.e.,：
RL(t)=Kwalkt (13)
Range walk slope KwalkIt is range walk RL(t) first derivative on time t, i.e.,：
Because can not learn the flying speed v and angle of squint θ of piggyback satellite when scouting satellite-borne SAR signals, can only use
The mode estimated distance of estimation is walked about slope Kwalk.Next be exactly that Radon becomes and brings estimation and walk about slope KwalkSpecific step
Suddenly：
S41：The signal data plane D after Range compress is chosen, wherein data plane transverse and longitudinal axis indicates orientation respectively
To with distance to sampling number, each data point indicates the amplitude of pixel；
S42：Then the data plane D that changes commanders is become by Radon and is mapped to p- θ planes Rf(p,θ)；
S43：Seek p- θ planes RfMaximum value max (the R of (p, θ)f(p, θ)) corresponding angle, θf；
S44：Calculate the range walk slope K of estimationwalk=tan (θf)；
S45：To signal s2(τ, t) obtains S into row distance to Fourier transform2(fτ,t)；
S46：By S2(fτ, t) and phase multiplication device GLRCMCIt is multiplied：
Phase multiplier is：
S47：Adaptive range walk correction is obtained into row distance to inverse fourier transform to the signal that is handled in S46 again
Satellite-borne SAR signal s3(τ, t) is：
Wherein RLRCMC(t)=R (t)-RL(t)。
S5：Orientation is estimated from range delay curve and receives power, obtains orientation power diagram, according to reception power
Form judgement satellite-borne SAR operating mode.Power conversion under band pattern is fastest, the power conversion under beam bunching mode
Minimum, sliding pack fall between.Then the operating mode of satellite-borne SAR is adjudicated according to the form for receiving power.
Beneficial effects of the present invention：
The present invention starts with from the satellite-borne SAR signal spied out, estimates satellite-borne SAR signal using fraction Fourier conversion
Distance carries out pulse compression to parameter, and according to distance to parameter, and Radon is recycled to convert to obtain the progress of range walk slope certainly
Range walk correction is adapted to, finally recovers orientation from the two-dimensional distance delay curve of focusing and completion range walk correction
Power diagram adjudicates the operating mode of satellite-borne SAR according to power diagram.Join to signal with traditional dependence satellite orbit parameter and distance
Number information carries out operating mode decision method and differs, and the orientation for obtaining satellite-borne SAR can be gone to from the angle of Radar Signal Processing
To power diagram is received, differentiate that accuracy rate and reliability are better than conventional method.
Description of the drawings
Fig. 1 is the flow diagram of technical solution of the present invention.
Fig. 2 is reconnaissance plane echo simulation signal.
Fig. 3 is result of the signal through fraction Fourier conversion.
Fig. 4 is the satellite-borne SAR signal after Range compress.
Fig. 5 is that entropy converts trend with step delta K.
Fig. 6 is the satellite-borne SAR signal after the correction of adaptive range walk.
Fig. 7 is that satellite-borne SAR is operated in the reception power diagram of the orientation under band pattern.
Fig. 8 is that satellite-borne SAR is operated in the reception power diagram of the orientation under beam bunching mode.
Fig. 9 is that the orientation that satellite-borne SAR is operated under sliding beam bunching mode receives power diagram.
Specific implementation mode
The method of the present invention is described further below in conjunction with the accompanying drawings.
As shown in Figure 1, its specific implementation step is as follows：
S1：Satellite-borne SAR is generated according to the scouting model of place under satellite-borne SAR different working modes, and using Matlab
Satellite-borne SAR emulates signal (such as Fig. 2).
S2：To the satellite-borne SAR signal of receiver output end into row distance to parameter Estimation, to obtain distance to frequency modulation rate
Kr, the equidistant descriscent parameter informations of residual frequency Δ f, be as follows：
S21：If the satellite-borne SAR signal received is s (t), then the p rank fraction Fourier conversions of s (t) are a lines
Property integral operation：
Wherein, p is the exponent number of FrFT, and α is coordinate system rotation angle, wherein α=p pi/2s, Kp(t, u) is the core letter of FrFT
Number, i.e.,：
(18) are substituted into (17), then the p ranks FrFT of signal s (t) can be expressed as：
S22：The distance for detecting satellite-borne SAR is exactly scanned using rotation angle α as variable to signal, and satellite-borne SAR is asked to believe
Number s0The distance of (τ, t) (is such as schemed to the FrFT of signal to form Two dimensional Distribution of the signal energy in parameter { α, u } plane
3) two-dimensional search for, carrying out peak point by threshold value on that plane obtains
Satellite-borne SAR distance is to the distance of signal to frequency modulation rate KrWith residual frequency Δ f and parameterRelationship be：
Distance is estimated to the distance of signal to frequency modulation rate K using above-mentioned formularWith frequency difference Δ f；
S23：Utilize the frequency difference Δ f structure residual frequency filters H estimated1(Δf)：
H1(Δ f)=exp {-j2 π Δ f τ } (22)
By satellite-borne SAR signal s0(τ, t) and residual frequency filter H1(Δ f) is multiplied, the satellite-borne SAR for the frequency difference that is eliminated
Signal s1(τ,t)：
S3：According to distance to the distance of parameter Estimation to frequency modulation rate KrDistance is built to matched filter H2(fτ)：
Wherein fτIt is distance to frequency.Then the satellite-borne SAR signal s except frequency difference is offseted1(τ, t) carries out Range compress, specifically
Steps are as follows：
S31：To SAR signals s1(τ, t) obtains S into row distance to Fourier transform1(fτ,t)；
S32：Then by S1(fτ, t) with distance to matched filter H2(fτ) be multiplied；
S33：The satellite-borne SAR after Range compress is obtained into row distance to inverse fourier transform to the signal that is handled in S32 again
Signal s2(τ, t) is
The two-dimensional distance delay curve (such as Fig. 4) just focused by above-mentioned processing.
S4：Estimated distance is brought using Radon changes to walk about slope Kwalk, and the two-dimensional distance delay curve of focusing is carried out
Range walk is corrected：
SAR signals s after Range compress2The range migration amount of (τ, t) is by the oblique distance R (t) of sinc functions in formula (25)
It determines.No matter under which kind of imaging pattern, the instantaneous oblique distance R (t) of reconnaissance plane to satellite is all identical, is expressed as：
Wherein ts=R0tan(θs)/v, R0It is satellite to reconnaissance plane minimum distance, θsIt is angle of squint, v is the flight speed of satellite
Degree.
Instantaneous oblique distance R (t) can be indicated with following formula
R (t)=R (t0)+RL(t)+RC(t) (27)
Wherein, R (t0) be the beam center moment instantaneous oblique distance, RL(t) be instantaneous oblique distance linear component (also referred to as away from
From walking about), RC(t) be instantaneous oblique distance high order component.Range walk RL(t) it is range walk slope KwalkWith multiplying for time t
Product, i.e.,：
RL(t)=Kwalkt (28)
Range walk slope KwalkIt is range walk RL(t) first derivative on time t, i.e.,：
Because can not learn the flying speed v and angle of squint θ of piggyback satellite when scouting satellite-borne SAR signals, can only use
The mode estimated distance of estimation is walked about slope Kwalk.Next be exactly that Radon becomes and brings estimated distance and walk about slope KwalkIt is specific
Step：
S41：The signal data plane D after Range compress is chosen, wherein data plane transverse and longitudinal axis indicates orientation respectively
To with distance to sampling number, each data point indicates the amplitude of pixel；
S42：Then the data plane D that changes commanders is become by Radon and is mapped to p- θ planes Rf(p,θ)；
S43：Seek p- θ planes RfMaximum value max (the R of (p, θ)f(p, θ)) corresponding angle, θf(such as Fig. 5)；
S44：Calculate the range walk slope K of estimationwalk=tan (θf)；
S45：To signal s2(τ, t) obtains S into row distance to Fourier transform2(fτ,t)；
S46：By S2(fτ, t) and phase multiplication device GLRCMCIt is multiplied：
Phase multiplier is：
S47：Adaptive range walk correction is obtained into row distance to inverse fourier transform to the signal that is handled in S46 again
Satellite-borne SAR signal s3(τ, t) is：
Wherein RLRCMC(t)=R (t)-RL(t).The range delay curve (such as Fig. 6) corrected and focused.
S5：Orientation is estimated from range delay curve and receives power, obtains orientation power diagram (such as Fig. 7-9), root
The operating mode of satellite-borne SAR is adjudicated according to the form for receiving power.Power conversion under band pattern is fastest, under beam bunching mode
Power conversion it is minimum, sliding pack falls between.Then the Working mould of satellite-borne SAR is adjudicated according to the form for receiving power
Formula.
Claims (5)
1. a kind of scouting discrimination method of satellite-borne synthetic aperture radar operating mode, it is characterised in that include the following steps：
S1：Satellite-borne SAR signal is intercepted and captured using ground reconnaissance plane, reception diagram is carried out to the satellite-borne SAR signal received
Compensation and range attenuation power back-off obtain the satellite-borne SAR signal of receiver output end output；
S2：To the satellite-borne SAR signal of receiver output end into row distance to parameter Estimation, to obtain distance to parameter information：Away from
Descriscent frequency modulation rate Kr, residual frequency Δ f；
S3：Estimate the distance obtained to frequency modulation rate K to parameter information according to distancer, distance is built to matched filter, and is passed through
The filter carries out Range compress, the two-dimensional distance delay curve focused to satellite-borne SAR signal；
S4：Radon transformation is carried out to the satellite-borne SAR signal after Range compress, estimates the range walk of satellite-borne SAR signal
Slope Kwalk, and according to the range walk slope K estimatedwalkRange walk is carried out to the two-dimensional distance delay curve of focusing to rectify
Just, the range delay curve after being corrected；
S5：Orientation is estimated from the range delay curve after correction and receives power, orientation power diagram is obtained, according to reception
The operating mode of the form judgement satellite-borne SAR of power.
2. the scouting discrimination method of satellite-borne synthetic aperture radar operating mode according to claim 1, it is characterised in that step
The satellite-borne SAR signal s that receiver output end exports in rapid S10(τ, t) indicates as follows：
Wherein A0It is distance including scattering coefficient to overall gain, τ is distance to the fast time, and t is orientation slow time, t0
Deviate time, w for beam centerrg() and waz() be respectively distance to orientation envelope function, KrIt is distance to frequency modulation
Rate, R (t) are instantaneous distance, and c is the light velocity, and Δ f is residual frequency, and λ is wavelength, and j indicates plural number.
3. the scouting discrimination method of satellite-borne synthetic aperture radar operating mode according to claim 2, it is characterised in that step
Rapid S2 utilizes fraction Fourier conversion estimated distance to parameter frequency modulation rate KrWith frequency difference Δ f, residual frequency is then eliminated；Specifically
Steps are as follows：
S21：If the satellite-borne SAR signal received is s (t), then the p rank fraction Fourier conversions of s (t) are a linear products
Partite transport is calculated：
Wherein, p is the exponent number of Frft, and α is coordinate system rotation angle, wherein α=p pi/2s, Kp(t, u) is the kernel function of FrFT, i.e.,：
(3) are substituted into (2), then the p ranks FrFT of signal s (t) can be expressed as：
S22：The distance for detecting satellite-borne SAR is exactly scanned using rotation angle α as variable to parameter, seeks satellite-borne SAR signal s0
FrFT from the distance of (τ, t) to signal, to form Two dimensional Distribution of the signal energy in parameter { α, u } plane, in this plane
On by threshold value carry out peak point two-dimensional search obtain
The distance of satellite-borne SAR signal is to frequency modulation rate KrWith residual frequency Δ f and parameterRelationship be：
The distance of satellite-borne SAR signal is estimated to frequency modulation rate K using above-mentioned formularWith frequency difference Δ f；
S23：Utilize the frequency difference Δ f structure residual frequency filters H estimated1(Δf)：
H1(Δ f)=exp {-j2 π Δ f τ } (7)
By satellite-borne SAR signal s0(τ, t) and residual frequency filter H1(Δ f) is multiplied, the satellite-borne SAR signal for the frequency difference that is eliminated
s1(τ,t)：
4. the scouting discrimination method of satellite-borne synthetic aperture radar operating mode according to claim 3, it is characterised in that step
Rapid S3 utilizes distance to frequency modulation rate KrDistance is built to matched filter H2(fτ)：
Wherein fτIt is distance to frequency；
Then the satellite-borne SAR signal s except frequency difference is offseted1(τ, t) carries out Range compress, is as follows：
S31：Offset the satellite-borne SAR signal s except frequency difference1(τ, t) obtains S into row distance to Fourier transformation1(fτ,t)；
S32：Then by S1(fτ, t) with distance to matched filter H2(fτ) be multiplied；
S33：The satellite-borne SAR signal after Range compress is obtained into row distance to inverse Fourier transform to the signal that is handled in S32 again
s2(τ, t) is
The two-dimensional distance delay curve just focused by above-mentioned processing.
5. the scouting discrimination method of satellite-borne synthetic aperture radar operating mode according to claim 4, it is characterised in that S4
It is walked about slope K using Radon transformation estimated distanceswalk, and complete range walk correction：
SAR signals s after Range compress2The range migration amount of (τ, t) is determined by the oblique distance R (t) of sinc functions in formula (10)
's；No matter under which kind of imaging pattern, the instantaneous oblique distance R (t) of reconnaissance plane to satellite is all identical, is expressed as：
Wherein ts=R0tan(θs)/v, R0It is minimum distance of the satellite to reconnaissance plane, θsIt is angle of squint, v is the flight speed of satellite
Degree；
Instantaneous oblique distance R (t) can be rewritten as following form
R (t)=R (t0)+RL(t)+RC(t) (12)
Wherein, R (t0) be the beam center moment oblique distance, RL(t) be instantaneous oblique distance linear component, RC(t) it is instantaneous oblique distance
High order component；Range walk RL(t) it is range walk slope KwalkWith the product of time t, i.e.,：
RL(t)=Kwalkt (13)
Range walk slope KwalkIt is range walk RL(t) first derivative on time t, i.e.,：
Because can not learn the flying speed v and angle of squint θ for carrying satellite when scouting satellite-borne SAR signals, estimation can only be used
Mode obtain range walk slope Kwalk；Next be exactly that Radon becomes and brings estimated distance and walk about slope KwalkSpecific step
Suddenly：
S41：Choose signal data plane D after Range compress, wherein data plane transverse and longitudinal axis indicate respectively orientation and
Distance to sampling number, each data point indicates the amplitude of pixel；
S42：Then the data plane D that changes commanders is become by Radon and is mapped to p- θ planes Rf(p,θ)；
S43：Seek p- θ planes RfMaximum value max (the R of (p, θ)f(p, θ)) corresponding angle, θf；
S44：Calculate the range walk slope K of estimationwalk=tan (θf)；
S45：To signal s2(τ, t) obtains S into row distance to Fourier transform2(fτ,t)；
S46：By S2(fτ, t) and phase multiplication device GLRCMCIt is multiplied：
Phase multiplier is：
S47：The star of adaptive range walk correction is obtained into row distance to inverse fourier transform to the signal that is handled in S46 again
Carry SAR signals s3(τ, t) is：
Wherein RLRCMC(t)=R (t)-RL(t)。
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| CN109711016B (en) * | 2018-12-14 | 2020-09-04 | 中国地质大学（武汉） | Method and system for simulating imaging form and dynamically simulating two-sided SAR (synthetic Aperture Radar) satellite |
| CN115144820B (en) * | 2022-09-02 | 2022-12-13 | 北京轩涌科技发展有限公司 | Space radar load signal analysis and evaluation system and evaluation method |
| CN115166662A (en) * | 2022-09-08 | 2022-10-11 | 北京轩涌科技发展有限公司 | Method and device for identifying working mode of space radar |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102879784A (en) * | 2012-10-25 | 2013-01-16 | 西安电子科技大学 | Unified imaging method for synthetic aperture radar (SAR) in four modes |
| CN103135100A (en) * | 2013-01-31 | 2013-06-05 | 西安电子科技大学 | Moving-target parameter estimation method of common-rail bistatic synthetic aperture radar (SAR) |
-
2016
- 2016-05-19 CN CN201610338223.8A patent/CN106054145B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102879784A (en) * | 2012-10-25 | 2013-01-16 | 西安电子科技大学 | Unified imaging method for synthetic aperture radar (SAR) in four modes |
| CN103135100A (en) * | 2013-01-31 | 2013-06-05 | 西安电子科技大学 | Moving-target parameter estimation method of common-rail bistatic synthetic aperture radar (SAR) |
Non-Patent Citations (7)
| Title |
|---|
| A Geometry-Based Doppler Centroid Estimator for Bistatic Forward-Looking SAR;Wenchao Li 等;《IEEE GEOSCIENE AND REMOTE SENSING LETTERS》;20120531;第9卷(第3期);388-392 * |
| Improved Early Crop Type Identification By Joint Use of High Temporal Resolution SAR And Optical Image Time Series;Jordi Inglada 等;《remote sensing》;20160426;1-21 * |
| 一种双站合成孔径雷达的高分辨率成像与合成方法;钟华 等;《上海交通大学学报》;20140331;第48卷(第3期);317-322 * |
| 基于分数阶傅里叶变换的星载SAR信号参数实时估计;杨光 等;《系统工程与电子技术》;20100831;第32卷(第8期);1649-1656 * |
| 对不同工作模式星载合成孔径雷达的侦察研究;陈颖颖 等;《计算机工程与应用》;20120321;第49卷(第12期);223-241 * |
| 对聚束和滑动聚束模式下星载合成孔径雷达的旁瓣侦察比较研究;陈颖颖 等;《科学技术与工程》;20120331;第12卷(第8期);1785-1789 * |
| 条带模式、聚束模式和滑动聚束模式的比较;刘寒艳 等;《中国科学院研究生院学报》;20110531;第28卷(第3期);410-417 * |
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